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					                                                                            TransGlobal Airlines Letter of Compliance
                                                                                 Part 121 – Rev B Submission




                                                                                                                                                                                                       FAA
                  N/A                                      Requirement                                              Manual References             TransGlobal Policies/Comments




                                                                                                                                                                                                  RA
FAR/SRR


Subpart H - Aircraft Requirements
121.151 Applicability
   § 121.151            This subpart prescribes aircraft requirements for all certificate holders.


121.153 Aircraft Requirements: General
                        Except as provided in paragraph (c) of this section, no certificate holder may operate
   121.153(a)
                        an aircraft unless that aircraft -
                                                                                                                                        Certificate is required by the GMM 5.18 and is verified
                                                                                                                       GMM 5.18         during the conformity inspection
                        Is registered as a civil aircraft of the United States and carries an appropriate current     GMM 6.15.2
  121.153(a)(1)
                        airworthiness certificate issued under this chapter; and                                     GMM 6.15.4(16)     TransGlobal Airlines flight crewmembers shall confirm
                                                                                                                     FOM 6.1.5 A&B      the presences of a current airworthiness certificate
                                                                                                                                        during the preflight inspection
                                                                                                                                        Initial airworthiness is determined through conformity
                                                                                                                                        inspection and maintained through TransGlobal
                                                                                                                       GMM 6.15.1       Airlines CAMP
                        Is in an airworthy condition and meets the applicable airworthiness requirements of
  121.153(a)(2)
                        this chapter, including those relating to identification and equipment.                         GMM 5.9.1
                                                                                                                      FOM 6.1.5 A&B     TransGlobal Airlines flight crewmembers shall confirm
                                                                                                                                        the presences of a current airworthiness certificate
                                                                                                                                        during the preflight inspection
                        A certificate holder may use an approved weight and balance control system based                                GMM 6.10 for the establishment of the 36 month
                                                                                                                         WBP
   121.153(b)           on average, assumed, or estimated weight to comply with applicable airworthiness                                BOW. TransGlobal Airlines does not use average,
                        requirements and operating limitations.                                                         GMM 6.10
                                                                                                                                        assumed or estimated weights.
                        A certificate holder may operate in common carriage, and for the carriage of mail, a
                                                                                                                                        N/A Not currently applicable since TransGlobal Airlines
   121.153(c)           civil aircraft which is leased or chartered to it without crew and is registered in a
                        country which is a party to the Convention on International Civil Aviation if -                                                 does not lease aircraft.
                        The aircraft carries an appropriate airworthiness certificate issued by the country of
                                                                                                                                        N/A Not currently applicable since TransGlobal Airlines
  121.153(c)(1)         registration and meets the registration and identification requirements of that
                        country;                                                                                                                        does not lease aircraft.




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                                                                           TransGlobal Airlines Letter of Compliance
                                                                                Part 121 – Rev B Submission




                                                                                                                                                                                                      FAA
                  N/A                                      Requirement                                             Manual References             TransGlobal Policies/Comments




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FAR/SRR


                        The aircraft is of a type design which is approved under a U.S. type certificate and
                        complies with all of the requirements of this chapter (14 CFR Chapter 1) that would
                        be applicable to that aircraft were it registered in the United States, including the
                        requirements which must be met for issuance of a U.S. standard airworthiness                                   N/A Not currently applicable since TransGlobal Airlines
  121.153(c)(2)
                        certificate (including type design conformity, condition for safe operation, and the                                           does not lease aircraft.
                        noise, fuel venting, and engine emission requirements of this chapter), except that a
                        U.S. registration certificate and a U.S. standard airworthiness certificate will not be
                        issued for the aircraft;
                        The aircraft is operated by U.S.-certificated airmen employed by the certificate                               N/A Not currently applicable since TransGlobal Airlines
  121.153(c)(3)
                        holder; and                                                                                                                    does not lease aircraft.
                        The certificate holder files a copy of the aircraft lease or charter agreement with the
                        FAA Aircraft Registry, Department of Transportation, 6400 South MacArthur                                      N/A Not currently applicable since TransGlobal Airlines
  121.153(c)(4)
                        Boulevard, Oklahoma City, Oklahoma (Mailing address: P.O. Box 25504, Oklahoma                                                  does not lease aircraft.
                        City, Oklahoma 73125).


121.155
   § 121.155            [Reserved]


121.157 Aircraft Certification and Equipment Requirements
                        Airplanes certificated before July 1, 1942. No certificate holder may operate an
   121.157(a)
                        airplane that was type certificated before July 1, 1942, unless -                                                           N/A by type certification date
  121.157(a)(1)         That airplane meets the requirements of § 121.173(c), or                                                                    N/A by type certification date
                        That airplane and all other airplanes of the same or related type operated by that
                        certificate holder meet the performance requirements of sections 4a.737-T through
  121.157(a)(2)         4a.750-T of the Civil Air Regulations as in effect on January 31, 1965; or §§ 25.45                                         N/A by type certification date
                        through 25.75 {There is no § 25.45 nor § 25.75 - Ed.} and § 121.173(a), (b), (d), and
                        (e) of this title.
                        Airplanes certificated after June 30, 1942. Except as provided in paragraphs (c), (d),
                        (e), and (f) of this section, no certificate holder may operate an airplane that was                           TransGlobal Airlines ERJ-170 is certificated in the
   121.157(b)
                        type certificated after June 30, 1942, unless it is certificated as a transport category         TCDS
                                                                                                                                       transport category
                        airplane and meets the requirements of § 121.173(a), (b), (d), and (e).
                        C-46 type airplanes: passenger carrying operations. No certificate holder may
                        operate a C-46 airplane in passenger carrying operations unless that airplane is
                        operated in accordance with the operating limitations for transport category airplanes
   121.157(c)
                        and meets the requirements of paragraph (b) of this section or meets the                                       N/A TransGlobal Airlines does not operate C46 aircraft
                        requirements of Part 4b, as in effect July 20, 1950, and the requirements of §
                        121.173(a), (b), (d) and (e), except that -
                        The requirements of sections 4b.0 through 4b.19 as in effect May 18, 1954, must be
  121.157(c)(1)
                        complied with;                                                                                                 N/A TransGlobal Airlines does not operate C46 aircraft

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  121.157(c)(2)            The birdproof windshield requirements of section 4b.352 need not be complied with;                            N/A TransGlobal Airlines does not operate C46 aircraft
                           The provisions of sections 4b.480 through 4b.490 (except sections 4b.484(a)(1) and
  121.157(c)(3)
                           4b.487(e)), as in effect May 16, 1953, must be complied with; and                                             N/A TransGlobal Airlines does not operate C46 aircraft
                           The provisions of paragraph 4b.484(a)(1), as in effect July 20, 1950, must be
  121.157(c)(4)
                           complied with.                                                                                                N/A TransGlobal Airlines does not operate C46 aircraft
                           In determining the takeoff path in accordance with section 4b.116 and the one
                           engine inoperative climb in accordance with section 4b.120 (a) and (b), the propeller
                           of the inoperative engine may be assumed to be feathered if the airplane is equipped
                           with either an approved means for automatically indicating when the particular
                           engine has failed or an approved means for automatically feathering the propeller of
   121.157 (c)
                           the inoperative engine. The Administrator may authorize deviations from compliance                            N/A TransGlobal Airlines does not operate C46 aircraft
                           with the requirements of sections 4b.130 through 4b.190 and Subparts C, D, E, and
                           F of Part 4b (as designated in this paragraph) if he finds that (considering the effect
                           of design changes) compliance is extremely difficult to accomplish and that service
                           experience with the C-46 airplane justifies the deviation.
                           C-46 type airplanes: cargo operations. No certificate holder may use a nontransport
   121.157(d)
                           category C-46 type airplane in cargo operations unless -                                                      N/A TransGlobal Airlines does not operate C46 aircraft
  121.157(d)(1)            It is certificated at a maximum gross weight that is not greater than 48,000 pounds;                          N/A TransGlobal Airlines does not operate C46 aircraft
                           It meets the requirements of §§ 121.199 through 121.205 using the performance
  121.157(d)(2)
                           data in Appendix C to this part;                                                                              N/A TransGlobal Airlines does not operate C46 aircraft
  121.157(d)(3)            Before each flight, each engine contains at least 25 gallons of oil; and                                      N/A TransGlobal Airlines does not operate C46 aircraft
  121.157(d)(4)            After December 31, 1964 -                                                                                     N/A TransGlobal Airlines does not operate C46 aircraft
                           It is powered by a type and model engine as set forth in Appendix C of this part,
 121.157(d)(4)(i)          when certificated at a maximum gross takeoff weight greater than 45,000 pounds;                               N/A TransGlobal Airlines does not operate C46 aircraft
                           and
                           It complies with the special airworthiness requirement set forth in §§ 121.213
 121.157(d)(4)(ii)
                           through 121.287 of this part or in Appendix C of this part.                                                   N/A TransGlobal Airlines does not operate C46 aircraft
                           Commuter category airplanes. Except as provided in paragraph (f) of this section, no
                           certificate holder may operate under this part a nontransport category airplane type
   121.157(e)              certificated after December 31, 1964, and before March 30, 1995, unless it meets                                                 N/A by category
                           the applicable requirements of § 121.173 (a), (b), (d), and (e), and was type
                           certificated in the commuter category.
                           Other nontransport category airplanes. No certificate holder may operate under this
                           part a nontransport category airplane type certificated after December 31, 1964,
    121.157(f)
                           unless it meets the applicable requirements of § 121.173 (a), (b), (d), and (e), was                                             N/A by category
                           manufactured before March 20, 1997, and meets one of the following:
  121.157(f)(1)            Until December 20, 2010:                                                                                                         N/A by category
                           The airplane was type certificated in the normal category before July 1, 1970, and
 121.157(f)(1)(i)          meets special conditions issued by the Administrator for airplanes intended for use in                                           N/A by category
                           operations under part 135 of this chapter.

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                                                                               TransGlobal Airlines Letter of Compliance
                                                                                    Part 121 – Rev B Submission




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                            The airplane was type certificated in the normal category before July 19, 1970, and
 121.157(f)(1)(ii)
                            meets the additional airworthiness standards in SFAR No. 23, 14 CFR part 23.                                                       N/A by category
                            The airplane was type certificated in the normal category and meets the additional
 121.157(f)(1)(iii)
                            airworthiness standards in appendix A of part 135 of this chapter.                                                                 N/A by category
                            The airplane was type certificated in the normal category and complies with either
 121.157(f)(1)(iv)
                            section 1.(a) or 1.(b) of SFAR No. 41 of 14 CFR part 21.                                                                           N/A by category
                            The airplane was type certificated in the normal category, meets the additional
  121.157(f)(2)             requirements described in paragraphs (f)(1)(i) through (f)(1)(iv) of this section, and                                             N/A by category
                            meets the performance requirements in appendix K of this part.
                            Certain newly manufactured airplanes. No certificate holder may operate an airplane
                            under this part that was type certificated as described in paragraphs (f)(1)(i) through
   121.157(g)
                            (f)(1)(iv) of this section and that was manufactured after March 20, 1997, unless it                                               N/A by category
                            meets the performance requirements in appendix K of this part.
                            Newly type certificated airplanes. No person may operate under this part an airplane
   121.157(h)               for which the application for a type certificate is submitted after March 29, 1995,              TCDS          The ERJ-170 is certificated under FAR Part 25
                            unless the airplane is type certificated under part 25 of this chapter.


121.159 Single-Engine Airplanes Prohibited
    § 121.159               No certificate holder may operate a single-engine airplane under this part.                                                      N/A by aircraft type

121.161 Airplane Limitations: Type of Route
                                                                                                                                           Unless authorized by the FAA, based on the character
                            Unless authorized by the Administrator, based on the character of the terrain, the
                            kind of operation, or the performance of the airplane to be used, no certificate holder                        of the terrain, the kind of operation, or the performance
                            may operate two engine or three engine airplanes (except a three engine turbine                DPM 23.1A       of the airplane to be used, TransGlobal Airlines will not
   121.161(a)
                            powered airplane) over a route that contains a point farther than 1 hour flying time (in      FOM 19.2.1C      operate over a route that contains a point farther than
                            still air at normal cruising speed with one engine inoperative) from an adequate
                                                                                                                                           1 hour flying time (in still air at normal cruising speed
                            airport.
                                                                                                                                           with one engine inoperative) from an adequate airport.
                            Except as provided in paragraph (c) of this section, no certificate holder may operate
                            a land airplane (other than a DC-3, C-46, CV-240, CV-340, CV-440, CV-580, CV-
                                                                                                                                             N/A TransGlobal Airlines will not conduct extended
   121.161(b)               600, CV-640, or Martin 404) in an extended overwater operation unless it is
                            certificated or approved as adequate for ditching under the ditching provisions of part                                       overwater operations
                            25 of this chapter.
                            Until December 20, 2010, a certificate holder may operate, in an extended overwater
                            operation, a nontransport category land airplane type certificated after December 31,
   121.161(c)
                            1964, that was not certificated or approved as adequate for ditching under the                                                     N/A by category
                            ditching provisions of part 25 of this chapter.



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                                                                            TransGlobal Airlines Letter of Compliance
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                  N/A                                      Requirement                                              Manual References             TransGlobal Policies/Comments




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121.163 Aircraft Proving Tests
   121.163(a)           Initial airplane proving tests-
                        No person may operate an airplane not before proven for use in a kind of operation
                        under this part or part 135 of this chapter unless an airplane of that type has had, in                         TransGlobal Airlines will submit a plan for the proving
   121.163(a)           addition to the airplane certification tests, at least 100 hours of proving tests                               runs 30 days prior to the planned start of the proving
                        acceptable to the Administrator, including a representative number of flights into en                           runs
                        route airports.
                        The requirement for at least 100 hours of proving tests may be reduced by the                                   TransGlobal Airlines will submit a plan for the proving
   121.163(a)           Administrator if the Administrator determines that a satisfactory level of proficiency                          runs 30 days prior to the planned start of the proving
                        has been demonstrated to justify the reduction.                                                                 runs
                                                                                                                                        TransGlobal Airlines will submit a plan for the proving
   121.163(a)           At least 10 hours of proving flights must be flown at night; these tests are irreducible.                       runs 30 days prior to the planned start of the proving
                                                                                                                                        runs
                        Proving tests for kinds of operations. Unless otherwise authorized by the                                       TransGlobal Airlines will submit a plan for the proving
                        Administrator, for each type of airplane, a certificate holder must conduct at least 50
   121.163(b)
                        hours of proving tests acceptable to the Administrator for each kind of operation it                            runs 30 days prior to the planned start of the proving
                        intends to conduct, including a representative number of flights into en route airports.                        runs
                        Proving tests for materially altered airplanes. Unless otherwise authorized by the
                        Administrator, for each type of airplane that is materially altered in design, a
   121.163(c)           certificate holder must conduct at least 50 hours of proving tests acceptable to the                              N/A The ERJ-170 has not been materially altered
                        Administrator for each kind of operation it intends to conduct with that airplane,
                        including a representative number of flights into en route airports.
                        Definition of materially altered. For the purposes of paragraph (c) of this section, a
   121.163(d)           type of airplane is considered to be materially altered in design if the alteration                               N/A The ERJ-170 has not been materially altered
                        includes -
                        The installation of powerplants other than those of a type similar to those with which
  121.163(d)(1)
                        it is certificated; or                                                                                            N/A The ERJ-170 has not been materially altered
                        Alterations to the aircraft or its components that materially affect flight
  121.163(d)(2)
                        characteristics.                                                                                                  N/A The ERJ-170 has not been materially altered
                        No certificate holder may carry passengers in an aircraft during proving tests, except                          TransGlobal Airlines will submit a plan for the proving
   121.163(e)           for those needed to make the test and those designated by the Administrator.                                    runs 30 days prior to the planned start of the proving
                        However, it may carry mail, express, or other cargo, when approved.                                             runs




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FAR/SRR


Subpart I – AIRPLANE PERFORMANCE OPERATING LIMITATIONS
121.171 Applicability
                        This subpart prescribes airplane performance operating limitations for all certificate
   121.171(a)
                        holders.
                        For purposes of this part, "effective length of the runway" for landing means the
                        distance from the point at which the obstruction clearance plane associated with the
   121.171(b)
                        approach end of the runway intersects the centerline of the runway to the far end           170-PFM 2.2 E
                        thereof.
                        For the purposes of this subpart, "obstruction clearance plane" means a plane
                        sloping upward from the runway at a slope of 1:20 to the horizontal, and tangent to
                        or clearing all obstructions within a specified area surrounding the runway as shown
                        in a profile view of that area. In the plan view, the centerline of the specified area
                        coincides with the centerline of the runway, beginning at the point where the
                        obstruction clearance plane intersects the centerline of the runway and proceeding
                        to a point at least 1,500 feet from the beginning point. Thereafter the centerline
                        coincides with the takeoff path over the ground for the runway (in the case of
   121.171(c)           takeoffs) or with the instrument approach counterpart (for landings), or, where the         170-PFM 2.2 F
                        applicable one of these paths has not been established, it proceeds consistent with
                        turns of at least 4,000 foot radius until a point is reached beyond which the
                        obstruction clearance plane clears all obstructions. This area extends laterally 200
                        feet on each side of the centerline at the point where the obstruction clearance plane
                        intersects the runway and continues at this width to the end of the runway; then it
                        increases uniformly to 500 feet on each side of the centerline at a point 1,500 feet
                        from the intersection of the obstruction clearance plane with the runway; thereafter it
                        extends laterally 500 feet on each side of the centerline.


121.173 General
                        Except as provided in paragraph (c) of this section, each certificate holder operating
                                                                                                                                      N/A TransGlobal Airlines does not operate
   121.173(a)           a reciprocating-engine-powered airplane shall comply with §§ 121.175 through
                        121.187.                                                                                                            reciprocating powered aircraft
                        Except as provided in paragraph (c) of this section, each certificate holder operating
   121.173(b)           a turbine-engine-powered airplane shall comply with the applicable provisions of §§         170-PFM 2.2 D
                        121.189 through 121.197, except that when it operates -
                        A turbo-propeller-powered airplane type certificated after August 29, 1959, but
                                                                                                                                      N/A TransGlobal Airlines does not operate
  121.173(b)(1)         previously type certificated with the same number of reciprocating engines, the
                        certificate holder may comply with §§ 121.175 through 121.187; or                                                      turbopropeller aircraft
                        Until December 20, 2010, a turbo-propeller-powered airplane described in §
                                                                                                                                      N/A TransGlobal Airlines does not operate
  121.173(b)(2)         121.157(f), the certificate holder may comply with the applicable performance
                        requirements of appendix K of this part.                                                                               turbopropeller aircraft
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                      Each certificate holder operating a large nontransport category airplane type
                      certificated before January 1, 1965, shall comply with §§ 121.199 through 121.205
   121.173(c)
                      and any determination of compliance must be based only on approved performance                                                    N/A by type certification date
                      data.
                      The performance data in the Airplane Flight Manual applies in determining
                      compliance with §§ 121.175 through 121.197. Where conditions are different from
                                                                                                                                          APG Data allows for interpolation and includes
                      those on which the performance data is based, compliance is determined by
   121.173(d)
                      interpolation or by computing the effects of changes in the specific variables if the     ERJ-170 Runway Analysis   corrections for conditions that differ from the specific
                      results of the interpolation or computations are substantially as accurate as the                                   table.
                      results of direct tests.
                      Except as provided in paragraph (c) of this section, no person may take off a
                      reciprocating-engine-powered airplane at a weight that is more than the allowable
                      weight for the runway being used (determined under the runway takeoff limitations of                                      N/A TransGlobal Airlines does not operate
   121.173(e)
                      the transport category operating rules of 14 CFR part 121, subpart I) after taking into                                         reciprocating powered aircraft
                      account the temperature operating correction factors in the applicable Airplane Flight
                      Manual.
                      The Administrator may authorize in the operations specifications deviations from the
                                                                                                                                              N/A TransGlobal Airlines is not requesting any
   121.173(f)         requirements in the subpart if special circumstances make a literal observance of a
                      requirement unnecessary for safety.                                                                                                     deviations
                      The ten mile width specified in §§ 121.179 through 121.183 may be reduced to five
                      miles, for not more than 20 miles, when operating VFR or where navigation facilities                                    N/A TransGlobal Airlines is not requesting any
   121.173(g)
                      furnish reliable and accurate identification of high ground and obstructions located                                                    deviations
                      outside of five miles, but within ten miles, on each side of the intended track.


121.175 Airplanes: Reciprocating Engine Powered; Weight Limitations
                      No person may takeoff a reciprocating engine powered airplane from an airport
                                                                                                                                                N/A TransGlobal Airlines does not operate
   121.175(a)         located at an elevation outside of the range for which maximum takeoff weights have
                      been determined for that airplane.                                                                                              reciprocating powered aircraft
                      No person may takeoff a reciprocating engine powered airplane for an airport of
                                                                                                                                                N/A TransGlobal Airlines does not operate
   121.175(b)         intended destination that is located at an elevation outside of the range for which
                      maximum landing weights have been determined for that airplane.                                                                 reciprocating powered aircraft
                      No person may specify, or have specified, an alternate airport that is located at an
                                                                                                                                                N/A TransGlobal Airlines does not operate
   121.175(c)         elevation outside of the range for which maximum landing weights have been
                      determined for the reciprocating engine powered airplane concerned.                                                             reciprocating powered aircraft
                      No person may takeoff a reciprocating engine powered airplane at a weight more                                            N/A TransGlobal Airlines does not operate
   121.175(d)
                      than the maximum authorized takeoff weight for the elevation of the airport.                                                    reciprocating powered aircraft
                      No person may takeoff a reciprocating engine powered airplane if its weight on
                      arrival at the airport of destination will be more than the maximum authorized landing                                    N/A TransGlobal Airlines does not operate
   121.175(e)
                      weight for the elevation of that airport, allowing for normal consumption of fuel and                                           reciprocating powered aircraft
                      oil enroute.
   121.175(f)         This section does not apply to large nontransport category airplanes operated under                                       N/A TransGlobal Airlines does not operate
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                        § 121.173(c).                                                                                                           reciprocating powered aircraft

121.177 Airplanes: Reciprocating Engine Powered; Takeoff Limitations
                        No person operating a reciprocating engine powered airplane may takeoff that                                      N/A TransGlobal Airlines does not operate
   121.177(a)
                        airplane unless it is possible -                                                                                        reciprocating powered aircraft
                        To stop the airplane safely on the runway, as shown by the accelerate-stop distance                               N/A TransGlobal Airlines does not operate
  121.177(a)(1)
                        data, at any time during takeoff until reaching critical engine failure speed;                                          reciprocating powered aircraft
                        If the critical engine fails at any time after the airplane reaches critical engine failure
                                                                                                                                          N/A TransGlobal Airlines does not operate
  121.177(a)(2)         speed V1, to continue the takeoff and reach a height of 50 feet, as indicated by the
                        takeoff path data, before passing over the end of the runway; and                                                       reciprocating powered aircraft
                        To clear all obstacles either by at least 50 feet vertically (as shown by the takeoff
                        path data) or 200 feet horizontally within the airport boundaries and 300 feet
                                                                                                                                          N/A TransGlobal Airlines does not operate
  121.177(a)(3)         horizontally beyond the boundaries, without banking before reaching a height of 50
                        feet (as shown by the takeoff path data) and thereafter without banking more than 15                                    reciprocating powered aircraft
                        °.
                        In applying this section, corrections must be made for the effective runway gradient.
                        To allow for wind effect, takeoff data based on still air may be corrected by taking                              N/A TransGlobal Airlines does not operate
   121.177(b)
                        into account not more than 50 percent of any reported headwind component and not                                        reciprocating powered aircraft
                        less than 150 percent of any reported tailwind component.
                        This section does not apply to large nontransport category airplanes operated under                               N/A TransGlobal Airlines does not operate
   121.177(c)
                        § 121.173(c).                                                                                                           reciprocating powered aircraft

121.179 Airplanes: Reciprocating Engine Powered; Enroute Limitations; All Engines Operating
                        No person operating a reciprocating engine powered airplane may takeoff that
                        airplane at a weight, allowing for normal consumption of fuel and oil, that does not
                        allow a rate of climb (in feet per minute), with all engines operating, of at least 6.90                          N/A TransGlobal Airlines does not operate
   121.179(a)
                        VS0 (that is, the number of feet per minute is obtained by multiplying the number of                                    reciprocating powered aircraft
                        knots by 6.90) at an altitude of at least 1,000 feet above the highest ground or
                        obstruction within ten miles of each side of the intended track.
                        This section does not apply to airplanes certificated under Part 4a of the Civil Air                              N/A TransGlobal Airlines does not operate
   121.179(b)
                        Regulations.                                                                                                            reciprocating powered aircraft
                        This section does not apply to large nontransport category airplanes operated under                               N/A TransGlobal Airlines does not operate
   121.179(c)
                        § 121.173(c).                                                                                                           reciprocating powered aircraft

121.181 Airplanes: Reciprocating Engine Powered; Enroute Limitations; One Engine Inoperative
   121.181(a)           Except as provided in paragraph (b) of this section, no person operating a                                        N/A TransGlobal Airlines does not operate
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                         reciprocating engine powered airplane may takeoff that airplane at a weight, allowing                                  reciprocating powered aircraft
                         for normal consumption of fuel and oil, that does not allow a rate of climb (in feet per
                         minute), with one engine inoperative, of at least
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.181(a)            0.079 - (0.106 / N) * VS0 2
                                                                                                                                                reciprocating powered aircraft
                         (where N is the number of engines installed and VS0 is expressed in knots) at an
                         altitude of at least 1,000 feet above the highest ground or obstruction within 10 miles
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.181 (a)           of each side of the intended track. However, for the purposes of this paragraph the
                         rate of climb for airplanes certificated under Part 4a of the Civil Air Regulations is                                 reciprocating powered aircraft
                         0.026 VS02.
                         In place of the requirements of paragraph (a) of this section, a person may, under an
                         approved procedure, operate a reciprocating engine powered airplane, at an all
                         engines operating altitude that allows the airplane to continue, after an engine
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.181(b)            failure, to an alternate airport where a landing can be made in accordance with §
                         121.187, allowing for normal consumption of fuel and oil. After the assumed failure,                                   reciprocating powered aircraft
                         the flight path must clear the ground and any obstruction within five miles on each
                         side of the intended track by at least 2,000 feet.
                         If an approved procedure under paragraph (b) of this section is used, the certificate                            N/A TransGlobal Airlines does not operate
   121.181(c)
                         holder shall comply with the following:                                                                                reciprocating powered aircraft
                         The rate of climb (as prescribed in the Airplane Flight Manual for the appropriate
                                                                                                                                          N/A TransGlobal Airlines does not operate
  121.181(c)(1)          weight and altitude) used in calculating the airplane's flight path shall be diminished
                         by an amount, in feet per minute, equal to                                                                             reciprocating powered aircraft
                                                                                                                                          N/A TransGlobal Airlines does not operate
  121.181 (c)(1)           0.079 - (0.106 / N) * VS02
                                                                                                                                                reciprocating powered aircraft
                           (where N is the number of engines installed and VS0 is expressed in knots) for
                                                                                                                                          N/A TransGlobal Airlines does not operate
  121.181 (c)(1)         airplanes certificated under Part 25 of this chapter and by 0.026 VS02 for airplanes
                         certificated under Part 4a of the Civil Air Regulations.                                                               reciprocating powered aircraft
                         The all engines operating altitude shall be sufficient so that in the event the critical
                         engine becomes inoperative at any point along the route, the flight will be able to
                         proceed to a predetermined alternate airport by use of this procedure. In determining
                         the takeoff weight, the airplane is assumed to pass over the critical obstruction                                N/A TransGlobal Airlines does not operate
  121.181(c)(2)
                         following engine failure at a point no closer to the critical obstruction than the nearest                             reciprocating powered aircraft
                         approved radio navigational fix, unless the Administrator approves a procedure
                         established on a different basis upon finding that adequate operational safeguards
                         exist.
                         The airplane must meet the provisions of paragraph (a) of this section at 1,000 feet                             N/A TransGlobal Airlines does not operate
  121.181(c)(3)
                         above the airport used as an alternate in this procedure.                                                              reciprocating powered aircraft
                         The procedure must include an approved method of accounting for winds and                                        N/A TransGlobal Airlines does not operate
  121.181(c)(4)
                         temperatures that would otherwise adversely affect the flight path.                                                    reciprocating powered aircraft
  121.181(c)(5)          In complying with this procedure fuel jettisoning is allowed if the certificate holder                           N/A TransGlobal Airlines does not operate
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                        shows that it has an adequate training program, that proper instructions are given to                                 reciprocating powered aircraft
                        the flight crew, and all other precautions are taken to insure a safe procedure.
                        The certificate holder shall specify in the dispatch or flight release an alternate                             N/A TransGlobal Airlines does not operate
  121.181(c)(6)
                        airport that meets the requirements of § 121.625.                                                                     reciprocating powered aircraft
                        This section does not apply to large nontransport category airplanes operated under                             N/A TransGlobal Airlines does not operate
   121.181(d)
                        § 121.173(c).                                                                                                         reciprocating powered aircraft

121.183 Part 25 – Airplanes with Four or More Engines: Reciprocating Engine Powered; Enroute Limitations; Two Engines
Inoperative
                        No person may operate an airplane certificated under Part 25 and having four or
   121.183(a)
                        more engines unless -                                                                                                      N/A by aircraft type
                        There is no place along the intended track that is more than 90 minutes (with all
  121.183(a)(1)         engines operating at cruising power) from an airport that meets the requirements of                                        N/A by aircraft type
                        § 121.187; or
                        It is operated at a weight allowing the airplane, with the two critical engines
                        inoperative, to climb at 0.013 VS02 feet per minute (that is, the number of feet per
  121.183(a)(2)         minute is obtained by multiplying the number of knots squared by 0.013) at an                                              N/A by aircraft type
                        altitude of 1,000 feet above the highest ground or obstruction within 10 miles on
                        each side of the intended track, or at an altitude of 5,000 feet, whichever is higher.
   121.183(b)           For the purposes of paragraph (a)(2) of this section, it is assumed that -                                                 N/A by aircraft type
                        The two engines fail at the point that is most critical with respect to the takeoff
  121.183(b)(1)
                        weight:                                                                                                                    N/A by aircraft type
                        Consumption of fuel and oil is normal with all engines operating up to the point
  121.183(b)(2)
                        where the two engines fail and with two engines operating beyond that point;                                               N/A by aircraft type
                        Where the engines are assumed to fail at an altitude above the prescribed minimum
                        altitude, compliance with the prescribed rate of climb at the prescribed minimum
                        altitude need not be shown during the descent from the cruising altitude to the
  121.183(b)(3)         prescribed minimum altitude, if those requirements can be met once the prescribed                                          N/A by aircraft type
                        minimum altitude is reached, and assuming descent to be along a net flight path and
                        the rate of descent to be 0.013 VS02 greater than the rate in the approved
                        performance data; and
                        If fuel jettisoning is provided, the airplane's weight at the point where the two engines
                        fail is considered to be not less than that which would include enough fuel to proceed
  121.183(b)(4)
                        to an airport meeting the requirements of § 121.187 and to arrive at an altitude of at                                     N/A by aircraft type
                        least 1,000 feet directly over that airport.




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121.185 Airplanes: Reciprocating Engine Powered; Landing Limitations; Destination Airport
                        (a) Except as provided in paragraph (b) of this section no person operating a
                        reciprocating engine powered airplane may takeoff that airplane, unless its weight on
                        arrival, allowing for normal consumption of fuel and oil in flight, would allow a full
                                                                                                                                       N/A TransGlobal Airlines does not operate
   § 121.185            stop landing at the intended destination within 60 percent of the effective length of
                        each runway described below from a point 50 feet directly above the intersection of                                  reciprocating powered aircraft
                        the obstruction clearance plane and the runway. For the purposes of determining the
                        allowable landing weight at the destination airport the following is assumed:
                        The airplane is landed on the most favorable runway and in the most favorable                                  N/A TransGlobal Airlines does not operate
  121.185(a)(1)         direction in still air.
                                                                                                                                             reciprocating powered aircraft
                        The airplane is landed on the most suitable runway considering the probable wind
                        velocity and direction (forecast for the expected time of arrival), the ground handling
                        characteristics of the type of airplane, and other conditions such as landing aids and                         N/A TransGlobal Airlines does not operate
  121.185(a)(2)
                        terrain, and allowing for the effect of the landing path and roll of not more than 50                                reciprocating powered aircraft
                        percent of the headwind component or not less than 150 percent of the tailwind
                        component.
                        An airplane that would be prohibited from being taken off because it could not meet
                        the requirements of paragraph (a)(2) of this section may be taken off if an alternate
                                                                                                                                       N/A TransGlobal Airlines does not operate
   121.185(b)           airport is specified that meets all of the requirements of this section except that the
                        airplane can accomplish a full stop landing within 70 percent of the effective length of                             reciprocating powered aircraft
                        the runway.
                        This section does not apply to large nontransport category airplanes operated under                            N/A TransGlobal Airlines does not operate
   121.185(c)           § 121.173(c).
                                                                                                                                             reciprocating powered aircraft

121.187 Airplanes: Reciprocating Engine Powered; Landing Limitations; Alternate Airport
   121.187(a)           No person may list an airport as an alternate airport in a dispatch or flight release
                        unless the airplane (at the weight anticipated at the time of arrival at the airport),                         N/A TransGlobal Airlines does not operate
                        based on the assumptions in § 121.185, can be brought to a full stop landing, within                                 reciprocating powered aircraft
                        70 percent of the effective length of the runway.
   121.187(b)           This section does not apply to large nontransport category airplanes operated under                            N/A TransGlobal Airlines does not operate
                        § 121.173(c).                                                                                                        reciprocating powered aircraft

121.189 Airplanes: Turbine Engine Powered; Takeoff Limitations
                        No person operating a turbine engine powered airplane may takeoff that airplane at
   121.189(a)           a weight greater than that listed in the Airplane Flight Manual for the elevation of the    170-PFM 2.3.1 A
                        airport and for the ambient temperature existing at takeoff.



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                        No person operating a turbine engine powered airplane certificated after August 26,
                        1957, but before August 30, 1959 (SR422, 422A), may takeoff that airplane at a
                        weight greater than that listed in the Airplane Flight Manual for the minimum
   121.189(b)
                        distances required for takeoff. In the case of an airplane certificated after September                            N/A by certification date
                        30, 1958 (SR422A, 422B), the takeoff distance may include a clearway distance but
                        the clearway distance included may not be greater than 1/2 of the takeoff run.
                        No person operating a turbine engine powered airplane certificated after August 29,
   121.189(c)           1959 (SR422B), may takeoff that airplane at a weight greater than that listed in the        170-PFM 2.3.1 C
                        Airplane Flight Manual at which compliance with the following may be shown:
                        The accelerate-stop distance must not exceed the length of the runway plus the
  121.189(c)(1)
                        length of any stopway.                                                                      170-PFM 2.3.1 C1
                        The takeoff distance must not exceed the length of the runway plus the length of any
  121.189(c)(2)         clearway except that the length of any clearway included must not be greater than           170-PFM 2.3.1 C2
                        one-half the length of the runway.
  121.189(c)(3)         The takeoff run must not be greater than the length of the runway.                          170-PFM 2.3.1 C3
                        No person operating a turbine engine powered airplane may takeoff that airplane at
   121.189(d)
                        a weight greater than that listed in the Airplane Flight Manual -                           170-PFM 2.3.1 D
                        In the case of an airplane certificated after August 26, 1957, but before October 1,
                        1958 (SR422), that allows a takeoff path that clears all obstacles either by at least
  121.189(d)(1)         (35 + 0.01 * D) feet vertically (D is the distance along the intended flight path from                             N/A by certification date
                        the end of the runway in feet), or by at least 200 feet horizontally within the airport
                        boundaries and by at least 300 feet horizontally after passing the boundaries; or
                        In the case of an airplane certificated after September 30, 1958 (SR 422A, 422B),
                        that allows a net takeoff flight path that clears all obstacles either by a height of at
  121.189(d)(2)
                        least 35 feet vertically, or by at least 200 feet horizontally within the airport           170-PFM 2.3.1 D1
                        boundaries and by at least 300 feet horizontally after passing the boundaries.
                        In determining maximum weights, minimum distances, and flight paths under
                        paragraphs (a) through (d) of this section, correction must be made for the runway to
                        be used, the elevation of the airport, the effective runway gradient, the ambient
                        temperature and wind component at the time of takeoff, and, if operating limitations
                        exist for the minimum distances required for takeoff from wet runways, the runway
   121.189(e)
                        surface condition (dry or wet). Wet runway distances associated with grooved or             170-PFM 2.3.1 E
                        porous friction course runways, if provided in the Airplane Flight Manual, may be
                        used only for runways that are grooved or treated with a porous friction course (PFC)
                        overlay, and that the operator determines are designed, constructed, and maintained
                        in a manner acceptable to the Administrator.
                        For the purposes of this section, it is assumed that the airplane is not banked before
                        reaching a height of 50 feet, as shown by the takeoff path or net takeoff flight path
   121.189(f)
                        data (as appropriate) in the Airplane Flight Manual, and thereafter that the maximum        170-PFM 2.3.1 F
                        bank is not more than 15°.



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                        For the purposes of this section the terms, "takeoff distance," "takeoff run," "net
   121.189(g)           takeoff flight path" and "takeoff path" have the same meanings as set forth in the            170-PFM 2.3.1 G
                        rules under which the airplane was certificated.


121.191 Airplanes: Turbine Engine Powered; Enroute Limitations; One Engine Inoperative
                        No person operating a turbine engine powered airplane may takeoff that airplane at
                        a weight, allowing for normal consumption of fuel and oil, that is greater than that
   121.191(a)           which (under the approved, one engine inoperative, enroute net flight path data in            170-PFM 2.3.2 A
                        the Airplane Flight Manual for that airplane) will allow compliance with paragraph (a)
                        (1) or (2) of this section, based on the ambient temperatures expected enroute:
                        There is a positive slope at an altitude of at least 1,000 feet above all terrain and
                        obstructions within five statute miles on each side of the intended track, and, in
  121.191(a)(1)         addition, if that airplane was certificated after August 29, 1959 (SR 422B) there is a        170-PFM 2.3.2 A
                        positive slope at 1,500 feet above the airport where the airplane is assumed to land
                        after an engine fails.
                        The net flight path allows the airplane to continue flight from the cruising altitude to
                        an airport where a landing can be made under § 121.197, clearing all terrain and
                        obstructions within five statute miles of the intended track by at least 2,000 feet
  121.191(a)(2)         vertically and with a positive slope at 1,000 feet above the airport where the airplane        170-PFM 2.9 B
                        lands after an engine fails, or, if that airplane was certificated after September 30,
                        1958 (SR 422A, 422B), with a positive slope at 1,500 feet above the airport where
                        the airplane lands after an engine fails.
   121.191(b)           For the purposes of paragraph (a)(2) of this section, it is assumed that -
  121.191(b)(1)         The engine fails at the most critical point enroute;                                           170-PFM 2.9 B
                        The airplane passes over the critical obstruction, after engine failure at a point that is
                        no closer to the obstruction than the nearest approved radio navigation fix, unless
  121.191(b)(2)
                        the Administrator authorizes a different procedure based on adequate operational               170-PFM 2.9 B
                        safeguards;
  121.191(b)(3)         An approved method is used to allow for adverse winds:                                         170-PFM 2.9 B
                        Fuel jettisoning will be allowed if the certificate holder shows that the crew is properly
  121.191(b)(4)         instructed, that the training program is adequate, and that all other precautions are                            N/A The ERJ-170 cannot jettison fuel
                        taken to insure a safe procedure;
                        The alternate airport is specified in the dispatch or flight release and meets the
  121.191(b)(5)
                        prescribed weather minimums; and                                                               170-PFM 2.9 B
                        The consumption of fuel and oil after engine failure is the same as the consumption
  121.191(b)(6)
                        that is allowed for in the approved net flight path data in the Airplane Flight Manual.        170-PFM 2.9 B




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121.193 Airplanes: Turbine Engine Powered; Enroute Limitations; Two Engines Inoperative
                        Airplanes certificated after August 26, 1957, but before October 1, 1958 (SR 422).
   121.193(a)           No person may operate a turbine engine powered airplane along an intended route                                           N/A by aircraft type
                        unless he complies with either of the following:
                        There is no place along the intended track that is more than 90 minutes (with all
  121.193(a)(1)         engines operating at cruising power) from an airport that meets the requirements of                                       N/A by aircraft type
                        § 121.197.
                        Its weight, according to the two engine inoperative, enroute, net flight path data in
                        the Airplane Flight Manual, allows the airplane to fly from the point where the two
                        engines are assumed to fail simultaneously to an airport that meets the requirements
  121.193(a)(2)         of § 121.197, with a net flight path (considering the ambient temperature anticipated                                     N/A by aircraft type
                        along the track) having a positive slope at an altitude of at least 1,000 feet above all
                        terrain and obstructions within five miles on each side of the intended track, or at an
                        altitude of 5,000 feet, whichever is higher.
                           For the purposes of paragraph (a)(2) of this section, it is assumed that the two
                        engines fail at the most critical point enroute, that if fuel jettisoning is provided, the
                        airplane's weight at the point where the engines fail includes enough fuel to continue
                        to the airport and to arrive at an altitude of at least 1,000 feet directly over the airport,                             N/A by aircraft type
                        and that the fuel and oil consumption after engine failure is the same as the
                        consumption allowed for in the net flight path data in the Airplane Flight Manual.
                        Aircraft certificated after September 30, 1958, but before August 30, 1959 (SR
   121.193(b)           422A). No person may operate a turbine engine powered airplane along an intended                                          N/A by aircraft type
                        route unless he complies with either of the following:
                        There is no place along the intended track that is more than 90 minutes (with all
  121.193(b)(1)         engines operating at cruising power) from an airport that meets the requirements of                                       N/A by aircraft type
                        § 121.197.
                        Its weight, according to the two engine inoperative, enroute, net flight path data in
                        the Airplane Flight Manual, allows the airplane to fly from the point where the two
                        engines are assumed to fail simultaneously to an airport that meets the requirements
  121.193(b)(2)         of § 121.197, with a net flight path (considering the ambient temperatures anticipated                                    N/A by aircraft type
                        along the track) having a positive slope at an altitude of at least 1,000 feet above all
                        terrain and obstructions within 5 miles on each side of the intended track, or at an
                        altitude of 2,000 feet, whichever is higher.
                           For the purposes of paragraph (b)(2) of this section, it is assumed that the two
                        engines fail at the most critical point enroute, that the airplane's weight at the point
                        where the engines fail includes enough fuel to continue to the airport, to arrive at an
                        altitude of at least 1,500 feet directly over the airport, and thereafter to fly for 15                                   N/A by aircraft type
                        minutes at cruise power or thrust, or both, and that the consumption of fuel and oil
                        after engine failure is the same as the consumption allowed for in the net flight path
                        data in the Airplane Flight Manual.



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                            Aircraft certificated after August 29, 1959 (SR 422B). No person may operate a
    121.193(c)              turbine engine powered airplane along an intended route unless he complies with                                      N/A by aircraft type
                            either of the following:
                            There is no place along the intended track that is more than 90 minutes (with all
  121.193(c)(1)             engines operating at cruising power) from an airport that meets the requirements of                                  N/A by aircraft type
                            § 121.197.
                            Its weight, according to the two engine inoperative, enroute, net flight path data in
                            the Airplane Flight Manual, allows the airplane to fly from the point where the two
                            engines are assumed to fail simultaneously to an airport that meets the requirements
  121.193(c)(2)             of § 121.197, with the net flight path (considering the ambient temperatures                                         N/A by aircraft type
                            anticipated along the track) clearing vertically by at least 2,000 feet all terrain and
                            obstructions within five statute miles (4.34 nautical miles) on each side of the
                            intended track. For the purposes of this subparagraph, it is assumed that -
 121.193(c)(2)(i)           The two engines fail at the most critical point enroute;                                                             N/A by aircraft type
                            The net flight path has a positive slope at 1,500 feet above the airport where the
 121.193(c)(2)(ii)
                            landing is assumed to be made after the engines fail;                                                                N/A by aircraft type
                            Fuel jettisoning will be approved if the certificate holder shows that the crew is
 121.193(c)(2)(iii)         properly instructed, that the training program is adequate, and that all other                                       N/A by aircraft type
                            precautions are taken to ensure a safe procedure;
                            The airplane's weight at the point where the two engines are assumed to fail
                            provides enough fuel to continue to the airport, to arrive at an altitude of at least
 121.193(c)(2)(iv)
                            1,500 feet directly over the airport, and thereafter to fly for 15 minutes at cruise                                 N/A by aircraft type
                            power or thrust, or both; and
                            The consumption of fuel and oil after the engine failure is the same as the
 121.193(c)(2)(v)           consumption that is allowed for in the net flight path data in the Airplane Flight                                   N/A by aircraft type
                            Manual.


121.195 Airplanes: Turbine Engine Powered; Landing Limitations; Destination Airports
                            No person operating a turbine engine powered airplane may takeoff that airplane at
                            such a weight that (allowing for normal consumption of fuel and oil in flight to the
                            destination or alternate airport) the weight of the airplane on arrival would exceed the
    121.195(a)
                            landing weight set forth in the Airplane Flight Manual for the elevation of the             170-PFM 2.3.3 A
                            destination or alternate airport and the ambient temperature anticipated at the time
                            of landing.




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                        Except as provided in paragraph (c), (d), or (e) of this section, no person operating a
                        turbine engine powered airplane may takeoff that airplane unless its weight on
                        arrival, allowing for normal consumption of fuel and oil in flight (in accordance with
                        the landing distance set forth in the Airplane Flight Manual for the elevation of the
                        destination airport and the wind conditions anticipated there at the time of landing),
   121.195(b)
                        would allow a full stop landing at the intended destination airport within 60 percent of     170-PFM 2.3.3 B
                        the effective length of each runway described below from a point 50 feet above the
                        intersection of the obstruction clearance plane and the runway. For the purpose of
                        determining the allowable landing weight at the destination airport the following is
                        assumed:
                        The airplane is landed on the most favorable runway and in the most favorable
  121.195(b)(1)
                        direction, in still air.                                                                     170-PFM 2.3.3 B
                        The airplane is landed on the most suitable runway considering the probable wind
  121.195(b)(2)         velocity and direction and the ground handling characteristics of the airplane, and          170-PFM 2.3.3 B
                        considering other conditions such as landing aids and terrain.
                        A turbopropeller powered airplane that would be prohibited from being taken off
                        because it could not meet the requirements of paragraph (b)(2) of this section, may
                                                                                                                                        N/A TransGlobal Airlines does not operate
   121.195(c)           be taken off if an alternate airport is specified that meets all the requirements of this
                        section except that the airplane can accomplish a full stop landing within 70 percent                                turbopropeller powered aircraft
                        of the effective length of the runway.
                        Unless, based on a showing of actual operating landing techniques on wet runways,
                        a shorter landing distance (but never less than that required by paragraph (b) of this
                        section) has been approved for a specific type and model airplane and included in
                        the Airplane Flight Manual, no person may takeoff a turbojet powered airplane when
   121.195(d)
                        the appropriate weather reports and forecasts, or a combination thereof, indicate that       170-PFM 2.3.3 C
                        the runways at the destination airport may be wet or slippery at the estimated time of
                        arrival unless the effective runway length at the destination airport is at least 115
                        percent of the runway length required under paragraph (b) of this section.
                        A turbojet powered airplane that would be prohibited from being taken off because it
                        could not meet the requirements of paragraph (b)(2) of this section may be taken off
   121.195(e)
                        if an alternate airport is specified that meets all the requirements of paragraph (b) of     170-PFM 2.3.3 D
                        this section.


121.197 Airplanes: Turbine Engine Powered; Landing Limitations; Alternate Airports
                        No person may list an airport as an alternate airport in a dispatch or flight release for
                        a turbine engine powered airplane unless (based on the assumptions in §
                        121.195(b)) that airplane at the weight anticipated at the time of arrival can be
   § 121.197            brought to a full stop landing within 70 percent of the effective length of the runway        170-PFM 2.3.4
                        for turbopropeller powered airplanes and 60 percent of the effective length of the
                        runway for turbojet powered airplanes, from a point 50 feet above the intersection of
                        the obstruction clearance plane and the runway.


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                        In the case of an alternate airport for departure, as provided in § 121.617, allowance
   § 121.197            may be made for fuel jettisoning in addition to normal consumption of fuel and oil                                  N/A The ERJ-170 cannot jettison fuel
                        when determining the weight anticipated at the time of arrival.


121.198 Cargo Service Airplanes: Increased Zero Fuel and Landing Weights
                        Notwithstanding the applicable structural provisions of the airworthiness regulations
                        but subject to paragraphs (b) through (g) of this section, a certificate holder may
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
   121.198(a)           operate (for cargo service only) any of the following airplanes (certificated under Part
                        4b of the Civil Air Regulations effective before March 13, 1956) at increased zero                                           Service airplanes
                        fuel and landing weights -
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
  121.198(a)(1)         DC-6A, DC-6B, DC-7B, and DC-7C; and
                                                                                                                                                     Service airplanes
                        L1049B, C, D, E, F, G, and H, and the L1649A when modified in accordance with                                  N/A TransGlobal Airlines does not operate Cargo
  121.198(a)(2)
                        supplemental type certificate SA 4-1402.                                                                                     Service airplanes
                        The zero fuel weight (maximum weight of the airplane with no disposable fuel and
                        oil) and the structural landing weight may be increased beyond the maximum                                     N/A TransGlobal Airlines does not operate Cargo
   121.198(b)
                        approved in full compliance with applicable regulations only if the Administrator finds                                      Service airplanes
                        that -
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
  121.198(b)(1)         The increase is not likely to reduce seriously the structural strength;
                                                                                                                                                     Service airplanes
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
  121.198(b)(2)         The probability of sudden fatigue failure is not noticeably increased;
                                                                                                                                                     Service airplanes
                        The flutter, deformation, and vibration characteristics do not fall below those required                       N/A TransGlobal Airlines does not operate Cargo
  121.198(b)(3)
                        by applicable regulations; and                                                                                               Service airplanes
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
  121.198(b)(4)         All other applicable weight limitations will be met.
                                                                                                                                                     Service airplanes
                        No zero fuel weight may be increased by more than five percent, and the increase in
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
   121.198(c)           the structural landing weight may not exceed the amount, in pounds, of the increase
                        in zero fuel weight.                                                                                                         Service airplanes
                        Each airplane must be inspected in accordance with the approved special inspection
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
   121.198(d)           procedure s, for operations at increased weights, established and issued by the
                        manufacturer of the type of airplane.                                                                                        Service airplanes
                        Each airplane operated under this section must be operated in accordance with the                              N/A TransGlobal Airlines does not operate Cargo
   121.198(e)
                        passenger carrying performance operating limitations prescribed in this part.                                                Service airplanes
                        The Airplane Flight Manual for each airplane operated under this section must be
                                                                                                                                       N/A TransGlobal Airlines does not operate Cargo
   121.198(f)           appropriately revised to include the operating limitations and information needed for
                        operation at the increased weights.                                                                                          Service airplanes

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                        Except as provided for the carrying of persons under § 121.583 each airplane
                        operated at an increased weight under this section must, before it is used in
                                                                                                                                        N/A TransGlobal Airlines does not operate Cargo
   121.198(g)           passenger service, be inspected under the special inspection procedure s for return
                        to passenger service established and issued by the manufacturer and approved by                                               Service airplanes
                        the Administrator.


121.199 Nontransport Category Airplanes: Takeoff Limitations
                        No person operating a nontransport category airplane may takeoff that airplane at a
                        weight greater than the weight that would allow the airplane to be brought to a safe
                        stop within the effective length of the runway, from any point during the takeoff
   121.199(a)           before reaching 105 percent of minimum control speed (the minimum speed at which                                               N/A by category
                        an airplane can be safely controlled in flight after an engine becomes inoperative) or
                        115 percent of the power off stalling speed in the takeoff configuration, whichever is
                        greater.
   121.199(b)           For the purposes of this section -                                                                                             N/A by category
  121.199(b)(1)         It may be assumed that takeoff power is used on all engines during the acceleration;                                           N/A by category
                        Not more than 50 percent of the reported headwind component, or not less than 150
  121.199(b)(2)
                        percent of the reported tailwind component, may be taken into account;                                                         N/A by category
                        The average runway gradient (the difference between the elevations of the
  121.199(b)(3)         endpoints of the runway divided by the total length) must be considered if it is more                                          N/A by category
                        than one-half of 1 percent;
  121.199(b)(4)         It is assumed that the airplane is operating in standard atmosphere; and                                                       N/A by category
                        The "effective length of the runway" for takeoff means the distance from the end of
                        the runway at which the takeoff is started to a point at which the obstruction
  121.199(b)(5)
                        clearance plane associated with the other end of the runway intersects the runway                                              N/A by category
                        centerline.


121.201 Nontransport Category Airplanes: Enroute Limitations; One Engine Inoperative
                        Except as provided in paragraph (b) of this section, no person operating a
                        nontransport category airplane may takeoff that airplane at a weight that does not
   121.201(a)           allow a rate of climb of at least 50 feet a minute, with the critical engine inoperative,                                      N/A by category
                        at an altitude of at least 1,000 feet above the highest obstruction within five miles on
                        each side of the intended track, or 5,000 feet, whichever is higher.




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                           Notwithstanding paragraph (a) of this section, if the Administrator finds that safe
                           operations are not impaired, a person may operate the airplane at an altitude that
                           allows the airplane, in case of engine failure, to clear all obstructions within 5 miles
                           on each side of the intended track by 1,000 feet. If this procedure is used, the rate of
   121.201(b)
                           descent for the appropriate weight and altitude is assumed to be 50 feet a minute                                     N/A by category
                           greater than the rate in the approved performance data. Before approving such a
                           procedure, the Administrator considers the following for the route, route segment, or
                           area concerned:
  121.201(b)(1)            The reliability of wind and weather forecasting.                                                                      N/A by category
  121.201(b)(2)            The location and kinds of navigation aids.                                                                            N/A by category
                           The prevailing weather conditions, particularly the frequency and amount of
  121.201(b)(3)
                           turbulence normally encountered.                                                                                      N/A by category
  121.201(b)(4)            Terrain features.                                                                                                     N/A by category
  121.201(b)(5)            Air traffic control problems.                                                                                         N/A by category
  121.201(b)(6)            Any other operational factors that affect the operation.                                                              N/A by category
   121.201(c)              For the purposes of this section, it is assumed that -                                                                N/A by category
  121.201(c)(1)            The critical engine is inoperative;                                                                                   N/A by category
  121.201(c)(2)            The propeller of the inoperative engine is in the minimum drag position;                                              N/A by category
  121.201(c)(3)            The wing flaps and landing gear are in the most favorable position;                                                   N/A by category
  121.201(c)(4)            The operating engines are operating at the maximum continuous power available;                                        N/A by category
  121.201(c)(5)            The airplane is operating in standard atmosphere; and                                                                 N/A by category
                           The weight of the airplane is progressively reduced by the anticipated consumption
  121.201(c)(6)
                           of fuel and oil.                                                                                                      N/A by category


121.203 Nontransport Category Airplanes: Landing Limitations; Destination Airport
                           No person operating a nontransport category airplane may takeoff that airplane at a
   121.203(a)
                           weight that -                                                                                                         N/A by category
                           Allowing for anticipated consumption of fuel and oil, is greater than the weight that
  121.203(a)(1)            would allow a full stop landing within 60 percent of the effective length of the most                                 N/A by category
                           suitable runway at the destination airport; and
  121.203(a)(2)            Is greater than the weight allowable if the landing is to be made on the runway -                                     N/A by category
 121.203(a)(2)(i)          With the greatest effective length in still air; and                                                                  N/A by category
                           Required by the probable wind, taking into account not more than 50 percent of the
 121.203(a)(2)(ii)
                           headwind component or not less than 150 percent of the tailwind component.                                            N/A by category
   121.203(b)              For the purposes of this section, it is assumed that -                                                                N/A by category

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                        The airplane passes directly over the intersection of the obstruction clearance plane
  121.203(b)(1)         and the runway at a height of 50 feet in a steady gliding approach at a true indicated                                               N/A by category
                        airspeed of at least 1.3 VS0;
  121.203(b)(2)         The landing does not require exceptional pilot skill; and                                                                            N/A by category
  121.203(b)(3)         The airplane is operating in standard atmosphere.                                                                                    N/A by category

121.205 Nontransport Category Airplanes: Landing Limitations; Alternate Airport
                        No person may list an airport as an alternate airport in a dispatch or flight release for
                        a nontransport category airplane unless that airplane (at the weight anticipated at the
   § 121.205
                        time of arrival) based on the assumptions contained in § 121.203, can be brought to                                                  N/A by category
                        a full stop landing within 70 percent of the effective length of the runway.


121.207 Provisionally Certificated Airplanes: Operating Limitations
                        In addition to the limitations in § 91.317 of this chapter, the following limitations apply                             N/A TransGlobal Airlines does not operate
   § 121.207
                        to the operation of provisionally certificated airplanes by certificate holders:                                           Provisionally Certificated Airplanes
                        In addition to crewmembers, each certificate holder may carry on such an airplane
                                                                                                                                                N/A TransGlobal Airlines does not operate
   121.207(a)           only those persons who are listed in § 121.547(c) or who are specifically authorized
                        by both the certificate holder and the Administrator.                                                                      Provisionally Certificated Airplanes
                        Each certificate holder shall keep a log of each flight conducted under this section
                        and shall keep accurate and complete records of each inspection made and all
                                                                                                                                                N/A TransGlobal Airlines does not operate
   121.207(b)           maintenance performed on the airplane. The certificate holder shall make the log
                        and records made under this section available to the manufacturer and the                                                  Provisionally Certificated Airplanes
                        Administrator.


Subpart J – SPECIAL AIRWORTHINESS REQUIREMENTS
121.211 Applicability
                        This subpart prescribes special airworthiness requirements applicable to certificate
   121.211(a)
                        holders as stated in paragraphs (b) through (e) of this section.
                        Except as provided in paragraph (d) of this section, each airplane type certificated
                        under Aero Bulletin 7A or part 04 of the Civil Air Regulations in effect before
   121.211(b)
                        November 1, 1946 must meet the special airworthiness requirements in §§ 121.215                                           N/A by type certificate status and date
                        through 121.283.
                        Each certificate holder must comply with the requirements of §§ 121.285 through                                   TransGlobal Airlines will comply with the requirements
   121.211(c)
                        121.291.                                                                                                          of §§ 121.285 through 121.291 as applicable

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                       If the Administrator determines that, for a particular model of airplane used in cargo
                       service, literal compliance with any requirement under paragraph (b) of this section
                                                                                                                                     N/A since TransGlobal Airlines does not engage in
   121.211(d)          would be extremely difficult and that compliance would not contribute materially to
                       the objective sought, he may require compliance only with those requirements that                                              cargo service
                       are necessary to accomplish the basic objectives of this part.
                       No person may operate under this part a nontransport category airplane type
   121.211(e)          certificated after December 31, 1964, unless the airplane meets the special                                                    N/A by category
                       airworthiness requirements in § 121.293.


121.213
   § 121.213           [Removed and Reserved]


121.215 Cabin Interiors
                       Except as provided in § 121.312, each compartment used by the crew or                                        N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.215(a)
                       passengers must meet the requirements of this section.                                                                             of 121.211(b)
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.215(b)          Materials must be at least flash resistant.
                                                                                                                                                          of 121.211(b)
                       The wall and ceiling linings and the covering of upholstering, floors, and furnishings                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.215(c)
                       must be flame resistant.                                                                                                           of 121.211(b)
                       Each compartment where smoking is to be allowed must be equipped with self-
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.215(d)          contained ash trays that are completely removable and other compartments must be
                       placarded against smoking.                                                                                                         of 121.211(b)
                       Each receptacle for used towels, papers, and wastes must be of fire resistant
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.215(e)          material and must have a cover or other means of containing possible fires started in
                       the receptacles.                                                                                                                   of 121.211(b)

121.217 Internal Doors
   § 121.217           In any case where internal doors are equipped with louvers or other ventilating
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
                       means, there must be a means convenient to the crew for closing the flow of air
                       through the door when necessary.                                                                                                   of 121.211(b)

121.219 Ventilation
                       Each passenger or crew compartment must be suitably ventilated. Carbon monoxide
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.219           concentration may not be more than one part in 20,000 parts of air, and fuel fumes
                       may not be present.                                                                                                                of 121.211(b)

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                        In any case where partitions between compartments have louvers or other means
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.219            allowing air to flow between compartments, there must be a means convenient to the
                        crew for closing the flow of air through the partitions, when necessary.                                                            of 121.211(b)

121.221 Fire Precautions
                        Each compartment must be designed so that, when used for storing cargo or                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(a)
                        baggage, it meets the following requirements:                                                                                       of 121.211(b)
                        No compartment may include controls, wiring, lines, equipment, or accessories that
                        would upon damage or failure, affect the safe operation of the airplane unless the
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(a)(1)         item is adequately shielded, isolated, or otherwise protected so that it cannot be
                        damaged by movement of cargo in the compartment and so that damage to or                                                            of 121.211(b)
                        failure of the item would not create a fire hazard in the compartment.
                        Cargo or baggage may not interfere with the functioning of the fire protective                                N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(a)(2)
                        features of the compartment.                                                                                                        of 121.211(b)
                        Materials used in the construction of the compartments, including tie down                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(a)(3)
                        equipment, must be at least flame resistant.                                                                                        of 121.211(b)
                        Each compartment must include provisions for safeguarding against fires according                             N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(a)(4)
                        to the classifications set forth in paragraphs (b) through (f) of this section.                                                     of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(b)           Class A. Cargo and baggage compartments are classified in the "A" category if -
                                                                                                                                                            of 121.211(b)
                        A fire therein would be readily discernible to a member of the crew while at his                              N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(b)(1)
                        station; and                                                                                                                        of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(b)(2)         All parts of the compartment are easily accessible in flight.
                                                                                                                                                            of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221 (b)          There must be a hand fire extinguisher available for each Class A compartment.
                                                                                                                                                            of 121.211(b)
                        Class B. Cargo and baggage compartments are classified in the "B" category if
                        enough access is provided while in flight to enable a member of the crew to
                        effectively reach all of the compartment and its contents with a hand fire extinguisher
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(c)           and the compartment is so designed that, when the access provisions are being
                        used, no hazardous amount of smoke, flames, or extinguishing agent enters any                                                       of 121.211(b)
                        compartment occupied by the crew or passengers. Each Class B compartment must
                        comply with the following:
                        It must have a separate approved smoke or fire detector system to give warning at                             N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(c)(1)
                        the pilot or flight engineer station.                                                                                               of 121.211(b)


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                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(c)(2)         There must be a hand fire extinguisher available for the compartment.
                                                                                                                                                            of 121.211(b)
                        It must be lined with fire resistant material, except that additional service lining of                       N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(c)(3)
                        flame resistant material may be used.                                                                                               of 121.211(b)
                        Class C. Cargo and baggage compartments are classified in the "C" category if they
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(d)           do not conform with the requirements for the "A", "B", "D", or "E" categories. Each
                        Class C compartment must comply with the following:                                                                                 of 121.211(b)
                        It must have a separate approved smoke or fire detector system to give warning at                             N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(d)(1)
                        the pilot or flight engineer station.                                                                                               of 121.211(b)
                        It must have an approved built-in fire extinguishing system controlled from the pilot                         N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(d)(2)
                        or flight engineer station.                                                                                                         of 121.211(b)
                        It must be designed to exclude hazardous quantities of smoke, flames, or
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(d)(3)         extinguishing agents from entering into any compartment occupied by the crew or
                        passengers.                                                                                                                         of 121.211(b)
                        It must have ventilation and draft controlled so that the extinguishing agent provided                        N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(d)(4)
                        can control any fire that may start in the compartment.                                                                             of 121.211(b)
                        It must be lined with fire resistant material, except that additional service lining of                       N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(d)(5)
                        flame resistant material may be used.                                                                                               of 121.211(b)
                        Class D. Cargo and baggage compartments are classified in the "D" category if they
                        are so designed and constructed that a fire occurring therein will be completely                              N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(e)
                        confined without endangering the safety of the airplane or the occupants. Each                                                      of 121.211(b)
                        Class D compartment must comply with the following:
                        It must have a means to exclude hazardous quantities of smoke, flames, or noxious                             N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(e)(1)
                        gases from entering any compartment occupied by the crew or passengers.                                                             of 121.211(b)
                        Ventilation and drafts must be controlled within each compartment so that any fire                            N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(e)(2)
                        likely to occur in the compartment will not progress beyond safe limits.                                                            of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(e)(3)         It must be completely lined with fire resistant material.
                                                                                                                                                            of 121.211(b)
                        Consideration must be given to the effect of heat within the compartment on                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(e)(4)
                        adjacent critical parts of the airplane.                                                                                            of 121.211(b)
                        Class E. On airplanes used for the carriage of cargo only, the cabin area may be
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.221(f)           classified as a Class "E" compartment. Each Class E compartment must comply with
                        the following:                                                                                                                      of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(f)(1)         It must be completely lined with fire resistant material.
                                                                                                                                                            of 121.211(b)


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                        It must have a separate system of an approved type smoke or fire detector to give                            N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(f)(2)
                        warning at the pilot or flight engineer station.                                                                                   of 121.211(b)
                        It must have a means to shut off the ventilating air flow to or within the compartment
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(f)(3)         and the controls for that means must be accessible to the flight crew in the crew
                        compartment.                                                                                                                       of 121.211(b)
                        It must have a means to exclude hazardous quantities of smoke, flames, or noxious                            N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(f)(4)
                        gases from entering the flight crew compartment.                                                                                   of 121.211(b)
                        Required crew emergency exits must be accessible under all cargo loading                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.221(f)(5)
                        conditions.                                                                                                                        of 121.211(b)

121.223 Proof of Compliance with § 121.221
                        Compliance with those provisions of § 121.221 that refer to compartment
                        accessibility, the entry of hazardous quantities of smoke or extinguishing agent into                        N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.223
                        compartments occupied by the crew or passengers, and the dissipation of the                                                        of 121.211(b)
                        extinguishing agent in Class "C" compartments must be shown by tests in flight.
                        During these tests it must be shown that no inadvertent operation of smoke or fire
                        detectors in other compartments within the airplane would occur as a result of fire
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.223            contained in any one compartment, either during the time it is being extinguished, or
                        thereafter, unless the extinguishing system floods those compartments                                                              of 121.211(b)
                        simultaneously.


121.225 Propeller Deicing Fluid
                        If combustible fluid is used for propeller deicing, the certificate holder must comply                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.225
                        with § 121.255.                                                                                                                    of 121.211(b)

121.227 Pressure Cross Feed Arrangements
                        Pressure cross feed lines may not pass through parts of the airplane used for
   121.227(a)
                        carrying persons or cargo unless -
                        There is a means to allow crewmembers to shut off the supply of fuel to these lines;                         N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.227(a)(1)
                        or                                                                                                                                 of 121.211(b)
                        The lines are enclosed in a fuel and fume proof enclosure that is ventilated and                             N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.227(a)(2)
                        drained to the exterior of the airplane.                                                                                           of 121.211(b)
                        However, such an enclosure need not be used if those lines incorporate no fittings
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
                        on or within the personnel or cargo areas and are suitably routed or protected to
                        prevent accidental damage.                                                                                                         of 121.211(b)

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                       Lines that can be isolated from the rest of the fuel system by valves at each end
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.227(b)          must incorporate provisions for relieving excessive pressures that may result from
                       exposure of the isolated line to high temperatures.                                                                                 of 121.211(b)

121.229 Location Of Fuel Tanks
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.229(a)          Fuel tanks must be located in accordance with § 121.255.
                                                                                                                                                           of 121.211(b)
                       No part of the engine nacelle skin that lies immediately behind a major air outlet from                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.229(b)
                       the engine compartment may be used as the wall of an integral tank.                                                                 of 121.211(b)
                       Fuel tanks must be isolated from personnel compartments by means of fume and                                  N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.229(c)
                       fuel proof enclosures.                                                                                                              of 121.211(b)

121.231 Fuel System Lines And Fittings
                       Fuel lines must be installed and supported so as to prevent excessive vibration and
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.231(a)          so as to be adequate to withstand loads due to fuel pressure and accelerated flight
                       conditions.                                                                                                                         of 121.211(b)
                       Lines connected to components of the airplanes between which there may be                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.231(b)
                       relative motion must incorporate provisions for flexibility.                                                                        of 121.211(b)
                       Flexible connections in lines that may be under pressure and subject to axial loading                         N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.231(c)
                       must use flexible hose assemblies rather than hose clamp connections.                                                               of 121.211(b)
                       Flexible hose must be of an acceptable type or proven suitable for the particular                             N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.231(d)
                       application.                                                                                                                        of 121.211(b)

121.233 Fuel Lines And Fittings In Designated Fire Zones
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.233            Fuel lines and fittings in each designated fire zone must comply with § 121.259.
                                                                                                                                                           of 121.211(b)

121.235 Fuel Valves
    121.235            Each fuel valve must -
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.235(a)          Comply with § 121.257;
                                                                                                                                                           of 121.211(b)


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                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.235(b)           Have positive stops or suitable index provisions in the "on" and "off" positions; and
                                                                                                                                                          of 121.211(b)
                        Be supported so that loads resulting from its operation or from accelerated flight                          N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.235(c)
                        conditions are not transmitted to the lines connected to the valve.                                                               of 121.211(b)

121.237 Oil Lines And Fittings In Designated Fire Zones
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.237             Oil line and fittings in each designated fire zone must comply with § 121.259.
                                                                                                                                                          of 121.211(b)

121.239 Oil Valves
   121.239(a)           Each oil valve must -
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.239(a)(1)         Comply with § 121.257;
                                                                                                                                                          of 121.211(b)
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.239(a)(2)         Have positive stops or suitable index provisions in the "on" and "off" positions; and
                                                                                                                                                          of 121.211(b)
                        Be supported so that loads resulting from its operation or from accelerated flight                          N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.239(a)(3)
                        conditions are not transmitted to the lines attached to the valve.                                                                of 121.211(b)
                        The closing of an oil shutoff means must not prevent feathering the propeller, unless                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.239(b)
                        equivalent safety provisions are incorporated.                                                                                    of 121.211(b)

121.241 Oil System Drains
                        Accessible drains incorporating either a manual or automatic means for positive
                                                                                                                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.241             locking in the closed position, must be provided to allow safe drainage of the entire
                        oil system.                                                                                                                       of 121.211(b)

121.243 Engine Breather Lines
                        Engine breather lines must be so arranged that condensed water vapor that may                               Aircraft certified under FAR Part 25 N/A by virtue of
   121.243(a)
                        freeze and obstruct the line cannot accumulate at any point.                                                                      121.211(b)
                        Engine breathers must discharge in a location that does not constitute a fire hazard
                                                                                                                                    Aircraft certified under FAR Part 25 N/A by virtue of
   121.243(b)           in case foaming occurs and so that oil emitted from the line does not impinge upon
                        the pilots' windshield.                                                                                                           121.211(b)


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                                                                                                                                      Aircraft certified under FAR Part 25 N/A by virtue of
   121.243(c)          Engine breathers may not discharge into the engine air induction system.
                                                                                                                                                            121.211(b)

121.245 Fire Walls
                       Each engine, auxiliary power unit, fuel burning heater, or other item of combustion
                                                                                                                                      Aircraft certified under FAR Part 25 N/A by virtue of
    121.245            equipment that is intended for operation in flight must be isolated from the rest of the
                       airplane by means of firewalls or shrouds, or by other equivalent means.                                                             121.211(b)

121.247 Firewall Construction
    121.247            Each firewall and shroud must -
                       Be so made that no hazardous quantity of air, fluids, or flame can pass from the                               N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.247 (a)
                       engine compartment to other parts of the airplane;                                                                                   of 121.211(b)
                       Have all openings in the fire wall or shroud sealed with close fitting fireproof                               N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.247 (b)
                       grommets, bushings, or firewall fittings;                                                                                            of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.247 (c)          Be made of fireproof material; and
                                                                                                                                                            of 121.211(b)
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.247 (d)          Be protected against corrosion.
                                                                                                                                                            of 121.211(b)

121.249 Cowling
                       Cowling must be made and supported so as to resist the vibration inertia, and air                              N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.249(a)
                       loads to which it may be normally subjected.                                                                                         of 121.211(b)
                       Provisions must be made to allow rapid and complete drainage of the cowling in
                       normal ground and flight attitudes. Drains must not discharge in locations
                       constituting a fire hazard. Parts of the cowling that are subjected to high
                                                                                                                                      N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.249(b)          temperatures because they are near exhaust system parts or because of exhaust
                       gas impingement must be made of fireproof material. Unless otherwise specified in                                                    of 121.211(b)
                       these regulations all other parts of the cowling must be made of material that is at
                       least fire resistant.




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121.251 Engine Accessory Section Diaphragm
                        Unless equivalent protection can be shown by other means, a diaphragm that
                        complies with § 121.247 must be provided on air cooled engines to isolate the                                N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.251
                        engine power section and all parts of the exhaust system from the engine accessory                                                 of 121.211(b)
                        compartment.


121.253 Powerplant Fire Protection
                        Designated fire zones must be protected from fire by compliance with §§ 121.255                              N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.253(a)
                        through 121.261.                                                                                                                   of 121.211(b)
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.253(b)           Designated fire zones are -
                                                                                                                                                           of 121.211(b)
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.253(b)(1)         Engine accessory sections;
                                                                                                                                                           of 121.211(b)
                        Installations where no isolation is provided between the engine and accessory                                N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.253(b)(2)
                        compartment; and                                                                                                                   of 121.211(b)
                        Areas that contain auxiliary power units, fuel burning heaters, and other combustion                         N/A Aircraft certified under FAR Part 25 N/A by virtue
  121.253(b)(3)
                        equipment.                                                                                                                         of 121.211(b)

121.255 Flammable Fluids
                        No tanks or reservoirs that are a part of a system containing flammable fluids or
                        gases may be located in designated fire zones, except where the fluid contained, the                         N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.255(a)
                        design of the system, the materials used in the tank, the shutoff means, and the                                                   of 121.211(b)
                        connections, lines, and controls provide equivalent safety.
                        At least one-half inch of clear airspace must be provided between any tank or                                N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.255(b)
                        reservoir and a firewall or shroud isolating a designated fire zone.                                                               of 121.211(b)

121.257 Shutoff Means
                        Each engine must have a means for shutting off or otherwise preventing hazardous
                        amounts of fuel, oil, deicer, and other flammable fluids from flowing into, within, or                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.257(a)
                        through any designated fire zone. However, means need not be provided to shut off                                                  of 121.211(b)
                        flow in lines that are an integral part of an engine.
                        The shutoff means must allow an emergency operating sequence that is compatible
                                                                                                                                     N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.257(b)           with the emergency operation of other equipment, such as feathering the propeller,
                        to facilitate rapid and effective control of fires.                                                                                of 121.211(b)

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                       Shutoff means must be located outside of designated fire zones, unless equivalent
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.257(c)          safety is provided, and it must be shown that no hazardous amount of flammable
                       fluid will drain into any designated fire zone after a shut off.                                                                      of 121.211(b)
                       Adequate provisions must be made to guard against inadvertent operation of the
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.257(d)          shutoff means and to make it possible for the crew to reopen the shutoff means after
                       it has been closed.                                                                                                                   of 121.211(b)

121.259 Lines And Fittings
                       Each line, and its fittings, that is located in a designated fire zone, if it carries
                       flammable fluids or gases under pressure, or is attached directly to the engine, or is
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.259(a)          subject to relative motion between components (except lines and fittings forming an
                       integral part of the engine), must be flexible and fire resistant with fire resistant,                                                of 121.211(b)
                       factory fixed, detachable, or other approved fire resistant ends.
                       Lines and fittings that are not subject to pressure or to relative motion between                               N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.259(b)
                       components must be of fire resistant materials.                                                                                       of 121.211(b)

121.261 Vent And Drain Lines
                       All vent and drain lines and their fittings, that are located in a designated fire zone
                       must, if they carry flammable fluids or gases, comply with § 121.259, if the                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.261
                       Administrator finds that the rupture or breakage of any vent or drain line may result                                                 of 121.211(b)
                       in a fire hazard.


121.263 Fire Extinguishing Systems
                       Unless the certificate holder shows that equivalent protection against destruction of
                       the airplane in case of fire is provided by the use of fireproof materials in the nacelle                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.263(a)
                       and other components that would be subjected to flame, fire extinguishing systems                                                     of 121.211(b)
                       must be provided to serve all designated fire zones.
                       Materials in the fire extinguishing system must not react chemically with the                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.263(b)          extinguishing agent so as to be a hazard.
                                                                                                                                                             of 121.211(b)

121.265 Fire Extinguishing Agents
                       Only methyl bromide, carbon dioxide, or another agent that has been shown to                                    N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.265            provide equivalent extinguishing action may be used as a fire extinguishing agent.
                                                                                                                                                             of 121.211(b)



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                       If methyl bromide or any other toxic extinguishing agent is used, provisions must be
                       made to prevent harmful concentrations of fluid or fluid vapors from entering any
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.265            personnel compartment either because of leakage during normal operation of the
                       airplane or because of discharging the fire extinguisher on the ground or in flight                                               of 121.211(b)
                       when there is a defect in the extinguishing system.
                       If a methyl bromide system is used, the containers must be charged with dry agent
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.265            and sealed by the fire extinguisher manufacturer or some other person using
                       satisfactory recharging equipment.                                                                                                of 121.211(b)
                       If carbon dioxide is used, it must not be possible to discharge enough gas into the                         N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.265            personnel compartments to create a danger of suffocating the occupants.
                                                                                                                                                         of 121.211(b)

121.267 Extinguishing Agent Container Pressure Relief
                       Extinguishing agent containers must be provided with a pressure relief to prevent
                       bursting of the container because of excessive internal pressures. The discharge line
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.267            from the relief connection must terminate outside the airplane in a place convenient
                       for inspection on the ground. An indicator must be provided at the discharge end of                                               of 121.211(b)
                       the line to provide a visual indication when the container has discharged.


121.269 Extinguishing Agent Container Compartment Temperature
                       Precautions must be taken to insure that the extinguishing agent containers are
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
    121.269            installed in places where reasonable temperatures can be maintained for effective
                       use of the extinguishing system.                                                                                                  of 121.211(b)

121.271 Fire Extinguishing System Materials
                       Except as provided in paragraph (b) of this section, each component of a fire
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.271(a)          extinguishing system that is in a designated fire zone must be made of fireproof
                       materials.                                                                                                                        of 121.211(b)
                       Connections that are subject to relative motion between components of the airplane
                                                                                                                                   N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.271(b)          must be made of flexible materials that are at least fire resistant and be located so
                       as to minimize the probability of failure.                                                                                        of 121.211(b)

121.273 Fire Detector Systems
                       Enough quick acting fire detectors must be provided in each designated fire zone to                         N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.273
                       assure the detection of any fire that may occur in that zone.                                                                     of 121.211(b)



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121.275 Fire Detectors
                       Fire detectors must be made and installed in a manner that assures their ability to
                       resist, without failure, all vibration, inertia, and other loads to which they may be                           N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.275
                       normally subjected. Fire detectors must be unaffected by exposure to fumes, oil,                                                      of 121.211(b)
                       water, or other fluids that may be present.


121.277 Protection of Other Airplane Components Against Fire
                       Except as provided in paragraph (b) of this section, all airplane surfaces aft of the
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.277(a)          nacelles in the area of one nacelle diameter on both sides of the nacelle centerline
                       must be made of material that is at least fire resistant.                                                                             of 121.211(b)
                       Paragraph (a) of this section does not apply to tail surfaces lying behind nacelles
                       unless the dimensional configuration of the airplane is such that the tail surfaces                             N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.277(b)
                       could be affected readily by heat, flames, or sparks emanating from a designated fire                                                 of 121.211(b)
                       zone or from the engine compartment of any nacelle.


121.279 Control Of Engine Rotation
                       Except as provided in paragraph (b) of this section, each airplane must have a                                  N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.279(a)
                       means of individually stopping and restarting the rotation of any engine in flight.                                                   of 121.211(b)
                       In the case of turbine engine installations, a means of stopping the rotation need be
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.279(b)          provided only if the Administrator finds that rotation could jeopardize the safety of the
                       airplane.                                                                                                                             of 121.211(b)

121.281 Fuel System Independence
                       Each airplane fuel system must be arranged so that the failure of any one
                                                                                                                                       N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.281(a)          component does not result in the irrecoverable loss of power of more than one
                       engine.                                                                                                                               of 121.211(b)
                       A separate fuel tank need not be provided for each engine if the certificate holder                             N/A Aircraft certified under FAR Part 25 N/A by virtue
   121.281(b)
                       shows that the fuel system incorporates features that provide equivalent safety.                                                      of 121.211(b)

121.283 Induction System Ice Prevention
                       A means for preventing the malfunctioning of each engine due to ice accumulation in                             N/A Aircraft certified under FAR Part 25 N/A by virtue
   § 121.283
                       the engine air induction system must be provided for each airplane.                                                                   of 121.211(b)



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121.285 Carriage Of Cargo In Passenger Compartments
                        Except as provided in paragraph (b), (c), or (d) or this section, no certificate holder                       N/A TransGlobal Airlines prohibits the carriage of
   121.285(a)
                        may carry cargo in the passenger compartment of an airplane.                                                       cargo in the passenger compartments
                        Cargo may be carried anywhere in the passenger compartment if it is carried in an                             N/A TransGlobal Airlines prohibits the carriage of
   121.285(b)
                        approved cargo bin that meets the following requirements:                                                          cargo in the passenger compartments
                        The bin must withstand the load factors and emergency landing conditions
                        applicable to the passenger seats of the airplane in which the bin is installed,                              N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(1)
                        multiplied by a factor of 1.15, using the combined weight of the bin and the maximum                               cargo in the passenger compartments
                        weight of cargo that may be carried in the bin.
                        The maximum weight of cargo that the bin is approved to carry and any instructions
                                                                                                                                      N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(2)         necessary to insure proper weight distribution within the bin must be conspicuously
                        marked on the bin.                                                                                                 cargo in the passenger compartments
                        The bin may not impose any load on the floor or other structure of the airplane that                          N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(3)
                        exceeds the load limitations of that structure.                                                                    cargo in the passenger compartments
                        The bin must be attached to the seat tracks or to the floor structure of the airplane,
                        and its attachment must withstand the load factors and emergency landing
                        conditions applicable to the passenger seats of the airplane in which the bin is                              N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(4)
                        installed, multiplied by either the factor 1.15 or the seat attachment factor specified                            cargo in the passenger compartments
                        for the airplane, whichever is greater, using the combined weight of the bin and the
                        maximum weight of cargo that may be carried in the bin.
                        The bin may not be installed in a position that restricts access to or use of any                             N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(5)
                        required emergency exit, or of the aisle in the passenger compartment.                                             cargo in the passenger compartments
                                                                                                                                      N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(6)         The bin must be fully enclosed and made of material that is at least flame resistant.
                                                                                                                                           cargo in the passenger compartments
                        Suitable safeguards must be provided within the bin to prevent the cargo from                                 N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(7)
                        shifting under emergency landing conditions.                                                                       cargo in the passenger compartments
                        The bin may not be installed in a position that obscures any passenger's view of the
                                                                                                                                      N/A TransGlobal Airlines prohibits the carriage of
  121.285(b)(8)         "seat belt" sign "no smoking" sign, or any required exit sign, unless an auxiliary sign
                        or other approved means for proper notification of the passenger is provided.                                      cargo in the passenger compartments
                        Cargo may be carried aft of a bulkhead or divider in any passenger compartment
                                                                                                                                      N/A TransGlobal Airlines prohibits the carriage of
   121.285(c)           provided the cargo is restrained to the load factors in § 25.561(b)(3) and is loaded as
                        follows:                                                                                                           cargo in the passenger compartments
                        It is properly secured by a safety belt or other tie down having enough strength to
                                                                                                                                      N/A TransGlobal Airlines prohibits the carriage of
  121.285(c)(1)         eliminate the possibility of shifting under all normally anticipated flight and ground
                        conditions.                                                                                                        cargo in the passenger compartments
                        It is packaged or covered in a manner to avoid possible injury to passengers and                              N/A TransGlobal Airlines prohibits the carriage of
  121.285(c)(2)
                        passenger compartment occupants.                                                                                   cargo in the passenger compartments

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                        It does not impose any load on seats or the floor structure that exceeds the load                                 N/A TransGlobal Airlines prohibits the carriage of
  121.285(c)(3)
                        limitation for those components.                                                                                       cargo in the passenger compartments
                        Its location does not restrict access to or use of any required emergency or regular                              N/A TransGlobal Airlines prohibits the carriage of
  121.285(c)(4)
                        exit, or of the aisle in the passenger compartment.                                                                    cargo in the passenger compartments
                        Its location does not obscure any passenger's view of the "seat belt" sign, "no
                                                                                                                                          N/A TransGlobal Airlines prohibits the carriage of
  121.285(c)(5)         smoking" sign, or required exit sign, unless an auxiliary sign or other approved
                        means for proper notification of the passenger is provided.                                                            cargo in the passenger compartments
                        Cargo, including carry-on baggage, may be carried anywhere in the passenger
                        compartment of a nontransport category airplane type certificated after December
                                                                                                                                          N/A TransGlobal Airlines prohibits the carriage of
   121.285(d)           31, 1964, if it is carried in an approved cargo rack, bin, or compartment installed in or
                        on the airplane, if it is secured by an approved means, or if it is carried in                                         cargo in the passenger compartments
                        accordance with each of the following:
                        For cargo, it is properly secured by a safety belt or other tie-down having enough
                        strength to eliminate the possibility of shifting under all normally anticipated flight and                       N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(1)
                        ground conditions, or for carry-on baggage, it is restrained so as to prevent its                                      cargo in the passenger compartments
                        movement during air turbulence.
                                                                                                                                          N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(2)         It is packaged or covered to avoid possible injury to occupants.
                                                                                                                                               cargo in the passenger compartments
                        It does not impose any load on seats or in the floor structure that exceeds the load                              N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(3)
                        limitation for those components.                                                                                       cargo in the passenger compartments
                        It is not located in a position that obstructs the access to, or use of, any required
                        emergency or regular exit, or the use of the aisle between the crew and the
                        passenger compartment, or is located in a position that obscures any passenger's                                  N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(4)
                        view of the "seat belt" sign, "no smoking" sign or placard, or any required exit sign,                                 cargo in the passenger compartments
                        unless an auxiliary sign or other approved means for proper notification of the
                        passengers is provided.
                                                                                                                                          N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(5)         It is not carried directly above seated occupants.
                                                                                                                                               cargo in the passenger compartments
                                                                                                                                          N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(6)         It is stowed in compliance with this section for takeoff and landing.
                                                                                                                                               cargo in the passenger compartments
                        For cargo-only operations, paragraph (d)(4) of this section does not apply if the
                        cargo is loaded so that at least one emergency or regular exit is available to provide                            N/A TransGlobal Airlines prohibits the carriage of
  121.285(d)(7)
                        all occupants of the airplane a means of unobstructed exit from the airplane if an                                     cargo in the passenger compartments
                        emergency occurs.




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121.287 Carriage Of Cargo In Cargo Compartments
                        When cargo is carried in cargo compartments that are designed to require the
                        physical entry of a crewmember to extinguish any fire that may occur during flight the                             N/A by virtue of cargo compartment type
    121.287
                        cargo must be loaded so as to allow a crewmember to effectively reach all parts of                              The ERJ-170 has class “C” cargo compartments
                        the compartment with the contents of a hand fire extinguisher.


121.289 Landing Gear: Aural Warning Device
                        Except for airplanes that comply with the requirements of § 25.729 of this chapter on
                                                                                                                                      Complied with by virtue of FAR 25.729 on the date of
   121.289(a)           or after January 6, 1992, each airplane must have a landing gear aural warning                  TCDS
                        device that functions continuously under the following conditions:                                                           aircraft manufacture
                        For airplanes with an established approach wing flap position, whenever the wing
                        flaps are extended beyond the maximum certificated approach climb configuration                               Complied with by virtue of FAR 25.729 on the date of
  121.289(a)(1)
                        position in the Airplane Flight Manual and the landing gear is not fully extended and           TCDS
                                                                                                                                                     aircraft manufacture
                        locked.
                        For airplanes without an established approach climb wing flap position, whenever
                                                                                                                                      Complied with by virtue of FAR 25.729 on the date of
  121.289(a)(2)         the wing flaps are extended beyond the position at which landing gear extension is              TCDS
                        normally performed and the landing gear is not fully extended and locked.                                                    aircraft manufacture
                        The warning system required by paragraph (a) of this section -                                                Complied with by virtue of FAR 25.729 on the date of
   121.289(b)                                                                                                           TCDS
                                                                                                                                                     aircraft manufacture
                        May not have a manual shutoff;                                                                                Complied with by virtue of FAR 25.729 on the date of
  121.289(b)(1)                                                                                                         TCDS
                                                                                                                                                     aircraft manufacture
                        Must be in addition to the throttle actuated device installed under the type                                  Complied with by virtue of FAR 25.729 on the date of
  121.289(b)(2)         certification airworthiness requirements; and                                                   TCDS
                                                                                                                                                     aircraft manufacture
                        May utilize any part of the throttle actuated system including the aural warning                              Complied with by virtue of FAR 25.729 on the date of
  121.289(b)(3)         device.                                                                                         TCDS
                                                                                                                                                     aircraft manufacture
                        The flap position sensing unit may be installed at any suitable place in the airplane.                        Complied with by virtue of FAR 25.729 on the date of
   121.289(c)                                                                                                           TCDS
                                                                                                                                                     aircraft manufacture

121.291 Demonstration of Emergency Evacuation Procedures
                        Except as provided in paragraph (a)(1) of this section, each certificate holder must
                        conduct an actual demonstration of emergency evacuation procedures in
                        accordance with paragraph (a) of appendix D to this part to show that each type and
   121.291(a)
                        model of airplane with a seating capacity of more than 44 passengers to be used in                                  N/A by virtue of FAR Part 121.291(a)(1)
                        its passenger carrying operations allows the evacuation of the full capacity, including
                        crewmembers, in 90 seconds or less.



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                        An actual demonstration need not be conducted if that airplane type and model has                                 TransGlobal Airlines will submit a plan to demonstrate
                        been shown to be in compliance with this paragraph in effect on or after October 24,
  121.291(a)(1)
                        1967, or, if during type certification, with § 25.803 of this chapter in effect on or after                       the emergency evacuation 30 days prior to the
                        December 1, 1978.                                                                                                 planned demonstration date
                        Any actual demonstration conducted after September 27, 1993, must be in                                           TransGlobal Airlines will submit a plan to demonstrate
                        accordance with paragraph (a) of Appendix D to this part in effect on or after that
  121.291(a)(2)                                                                                                                           the emergency evacuation 30 days prior to the
                        date or with § 25.803 in effect on or after that date.
                                                                                                                                          planned demonstration date
                        Each certificate holder conducting operations with airplanes with a seating capacity                              TransGlobal Airlines will submit a plan to demonstrate
                        of more than 44 passengers must conduct a partial demonstration of emergency
   121.291(b)                                                                                                                             the emergency evacuation 30 days prior to the
                        evacuation procedures in accordance with paragraph (c) of this section upon:
                                                                                                                                          planned demonstration date
                        Initial introduction of a type and model of airplane into passenger/carrying operation,                           TransGlobal Airlines will submit a plan to demonstrate
                        if the certificate holder has not conducted an actual demonstration under paragraph
  121.291(b)(1)                                                                                                                           the emergency evacuation 30 days prior to the
                        (a) of this section;
                                                                                                                                          planned demonstration date
                        Changing the number, location, or emergency evacuation duties or procedures of                                    TransGlobal Airlines will submit a plan to demonstrate
                        flight attendants who are required by § 121.391; or
  121.291(b)(2)                                                                                                                           the emergency evacuation 30 days prior to the
                                                                                                                                          planned demonstration date
                        Changing the number, location, type of emergency exits, or type of opening                                        TransGlobal Airlines will submit a plan to demonstrate
                        mechanism on emergency exits available for evacuation.
  121.291(b)(3)                                                                                                                           the emergency evacuation 30 days prior to the
                                                                                                                                          planned demonstration date
                        In conducting the partial demonstration required by paragraph (b) of this section,                                TransGlobal Airlines will submit a plan to demonstrate
                        each certificate holder must:
   121.291(c)                                                                                                                             the emergency evacuation 30 days prior to the
                                                                                                                                          planned demonstration date
                        Demonstrate the effectiveness of its crewmember emergency training and
                        evacuation procedures by conducting a demonstration, not requiring passengers and
                        observed by the Administrator, in which the flight attendants for that type and model
                        of airplane, using that operator's line operating procedures, open 50 percent of the                              TransGlobal Airlines will submit a plan to demonstrate
  121.291(c)(1)         required floor-level emergency exits and 50 percent of the required non floor-level                               the emergency evacuation 30 days prior to the
                        emergency exits whose opening by a flight attendant is defined as an emergency                                    planned demonstration date
                        evacuation duty under § 121.397, and deploy 50 percent of the exit-slides. The exits
                        and slides will be selected by the administrator and must be ready for use within 15
                        seconds;
                        Apply for and obtain approval from the certificate-holding district office before                                 TransGlobal Airlines will submit a plan to demonstrate
                        conducting the demonstration;
  121.291(c)(2)                                                                                                                           the emergency evacuation 30 days prior to the
                                                                                                                                          planned demonstration date
                        Use flight attendants in this demonstration who have been selected at random by the                               TransGlobal Airlines will submit a plan to demonstrate
                        Administrator, have completed the certificate holder's FAA-approved training
  121.291(c)(3)
                        program for the type and model of airplane, and have passed a written or practical                                the emergency evacuation 30 days prior to the
                        examination on the emergency equipment and procedures; and                                                        planned demonstration date
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                         Apply for and obtain approval from the certificate-holding district office before                                TransGlobal Airlines will submit a plan to demonstrate
                         commencing operations with this type and model airplane.
   121.291(c)(4)                                                                                                                          the emergency evacuation 30 days prior to the
                                                                                                                                          planned demonstration date
                         Each certificate holder operating or proposing to operate one or more landplanes in
                         extended overwater operations, or otherwise required to have certain equipment
                         under § 121.339, must show, by simulated ditching conducted in accordance with
    121.291(d)           paragraph (b) of Appendix D to this part, that it has the ability to efficiently carry out                       N/A TransGlobal does not operate extended overwater
                         its ditching procedures. For certificate holders subject to § 121.2(a)(1), this
                         paragraph applies only when a new type or model airplane is introduced into the
                         certificate holder's operations after January 19, 1996.
                         For a type and model airplane for which the simulated ditching specified in
                         paragraph (d) has been conducted by a Part 121 certificate holder, the requirements
                         of paragraphs (b)(2), (b)(4), and (b)(5) of Appendix D to this part are complied with if
121.291(e)               each life raft is removed from stowage, one life raft is launched and inflated (or one                           N/A TransGlobal does not operate extended overwater
                         slide life raft is inflated) and crewmembers assigned to the inflated life raft display
                         and describe the use of each item of required emergency equipment. The life raft or
                         slide life raft to be inflated will be selected by the Administrator.


121.293 Special Airworthiness Requirements for Nontransport Category Airplanes Type Certificated after December 31,
1964
                         No certificate holder may operate a nontransport category airplane manufactured
                         after December 20, 1999 unless the airplane contains a takeoff warning system that
                         meets the requirements of 14 CFR 25.703. However, the takeoff warning system
    § 121.293
                         does not have to cover any device for which it has been demonstrated that takeoff                                                   N/A by category
                         with that device in the most adverse position would not create a hazardous
                         condition.


Subpart K – INSTRUMENT AND EQUIPMENT REQUIREMENTS
121.301 Applicability
                         This subpart prescribes instrument and equipment requirements for all certificate
    § 121.301
                         holders.


121.303 Airplane Instruments And Equipment
                         Unless otherwise specified, the instrument and equipment requirements of this
    121.303(a)
                         subpart apply to all operations under this part.


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                        Instruments and equipment required by §§ 121.305 through 121.359 and 121.803                                  Complied with by virtue of FAR Part 25 at manufacture
   121.303(b)           must be approved and installed in accordance with the airworthiness requirements             GMM 6.15.4
                        applicable to them.                                                                                           Verified at conformity inspection (conformity checklist)
                        Each airspeed indicator must be calibrated in knots, and each airspeed limitation
   121.303(c)           and item of related information in the Airplane Flight Manual and pertinent placards       GMM 6.15.4(131)    Verified at conformity inspection
                        must be expressed in knots.
                        Except as provided in §§ 121.627(b) and 121.628, no person may takeoff any
   121.303(d)
                        airplane unless the following instruments and equipment are in operable condition:
                                                                                                                                      The captain is responsible to ensure the airplane
                                                                                                                                      will not depart with inoperable instruments
                        Instruments and equipment required to comply with airworthiness requirements
                                                                                                                     FOM 4.5.1F       and equipment, inoperable navigational
  121.303(d)(1)         under which the airplane is type certificated and as required by §§ 121.213 through
                        121.283 and 121.289.                                                                           MEL            equipment, unless the approved MEL will permit
                                                                                                                                      the airplane to continue to
                                                                                                                                      operate in an airworthy condition
                                                                                                                                      The captain is responsible to ensure the airplane
                        Instruments and equipment specified in §§ 121.305 through 121.321, 121.359,                                   will not depart with inoperable instruments
                        121.360, and 121.803 for all operations, and the instruments and equipment                   FOM 4.5.1 D      and equipment, inoperable navigational
  121.303(d)(2)
                        specified in §§ 121.323 through 121.351 for the kind of operation indicated,                    MEL           equipment, unless the approved MEL will permit
                        wherever these items are not already required by paragraph (d)(1) of this section.                            the airplane to continue to
                                                                                                                                      operate in an airworthy condition

121.305 Flight And Navigational Equipment
                                                                                                                                      TransGlobal Airlines verifies that each aircraft has the
                        No person may operate an airplane unless it is equipped with the following flight and                         required flight and navigation equipment by performing
   § 121.305
                        navigational instruments and equipment:                                                      GMM 6.15.4
                                                                                                                                      an aircraft conformity inspection prior to the aircraft
                                                                                                                                      being added to the aircraft listing Ops Spec
                        An airspeed indicating system with heated pitot tube or equivalent means for
   121.305(a)
                        preventing malfunctioning due to icing.                                                    GMM 6.15.4(130)    Verified at conformity inspection (conformity checklist)
   121.305(b)           A sensitive altimeter.                                                                     GMM 6.15.4(131)    Verified at conformity inspection (conformity checklist)
   121.305(c)           A sweep-second hand clock (or approved equivalent).                                        GMM 6.15.4(132)    Verified at conformity inspection (conformity checklist)
   121.305(d)           A free air temperature indicator.                                                          GMM 6.15.4(135)    Verified at conformity inspection (conformity checklist)
   121.305(e)           A gyroscopic bank and pitch indicator (artificial horizon).                                GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
                        A gyroscopic rate of turn indicator combined with an integral slip/skid indicator (turn
                        and bank indicator) except that only a slip/skid indicator is required when a third
   121.305(f)
                        attitude instrument system usable through flight attitudes of 360° of pitch and roll is    GMM 6.15.4(137)    Verified at conformity inspection (conformity checklist)
                        installed in accordance with paragraph (k) of this section.


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   121.305(g)           A gyroscopic direction indicator (directional gyro or equivalent).                         GMM 6.15.4(138)    Verified at conformity inspection (conformity checklist)
   121.305(h)           A magnetic compass.                                                                        GMM 6.15.4(139)    Verified at conformity inspection (conformity checklist)
   121.305(i)           A vertical speed indicator (rate of climb indicator).                                      GMM 6.15.4(140)    Verified at conformity inspection (conformity checklist)
                        On the airplane described in this paragraph, in addition to two gyroscopic bank and
   121.305(j)           pitch indicators (artificial horizons) for use at the pilot stations, a third such
                        instrument is installed in accordance with paragraph (k) of this section:
  121.305(j)(1)         On each turbojet powered airplane.                                                         GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
                        On each turbopropeller powered airplane having a passenger-seat configuration of
                                                                                                                                            N/A TransGlobal Airlines does not operate
  121.305(j)(2)         more than 30 seats, excluding each crewmember seat, or a payload capacity of
                        more than 7,500 pounds.                                                                                                  turbopropeller powered aircraft
                        On each turbopropeller powered airplane having a passenger-seat configuration of
                                                                                                                                            N/A TransGlobal Airlines does not operate
  121.305(j)(3)         30 seats or fewer, excluding each crewmember seat, and a payload capacity of
                        7,500 pounds or less that is manufactured on or after March 20, 1997.                                                    turbopropeller powered aircraft
                        After December 20, 2010, on each turbopropeller powered airplane having a
                                                                                                                                            N/A TransGlobal Airlines does not operate
  121.305(j)(4)         passenger seat configuration of 10-30 seats and a payload capacity of 7,500 pounds
                        or less that was manufactured before March 20, 1997.                                                                     turbopropeller powered aircraft
                        When required by paragraph (j) of this section, a third gyroscopic bank-and-pitch
   121.305(k)
                        indicator (artificial horizon) that:
  121.305(k)(1)         Is powered from a source independent of the electrical generating system;                  GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
                        Continues reliable operation for a minimum of 30 minutes after total failure of the
  121.305(k)(2)
                        electrical generating system;                                                              GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
  121.305(k)(3)         Operates independently of any other attitude indicating system;                            GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
  121.305(k)(4)         Is operative without selection after total failure of the electrical generating system;    GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
                        Is located on the instrument panel in a position acceptable to the Administrator that
  121.305(k)(5)
                        will make it plainly visible to and usable by each pilot at his or her station; and        GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)
  121.305(k)(6)         Is appropriately lighted during all phases of operation.                                   GMM 6.15.4(134)    Verified at conformity inspection (conformity checklist)

121.306 Portable Electronic Devices
                                                                                                                                      The Captain will not allow portable electronic devices
                        Except as provided in paragraph (b) of this section, no person may operate, nor may                           to be operated on any aircraft, except for those
                                                                                                                     FAM 6.13.1A
   121.306(a)           any operator or pilot in command of an aircraft allow the operation of, any portable                          devices that have been determined by TransGlobal
                        electronic device on any U.S.-registered civil aircraft operating under this part.           FOM 31.4.1A
                                                                                                                                      Airlines to not cause interference with the navigation or
                                                                                                                                      communication system of the aircraft.
   121.306(b)           Paragraph (a) of this section does not apply to -
                                                                                                                     FAM 6.13.1.1
  121.306(b)(1)         Portable voice recorders;                                                                                     See Portable Electronic Devices table
                                                                                                                      FOM 31.4.2
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                                                                                                                  FAM 6.13.1.1
  121.306(b)(2)         Hearing aids;                                                                                              See Portable Electronic Devices table
                                                                                                                   FOM 31.4.2
                                                                                                                  FAM 6.13.1.1
  121.306(b)(3)         Heart pacemakers;                                                                                          See Portable Electronic Devices table
                                                                                                                   FOM 31.4.2
                                                                                                                  FAM 6.13.1.1
  121.306(b)(4)         Electric shavers; or                                                                                       See Portable Electronic Devices table
                                                                                                                   FOM 31.4.2
                        Any other portable electronic device that the part 119 certificate holder has                              TransGlobal Airlines shall determine whether other
                                                                                                                  FAM 6.13.1.1
  121.306(b)(5)         determined will not cause interference with the navigation or communication system                         portable electronic devices cause interference with the
                        of the aircraft on which it is to be used.                                                FOM 31.4.2A
                                                                                                                                   navigation or communication system of the aircraft
                                                                                                                                   TransGlobal Airlines shall determine whether other
                        The determination required by paragraph (b)(5) of this section shall be made by that      FAM 6.13.3
  121.306(b)(c)
                        part 119 certificate holder operating the particular device to be used.                                    portable electronic devices cause interference with the
                                                                                                                  FOM 31.4.4
                                                                                                                                   navigation or communication system of the aircraft

121.307 Engine Instruments
                                                                                                                                   TransGlobal Airlines verifies that each aircraft has the
                        Unless the Administrator allows or requires different instrumentation for turbine
                                                                                                                                   required engine instruments by performing an aircraft
   § 121.307            engine powered airplanes to provide equivalent safety, no person may conduct any
                        operation under this part without the following engine instruments:                                        conformity inspection prior to the aircraft being added
                                                                                                                                   to the aircraft listing Ops Spec
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.307(a)           A carburetor air temperature indicator for each engine.
                                                                                                                                                 reciprocating powered aircraft
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.307(b)           A cylinder head temperature indicator for each air cooled engine.
                                                                                                                                                 reciprocating powered aircraft
   121.307(c)           A fuel pressure indicator for each engine.                                              GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
                        A fuel flowmeter or fuel mixture indicator for each engine not equipped with an
   121.307(d)
                        automatic altitude mixture control.                                                     GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
   121.307(e)           A means for indicating fuel quantity in each fuel tank to be used.                      GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.307(f)           A manifold pressure indicator for each engine.
                                                                                                                                                 reciprocating powered aircraft
   121.307(g)           An oil pressure indicator for each engine.                                              GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
                        An oil quantity indicator for each oil tank when a transfer or separate oil reserve
   121.307(h)
                        supply is used.                                                                         GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
   121.307(i)           An oil in temperature indicator for each engine.                                        GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
   121.307(j)           A tachometer for each engine.                                                           GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)

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                        An independent fuel pressure warning device for each engine or a master warning
   121.307(k)           device for all engines with a means for isolating the individual warning circuits from       GMM 6.15.4(149)    Verified at conformity inspection (conformity checklist)
                        the master warning device.
                        A device for each reversible propeller, to indicate to the pilot when the propeller is in                        N/A TransGlobal Airlines does not operate propeller
   121.307(l)
                        reverse pitch, that complies with the following:                                                                                 powered aircraft
                        The device may be actuated at any point in the reversing cycle between the normal
                                                                                                                                         N/A TransGlobal Airlines does not operate propeller
  121.307(l)(1)         low pitch stop position and full reverse pitch, but it may not give an indication at or
                        above the normal low pitch stop position.                                                                                        powered aircraft
                        The source of indication must be actuated by the propeller blade angle or be directly                            N/A TransGlobal Airlines does not operate propeller
  121.307(l)(2)
                        responsive to it.                                                                                                                powered aircraft

121.308 Lavatory Fire Protection
                        Except as provided in paragraphs (c) and (d) of this section, no person may operate
                        a passenger-carrying airplane unless each lavatory in the airplane is equipped with a                           TransGlobal Airlines verifies that each aircraft has the
                        smoke detector system or equivalent that provides a warning light in the cockpit or
                                                                                                                                        required lavatory fire protection by performing an
   121.308(a)           provides a warning light or audio warning in the passenger cabin which would be              GMM 6.15.4(112)
                        readily detected by a flight attendant, taking into consideration the positioning of                            aircraft conformity inspection prior to the aircraft being
                        flight attendants throughout the passenger compartment during various phases of                                 added to the aircraft listing Ops Spec
                        flight.
                        Except as provided in paragraph (c) of this section, no person may operate a
                        passenger-carrying airplane unless each lavatory in the airplane is equipped with a                             Complied with by virtue of FAR Part 25.854 at
                        built-in fire extinguisher for each disposal receptacle for towels, paper, or waste             TCDS            manufacture
   121.308(b)
                        located within the lavatory. The built-in fire extinguisher must be designed to              GMM 6.15.4(112)
                        discharge automatically into each disposal receptacle upon occurrence of a fire in
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                        the receptacle.
                        Until December 22, 1997, a certificate holder described in § 121.2(a) (1) or (2) may
                        operate an airplane with a passenger seat configuration of 30 or fewer seats that
   121.308(c)           does not comply with the smoke detector system requirements described in                                                  N/A by configuration (over 30 seats)
                        paragraph (a) of this section and the fire extinguisher requirements described in
                        paragraph (b) of this section.
                        After December 22, 1997, no person may operate a nontransport category airplane
                        type certificated after December 31, 1964, with a passenger seat configuration of 10-
                        19 seats unless that airplane complies with the smoke detector system requirements
   121.308(d)
                        described in paragraph (a) of this section, except that the smoke detector system or                                                N/A by category
                        equivalent must provide a warning light in the cockpit or an audio warning that would
                        be readily detected by the flightcrew.




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121.309 Emergency Equipment
                                                                                                                                        TransGlobal Airlines verifies that each aircraft has the
                           General: No person may operate an airplane unless it is equipped with the                                    required emergency equipment by performing an
   121.309(a)
                           emergency equipment listed in this section and in § 121.310.                                                 aircraft conformity inspection prior to the aircraft being
                                                                                                                                        added to the aircraft listing Ops Spec
                           Each item of emergency and flotation equipment listed in this section and in §§
   121.309(b)
                           121.310, 121.339, and 121.340 -
                           Must be inspected regularly in accordance with inspection periods established in the
                                                                                                                     GMM 6.15.4(29)     Verified at conformity inspection and inspected in
  121.309(b)(1)            operations specifications to ensure its condition for continued serviceability and
                           immediate readiness to perform its intended emergency purposes;                              MTLM            accordance with the MTLM
                           Must be readily accessible to the crew and, with regard to equipment located in the
  121.309(b)(2)
                           passenger compartment, to passengers;                                                     GMM 6.15.4(87)     Verified at conformity inspection (conformity checklist)
  121.309(b)(3)            Must be clearly identified and clearly marked to indicate its method of operation; and    GMM 6.15.4(87)     Verified at conformity inspection (conformity checklist)
                           When carried in a compartment or container, must be carried in a compartment or
  121.309(b)(4)            container marked as to contents and the compartment or container, or the item itself,     GMM 6.15.4(87)     Verified at conformity inspection (conformity checklist)
                           must be marked as to date of last inspection.
                           Hand fire extinguishers for crew, passenger, cargo, and galley compartments. Hand
   121.309(c)              fire extinguishers of an approved type must be provided for use in crew, passenger,       GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                           cargo, and galley compartments in accordance with the following:
                           The type and quantity of extinguishing agent must be suitable for the kinds of fires
                           likely to occur in the compartment where the extinguisher is intended to be used and,
  121.309(c)(1)
                           for passenger compartments, must be designed to minimize the hazard of toxic gas          GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                           concentrations.
                           Cargo compartments. At least one hand fire extinguisher must be conveniently
                                                                                                                                              N/A by virtue of cargo compartment type
  121.309(c)(2)            located for use in each class E cargo compartment that is accessible to
                           crewmembers during flight.                                                                                   The ERJ-170 has class “C” cargo compartments
                           Galley compartments. At least one hand fire extinguisher must be conveniently
  121.309(c)(3)            located for use in each galley located in a compartment other than a passenger,           GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                           cargo, or crew compartment.
                           Flightcrew compartment. At least one hand fire extinguisher must be conveniently
  121.309(c)(4)
                           located on the flight deck for use by the flightcrew.                                     GMM 6.15.4(156)    Verified at conformity inspection (conformity checklist)
                           Passenger compartments. Hand fire extinguishers for use in passenger
                           compartments must be conveniently located and, when two or more are required,
  121.309(c)(5)
                           uniformly distributed throughout each compartment. Hand fire extinguishers shall be       GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                           provided in passenger compartments as follows:
                           For airplanes having passenger seats accommodating more than 6 but fewer than
 121.309(c)(5)(i)
                           31 passengers, at least one.                                                                                               N/A by seating configuration
                           For airplanes having passenger seats accommodating more than 30 but fewer than
 121.309(c)(5)(ii)
                           61 passengers, at least two.                                                                                               N/A by seating configuration

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                            For airplanes having passenger seats accommodating more than 60 passengers,
 121.309(c)(5)(iii)
                            there must be at least the following number of hand fire extinguishers:                   GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
 121.309(c)(5)(iii          Minimum Number of Hand Fire Extinguishers
 121.309(c)(5)(iii          Passenger seating accommodations:
 121.309(c)(5)(iii           61 through 200          3                                                                GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
 121.309(c)(5)(iii           201 through 300         4                                                                                                 N/A by seating configuration
 121.309(c)(5)(iii           301 through 400         5                                                                                                 N/A by seating configuration
 121.309(c)(5)(iii           401 through 500         6                                                                                                 N/A by seating configuration
 121.309(c)(5)(iii           501 through 600         7                                                                                                 N/A by seating configuration
 121.309(c)(5)(iii             601 or more             8                                                                                               N/A by seating configuration
                            Notwithstanding the requirement for uniform distribution of hand fire extinguishers as
                            prescribed in paragraph (c)(5) of this section, for those cases where a galley is
  121.309(c)(6)
                            located in a passenger compartment, at least one hand fire extinguisher must be           GMM 6.15.4(90)     Verified at conformity inspection (conformity checklist)
                            conveniently located and easily accessible for use in the galley.
                            At least two of the required hand fire extinguisher installed in passenger-carrying
                            airplanes must contain Halon 1211 (bromochlorofluoromethane) or equivalent as the
  121.309(c)(7)
                            extinguishing agent. At least one hand fire extinguisher in the passenger                 GMM 6.15.4(90)     Verified at conformity inspection (conformity checklist)
                            compartment must contain Halon 1211 or equivalent.
                            Removed and Reserved. {New-2001-5 (d) removed and reserved April 12, 2001,
    121.309(d)
                            effective May 12, 2004}
                            Crash ax. Except for nontransport category airplanes type certificated after
    121.309(e)
                            December 31, 1964, each airplane must be equipped with a crash ax.                        GMM 6.15.4(92)     Verified at conformity inspection (conformity checklist)
                            Megaphones. Each passenger carrying airplane must have a portable battery
    121.309(f)              powered megaphone or megaphones readily accessible to the crewmembers                     GMM 6.15.4(91)     Verified at conformity inspection (conformity checklist)
                            assigned to direct emergency evacuation, installed as follows:
                            One megaphone on each airplane with a seating capacity of more than 60 and less
                            than 100 passengers, at the most rearward location in the passenger cabin where it
                            would be readily accessible to a normal flight attendant seat. However, the
  121.309(f)(1)
                            Administrator may grant a deviation from the requirements of this subparagraph if he      GMM 6.15.4(91)     Verified at conformity inspection (conformity checklist)
                            finds that a different location would be more useful for evacuation of persons during
                            an emergency.
                            Two megaphones in the passenger cabin on each airplane with a seating capacity of
                            more than 99 passengers, one installed at the forward end and the other at the most
  121.309(f)(2)
                            rearward location where it would be readily accessible to a normal flight attendant                                       N/A by seating configuration
                            seat.




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121.310 Additional Emergency Equipment
                            Means for emergency evacuation. Each passenger carrying landplane emergency
                            exit (other than over the wing) that is more than 6 feet from the ground with the
                            airplane on the ground and the landing gear extended, must have an approved
                            means to assist the occupants in descending to the ground. The assisting means for
                            a floor-level emergency exit must meet the requirements of § 25.809(f)(1) of this
                            chapter in effect on April 30, 1972, except that, for any airplane for which the
                            application for the type certificate was filed after that date, it must meet the                           Complied with by virtue of FAR Part 25.809 at
                            requirements under which the airplane was type certificated. An assisting means that       TCDS            manufacture
    121.310(a)
                            deploys automatically must be armed during taxiing, takeoffs, and landings.             GMM 6.15.4(110)
                            However, if the Administrator finds that the design of the exit makes compliance
                                                                                                                                       Verified at conformity inspection (conformity checklist)
                            impractical, he may grant a deviation from the requirement of automatic deployment
                            if the assisting means automatically erects upon deployment and, with respect to
                            required emergency exits, if an emergency evacuation demonstration is conducted
                            in accordance with § 121.291(a). This paragraph does not apply to the rear window
                            emergency exit of DC-3 airplanes operated with less than 36 occupants, including
                            crewmembers and less than five exits authorized for passenger use.
                            Interior emergency exit marking. The following must be complied with for each
    121.310(b)
                            passenger carrying airplane:
                            Each passenger emergency exit, its means of access, and its means of opening
                            must be conspicuously marked. The identity and location of each passenger
                            emergency exit must be recognizable from a distance equal to the width of the cabin.
  121.310(b)(1)
                            The location of each passenger emergency exit must be indicated by a sign visible       GMM 6.15.4(107)    Verified at conformity inspection (conformity checklist)
                            to occupants approaching along the main passenger aisle. There must be a locating
                            sign -
                            Above the aisle near each over the wing passenger emergency exit, or at another
 121.310(b)(1)(i)
                            ceiling location if it is more practical because of low headroom;                       GMM 6.15.4(107)    Verified at conformity inspection (conformity checklist)
                            Next to each floor-level passenger emergency exit, except that one sign may serve
 121.310(b)(1)(ii)
                            two such exits if they both can be seen readily from that sign; and                     GMM 6.15.4(107)    Verified at conformity inspection (conformity checklist)
                            On each bulkhead or divider that prevents fore and aft vision along the passenger
 121.310(b)(1)(iii)         cabin, to indicate emergency exits beyond and obscured by it, except that if this is    GMM 6.15.4(107)    Verified at conformity inspection (conformity checklist)
                            not possible the sign may be placed at another appropriate location.
                            Each passenger emergency exit marking and each locating sign must meet the
  121.310(b)(2)
                            following:                                                                              GMM 6.15.4(107)    Verified at conformity inspection (conformity checklist)




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                            Except as provided in paragraph (b)(2)(iii) of this section, for an airplane for which
                            the application for the type certificate was filed prior to May 1, 1972, each passenger
                            emergency exit marking and each locating sign must be manufactured to meet the
                            requirements of § 25.812(b) of this chapter in effect on April 30, 1972. On these
                            airplanes, no sign may continue to be used if its luminescence (brightness)
 121.310(b)(2)(i)
                            decreases to below 100 microlamberts. The colors may be reversed if it increases                                            N/A by type certification date
                            the emergency illumination of the passenger compartment. However, the
                            Administrator may authorize deviation from the 2 inch background requirements if he
                            finds that special circumstances exist that make compliance impractical and that the
                            proposed deviation provides an equivalent level of safety.
                            For a transport category airplane for which the application for the type certificate was
                            filed on or after May 1, 1972, each passenger emergency exit marking and each                                  Complied with by virtue of FAR Part 25 at manufacture
                            locating sign must be manufactured to meet the interior emergency exit marking                 TCDS
 121.310(b)(2)(ii)
                            requirements under which the airplane was type certificated. On these airplanes, no         GMM 6.15.4(107)
                            sign may continue to be used if its luminescence (brightness) decreases to below                               Verified at conformity inspection (conformity checklist)
                            250 microlamberts.
                            For a nontransport category turbopropeller powered airplane type certificated after
                            December 31, 1964, each passenger emergency exit marking and each locating
 121.310(b)(2)(iii)         sign must be manufactured to meet the requirements of § 23.811(b) of this chapter.                                                 N/A by category
                            On these airplanes, no sign may continue to be used if its luminescence (brightness)
                            decreases to below 100 microlamberts.
                            Lighting for interior emergency exit markings. Except for nontransport category
                            airplanes type certificated after December 31, 1964, each passenger-carrying                                   Complied with by virtue of FAR Part 25.812 at
                            airplane must have an emergency lighting system, independent of the main lighting              TCDS            manufacture
    121.310(c)
                            system. However, sources of general cabin illumination may be common to both the            GMM 6.15.4(109)
                            emergency and the main lighting systems if the power supply to the emergency
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                            lighting system is independent of the power supply to the main lighting system.
                            The emergency lighting system must -
  121.310(c)(1)             Illuminate each passenger exit marking and locating sign;                                   GMM 6.15.4(109)    Verified at conformity inspection (conformity checklist)
                            Provide enough general lighting in the passenger cabin so that the average
  121.310(c)(2)             illumination when measured at 40 inch intervals at seat armrest height, on the              GMM 6.15.4(109)    Verified at conformity inspection (conformity checklist)
                            centerline of the main passenger aisle, is at least 0.05 foot-candles; and
                            For airplanes type certificated after January 1, 1958, after November 26, 1986,
  121.310(c)(3)             include floor proximity emergency escape path marking which meets the                       GMM 6.15.4(109)    Verified at conformity inspection (conformity checklist)
                            requirements of § 25.812(e) of this chapter in effect on November 26, 1984.
                            Emergency light operation. Except for lights forming part of emergency lighting
                            subsystems provided in compliance with § 25.812(h) of this chapter (as prescribed in                           Complied with by virtue of FAR Part 25.812 at
                            paragraph (h) of this section) that serve no more than one assist means, are                   TCDS            manufacture
    121.310(d)
                            independent of the airplane's main emergency lighting systems, and are                      GMM 6.15.4(109)
                            automatically activated when the assist means is deployed, each light required by
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                            paragraphs (c) and (h) of this section must comply with the following:
  121.310(d)(1)             Each light must -

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                            Be operable manually both from the flightcrew station and, for airplanes on which a                            Complied with by virtue of FAR Part 25 at manufacture
                                                                                                                           TCDS
 121.310(d)(1)(i)           flight attendant is required, from a point in the passenger compartment that is readily
                            accessible to a normal flight attendant seat;                                               GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                                                                                                                                           Complied with by virtue of FAR Part 25 at manufacture
                                                                                                                           TCDS
 121.310(d)(1)(ii)          Have a means to prevent inadvertent operation of the manual controls; and
                                                                                                                        GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                                                                                                                                           Complied with by virtue of FAR Part 25 at manufacture
                            When armed or turned on at either station, remain lighted or become lighted upon               TCDS
 121.310(d)(1)(iii)
                            interruption of the airplane's normal electric power.                                       GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                            Each light must be armed or turned on during taxiing, takeoff, and landing. In                                 Complied with by virtue of FAR Part 25 at manufacture
                                                                                                                           TCDS
  121.310(d)(2)             showing compliance with this paragraph a transverse vertical separation of the
                            fuselage need not be considered.                                                            GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                                                                                                                                           Complied with by virtue of FAR Part 25 at manufacture
                            Each light must provide the required level of illumination for at least 10 minutes at          TCDS
  121.310(d)(3)
                            the critical ambient conditions after emergency landing.                                    GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                                                                                                                                           Complied with by virtue of FAR Part 25 at manufacture
                            Each light must have a cockpit control device that has an "on," "off," and "armed"             TCDS
  121.310(d)(4)
                            position.                                                                                   GMM 6.15.4(109)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
    121.310(e)              Emergency exit operating handles.
                            For a passenger carrying airplane for which the application for the type certificate
                            was filed prior to May 1, 1972, the location of each passenger emergency exit
                            operating handle, and instructions for opening the exit, must be shown by a marking
  121.310(e)(1)
                            on or near the exit that is readable from a distance of 30 inches. In addition, for each                                    N/A by type certification date
                            Type I and Type II emergency exit with a locking mechanism released by rotary
                            motion of the handle, the instructions for opening must be shown by -
                            A red arrow with a shaft at least three-fourths inch wide and a head twice the width
 121.310(e)(1)(i)           of the shaft, extending along at least 70° of arc at a radius approximately equal to                                        N/A by type certification date
                            three-fourths of the handle length; and
                            The word "open" in red letters 1 inch high placed horizontally near the head of the
 121.310(e)(1)(ii)
                            arrow.                                                                                                                      N/A by type certification date
                            For a passenger carrying airplane for which the application for the type certificate
                            was filed on or after May 1, 1972, the location of each passenger emergency exit                               Complied with by virtue of FAR Part 25 at manufacture
                            operating handle and instructions for opening the exit must be shown in accordance             TCDS
  121.310(e)(2)
                            with the requirements under which the airplane was type certificated. On these              GMM 6.15.4(108)
                            airplanes, no operating handle or operating handle cover may continue to be used if                            Verified at conformity inspection (conformity checklist)
                            its luminescence (brightness) decreases to below 100 microlamberts.
                            Emergency exit access. Access to emergency exits must be provided as follows for
    121.310(f)
                            each passenger-carrying transport category airplane:
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                                                                                                                                            Complied with by virtue of FAR Part 25.813(a) at
                            Each passage way between individual passenger areas, or leading to a Type I or                  TCDS            manufacture
  121.310(f)(1)
                            Type II emergency exit, must be unobstructed and at least 20 inches wide.                    GMM 6.15.4(106)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
                            There must be enough space next to each Type I or Type II emergency exit to allow
                            a crewmember to assist in the evacuation of passengers without reducing the                                     Complied with by virtue of FAR Part 25.813(b) at
                            unobstructed width of the passageway below that required in paragraph (f)(1) of this
                                                                                                                            TCDS            manufacture
  121.310(f)(2)             section. However the Administrator may authorize deviation from this requirement for
                            an airplane certificated under the provisions of Part 4b of the Civil Air Regulations in     GMM 6.15.4(106)
                            effect before December 20, 1951, if he finds that special circumstances exist that                              Verified at conformity inspection (conformity checklist)
                            provide an equivalent level of safety.
                            There must be access from the main aisle to each Type III and Type IV exit. The
  121.310(f)(3)             access from the aisle to these exits must not be obstructed by seats, berths, or other                              N/A The ERJ-170 is equipped with Type I exits
                            protrusions in a manner that would reduce the effectiveness of the exit. In addition -
                            For an airplane for which the application for the type certificate was filed prior to May
 121.310(f)(3)(i)           1, 1972, the access must meet the requirements of § 25.813(c) of this chapter in                                    N/A The ERJ-170 is equipped with Type I exits
                            effect on April 30, 1972; and
                            For an airplane for which the application for the type certificate was filed on or after
 121.310(f)(3)(ii)          May 1, 1972, the access must meet the emergency exit access requirements under                                      N/A The ERJ-170 is equipped with Type I exits
                            which the airplane was type certificated; except that,
                            After December 3, 1992, the access for an airplane type certificated after January 1,
 121.310(f)(3)(iii)         1958, must meet the requirements of § 25.813(c) of this chapter, effective June 3,                                  N/A The ERJ-170 is equipped with Type I exits
                            1992.
                            Contrary provisions of this section notwithstanding, the Manager of the Transport
                            Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration,
                            may authorize deviation from the requirements of paragraph (f)(3)(iii) of this section if
                            it is determined that special circumstances make compliance impractical. Such
                            special circumstances include, but are not limited to, the following conditions when
                            they preclude achieving compliance with § 25.813(c)(1)(i) or (ii) without a reduction
                            in the total number of passenger seats; emergency exits located in close proximity to
 121.310(f)(3)(iv)          each other; fixed installations such as lavatories, galleys, etc.; permanently mounted                              N/A The ERJ-170 is equipped with Type I exits
                            bulkheads; an insufficient number of rows ahead of or behind the exit to enable
                            compliance without a reduction in the seat row pitch of more than one inch; or an
                            insufficient number of such rows to enable compliance without a reduction in the
                            seat row pitch to less than 30 inches. A request for such grant of deviation must
                            include credible reasons as to why literal compliance with § 25.813(c)(1)(i) or (ii) is
                            impractical and a description of the steps taken to achieve a level of safety as close
                            to that intended by § 25.813(c)(1)(i) or (ii) as is practical.




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                          The Manager of the Transport Airplane Directorate, Aircraft Certification Service,
                          Federal Aviation Administration, may also authorize a compliance date later than
                          December 3, 1992, if it is determined that special circumstances make compliance
                          by that date impractical. A request for such grant of deviation must outline the
 121.310(f)(3)(v)
                          airplanes for which compliance will be achieved by December 3, 1992, and include a                                 N/A The ERJ-170 is equipped with Type I exits
                          proposed schedule for incremental compliance of the remaining airplanes in the
                          operator's fleet. In addition, the request must include credible reasons why
                          compliance cannot be achieved earlier.
                          If it is necessary to pass through a passageway between passenger compartments                                 Complied with by virtue of FAR Part 25.813 at
                          to reach any required emergency exit from any seat in the passenger cabin, the                 TCDS            manufacture
  121.310(f)(4)
                          passageway must not be obstructed. However, curtains may be used if they allow              GMM 6.15.4(104)
                          free entry through the passageway.
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                                                                                                                                         Complied with by virtue of FAR Part 25.813 at
                                                                                                                         TCDS            manufacture
  121.310(f)(5)           No door may be installed in any partition between passenger compartments.
                                                                                                                      GMM 6.15.4(104)
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                          If it is necessary to pass through a doorway separating the passenger cabin from
                          other areas to reach required emergency exit from any passenger seat, the door                                 Complied with by virtue of FAR Part 25.813 at
                          must have a means to latch it in open position, and the door must be latched open              TCDS            manufacture
  121.310(f)(6)
                          during each takeoff and landing. The latching means must be able to withstand the           GMM 6.15.4(104)
                          loads imposed upon it when the door is subjected to the ultimate inertia forces,
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                          relative to the surrounding structure, listed in § 25.561(b) of this chapter.
                          Exterior exit markings. Each passenger emergency exit and the means of opening
                          that exit from the outside must be marked on the outside of the airplane. There must                           Complied with by virtue of FAR Part 25.811 at
                          be a 2 inch colored band outlining each passenger emergency exit on the side of the            TCDS            manufacture
   121.310(g)
                          fuselage. Each outside marking, including the band, must be readily distinguishable         GMM 6.15.4(60)
                          from the surrounding fuselage area by contrast in color. The markings must comply
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                          with the following:
                                                                                                                                         Complied with by virtue of FAR Part 25.811 at
                          If the reflectance of the darker color is 15 percent or less, the reflectance of the           TCDS            manufacture
  121.310(g)(1)
                          lighter color must be at least 45 percent.                                                  GMM 6.15.4(60)
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                                                                                                                                         Complied with by virtue of FAR Part 25.811 at
                          If the reflectance of the darker color is greater than 15 percent, at least a 30 percent
                                                                                                                         TCDS            manufacture
  121.310(g)(2)           difference between its reflectance and the reflectance of the lighter color must be
                          provided.                                                                                   GMM 6.15.4(60)
                                                                                                                                         Verified at conformity inspection (conformity checklist)



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                           Exits that are not in the side of the fuselage must have the external means of
                           opening and applicable instructions marked conspicuously in red or, if red is
                           inconspicuous against the background color, in bright chrome yellow and, when the                                 N/A All exits on the ERJ-170 are in the side of the
  121.310(g)(3)
                           opening means for such an exit is located on only one side of the fuselage, a                                                           fuselage
                           conspicuous marking to that effect must be provided on the other side. "Reflectance"
                           is the ratio of the luminous flux reflected by a body to the luminous flux it receives.
   121.310(h)              Exterior emergency lighting and escape route.
                           Except for nontransport category airplanes certificated after December 31, 1964,
  121.310(h)(1)            each passenger-carrying airplane must be equipped with exterior lighting that meets                                             N/A by aircraft category
                           the following requirements:
                           For an airplane for which the application for the type certificate was filed prior to May
 121.310(h)(1)(i)          1, 1972, the requirements of § 25.812(f) and (g) of this chapter in effect on April 30,                                         N/A type certificate date
                           1972.
                                                                                                                                           Complied with by virtue of FAR Part 25.812 at
                           For an airplane for which the application for the type certificate was filed on or after
                                                                                                                           TCDS            manufacture
 121.310(h)(1)(ii)         May 1, 1972, the exterior emergency lighting requirements under which the airplane
                           was type certificated.                                                                       GMM 6.15.4(47)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                           Each passenger carrying airplane must be equipped with a slip resistant escape
  121.310(h)(2)
                           route that meets the following requirements:
                           For an airplane for which the application for the type certificate was filed prior to May
 121.310(h)(2)(i)
                           1, 1972, the requirements of § 25.803(e) of this chapter in effect on April 30, 1972.                                           N/A type certificate date
                           For an airplane for which the application for the type certificate was filed on or after
 121.310(h)(2)(ii)         May 1, 1972, the slip resistant escape route requirements under which the airplane           GMM 6.15.4(61)     Verified at conformity inspection (conformity checklist)
                           was type certificated.
                           Floor-level exits. Each floor-level door or exit in the side of the fuselage (other than
                           those leading into a cargo or baggage compartment that is not accessible from the
                           passenger cabin) that is 44 or more inches high and 20 or more inches wide, but not                             Complied with by virtue of FAR Part 25 at manufacture
                           wider than 46 inches, each passenger ventral exit (except the ventral exits on M-404            TCDS
    121.310(i)
                           and CV-240 airplanes), and each tail cone exit, must meet the requirements of this           GMM 6.15.4(106)
                           section for floor-level emergency exits. However, the Administrator may grant a                                 Verified at conformity inspection (conformity checklist)
                           deviation from this paragraph if he finds that circumstances make full compliance
                           impractical and that an acceptable level of safety has been achieved.
                           Additional emergency exits. Approved emergency exits in the passenger
                           compartments that are in excess of the minimum number of required emergency
    121.310(j)
                           exits must meet all of the applicable provisions of this section except paragraphs                                       N/A No additional emergency exists
                           (f)(1), (2), and (3) of this section and must be readily accessible.
                           On each large passenger-carrying turbojet-powered airplane, each ventral exit and
   121.310(k)
                           tailcone exit must be -                                                                                             N/A The ERJ-170 does not have a ventral exit
  121.310(k)(1)            Designed and constructed so that it cannot be opened during flight; and                                             N/A The ERJ-170 does not have a ventral exit


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                         Marked with a placard readable from a distance of 30 inches and installed at a
  121.310(k)(2)          conspicuous location near the means of opening the exit, stating that the exit has                                        N/A The ERJ-170 does not have a ventral exit
                         been designed and constructed so that it cannot be opened during flight.
                         Portable lights. No person may operate a passenger-carrying airplane unless it is
   121.310(l)            equipped with flashlight stowage provisions accessible from each flight attendant             GMM 6.15.4(93)          Verified at conformity inspection (conformity checklist)
                         seat.
                         Except for an airplane used in operations under this part on October 16, 1987, and
                         having an emergency exit configuration installed and authorized for operation prior to
                         October 16, 1987, for an airplane that is required to have more than one passenger
   121.310(m)            emergency exit for each side of the fuselage, no passenger emergency exit shall be                                               N/A by virtue of applicability date
                         more than 60 feet from any adjacent passenger emergency exit on the same side of
                         the same deck of the fuselage, as measured parallel to the airplane's longitudinal
                         axis between the nearest exit edges.


121.311 Seats, Safety Belts, And Shoulder Harnesses
                         No person may operate an airplane unless there are available during the takeoff,
   121.311(a)
                         enroute flight, and landing -
                                                                                                                                               Verified at conformity inspection (conformity checklist)
                                                                                                                       GMM 6.15.4(98)
                         An approved seat or berth for each person on board the airplane who has reached                 FOM 4.20.3A           TransGlobal Airlines will not operate an airplane
  121.311(a)(1)
                         his second birthday; and                                                                        SOM 8.3.1.1           unless there is an approved seat is for each person on
                                                                                                                  (Imperative Emphasis Note)   board the airplane who has reached their second
                                                                                                                                               birthday
                                                                                                                                               Verified at conformity inspection (conformity checklist)

                         An approved safety belt for separate use by each person on board the airplane who             GMM 6.15.4(98)          TransGlobal Airlines will not operate an airplane
  121.311(a)(2)
                         has reached his second birthday, …                                                             FOM 4.20.3B            unless there is an approved safety belt for each
                                                                                                                                               person on board the airplane who has reached their
                                                                                                                                               second birthday
                         …, except that two persons occupying a berth may share one approved safety belt
 121.311 (a) (2)         and two persons occupying a multiple lounge or divan seat may share one approved                                              N/A The ERJ-170 does not have berths
                         safety belt during enroute flight only.
                         Except as provided in this paragraph, each person on board an airplane operated
                         under this part shall occupy an approved seat or berth with a separate safety belt                                    TransGlobal Airlines will not operate an airplane
                         properly secured about him or her during movement on the surface, takeoff, and                  FAM 9.3.2             unless each person onboard the airplane who has
   121.311(b)
                         landing. A safety belt provided for the occupant of a seat may not be used by more             FOM 4.20.3 A           reached their second birthday is occupying a seat and
                         than one person who has reached his or her second birthday. Notwithstanding the
                                                                                                                                               is using the safety belt provided at that seat
                         preceding requirements, a child may:

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                                                                                                                                            A child may be held by an adult who is occupying an
                              Be held by an adult who is occupying an approved seat or berth, provided the child
                                                                                                                           FAM 8.7.2A       approved seat, provided the child has not reached
   121.311(b)(1)              has not reached his or her second birthday and the child does not occupy or use any
                              restraining device; or                                                                       SOM 8.3.1.1      their second birthday and the child does not occupy or
                                                                                                                                            use any restraining device
                                                                                                                                            A child restraint seat will be accepted when it is
                              Notwithstanding any other requirement of this chapter, occupy an approved child
                                                                                                                           FAM 8.7.3A       furnished by the child’s parent, guardian, or
   121.311(b)(2)              restraint system furnished by the certificate holder or one of the persons described in
                              paragraph (b)(2)(i) of this section, provided:                                              SOM 8.3.1.3A1     attendant designated by the child’s parent or
                                                                                                                                            guardian
                                                                                                                                            The child in the restraint seat must be
                              The child is accompanied by a parent, guardian, or attendant designated by the               FAM 8.7.3B       accompanied by a parent, guardian, or attendant
  121.311(b)(2)(i)
                              child's parent or guardian to attend to the safety of the child during the flight;           SOM 8.3.1.2      designated by the child's parent or guardian to
                                                                                                                                            attend to the safety of the child during flight
                              Except as provided in paragraph (b)(2)(ii)(D) of this section, the approved child
 121.311(b)(2)(ii)
                              restraint system bears one or more labels as follows:
                                                                                                                                            Seats manufactured to US standards during the
                              Seats manufactured to U.S. standards between January 1, 1981, and February 25,
                                                                                                                           FAM 8.7.4A       applicable dates must bear a label that states the child
121.311(b)(2)(ii)(A)          1985, must bear the label: "This child restraint system conforms to all applicable
                              Federal motor vehicle safety standards.";                                                   SOM 8.3.1.3A2     restraint system conforms to all applicable Federal
                                                                                                                                            Motor Vehicle Safety Standards
                              Seats manufactured to U.S. standards on or after February 26, 1985, must bear two
121.311(b)(2)(ii)(B)
                              labels:
                                                                                                                                            Seats manufactured to US standards during the
121.311(b)(2)(ii)(B)(         "This child restraint system conforms to all applicable Federal motor vehicle safety         FAM 8.7.4B       applicable dates must bear a label that states the child
        1)                    standards"; and                                                                             SOM 8.3.1.3A2     restraint system conforms to all applicable Federal
                                                                                                                                            Motor Vehicle Safety Standards
                                                                                                                                            Seats manufactured to US standards during the
121.311(b)(2)(ii)(B)          "THIS RESTRAINT IS CERTIFIED FOR USE IN MOTOR VEHICLES AND                                   FAM 8.7.4B       applicable dates must bear a label that states in red
       (2)                    AIRCRAFT" in red lettering;                                                                 SOM 8.3.1.3A3     lettering that the restraint is certified for use in motor
                                                                                                                                            vehicles and aircraft
                                                                                                                                            Seats that do not qualify under the above labels, must
                              Seats that do not qualify under paragraphs (b)(2)(ii)(A) and (b)(2)(ii)(B) of this                            bear either a label showing approval of a foreign
                                                                                                                           FAM 8.7.4C
121.311(b)(2)(ii)(C)          section must bear either a label showing approval of a foreign government or a label                          government or a label showing that the seat was
                              showing that the seat was manufactured under the standards of the United Nations;           SOM 8.3.1.3A4
                                                                                                                                            manufactured under the standards of the United
                                                                                                                                            Nations




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                                                                                                                                                                                                         RA
FAR/SRR


                              Notwithstanding any other provisions of this section, booster-type child restraint                             Booster-type, vest-type, harness-type (snugglies) and
                                                                                                                            FAM 8.7.4D
                              systems (as defined in Federal Motor Vehicle Standard No. 213 (49 CFR 571.213)),                               lap-held child restraints restraint systems are not
121.311(b)(2)(ii)(D)
                              vest- and harness-type child restraint systems, and lap held child restraints are not        SOM 8.3.1.3A4
                                                                                                                                             approved and are prohibited for use on TransGlobal
                              approved for use in aircraft; and                                                               (note)
                                                                                                                                             Airlines aircraft
 121.311(b)(2)(iii)           The certificate holder complies with the following requirements:
                                                                                                                                             TransGlobal Airlines flight attendants will ensure that
                              The restraint system must be properly secured to an approved forward facing seat or           FAM 8.7.4E
121.311(b)(2)(iii)(A)
                              berth;                                                                                                         the child restraint seat is properly secured in a forward
                                                                                                                           SOM 8.3.1.3A1
                                                                                                                                             facing passenger seat
                                                                                                                                             TransGlobal Airlines flight attendants will ensure that
                              The child must be properly secured in the restraint system and must not exceed the            FAM 8.7.4E
121.311(b)(2)(iii)(B)
                              specified weight limit for the restraint system; and                                                           the child is properly restrained in the child restraint
                                                                                                                           SOM 8.3.1.3A1
                                                                                                                                             seat`
                                                                                                                                             TransGlobal Airlines prohibits the child restraint
121.311(b)(2)(iii)(C)         The restraint system must bear the appropriate label(s).                                      FAM 8.7.4E       system from being used unless it bears the
                                                                                                                                             appropriate labels
                              Except as provided in paragraph (c)(3) of this section, the following prohibitions
    121.311(c)
                              apply to certificate holders:
                                                                                                                                             TransGlobal Airlines will not permit a child to occupy a
                              No certificate holder may permit a child, in an aircraft, to occupy a booster-type child                       booster type child restraint system, a vest type child
                              restraint system, a vest-type child restraint system, a harness-type child restraint
   121.311(c)(1)
                              system, or a lap held child restraint system during take off, landing, and movement           FAM 8.7.5A       restraint system, a harness type child restraint system,
                              on the surface.                                                                                                or a lap held child restraint system during takeoff,
                                                                                                                                             landing, and movement on the surface
                                                                                                                                             TransGlobal Airlines will not prohibit a child, if
                              Except as required in paragraph (c)(1) of this section, no certificate holder may                              requested by the child’s parent, guardian, or
                              prohibit a child, if requested by the child's parent, guardian, or designated attendant,                       designated attendant, from occupying a child restraint
   121.311(c)(2)
                              from occupying a child restraint system furnished by the child's parent, guardian, or         FAM 8.7.5B
                                                                                                                                             system furnished by the child’s parent, guardian, or
                              designated attendant provided -
                                                                                                                                             designated attendant when the specified conditions
                                                                                                                                             are met
                              The child holds a ticket for an approved seat or berth or such seat or berth is                                The child must be ticketed and occupy a seat on the
  121.311(c)(2)(i)
                              otherwise made available by the certificate holder for the child's use;                       FAM 8.7.5B
                                                                                                                                             aircraft
                                                                                                                                             The child in the restraint seat must be
                                                                                                                                             accompanied by a parent, guardian, or attendant
 121.311(c)(2)(ii)            The requirements of paragraph (b)(2)(i) of this section are met;                              FAM 8.7.5B
                                                                                                                                             designated by the child's parent or guardian to
                                                                                                                                             attend to the safety of the child during flight



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                                                                                                                                         The flight attendants will ensure that the restraint
 121.311(c)(2)(iii)         The requirements of paragraph (b)(2)(iii) of this section are met; and                      FAM 8.7.5B       system is secured properly, the child is secured in the
                                                                                                                                         restraint system
                            The child restraint system has one or more of the labels described in paragraphs                             The flight attendants will ensure that the restraint
 121.311(c)(2)(iv)
                            (b)(2)(ii)(A) through (b)(2)(ii)(C) of this section.                                        FAM 8.7.5B
                                                                                                                                         system bears the appropriate labels
                            This section does not prohibit the certificate holder from providing child restraint                         TransGlobal Airlines does not provide restraint
  121.311(c)(3)
                            systems authorized by this section or, …                                                    FAM 8.7.5C
                                                                                                                                         systems
                                                                                                                                         TransGlobal Airlines, consistent with safe operating
                            …, consistent with safe operating practices, determining the most appropriate
  121.311 (c)(3)
                            passenger seat location for the child restraint system.                                      FAM 8.7.5       practices, may determine the most appropriate
                                                                                                                                         passenger seat location for the child restraint system
                            Each sideward facing seat must comply with the applicable requirements of §
    121.311(d)
                            25.785(c) of this chapter.                                                                                                     N/A by configuration
                            Except as provided in paragraphs (e)(1) through (e)(3) of this section, no certificate
                                                                                                                                         All seat backs will be in the upright position during
    121.311(e)              holder may take off or land an airplane unless each passenger seat back is in the             FAM 6.3
                            upright position. ….                                                                                         takeoff and landing
                                                                                                                                         Each passenger shall comply with instructions given
                            …. Each passenger shall comply with instructions given by a crewmember in
    121.311(e)
                            compliance with this paragraph.                                                               FAM 6.3        by a crewmember concerning placing their seat backs
                                                                                                                                         in an upright position
                            This paragraph does not apply to seat backs placed in other than the upright position
  121.311(e)(1)
                            in compliance with § 121.310(f)(3).                                                                              N/A The ERJ-170 is equipped with Type I exits
                            This paragraph does not apply to seats on which cargo or persons who are unable to
                            sit erect for a medical reason are carried in accordance with procedures in the                               N/A TransGlobal Airlines does not carry passengers
  121.311(e)(2)
                            certificate holder's manual if the seat back does not obstruct any passenger's access                              who are medically unable to sit normally
                            to the aisle or to any emergency exit.
                            On airplanes with no flight attendant, the certificate holder may take off or land as
  121.311(e)(3)             long as the flightcrew instructs each passenger to place his or her seat back in the                                      N/A by seating configuration
                            upright position for takeoff and landing.
                            No person may operate a transport category airplane that was type certificated after
                            January 1, 1958, or a nontransport category airplane manufactured after March 20,                            Complied with by virtue of FAR Part 25 at manufacture
                                                                                                                         TCDS
    121.311(f)              1997, unless it is equipped at each flight deck station with a combined safety belt
                            and shoulder harness that meets the applicable requirements specified in § 25.785         GMM 6.15.4(159)
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                            of this chapter, effective March 6, 1980, except that -
                            Shoulder harnesses and combined safety belt and shoulder harnesses that were
  121.311(f)(1)
                            approved and installed before March 6, 1980, may continue to be used; and                                                    N/A by applicable date
                                                                                                                                         Complied with by virtue of FAR Part 25 at manufacture
                            Safety belt and shoulder harness restraint systems may be designed to the inertia            TCDS
  121.311(f)(2)
                            load factors established under the certification basis of the airplane.                   GMM 6.15.4(159)
                                                                                                                                         Verified at conformity inspection (conformity checklist)

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FAR/SRR


                                                                                                                                   Complied with by virtue of FAR Part 25.785 at
                        Each flight attendant must have a seat for takeoff and landing in the passenger
                                                                                                                   TCDS            manufacture
   121.311(g)           compartment that meets the requirements of § 25.785 of this chapter, effective
                        March 6, 1980, except that -                                                            GMM 6.15.4(99)
                                                                                                                                   Verified at conformity inspection (conformity checklist)
                        Combined safety belt and shoulder harnesses that were approved and installed
  121.311(g)(1)
                        before March, 6, 1980, may continue to be used; and                                                                        N/A by applicable date
                        Safety belt and shoulder harness restraint systems may be designed to the inertia
  121.311(g)(2)
                        load factors established under the certification basis of the airplane.                                           N/A by virtue of FAR Part 121.311(g)(1)
                        The requirements of § 25.785(h) do not apply to passenger seats occupied by flight
  121.311(g)(3)
                        attendants not required by § 121.391.
                                                                                                                                   Each crewmember while occupying a seat equipped
                        Each occupant of a seat equipped with a shoulder harness or with a combined
                        safety belt and shoulder harness must have the shoulder harness or combined                                with shoulder harness or with a combined safety belt
                        safety belt and shoulder harness properly secured about that occupant during             FOM 4.20.3D       and shoulder harness, must have the shoulder
   121.311(h)
                        takeoff and landing, except that a shoulder harness that is not combined with a          FAM 6.11.1 A      harness or the combination safety belt and shoulder
                        safety belt may be unfastened if the occupant cannot perform the required duties
                                                                                                                                   harness properly secured about them during taxi, take
                        with the shoulder harness fastened.
                                                                                                                                   off and landing
                                                                                                                                   At any unoccupied seat location where a shoulder
                        At each unoccupied seat, the safety belt and shoulder harness, if installed, must be      FOM 4.20.3E      harness and safety belt is installed they must be
   121.311(i)           secured so as not to interfere with crewmembers in the performance of their duties         FAM 19.1 A      secured so as to not interfere with the performance of
                        or with the rapid egress of occupants in an emergency.                                       (Note)        a person’s duties or the rapid egress of any person in
                                                                                                                                   case of emergency

121.312 Materials For Compartment Interiors
                        All interior materials; transport category airplanes and nontransport category
                        airplanes type certificated before January 1, 1965. Except for the materials covered
                        by paragraph (b) of this section, all materials in each compartment of a transport
   121.312(a)           category airplane, or a nontransport category airplane type certificated before                                            N/A by certification date
                        January 1, 1965, used by the crewmembers and passengers, must meet the
                        requirements of § 25.853 of this chapter in effect as follows, or later amendment
                        thereto:
  121.312(a)(1)         Airplane with passenger seating capacity of 20 or more.                                                                    N/A by certification date




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                           Manufactured after August 19, 1988, but prior to August 20, 1990. Except as
                           provided in paragraph (a)(3)(ii) of this section, each airplane with a passenger
                           capacity of 20 or more and manufactured after August 19, 1988, but prior to August
                           20, 1990, must comply with the heat release rate testing provisions of § 25.853(d) in
 121.312(a)(1)(i)
                           effect March 6, 1995 (formerly § 25.853(a-1) in effect on August 20, 1986) (see App.                                             N/A by certification date
                           L of this part), except that the total heat release over the first 2 minutes of sample
                           exposure must not exceed 100 kilowatt minutes per square meter and the peak heat
                           release rate must not exceed 100 kilowatts per square meter.
                           Manufactured after August 19, 1990. Each airplane with a passenger capacity of 20                                Complied with by virtue of FAR Part 25.853 at
                                                                                                                            TCDS
                           or more and manufactured after August 19, 1990, must comply with the heat release                                manufacture
 121.312(a)(1)(ii)
                           rate and smoke testing provisions of § 25.853(d) in effect March 6, 1995 (formerly §          GMM 6.15.4(74)
                           25.853(a-1)(see app. L of this part) in effect on September 26, 1988).                        GMM 6.15.4(153)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
  121.312(a)(2)            Substantially complete replacement of the cabin interior on or after May 1, 1972. -
                           Airplane for which the application for type certificate was filed prior to May 1, 1972.
                           Except as provided in paragraph (a)(3)(i) or (a)(3)(ii) of this section, each airplane for
                           which the application for type certificate was filed prior to May 1, 1972, must comply
 121.312(a)(2)(i)
                           with the provisions of § 25.853 in effect on April 30, 1972, regardless of passenger                                          N/A by type certification date
                           capacity, if there is a substantially complete replacement of the cabin interior after
                           April 30, 1972.
                           Airplane for which the application for type certificate was filed on or after May 1,
                           1972. Except as provided in paragraph (a)(3)(i) or (a)(3)(ii) of this section, each                              The requirements of FAR Part 25 and FAR 121.312(a)
                           airplane for which the application for type certificate was filed on or after May 1,
 121.312(a)(2)(ii)
                           1972, must comply with the material requirements under which the airplane was type              GMM 9.5.1A       will be considered when an E.O. is drafted to replace a
                           certificated, regardless of passenger capacity, if there is a substantially complete                             cabin interior - (bullet 13 interior materials)
                           replacement of the cabin interior on or after that date.
                           Airplane type certificated after January 1, 1958, with passenger capacity of 20 or
  121.312(a)(3)
                           more.
                           Substantially complete replacement of the cabin interior on or after March 6, 1995.
                           Except as provided in paragraph (a)(3)(ii) of this section, each airplane that was type
                           certificated after January 1, 1958, and has a passenger capacity of 20 or more, must
                           comply with the heat release rate testing provisions of § 25.853(d) in effect March 6,                           The requirements of FAR Part 25 and FAR 121.312(a)
                           1995 (formerly § 25.853(a-1) in effect on August 20, 1986)(see app. L of this part), if
 121.312(a)(3)(i)
                           there is a substantially complete replacement of the cabin interior components                  GMM 9.5.1A       will be considered when an E.O. is drafted to replace a
                           identified in § 25.853(d), on or after that date, except that the total heat release over                        cabin interior - (bullet 13 interior materials)
                           the first 2 minutes of sample exposure shall not exceed 100 kilowatt-minutes per
                           square meter and the peak heat release rate must not exceed 100 kilowatts per
                           square meter.




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                                                                                                                                                                                                            RA
FAR/SRR


                           Substantially complete replacement of the cabin interior on or after August 20, 1990.
                           Each airplane that was type certificated after January 1, 1958, and has a passenger
                           capacity of 20 or more, must comply with the heat release rate and smoke testing                                  The requirements of FAR Part 25 and FAR 121.312(a)
 121.312(a)(3)(ii)         provisions of § 25.853(d) in effect March 6, 1995 (formerly § 25.853(a-1) in effect on           GMM 9.5.1A       will be considered when an E.O. is drafted to replace a
                           September 26, 1988)(see app. L of this part), if there is a substantially complete                                cabin interior - (bullet 13 interior materials)
                           replacement of the cabin interior components identified in § 25.853(d), on or after
                           August 20, 1990.
                           Contrary provisions of this section notwithstanding, the Manager of the Transport
                           Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration,
                           may authorize deviation from the requirements of paragraph (a)(1)(i), (a)(1)(ii),
                           (a)(3)(i), or (a)(3)(ii) of this section for specific components of the cabin interior that
                           do not meet applicable flammability and smoke emission requirements, if the                                       TransGlobal Airlines is not requesting a deviation at
                           determination is made that special circumstances exist that make compliance
                                                                                                                                             this time. The requirements of FAR Part 25 and FAR
  121.312(a)(4)            impractical. Such grants of deviation will be limited to those airplanes manufactured            GMM 9.5.1A
                           within 1 year after the applicable date specified in this section and those airplanes in                          121.312(a) will be considered when an E.O. is drafted
                           which the interior is replaced within 1 year of that date. A request for such grant of                            to replace a cabin interior - (bullet 13 interior materials)
                           deviation must include a thorough and accurate analysis of each component subject
                           to § 25.853(a-1) {Now § 25.853(d) - Ed.}, the steps being taken to achieve
                           compliance, and, for the few components for which timely compliance will not be
                           achieved, credible reasons for such noncompliance.
                           Contrary provisions of this section notwithstanding, galley carts and galley standard
                           containers that do not meet the flammability and smoke emission requirements of §                                 Verified at conformity inspection (conformity checklist)
                           25.853(d) in effect March 6, 1995 (formerly § 25.853(a-1)) (see app. L of this part)
  121.312(a)(5)
                           may be used in airplanes that must meet the requirements of paragraphs (a)(1)(i),              GMM 6.15.4(74)     (complied with as a part of verification of Compartment
                           (a)(1)(ii), (a)(3)(i), or (a)(3)(ii) of this section, provided the galley carts or standard                       Interior/Fire Resistance)
                           containers were manufactured prior to March 6, 1995.
                           Seat cushions. Seat cushions, except those on flight crewmember seats, in each
                           compartment occupied by crew or passengers, must comply with the requirements
   121.312(b)
                           pertaining to seat cushions in § 25.853(c) effective on November 26, 1984, on each
                           airplane as follows:
                                                                                                                                             Complied with by virtue of FAR Part 25.853 at
                                                                                                                             TCDS            manufacture
  121.312(b)(1)            Each transport category airplane type certificated after January 1, 1958; and
                                                                                                                          GMM 6.15.4(74)
                                                                                                                                             Verified at conformity inspection (conformity checklist)
                           On or after December 20, 2010, each nontransport category airplane type
  121.312(b)(2)
                           certificated after December 31, 1964.                                                                                                  N/A by category




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FAR/SRR


                        All interior materials; airplanes type certificated in accordance with SFAR No. 41 of
                        14 CFR part 21. No person may operate an airplane that conforms to an amended or
                        supplemental type certificate issued in accordance with SFAR No. 41 of 14 CFR part
   121.312(c)           21 for a maximum certificated takeoff weight in excess of 12,500 pounds unless the                                                   N/A by TCDS
                        airplane meets the compartment interior requirements set forth in § 25.853(a) in
                        effect March 6, 1995 (formerly § 25.853(a), (b), (b-1), (b-2), and (b-3) of this chapter
                        in effect on September 26, 1978)(see app. L of this part).
                        All interior materials; other airplanes. For each material or seat cushion to which a
                        requirement in paragraphs (a), (b), or (c) of this section does not apply, the material                              N/A by virtue of compliance with FAR Part
   121.312(d)
                        and seat cushion in each compartment used by the crewmembers and passengers                                                         121.312(b)(1)
                        must meet the applicable requirement under which the airplane was type certificated.
                        Thermal/acoustic insulation materials. For transport category airplanes type
   121.312(e)
                        certificated after January 1, 1958:
                        For airplanes manufactured before September 2, 2005, when thermal/acoustic                     TCDS            Complied with by virtue of FAR Part 25.856 at
                        insulation materials are installed in the fuselage as replacements after September 2,       GMM 6.15.4(74)     manufacture
  121.312(e)(1)
                        2005, those materials must meet the flame propagation requirements of § 25.856 of           GMM 6.15.4(153)
                        this chapter, effective September 2, 2003.
                                                                                                                    GMM 6.15.4(177)    Verified at conformity inspection (conformity checklist)
                                                                                                                       TCDS            Complied with by virtue of FAR Part 25.856 at
                        For airplanes manufactured after September 2, 2005, thermal/acoustic insulation
                                                                                                                    GMM 6.15.4(74)     manufacture
  121.312(e)(2)         materials installed in the fuselage must meet the flame propagation requirements of
                        § 25.856 of this chapter, effective September 2, 2003.                                      GMM 6.15.4(153)
                                                                                                                    GMM 6.15.4(177)    Verified at conformity inspection (conformity checklist)
                        For airplanes with a passenger capacity of 20 or greater, manufactured after                   TCDS            Complied with by virtue of FAR Part 25.856 at
                        September 3, 2007, thermal/acoustic insulation materials installed in the lower half of     GMM 6.15.4(74)     manufacture
  121.312(e)(3)
                        the fuselage must meet the flame penetration resistance requirements of § 25.856            GMM 6.15.4(153)
                        of this chapter, effective September 2, 2003.
                                                                                                                    GMM 6.15.4(177)    Verified at conformity inspection (conformity checklist)

121.313 Miscellaneous Equipment
                                                                                                                                       TransGlobal Airlines verifies that each aircraft has the
                        No person may conduct any operation unless the following equipment is installed in                             required miscellaneous equipment by performing an
    121.313
                        the airplane:                                                                                 GMM 6.15.4
                                                                                                                                       aircraft conformity inspection prior to the aircraft being
                                                                                                                                       added to the aircraft listing Ops Spec
                        If protective fuses are installed on an airplane, the number of spare fuses approved
   121.313(a)
                        for that airplane and appropriately described in the certificate holder's manual.           GMM 6.15.4(14)     Verified at conformity inspection (conformity checklist)
   121.313(b)           A windshield wiper or equivalent for each pilot station.                                    GMM 6.15.4(163)    Verified at conformity inspection (conformity checklist)



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FAR/SRR


                       A power supply and distribution system that meets the requirements of §§ 25.1309,
                       25.1331, 25.1351(a) and (b)(1) through (4), 25.1353, 25.1355, and 25.1431(b) or
                       that is able to produce and distribute the load for the required instruments and                              Complied with by virtue of FAR Part 25 at manufacture
                       equipment, with use of an external power supply if any one power source or                    TCDS
   121.313(c)
                       component of the power distribution system fails. The use of common elements in            GMM 6.15.4(144)
                       the system may be approved if the Administrator finds that they are designed to be                            Verified at conformity inspection (conformity checklist)
                       reasonably protected against malfunctioning. Engine driven sources of energy, when
                       used, must be on separate engines.
                                                                                                                                     Complied with by virtue of FAR Part 25.1331 at
                       A means for indicating the adequacy of the power being supplied to required flight            TCDS            manufacture
   121.313(d)
                       instruments.                                                                               GMM 6.15.4(144)
                                                                                                                                     Verified at conformity inspection (conformity checklist)
                       Two independent static pressure systems, vented to the outside atmospheric
                       pressure so that they will be least affected by air flow variation or moisture or other                       Complied with by virtue of FAR Part 25.1325 at
                       foreign matter, and installed so as to be airtight except for the vent. When a means          TCDS            manufacture
   121.313(e)
                       is provided for transferring an instrument from its primary operating system to an         GMM 6.15.4(44)
                       alternate system, the means must include a positive positioning control and must be
                                                                                                                                     Verified at conformity inspection (conformity checklist)
                       marked to indicate clearly which system is being used.
                       A door between the passenger and pilot compartments (i.e., flightdeck door), with a
                       locking means to prevent passengers from opening it without the pilot's permission,
                       except that nontransport category airplanes certificated after December 31, 1964,
   121.313(f)          are not required to comply with this paragraph. For airplanes equipped with a crew         GMM 6.15.4(164)    Verified at conformity inspection (conformity checklist)
                       rest area having separate entries from the flightdeck and the passenger
                       compartment, a door with such a locking means must be provided between the crew
                       rest area and the passenger compartment.
                       A key for each door that separates a passenger compartment from another
                       compartment that has emergency exit provisions. Except for flightdeck doors, a key
                       must be readily available for each crewmember. Except as provided below, no
                       person other than a person who is assigned to perform duty on the flightdeck may
   121.313(g)
                       have a key to the flightdeck door. Before April 22, 2003, any crewmember may have                               N/A This door type is not installed on the ERJ-170
                       a key to the flightdeck door but only if the flightdeck door has an internal flightdeck
                       locking device installed, operative, and in use. Such "internal flightdeck locking
                       device" has to be designed so that it can only be unlocked from inside the flightdeck.
                       A placard on each door that is the means of access to a required passenger
   121.313(h)
                       emergency exit, to indicate that it must be open during takeoff and landing.                                    N/A This door type is not installed on the ERJ-170
                       A means for the crew, in an emergency to unlock each door that leads to a
   121.313(i)          compartment that is normally accessible to passengers and that can be locked by            GMM 6.15.4(104)    Verified at conformity inspection (conformity checklist)
                       passengers.
                       After April 9, 2003, for airplanes required by paragraph (f) of this section to have a
                       door between the passenger and pilot or crew rest compartments, and for transport
   121.313(j)
                       category, all-cargo airplanes that have a door installed between the pilot
                       compartment and any other occupied compartment on January 15, 2002;

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                           After April 9, 2003, for airplanes required by paragraph (f) of this section to have a
  121.313(j)(1)
                           door between the passenger and pilot or crew rest compartments,
                                                                                                                                        Complied with by virtue of FAR Part 25.795 at
                           Each such door must meet the requirements of § 25.795(a)(1) and (2) in effect on             TCDS            manufacture
 121.313(j)(1)(i)
                           January 15, 2002; and                                                                     GMM 6.15.4(164)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                           Each operator must establish methods to enable a flight attendant to enter the pilot                         The normal method for access to the flightdeck by the
                           compartment in the event that a flightcrew member becomes incapacitated. Any
 121.313(j)(1)(ii)
                           associated signal or confirmation system must be operable by each flightcrew               FOM 4.13.3.1      flight attendant will allow access if one crewmember
                           member from that flightcrew member's duty station.                                                           becomes incapacitated
                           After October 1, 2003, for transport category, all-cargo airplanes that had a door
                           installed between the pilot compartment and any other occupied compartment on or
                           after January 15, 2002, each such door must meet the requirements of §                                       N/A TransGlobal Airlines does not operate cargo only
  121.313(j)(2)
                           25.795(a)(1) and (2) in effect on January 15, 2002; or the operator must implement a                                               airplanes
                           security program approved by the Transportation Security Administration (TSA) for
                           the operation of all airplanes in that operator's fleet.


121.314 Cargo And Baggage Compartments
                                                                                                                                        TransGlobal Airlines verifies that each aircraft has the
                                                                                                                                        required cargo and baggage compartments by
   § 121.314               For each transport category airplane type certificated after January 1, 1958:               GMM 6.15.4
                                                                                                                                        performing an aircraft conformity inspection prior to the
                                                                                                                                        aircraft being added to the aircraft listing Ops Spec
                                                                                                                                        Complied with by virtue of FAR Part 25.857 at
                           Each Class C or Class D compartment, as defined in § 25.857 of this Chapter in
                                                                                                                        TCDS            manufacture
   121.314(a)              effect on June 16, 1986 (see Appendix L to this part), that is greater than 200 cubic
                           feet in volume must have ceiling and sidewall liner panels which are constructed of:      GMM 6.15.4(177)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                     GMM 6.15.4(176)
  121.314(a)(1)            Glass fiber reinforced resin;                                                                                Verified at conformity inspection (conformity checklist)
                                                                                                                     GMM 6.15.4(177)
                           Materials which meet the test requirements of part 25, appendix F, part III of this       GMM 6.15.4(176)
  121.314(a)(2)
                           chapter; or                                                                                                  Verified at conformity inspection (conformity checklist)
                                                                                                                     GMM 6.15.4(177)
                                                                                                                     GMM 6.15.4(176)
  121.314(a)(3)            In the case of liner installations approved prior to March 20, 1989, aluminum.                               Verified at conformity inspection (conformity checklist)
                                                                                                                     GMM 6.15.4(177)
                           For compliance with paragraph (a) of this section, the term "liner" includes any
   121.314(b)              design feature, such as a joint or fastener, which would affect the capability of the
                           liner to safely contain a fire.



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                            After March 19, 2001, each Class D compartment, regardless of volume, must meet
                            the standards of §§ 25.857(c) and 25.858 of this Chapter for a Class C compartment                                  N/A by virtue of cargo compartment type
    121.314(c)
                            unless the operation is an all-cargo operation in which case each Class D                                        The ERJ-170 has class “C” cargo compartments
                            compartment may meet the standards in § 25.857(e) for a Class E compartment.
    121.314(d)              Reports of conversions and retrofits.
                            Until such time as all Class D compartments in aircraft operated under this part by
                            the certificate have been converted or retrofitted with appropriate detection and                                N/A TransGlobal Airlines aircraft have not been
  121.314(d)(1)
                            suppression systems, each certificate holder must submit written progress reports to                                              retrofitted
                            the FAA that contain the information specified below.
                            The serial number of each airplane listed in the operations specifications issued to
                                                                                                                                             N/A TransGlobal Airlines aircraft have not been
 121.314(d)(1)(i)           the certificate holder for operation under this part in which all Class D compartments
                            have been converted to Class C or Class E compartments;                                                                           retrofitted
                            The serial number of each airplane listed in the operations specification issued to the
                            certificate holder for operation under this part, in which all Class D compartments                              N/A TransGlobal Airlines aircraft have not been
 121.314(d)(1)(ii)
                            have been retrofitted to meet the fire detection and suppression requirements for                                                 retrofitted
                            Class C or the fire detection requirements for Class E; and
                            The serial number of each airplane listed in the operations specifications issued to
                                                                                                                                             N/A TransGlobal Airlines aircraft have not been
 121.314(d)(1)(iii)         the certificate holder for operation under this part that has at least one Class D
                            compartment that has not been converted or retrofitted.                                                                           retrofitted
                            The written report must be submitted to the Certificate Holding District Office by July                          N/A TransGlobal Airlines aircraft have not been
  121.314(d)(2)
                            1, 1998, and at each three-month interval thereafter.                                                                             retrofitted

121.315 Cockpit Check Procedure
                            Each certificate holder shall provide an approved cockpit check procedure for each
    121.315(a)
                            type of aircraft.                                                                            FOM 4.11.1
                            The approved procedures must include each item necessary for flight crewmembers
                            to check for safety before starting engines, taking off, or landing, and in engine and      FOM 4.11.1.3A     AOM1 Chapter 7 is a copy of the EMB-170 Normal
    121.315(b)
                            systems emergencies. The procedures must be designed so that a flight                       170-SOP CH7       Checklist
                            crewmember will not need to rely upon his memory for items to be checked.
                            The approved procedures must be readily usable in the cockpit of each aircraft and
    121.315(c)
                            the flight crew shall follow them when operating the aircraft.                              FOM 4.11.1.2A


121.316 Fuel Tanks
                                                                                                                                          Complied with by virtue of FAR Part 25.963 at
                            Each turbine powered transport category airplane operated after October 30, 1991,
                                                                                                                          TCDS            manufacture
    § 121.316               must meet the requirements of § 25.963(e) of this Chapter in effect on October 30,
                            1989.                                                                                      GMM 6.15.4(64)
                                                                                                                                          Verified at conformity inspection (conformity checklist)

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121.317 Passenger Information Requirements, Smoking Prohibitions, and Additional Seat Belt Requirements
                           Except as provided in paragraph (l) of this section, no person may operate an                TCDS            Complied with by virtue of FAR Part 25.791 at
                           airplane unless it is equipped with passenger information signs that meet the
                                                                                                                     GMM 6.15.4(76)     manufacture
   121.317(a)              requirements of § 25.791 of this chapter. Except as provided in paragraph (l) of this
                           section, the signs must be constructed so that the crewmembers can turn them on           GMM 6.15.4(102)
                           and off.                                                                                  GMM 6.15.4(103)    Verified at conformity inspection (conformity checklist)
                           Except as provided in paragraph (l) of this section, the "Fasten Seat Belt" sign shall
   121.317(b)              be turned on during any movement on the surface, for each takeoff, for each landing,       FOM 18.5.1.4A
                           and at any other time considered necessary by the pilot in command.
                                                                                                                                        Complied with by virtue of FAR Part 25.1541 at
                           No person may operate an airplane on a flight on which smoking is prohibited by part
                           252 of this title unless either the "No Smoking" passenger information signs are                             manufacture
                           lighted during the entire flight, or one or more "No Smoking" placards meeting the           TCDS
   121.317(c)
                           requirements of § 25.1541 of this chapter are posted during the entire flight segment.    GMM 6.15.4(59)     Verified at conformity inspection (conformity checklist)
                           If both the lighted signs and the placards are used, the signs must remain lighted
                           during the entire flight segment.
                                                                                                                                        TransGlobal Airlines prohibits smoking at all times
                           No person may operate a passenger carrying airplane under this part unless at least
                           one legible sign or placard that reads "Fasten Seat Belt While Seated" is visible from
   121.317(d)
                           each passenger seat. These signs or placards need not meet the requirements of            GMM 6.15.4(103)    Verified at conformity inspection (conformity checklist)
                           paragraph (a) of this section.
                           No person may operate an airplane unless there is installed in each lavatory a sign
                           or placard that reads: "Federal law provides for a penalty of up to $2,000 for
   121.317(e)
                           tampering with the smoke detector installed in this lavatory." These signs or placards    GMM 6.15.4(76)     Verified at conformity inspection (conformity checklist)
                           need not meet the requirements of paragraph (a) of this section.
                                                                                                                                        Federal Aviation Regulations and TransGlobal Airlines
                           Each passenger required by § 121.311(b) to occupy a seat or berth shall fasten his          FAM 6.14.1 B
                                                                                                                                        require that whenever the seatbelt sign is illuminated,
    121.317(f)             or her safety belt about him or her and keep it fastened while the "Fasten Seat Belt"      FOM 18.5.1.4 A
                           sign is lighted.                                                                                             each passenger must be seated with a seatbelt
                                                                                                                         (bullet)
                                                                                                                                        fastened
                           {New-2000-7 (g) revised June 9, 2000, effective June 4, 2000}
                           No person may smoke while a "No Smoking" sign is lighted or while "No Smoking"              FAM 6.14.2
   121.317(g)
                           placards are posted, except as follows:                                                                      The Company prohibits smoking on all flights
                                                                                                                      FOM 18.5.1.3
                           Supplemental operations. The pilot in command of an airplane engaged in a
                           supplemental operation may authorize smoking on the flight deck (if it is physically                            N/A TransGlobal Airlines prohibits smoking on all
  121.317(g)(1)
                           separated from any passenger compartment), but not in any of the following                                                           flights
                           situations:
                                                                                                                                           N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(1)(i)          During airplane movement on the surface or during takeoff or landing;
                                                                                                                                                                flights
                           During scheduled passenger-carrying public charter operations conducted under                                   N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(1)(ii)
                           part 380 of this title; or                                                                                                           flights
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                            During any operation where smoking is prohibited by part 252 of this title or by                                N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(1)(iii)
                            international agreement.                                                                                                             flights
                            Certain intrastate domestic operations. Except during airplane movement on the
                            surface or during takeoff or landing, a pilot in command of an airplane engaged in a                            N/A TransGlobal Airlines prohibits smoking on all
  121.317(g)(2)
                            domestic operation may authorize smoking on the flight deck (if it is physically                                                     flights
                            separated from the passenger compartment) if--
                                                                                                                                            N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(2)(i)           Smoking on the flight deck is not otherwise prohibited by part 252 of this title;
                                                                                                                                                                 flights
                            The flight is conducted entirely within the same State of the United States (a flight
                                                                                                                                            N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(2)(ii)          from one place in Hawaii to another place in Hawaii through the airspace over a
                            place outside of Hawaii is not entirely within the same State); and                                                                  flights
                            The airplane is either not turbojet-powered or the airplane is not capable of carrying                          N/A TransGlobal Airlines prohibits smoking on all
 121.317(g)(2)(iii)
                            at least 30 passengers.                                                                                                              flights
    121.317(h)              No person may smoke in any airplane lavatory.                                               FAM 6.14.2       TransGlobal Airlines prohibits smoking on all flights
                                                                                                                                         No person may tamper with, disable, or destroy any
                                                                                                                                         smoke detector installed in any airplane lavatory
                            No person may tamper with, disable, or destroy any smoke detector installed in any
    121.317(i)
                            airplane lavatory.                                                                          FAM 6.14.2       TransGlobal Airlines ERJ-170 lavatories have a posted
                                                                                                                                         sign that reads “Federal law provides for a penalty of
                                                                                                                                         up to $2,000 for tampering with the smoke detector
                                                                                                                                         installed in this lavatory
                            On flight segments other than those described in paragraph (c) of this section, the
                            "No Smoking" sign must be turned on during any movement on the surface, for each            FAM 6.14.2       “No Smoking” placards are installed at each seat on all
    121.317(j)
                            takeoff, for each landing, and at any other time considered necessary by the pilot in      FOM 18.5.1.3      TransGlobal Airlines aircraft
                            command.
                                                                                                                                         Passengers shall comply with instructions given to
                            Each passenger shall comply with instructions given him or her by a crewmember               FAM 6.14        them by crewmembers regarding Seat Belts, No
    121.317(k)
                            regarding compliance with paragraphs (f), (g), (h), and (l) of this section.                 FOM 18.5        Smoking, No smoking in lavatories and Tampering
                                                                                                                                         with or disabling smoke detectors.
                            A certificate holder may operate a nontransport category airplane type certificated
                            after December 31, 1964, that is manufactured before December 20, 1997, if it is
                            equipped with at least one placard that is legible to each person seated in the cabin
    121.317(l)
                            that states "Fasten Seat Belt," and if, during any movement on the surface, for each                                            N/A by category
                            takeoff, for each landing, and at any other time considered necessary by the pilot in
                            command, a crewmember orally instructs the passengers to fasten their seat belts.




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121.318 Public Address System
                                                                                                                                 TransGlobal Airlines verifies that each aircraft has the
                       No person may operate an airplane with a seating capacity of more than 19                                 required public address system by performing an
   § 121.318
                       passengers unless it is equipped with a public address system which -                    GMM 6.15.4
                                                                                                                                 aircraft conformity inspection prior to the aircraft being
                                                                                                                                 added to the aircraft listing Ops Spec
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                       Is capable of operation independent of the crewmember interphone system required
                                                                                                                 TCDS            manufacture
   121.318(a)          by § 121.319, except for handsets, headsets, microphones, selector switches, and
                       signaling devices;                                                                     GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                                                                                                                 TCDS            manufacture
   121.318(b)          Is approved in accordance with § 21.305 of this chapter;
                                                                                                              GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                       Is accessible for immediate use from each of two flight crewmember stations in the        TCDS            manufacture
   121.318(c)
                       pilot compartment;                                                                     GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)
                       For each required floor-level passenger emergency exit which has an adjacent flight                       Complied with by virtue of FAR Part 25.1423 at
                       attendant seat, has a microphone which is readily accessible to the seated flight
                                                                                                                 TCDS            manufacture
   121.318(d)          attendant, except that one microphone may serve more than one exit, provided the
                       proximity of the exits allows unassisted verbal communication between seated flight    GMM 6.15.4(114)
                       attendants;                                                                                               Verified at conformity inspection (conformity checklist)
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                       Is capable of operation within 10 seconds by a flight attendant at each of those          TCDS            manufacture
   121.318(e)
                       stations in the passenger compartment from which its use is accessible;                GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                       Is audible at all passenger seats, lavatories, and flight attendant seats and work        TCDS            manufacture
   121.318(f)
                       stations; and                                                                          GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)
                                                                                                                                 Complied with by virtue of FAR Part 25.1423 at
                       For transport category airplanes manufactured on or after November 27, 1990,              TCDS            manufacture
   121.318(g)
                       meets the requirements of § 25.1423 of this chapter.                                   GMM 6.15.4(114)
                                                                                                                                 Verified at conformity inspection (conformity checklist)

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121.319 Crewmember Interphone System
                                                                                                                                              TransGlobal Airlines verifies that each aircraft has the
                              No person may operate an airplane with a seating capacity of more than 19
                                                                                                                                              required crewmember interphone system by
    121.319(a)                passengers unless the airplane is equipped with a crewmember interphone system                 GMM 6.15.4
                              that:                                                                                                           performing an aircraft conformity inspection prior to the
                                                                                                                                              aircraft being added to the aircraft listing Ops Spec
    121.319(1)                 [Reserved]
                              Is capable of operation independent of the public address system required by §
    121.319(2)                121.318(a) except for handsets, headsets, microphones, selector switches, and                GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              signaling devices; and
    121.319(3)                Meets the requirements of paragraph (b) of this section.                                     GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              The crewmember interphone system required by paragraph (a) of this section must
   121.319(3)(b)              be approved in accordance with § 21.305 of this chapter and meet the following               GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              requirements:
                              It must provide a means of two-way communication between the pilot compartment
 121.319(3)(b)(1)
                              and -                                                                                        GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
121.319(3)(b)(1)(i)           Each passenger compartment; and                                                              GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
121.319(3)(b)(1)(ii)          Each galley located on other than the main passenger deck level.                             GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              It must be accessible for immediate use from each of two flight crewmember stations
 121.319(3)(b)(2)
                              in the pilot compartment;                                                                    GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              It must be accessible for use from at least one normal flight attendant station in each
 121.319(3)(b)(3)
                              passenger compartment;                                                                       GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              It must be capable of operation within 10 seconds by a flight attendant at those
 121.319(3)(b)(4)
                              stations in each passenger compartment from which its use is accessible; and                 GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
 121.319(3)(b)(5)             For large turbojet powered airplanes:                                                        GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              It must be accessible for use at enough flight attendant stations so that all floor-level
                              emergency exits (or entryways to those exits in the case of exits located within
121.319(3)(b)(5)(i)
                              galleys) in each passenger compartment are observable from one or more of those              GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              stations so equipped;
                              It must have an alerting system incorporating aural or visual signals for use by flight
121.319(3)(b)(5)(ii)          crewmembers to alert flight attendants and for use by flight attendants to alert flight      GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              crewmembers;
                              The alerting system required by paragraph (b)(5)(ii) of this section must have a
121.319(3)(b)(5)(iii)         means for the recipient of a call to determine whether it is a normal call or an             GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              emergency call; and
                              When the airplane is on the ground, it must provide a means of two-way
                              communication between ground personnel and either of at least two flight
121.319(3)(b)(5)(iv)          crewmembers in the pilot compartment. The interphone system station for use by               GMM 6.15.4(113)    Verified at conformity inspection (conformity checklist)
                              ground personnel must be so located that personnel using the system may avoid
                              visible detection from within the airplane.
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121.321
   § 121.321           [Reserved]


121.323 Instruments and Equipment for Operations at Night
                                                                                                                                     TransGlobal Airlines verifies that each aircraft has the
                       No person may operate an airplane at night unless it is equipped with the following                           required instruments and equipment for operations at
   § 121.323           instruments and equipment in addition to those required by §§ 121.305 through                GMM 6.15.4       night by performing an aircraft conformity inspection
                       121.321:                                                                                                      prior to the aircraft being added to the aircraft listing
                                                                                                                                     Ops Spec
    121.323            {New-2001-5 Intro paragraph revised April 12, 2001, effective May 12, 2004}
                       No person may operate an airplane at night under this part unless it is equipped with
    121.323            the following instruments and equipment in addition to those required by §§ 121.305
                       through 121.321 and 121.803:
   121.323(a)          Position lights.                                                                           GMM 6.15.4(49)     Verified at conformity inspection (conformity checklist)
   121.323(b)          An anti-collision light.                                                                   GMM 6.15.4(46)     Verified at conformity inspection (conformity checklist)
                       Two landing lights, except that only one landing light is required for nontransport
   121.323(c)
                       category airplanes type certificated after December 31, 1964.                              GMM 6.15.4(48)     Verified at conformity inspection (conformity checklist)
                       Instrument lights providing enough light to make each required instrument, switch, or
                       similar instrument, easily readable and installed so that the direct rays are shielded
   121.323(d)          from the flight crewmembers' eyes and that no objectionable reflections are visible to     GMM 6.15.4(145)    Verified at conformity inspection (conformity checklist)
                       them. There must be a means of controlling the intensity of illumination unless it is
                       shown that nondimming instrument lights are satisfactory.
                       An airspeed indicating system with heated pitot tube or equivalent means for
   121.323(e)
                       preventing malfunctioning due to icing.                                                    GMM 6.15.4(131)    Verified at conformity inspection (conformity checklist)
   121.323(f)          A sensitive altimeter.                                                                     GMM 6.15.4(132)    Verified at conformity inspection (conformity checklist)

121.325 Instruments and Equipment for Operations Under IFR or Over the Top
                                                                                                                                     TransGlobal Airlines verifies that each aircraft has the
                       No person may operate an airplane under IFR or over the top conditions unless it is                           required instruments and equipment for operations
   § 121.325           equipped with the following instruments and equipment, in addition to those required         GMM 6.15.4       under IFR by performing an aircraft conformity
                       by §§ 121.305 through 121.321:                                                                                inspection prior to the aircraft being added to the
                                                                                                                                     aircraft listing Ops Spec
    121.325            {New-2001-5 Intro paragraph revised April 12, 2001, effective May 12, 2004}
                       No person may operate an airplane under IFR or over-the-top conditions under this
    121.325
                       part unless it is equipped with the following instruments and equipment, in addition to
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                        those required by §§ 121.305 through 121.321 and 121.803:
                        An airspeed indicating system with heated pitot tube or equivalent means for
   121.325(a)
                        preventing malfunctioning due to icing.                                                    GMM 6.15.4(131)    Verified at conformity inspection (conformity checklist)
   121.325(b)           A sensitive altimeter.                                                                     GMM 6.15.4(132)    Verified at conformity inspection (conformity checklist)
                        Instrument lights providing enough light to make each required instrument, switch, or
                        similar instrument, easily readable and so installed that the direct rays are shielded
   121.325(c)           from the flight crewmembers' eyes and that no objectionable reflections are visible to     GMM 6.15.4(145)    Verified at conformity inspection (conformity checklist)
                        them, and a means of controlling the intensity of illumination unless it is shown that
                        nondimming instrument lights are satisfactory.


121.327 Supplemental Oxygen: Reciprocating Engine Powered Airplanes
                        General. Except where supplemental oxygen is provided in accordance with §
                        121.331, no person may operate an airplane unless supplemental oxygen is
                        furnished and used as set forth in paragraphs (b) and (c) of this section. The amount                               N/A TransGlobal Airlines does not operate
   121.327(a)
                        of supplemental oxygen required for a particular operation is determined on the                                           reciprocating powered aircraft
                        basis of flight altitudes and flight duration, consistent with the operation procedures
                        established for each operation and route.
                                                                                                                                            N/A TransGlobal Airlines does not operate
   121.327(b)           Crewmembers.
                                                                                                                                                  reciprocating powered aircraft
                        At cabin pressure altitudes above 10,000 feet up to and including 12,000 feet,
                        oxygen must be provided for, and used by, each member of the flight crew on flight                                  N/A TransGlobal Airlines does not operate
  121.327(b)(1)
                        deck duty, and must be provided for other crewmembers, for that part of the flight at                                     reciprocating powered aircraft
                        those altitudes that is of more than 30 minutes duration.
                        At cabin pressure altitudes above 12,000 feet, oxygen must be provided for, and
                                                                                                                                            N/A TransGlobal Airlines does not operate
  121.327(b)(2)         used by, each member of the flight crew on flight deck duty, and must be provided
                        for other crewmembers, during the entire flight time at those altitudes.                                                  reciprocating powered aircraft
                        When a flight crewmember is required to use oxygen, he must use it continuously,
                        except when necessary to remove the oxygen mask or other dispenser in connection
                        with his regular duties. Standby crewmembers who are on call or are definitely going
                        to have flight deck duty before completing the flight must be provided with an amount                               N/A TransGlobal Airlines does not operate
  121.327(b)(3)
                        of supplemental oxygen equal to that provided for crewmembers on duty other than                                          reciprocating powered aircraft
                        on flight deck duty. If a standby crewmember is not on call and will not be on flight
                        deck duty during the remainder of the flight, he is considered to be a passenger for
                        the purposes of supplemental oxygen requirements.
                        Passengers. Each certificate holder shall provide a supply of oxygen, approved for                                  N/A TransGlobal Airlines does not operate
   121.327(c)
                        passenger safety, in accordance with the following:                                                                       reciprocating powered aircraft
                        For flights of more than 30 minutes duration at cabin pressure altitudes above 8,000
                                                                                                                                            N/A TransGlobal Airlines does not operate
  121.327(c)(1)         feet up to and including 14,000 feet, enough oxygen for 30 minutes for 10 percent of
                        the passengers.                                                                                                           reciprocating powered aircraft

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                        For flights at cabin pressure altitudes above 14,000 feet up to and including 15,000
                                                                                                                                             N/A TransGlobal Airlines does not operate
  121.327(c)(2)         feet, enough oxygen for that part of the flight at those altitudes for 30 percent of the
                        passengers.                                                                                                                reciprocating powered aircraft
                        For flights at cabin pressure altitudes above 15,000 feet, enough oxygen for each                                    N/A TransGlobal Airlines does not operate
  121.327(c)(3)
                        passenger carried during the entire flight at those altitudes.                                                             reciprocating powered aircraft
                        For the purposes of this subpart "cabin pressure altitude" means the pressure
                        altitude corresponding with the pressure in the cabin of the airplane, and "flight
                                                                                                                                             N/A TransGlobal Airlines does not operate
   121.327(d)           altitude" means the altitude above sea level at which the airplane is operated. For
                        airplanes without pressurized cabins, "cabin pressure altitude" and "flight altitude"                                      reciprocating powered aircraft
                        mean the same thing.


121.329 Supplemental Oxygen for Sustenance: Turbine Engine Powered Airplanes
                                                                                                                                       TransGlobal Airlines verifies that each aircraft has the
                        General. When operating a turbine engine powered airplane, each certificate holder
                                                                                                                                       required supplemental oxygen by performing an
   121.329(a)           shall equip the airplane with sustaining oxygen and dispensing equipment for use as           GMM 6.15.4
                        set forth in this section:                                                                                     aircraft conformity inspection prior to the aircraft being
                                                                                                                                       added to the aircraft listing Ops Spec
                        The amount of oxygen provided must be at least the quantity necessary to comply
  121.329(a)(1)
                        with paragraphs (b) and (c) of this section.
                                                                                                                                       TransGlobal Airlines has determined the amount of
                        The amount of sustaining and first aid oxygen required for a particular operation to                           sustaining and first aid oxygen required for a particular
                        comply with the rules in this part is determined on the basis of cabin pressure                                operation in order to comply with the rules in this part
  121.329(a)(2)
                        altitudes and flight duration, consistent with the operating procedures established for                        based on cabin pressure altitudes and flight duration,
                        each operation and route.
                                                                                                                                       consistent with the operating procedures established
                                                                                                                                       for each operation and route
                                                                                                                                       TransGlobal Airlines has determined the oxygen
                                                                                                                                       requirements, based on cabin pressure altitude and
                        The requirements for airplanes with pressurized cabins are determined on the basis                             the assumption that a cabin pressurization failure will
                        of cabin pressure altitude and the assumption that a cabin pressurization failure will                         occur at the altitude or point of flight that is most
                        occur at the altitude or point of flight that is most critical from the standpoint of
                                                                                                                                       critical from the standpoint of oxygen need, and that
  121.329(a)(3)         oxygen need, and that after the failure the airplane will descend in accordance with
                        the emergency procedures specified in the Airplane Flight Manual, without                                      after the failure the airplane will descend in
                        exceeding its operating limitations, to a flight altitude that will allow successful                           accordance with the emergency procedures specified
                        termination of the flight.                                                                                     in the Airplane Flight Manual, without exceeding its
                                                                                                                                       operating limitations, to a flight altitude that will allow
                                                                                                                                       successful termination of the flight


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                                                                                                                                         Following the failure, TransGlobal Airlines considers
                        Following the failure, the cabin pressure altitude is considered to be the same as the                           the cabin pressure altitude to be the same as the flight
                        flight altitude unless it is shown that no probable failure of the cabin or pressurization                       altitude
  121.329(a)(4)         equipment will result in a cabin pressure altitude equal to the flight altitude. Under
                        those circumstances, the maximum cabin pressure altitude attained may be used as                                 Under those circumstances, the maximum cabin
                        a basis for certification or determination of oxygen supply, or both.
                                                                                                                                         pressure altitude attained is used as a basis for
                                                                                                                                         certification and determination of oxygen supply
                                                                                                                         TCDS            Complied with by virtue of FAR Part 25.2441, 25.1453
                        Crewmembers. Each certificate holder shall provide a supply of oxygen for                     GMM 6.15.4(86)     at manufacture
   121.329(b)
                        crewmembers in accordance with the following:                                                 GMM 6.15.4(88)
                                                                                                                      GMM 6.15.4(158)    Verified at conformity inspection (conformity checklist)
                                                                                                                                         At cabin pressure altitudes above 10,000 feet, up to
                        At cabin pressure altitudes above 10,000 feet, up to and including 12,000 feet,                                  and including 12,000 feet, oxygen will be provided for
                        oxygen must be provided for and used by each member of the flight crew on flight                FOM 30.1.2A      and used by each member of the flight crew on flight
  121.329(b)(1)
                        deck duty and must be provided for other crewmembers for that part of the flight at             FAM 15.21.2      deck duty and will be provided for other crewmembers
                        those altitudes that is of more than 30 minutes duration.
                                                                                                                                         for that part of the flight at those altitudes that is of
                                                                                                                                         more than 30 minutes duration
                                                                                                                                         At cabin pressure attitudes above 12, 000 feet, oxygen
                        At cabin pressure altitudes above 12,000 feet, oxygen must be provided for, and                                  will be provided for, and used by, each member of the
                                                                                                                        FOM 30.1.2B
  121.329(b)(2)         used by, each member of the flight crew on flight deck duty, and must be provided                                flight crew on flight deck duty, and will be provided for
                        for other crewmembers during the entire flight at those altitudes.                              FAM 15.21.2
                                                                                                                                         each crewmembers during the entire flight at those
                                                                                                                                         altitudes.
                        When a flight crewmember is required to use oxygen, he must use it continuously
                        except when necessary to remove the oxygen mask or other dispenser in connection
                        with his regular duties. Standby crewmembers who are on call or are definitely going                             When a flight crewmember is required to use oxygen,
                        to have flight deck duty before completing the flight must be provided with an amount           FOM 30.1.2C      it will be used continuously except when necessary to
  121.329(b)(3)
                        of supplemental oxygen equal to that provided for crewmembers on duty other than                FAM 15.21.2      remove the oxygen mask or other dispenser in
                        on flight duty. If a standby crewmember is not on call and will not be on flight deck
                                                                                                                                         connection with their regular duties
                        duty during the remainder of the flight, he is considered to be a passenger for the
                        purposes of supplemental oxygen requirements.
                                                                                                                         TCDS            Complied with by virtue of FAR Part 25.2441, 25.1453
                        Passengers. Each certificate holder shall provide a supply of oxygen for passengers           GMM 6.15.4(86)     at manufacture
   121.329(c)
                        in accordance with the following:                                                             GMM 6.15.4(87)
                                                                                                                      GMM 6.15.4(158)    Verified at conformity inspection (conformity checklist)



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FAR/SRR


                                                                                                                                         For flights at cabin pressure altitudes above 10,000
                          For flights at cabin pressure altitudes above 10,000 feet, up to and including 14,000                          feet, up to and including 14,000 feet, enough oxygen
                                                                                                                        FOM 30.1.3A
  121.329(c)(1)           feet, enough oxygen for that part of the flight at those altitudes that is of more than                        will be provided, for that part of the flight at those
                          30 minutes duration, for 10 percent of the passengers.                                        FAM 15.21.2
                                                                                                                                         altitudes that is of more than 30 minutes duration, for
                                                                                                                                         10 percent of the passengers
                                                                                                                                         For flights at cabin pressure altitudes above 14,000
                          For flights at cabin pressure altitudes above 14,000 feet, up to and including 15,000
                                                                                                                        FOM 30.1.3B      feet, up to and including 15,000 feet, enough oxygen
  121.329(c)(2)           feet, enough oxygen for that part of the flight at those altitudes for 30 percent of the
                          passengers.                                                                                   FAM 15.21.2      will be provided, for that part of the flight at those
                                                                                                                                         altitudes, for 30 percent of the passengers
                                                                                                                                         For flights at cabin pressure altitudes above 15,000
                          For flights at cabin pressure altitudes above 15,000 feet, enough oxygen for each             FOM 30.1.3C      feet, enough oxygen will be provided for each
  121.329(c)(3)
                          passenger carried during the entire flight at those altitudes.                                FAM 15.21.2      passenger carried during the entire flight at those
                                                                                                                                         altitudes

121.331 Supplemental Oxygen Requirements for Pressurized Cabin Airplanes: Reciprocating Engine Powered Airplanes
                          When operating a reciprocating engine powered airplane pressurized cabin, each
                                                                                                                                               N/A TransGlobal Airlines does not operate
   121.331(a)             certificate holder shall equip the airplane to comply with paragraphs (b) through (d)
                          of this section in the event of cabin pressurization failure.                                                              reciprocating powered aircraft
                          For crewmembers. When operating at flight altitudes above 10,000 feet, the
                          certificate holder shall provide enough oxygen for each crewmember for the entire
                          flight at those altitudes and not less than a two hour supply for each flight
                          crewmember on flight deck duty. The required two hours supply is that quantity of
                                                                                                                                               N/A TransGlobal Airlines does not operate
   121.331(b)             oxygen necessary for a constant rate of descent from the airplane's maximum
                          certificated operating altitude to 10,000 feet in ten minutes and followed by 110                                          reciprocating powered aircraft
                          minutes at 10,000 feet. The oxygen required by § 121.337 may be considered in
                          determining the supplemental breathing supply required for flight crewmembers on
                          flight deck duty in the event of cabin pressurization failure.
                          For passengers. When operating at flight altitudes above 8,000 feet, the certificate                                 N/A TransGlobal Airlines does not operate
   121.331(c)             holder shall provide oxygen as follows:
                                                                                                                                                     reciprocating powered aircraft
                          When an airplane is not flown at a flight altitude above flight level 250, enough
                          oxygen for 30 minutes for 10 percent of the passengers, if at any point along the                                    N/A TransGlobal Airlines does not operate
  121.331(c)(1)
                          route to be flown the airplane can safely descend to a flight altitude of 14,000 feet or                                   reciprocating powered aircraft
                          less within four minutes.
                          If the airplane cannot descend to a flight altitude of 14,000 feet or less within four                               N/A TransGlobal Airlines does not operate
  121.331(c)(2)           minutes, the following supply of oxygen must be provided:
                                                                                                                                                     reciprocating powered aircraft
                          For that part of the flight that is more than four minutes duration at flight altitudes                              N/A TransGlobal Airlines does not operate
 121.331(c)(2)(i)         above 15,000 feet, the supply required by § 121.327(c)(3).
                                                                                                                                                     reciprocating powered aircraft
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                            For that part of the flight at flight altitudes above 14,000 feet, up to and including                               N/A TransGlobal Airlines does not operate
 121.331(c)(2)(ii)          15,000 feet, the supply required by § 121.327(c)(2).
                                                                                                                                                       reciprocating powered aircraft
                            For flight at flight altitudes above 8,000 feet up to and including 14,000 feet, enough                              N/A TransGlobal Airlines does not operate
 121.331(c)(2)(iii)         oxygen for 30 minutes for 10 percent of the passengers.
                                                                                                                                                       reciprocating powered aircraft
                            When an airplane is flown at a flight altitude above flight level 250, enough oxygen
                            for 30 minutes for 10 percent of the passengers for the entire flight (including                                     N/A TransGlobal Airlines does not operate
  121.331(c)(3)
                            emergency descent) above 8,000 feet, up to and including 14,000 feet, and to                                               reciprocating powered aircraft
                            comply with § 121.327(c)(2) and (3) for flight above 14,000 feet.
                            For the purposes of this section it is assumed that the cabin pressurization failure
                            occurs at a time during flight that is critical from the standpoint of oxygen need and                               N/A TransGlobal Airlines does not operate
    121.331(d)
                            that after the failure the airplane will descend, without exceeding its normal operating                                   reciprocating powered aircraft
                            limitations, to flight altitudes allowing safe flight with respect to terrain clearance.


121.333 Supplemental Oxygen for Emergency Descent and for First Aid; Turbine Engine Powered Airplanes with
Pressurized Cabins
                                                                                                                            TCDS
                            General. When operating a turbine engine powered airplane with a pressurized                                   Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                        GMM 6.15.4(86)
                            cabin, the certificate holder shall furnish oxygen and dispensing equipment to                                 at manufacture
    121.333(a)
                            comply with paragraphs (b) through (e) of this section in the event of cabin                GMM 6.15.4(88)
                            pressurization failure.                                                                     GMM 6.15.4(158)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                                                                                                                          FOM 30.2.1
                            Crewmembers. When operating at flight altitudes above 10,000 feet, the certificate
                            holder shall supply enough oxygen to comply with § 121.329, but not less than a two             TCDS
                            hour supply for each flight crewmember on flight deck duty. The required two hours                             Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                        GMM 6.15.4(86)
                            supply is that quantity of oxygen necessary for a constant rate of descent from the                            at manufacture
    121.333(b)
                            airplane's maximum certificated operating altitude to 10,000 feet in ten minutes and        GMM 6.15.4(88)
                            followed by 110 minutes at 10,000 feet. The oxygen required in the event of cabin           GMM 6.15.4(158)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                            pressurization failure by § 121.337 may be included in determining the supply                 FOM 30.2.2
                            required for flight crewmembers on flight deck duty.
    121.333(c)              Use of oxygen masks by flight crewmembers.
                            When operating at flight altitudes above flight level 250, each flight crewmember on            TCDS
                            flight deck duty must be provided with an oxygen mask so designed that it can be                               Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                        GMM 6.15.4(86)
                            rapidly placed on his face from its ready position, properly secured, sealed, and                              at manufacture
  121.333(c)(1)
                            supplying oxygen upon demand; and so designed that after being placed on the face           GMM 6.15.4(88)
                            it does not prevent immediate communication between the flight crewmember and               GMM 6.15.4(158)
                                                                                                                                           Verified at conformity inspection (conformity checklist)
                            other crewmembers over the airplane intercommunication system. …                              FOM 30.2.3



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FAR/SRR


                                                                                                                                            When it is not being used at flight altitudes above flight
                            … When it is not being used at flight altitudes above flight level 250, the oxygen                              level 250, the oxygen mask must be kept in condition
  121.333(c)(1)             mask must be kept in condition for ready use and located so as to be within the                FOM 30.2.3A      for ready use and located so as to be within the
                            immediate reach of the flight crewmember while at his duty station.                                             immediate reach of the flight crewmember while at his
                                                                                                                                            duty station.
                            When operating at flight altitudes above flight level 250, one pilot at the controls of
  121.333(c)(2)             the airplane shall at all times wear and use an oxygen mask secured, sealed, and                                       N/A by virtue of FAR Part 121.333(c)(2)(i)
                            supplying oxygen, in accordance with the following:

                            The one pilot need not wear and use an oxygen mask at or below the following flight                             All TransGlobal Airlines aircraft are equipped with
                            levels if each flight crewmember on flight deck duty has a quick-donning type of                                quick-donning masks and a maximum service ceiling
 121.333(c)(2)(i)           oxygen mask that the certificate holder has shown can be placed on the face from its           FOM 30.2.3B      of flight level 410–This eliminates the requirement for
                            ready position, properly secured, sealed, and supplying oxygen upon demand, with                                one pilot to wear the oxygen mask above flight level
                            one hand and within five seconds:
                                                                                                                                            250
                            For airplanes having a passenger seat configuration of more than 30 seats,                                      The ERJ-170 has a maximum service ceiling of flight
121.333(c)(2)(i)(A)         excluding any required crewmember seat, or a payload capacity of more than 7,500               FOM 30.2.3B      level 410–This eliminates the requirement for one pilot
                            pounds, at or below flight level 410.                                                                           to wear the oxygen mask above flight level 250
                            For airplanes having a passenger seat configuration of less than 31 seats, excluding
121.333(c)(2)(i)(B)         any required crewmember seat, and a payload capacity of 7,500 pounds or less, at                                              N/A by seating configuration
                            or below flight level 350.
                            Whenever a quick-donning type of oxygen mask is to be used under this section, the                              TransGlobal Airlines will show that the quick-donning
                            certificate holder shall also show that the mask can be put on without disturbing eye                           type of oxygen mask required by this section, can be
                            glasses and without delaying the flight crewmember from proceeding with his
 121.333(c)(2)(ii)
                            assigned emergency duties. The oxygen mask after being put on must not prevent                170-SYS 18.2.2    put on without disturbing eye glasses and without
                            immediate communication between the flight crewmember and other crewmembers                                     delaying the flight crewmember from proceeding with
                            over the airplane intercommunication system.                                                                    his assigned emergency duties
                                                                                                                                            If for any reason at any time it is necessary for one
                            Notwithstanding paragraph (c)(2) of this section, if for any reason at any time it is                           pilot to leave his station at the controls of the airplane
                            necessary for one pilot to leave his station at the controls of the airplane when
                                                                                                                                            when operating at flight altitudes above flight level 250,
  121.333(c)(3)             operating at flight altitudes above flight level 250, the remaining pilot at the controls      FOM 30.2.3D
                            shall put on and use his oxygen mask until the other pilot has returned to his duty                             the remaining pilot at the controls shall put on and use
                            station.                                                                                                        his oxygen mask until the other pilot has returned to
                                                                                                                                            his duty station.
                                                                                                                                            Before the takeoff, each flight crewmember shall
                            Before the takeoff of a flight, each flight crewmember shall personally preflight his                           personally preflight his oxygen equipment to ensure
                            oxygen equipment to insure that the oxygen mask is functioning, fitted properly, and                            that the oxygen mask is functioning, fitted properly,
  121.333(c)(4)
                            connected to appropriate supply terminals, and that the oxygen supply and pressure             FOM 30.2.3E
                                                                                                                                            and connected to appropriate supply terminals, and
                            are adequate for use.
                                                                                                                                            that the oxygen supply and pressure are adequate for
                                                                                                                                            use
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FAR/SRR


                        Use of portable oxygen equipment by cabin attendants. Each attendant shall, during
                        flight above flight level 250 flight altitude, carry portable oxygen equipment with at                        Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                       TCDS
                        least a 15 minute supply of oxygen unless it is shown that enough portable oxygen                             at manufacture
   121.333(d)
                        units with masks or spare outlets and masks are distributed throughout the cabin to        GMM 6.15.4(88)
                        insure immediate availability of oxygen to each cabin attendant, regardless of his           FAM 15.17
                                                                                                                                      Verified at conformity inspection (conformity checklist)
                        location at the time of cabin depressurization.
                                                                                                                                      Complied with by virtue of FAR Part 25.2441, 25.1453
                        Passenger cabin occupants. When the airplane is operating at flight altitudes above           TCDS
                                                                                                                                      at manufacture
   121.333(e)           10,000 feet, the following supply of oxygen must be provided for the use of                GMM 6.15.4(86)
                        passenger cabin occupants:                                                                  FOM 30.2.4A
                                                                                                                                      Verified at conformity inspection (conformity checklist)
                        When an airplane certificated to operate at flight altitudes up to and including flight
                        level 250, can at any point along the route to be flown, descend safely to a flight
  121.333(e)(1)         altitude of 14,000 feet or less within four minutes, oxygen must be available at the                                  N/A by virtue of FAR Part 121.333(e)(2)
                        rate prescribed by this part for a 30 minute period for at least 10 percent of the
                        passenger cabin occupants.
                                                                                                                                      Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                                      at manufacture

                                                                                                                                      Verified at conformity inspection (conformity checklist)
                        When an airplane is operated at flight altitudes up to and including flight level 250
                        and cannot descend safely to a flight altitude of 14,000 feet within four minutes, or                         When an airplane is operated at flight altitudes above
                        when an airplane is operated at flight altitudes above flight level 250, oxygen must          TCDS            flight level 250, oxygen will be available for not less
                        be available at the rate prescribed by this part for not less than 10 percent of the
  121.333(e)(2)
                        passenger cabin occupants for the entire flight after cabin depressurization, at cabin     GMM 6.15.4(86)     than 10 percent of the passenger cabin occupants for
                        pressure altitudes above 10,000 feet up to and including 14,000 feet and, as               FOM 30.2.4A(2)     the entire flight after cabin depressurization, with cabin
                        applicable, to allow compliance with § 121.329(c)(2) and (3), except that there must                          pressure altitudes above 10,000 feet up to and
                        be not less than a 10 minute supply for the passenger cabin occupants.                                        including 14,000 feet and, as applicable, to allow
                                                                                                                                      compliance with 121.329(c) (2) and (3)

                                                                                                                                      In no case will there be less than a 10 minute supply
                                                                                                                                      for the passenger cabin occupants




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FAR/SRR


                                                                                                                                     Complied with by virtue of FAR Part 25.2441, 25.1453
                                                                                                                                     at manufacture

                                                                                                                                     Verified at conformity inspection (conformity checklist)

                        For first aid treatment of occupants who for physiological reasons might require                             For first aid treatment of occupants, who for
                        undiluted oxygen following descent from cabin pressure altitudes above flight level                          physiological reasons might require undiluted oxygen
                        250, a supply of oxygen in accordance with the requirements of § 25.1443(d) must             TCDS
                                                                                                                                     following descent from cabin pressure altitudes above
                        be provided for two percent of the occupants for the entire flight after cabin            GMM 6.15.4(86)
  121.333(e)(3)
                        depressurization at cabin pressure altitudes above 8,000 feet, but in no case to less                        flight level 250, a supply of oxygen must be provided
                                                                                                                  GMM 6.15.4(88)
                        than one person. An appropriate number of acceptable dispensing units, but in no                             for two percent of the occupants for the entire flight
                                                                                                                  FOM 30.2.4A(3)
                        case less than two, must be provided, with a means for the cabin attendants to use                           after cabin depressurization at cabin pressure altitude
                        this supply.                                                                                                 above 8,000 feet, but in no case to less than one
                                                                                                                                     person.

                                                                                                                                     The ERJ-170 has an appropriate number of
                                                                                                                                     acceptable dispensing units with a means for the cabin
                                                                                                                                     attendants to use the supply
                                                                                                                                     Verified at conformity inspection (conformity checklist)

                        Passenger briefing. Before flight is conducted above flight level 250, a crewmember                          Before every flight is conducted, a flight attendant shall
                        shall instruct the passengers on the necessity of using oxygen in the event of cabin      GMM 6.15.4(101)
   121.333(f)
                        depressurization and shall point out to them the location and demonstrate the use of                         instruct the passengers on the necessity of using
                                                                                                                    FAM 9.3.6
                        the oxygen dispensing equipment.                                                                             oxygen in the event of cabin depressurization and
                                                                                                                                     shall point out to them the location of and demonstrate
                                                                                                                                     the use of the oxygen dispensing equipment

121.335 Equipment Standards: Reciprocating Engine Powered Airplanes
                        The oxygen apparatus, the minimum rates of oxygen flow, and the supply of oxygen
                        necessary to comply with § 121.327 must meet the standards established in section
                        4b.651 of the Civil Air Regulations as in effect on July 20, 1950, except that if the                              N/A TransGlobal Airlines does not operate
   121.335(a)
                        certificate holder shows full compliance with those standards to be impracticable, the                              reciprocating engine powered airplanes.
                        Administrator may authorize any change in those standards that he finds will provide
                        an equivalent level of safety.




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FAR/SRR


                        Turbine engine powered airplanes. The oxygen apparatus, the minimum rate of
                        oxygen flow, and the supply of oxygen necessary to comply with §§ 121.329 and
                        121.333 must meet the standards established in section 4b.651 of the Civil Air
                                                                                                                                          N/A TransGlobal Airlines does not operate
   121.335(b)           Regulations as in effect on September 1, 1958, except that if the certificate holder
                        shows full compliance with those standards to be impracticable, the Administrator                                  reciprocating engine powered airplanes.
                        may authorize any changes in those standards that he finds will provide an
                        equivalent level of safety.


121.337 Protective Breathing Equipment
                                                                                                                                    TransGlobal Airlines verifies that each aircraft has the
                                                                                                                                    required protective breathing equipment by performing
                                                                                                                                    an aircraft conformity inspection prior to the aircraft
                                                                                                                                    being added to the aircraft listing Ops Spec
                        The certificate holder shall furnish approved protective breathing equipment (PBE)
                                                                                                                   GMM 6.15.4
   121.337(a)           meeting the equipment, breathing gas, and communication requirements contained
                        in paragraph (b) of this section.                                                         FAM 15.18.1A      TransGlobal Airlines provides protective breathing
                                                                                                                                    equipment (PBE) with a portable oxygen supply that is
                                                                                                                                    easily accessible and conveniently located throughout
                                                                                                                                    the cabin for immediate use by crewmembers in
                                                                                                                                    combating fires
                        Pressurized and nonpressurized cabin airplanes. Except as provided in paragraph (f)                         Complied with by virtue of FAR Part 25.1439 at
                                                                                                                    TCDS
                        of this section {There is no (f) in this section - Ed.}, no person may operate an                           manufacture
   121.337(b)
                        airplane unless protective breathing equipment meeting the requirements of this          GMM 6.15.4(94)
                        section is provided as follows:                                                          GMM 6.15.4(157)
                                                                                                                                    Verified at conformity inspection (conformity checklist)
                        General. The equipment must protect the flightcrew from the effects of smoke,                               Complied with by virtue of FAR Part 25.1439 at
                                                                                                                    TCDS
                        carbon dioxide or other harmful gases or an oxygen deficient environment caused by                          manufacture
  121.337(b)(1)
                        other than an airplane depressurization while on flight deck duty and must protect       GMM 6.15.4(94)
                        crewmembers from the above effects while combating fires on board the airplane.          GMM 6.15.4(157)
                                                                                                                                    Verified at conformity inspection (conformity checklist)
                        The equipment must be inspected regularly in accordance with inspection guidelines
                        and the inspection periods established by the equipment manufacturer to ensure its                          Complied with by virtue of FAR Part 25.1439 at
                                                                                                                    TCDS
                        condition for continued serviceability and immediate readiness to perform its                               manufacture
  121.337(b)(2)
                        intended emergency purposes. The inspection periods may be changed upon a                GMM 6.15.4(94)
                        showing by the certificate holder that the changes would provide an equivalent level     GMM 6.15.4(157)
                                                                                                                                    Verified at conformity inspection (conformity checklist)
                        of safety.
                        That part of the equipment protecting the eyes must not impair the wearer's vision to                       Complied with by virtue of FAR Part 25.1439 at
                                                                                                                    TCDS
                        the extent that a crewmember's duties cannot be accomplished and must allow                                 manufacture
  121.337(b)(3)
                        corrective glasses to be worn without impairment of vision or loss of the protection     GMM 6.15.4(94)
                        required by paragraph (b)(1) of this section.                                            GMM 6.15.4(157)
                                                                                                                                    Verified at conformity inspection (conformity checklist)
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                            The equipment, while in use, must allow the flightcrew to communicate using the
                            airplane radio equipment and to communicate by interphone with each other while at                          Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            their assigned duty stations. The equipment, while in use, must also allow                                  manufacture
  121.337(b)(4)
                            crewmember interphone communications between each of two flight crewmember               GMM 6.15.4(94)
                            stations in the pilot compartment and at least one normal flight attendant station in    GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                            each passenger compartment.
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                            The equipment, while in use, must allow any crewmember to use the airplane                  TCDS
                                                                                                                                        manufacture
  121.337(b)(5)             interphone system at any of the flight attendant stations referred to in paragraph       GMM 6.15.4(94)
                            (b)(4) of this section.                                                                  GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            The equipment may also be used to meet the supplemental oxygen requirements of                              manufacture
  121.337(b)(6)
                            this part provided it meets the oxygen equipment standards of § 121.335 of this part.    GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            Protective breathing gas duration and supply system equipment requirements are as                           manufacture
  121.337(b)(7)
                            follows:                                                                                 GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            The equipment must supply breathing gas for 15 minutes at a pressure altitude of                            manufacture
 121.337(b)(7)(i)
                            8,000 feet for the following:                                                            GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                                                                                                                                        manufacture
121.337(b)(7)(i)(A)         Flight crewmembers while performing flight deck duties; and                              GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                                                                                                                                        manufacture
121.337(b)(7)(i)(B)         Crewmembers while combating an in-flight fire.                                           GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            The breathing gas system must be free from hazards in itself, in its method of                              manufacture
 121.337(b)(7)(ii)
                            operation, and in its effect upon other components.                                      GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)


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                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                            For breathing gas systems other than chemical oxygen generators, there must be a            TCDS
                                                                                                                                        manufacture
 121.337(b)(7)(iii)         means to allow the crew to readily determine, during the equipment preflight             GMM 6.15.4(94)
                            described in paragraph (c) of this section, that the gas supply is fully charged.        GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            For each chemical oxygen generator, the supply system equipment must meet the                               manufacture
 121.337(b)(7)(iv)
                            requirements of § 25.1450(b) and (c) of this chapter.                                    GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                            Smoke and fume protection. Protective breathing equipment with a fixed or portable                          Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            breathing gas supply meeting the requirements of this section must be conveniently                          manufacture
  121.337(b)(8)
                            located on the flight deck and be easily accessible for immediate use by each            GMM 6.15.4(94)
                            required flight crewmember at his or her assigned duty station.                          GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                            Fire combating. Except for nontransport category airplanes type certificated after                          Complied with by virtue of FAR Part 25.1439 at
                            December 31, 1964, protective breathing equipment with a portable breathing gas             TCDS
                                                                                                                                        manufacture
  121.337(b)(9)             supply meeting the requirements of this section must be easily accessible and            GMM 6.15.4(94)
                            conveniently located for immediate use by crewmembers in combating fires as              GMM 6.15.4(157)
                            follows:                                                                                                    Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            One PBE is required for each hand fire extinguisher located for use in a galley other                       manufacture
 121.337(b)(9)(i)
                            than a galley located in a passenger, cargo, or crew compartment.                        GMM 6.15.4(94)
                                                                                                                     GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                                                                                                                                        Complied with by virtue of FAR Part 25.1439 at
                            One on the flight deck, except that the Administrator may authorize another location        TCDS
                                                                                                                                        manufacture
 121.337(b)(9)(ii)          for this PBE if special circumstances exist that make compliance impractical and the     GMM 6.15.4(94)
                            proposed deviation would provide an equivalent level of safety.                          GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                            In each passenger compartment, one for each hand fire extinguisher required by §
                            121.309 of this part, to be located within 3 feet of each required hand fire                                Complied with by virtue of FAR Part 25.1439 at
                                                                                                                        TCDS
                            extinguisher, except that the Administrator may authorize a deviation allowing                              manufacture
 121.337(b)(9)(iii)
                            locations of PBE more than 3 feet from required hand fire extinguisher locations if      GMM 6.15.4(94)
                            special circumstances exist that make compliance impractical and if the proposed         GMM 6.15.4(157)
                                                                                                                                        Verified at conformity inspection (conformity checklist)
                            deviation provides an equivalent level of safety.
    121.337(c)              Equipment preflight.
                            Before each flight, each item of PBE at flight crewmember duty stations must be                             Each PBE located at a flight crewmember duty
                                                                                                                       FOM 30.2.5C
  121.337(c)(1)             checked by the flight crewmember who will use the equipment to ensure that the                              station, will be checked by the flight crewmember
                            equipment -                                                                                FAM 15.18.5      who would use the equipment



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                           For other than chemical oxygen generator systems, is functioning, is serviceable, fits
                                                                                                                             FAM 15.18.5
 121.337(c)(1)(i)          properly (unless a universal fit type), and is connected to supply terminals and that                              The PBE installed on the ERJ-170 are self-contained.
                           the breathing gas supply and pressure are adequate for use; and                                 170-SOP 6.7.2.13
                           For chemical oxygen generator systems, is serviceable and fits properly (unless a                                     N/A The EMB170 does not use chemical oxygen
 121.337(c)(1)(ii)
                           universal fit type).                                                                                                              generating systems
                           Each item of PBE located at other than a flight crewmember duty station must be
                           checked by a designated crewmember to ensure that each is properly stowed and
                           serviceable, and, for other than chemical oxygen generator systems, the breathing                 FOM 30.2.5D      Any PBE not located at a flight crewmember duty
  121.337(c)(2)
                           gas supply is fully charged. Each certificate holder, in its operations manual, must              FAM 15.18.5      station, will be checked by the “A” flight attendant
                           designate at least one crewmember to perform those checks before he or she takes
                           off in that airplane for his or her first flight of the day.


121.339 Emergency Equipment for Extended Overwater Operations
                           Except where the Administrator, by amending the operations specifications of the
                           certificate holder, requires the carriage of all or any specific items of the equipment
                           listed below for any overwater operation, or upon application of the certificate holder,                               N/A The ERJ-170 is not certified for extended
   121.339(a)
                           the Administrator allows deviation for a particular extended overwater operation, no                                             overwater operations
                           person may operate an airplane in extended overwater operations without having on
                           the airplane the following equipment:
                           A life preserver equipped with an approved survivor locator light, for each occupant                                   N/A The ERJ-170 is not certified for extended
  121.339(a)(1)
                           of the airplane.                                                                                                                 overwater operations
                           Enough life rafts (each equipped with an approved survivor locator light) of a rated
                           capacity and buoyancy to accommodate the occupants of the airplane. Unless
                                                                                                                                                  N/A The ERJ-170 is not certified for extended
  121.339(a)(2)            excess rafts of enough capacity are provided, the buoyancy and seating capacity
                           beyond the rated capacity of the rafts must accommodate all occupants of the                                                     overwater operations
                           airplane in the event of a loss of one raft of the largest rated capacity.
                                                                                                                                                  N/A The ERJ-170 is not certified for extended
  121.339(a)(3)            At least one pyrotechnic signaling device for each life raft.
                                                                                                                                                            overwater operations
                           An approved survival type emergency locator transmitter. Batteries used in this
                           transmitter must be replaced (or recharged, if the battery is rechargeable) when the
                           transmitter has been in use for more than 1 cumulative hour, or when 50 percent of
                           their useful life (or for rechargeable batteries, 50 percent of their useful life of charge)
                                                                                                                                                  N/A The ERJ-170 is not certified for extended
  121.339(a)(4)            has expired, as established by the transmitter manufacturer under its approval. The
                           new expiration date for replacing (or recharging) the battery must be legibly marked                                             overwater operations
                           on the outside of the transmitter. The battery useful life (or useful life of charge)
                           requirements of this paragraph do not apply to batteries (such as water activated
                           batteries) that are essentially unaffected during probable storage intervals.




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                        The required life rafts, life preservers, and survival type emergency locator
                        transmitter must be easily accessible in the event of a ditching without appreciable                                N/A The ERJ-170 is not certified for extended
   121.339(b)
                        time for preparatory procedures. This equipment must be installed in conspicuously                                            overwater operations
                        marked, approved locations.
                        A survival kit, appropriately equipped for the route to be flown, must be attached to                               N/A The ERJ-170 is not certified for extended
   121.339(c)
                        each required life raft.                                                                                                      overwater operations

121.340 Emergency Flotation Means
                        Except as provided in paragraph (b) of this section, no person may operate an
                        airplane in any overwater operation unless it is equipped with life preservers in
   121.340(a)           accordance with § 121.339(a)(1) or with an approved flotation means for each                 GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                        occupant. This means must be within easy reach of each seated occupant and must
                        be readily removable from the airplane.
                        Upon application by the air carrier or commercial operator, the Administrator may
                        approve the operation of an airplane over water without the life preservers or
                        flotation means required by paragraph (a) of this section, if the air carrier or
   121.340(b)           commercial operator shows that the water over which the airplane is to be operated           GMM 6.15.4(89)     Verified at conformity inspection (conformity checklist)
                        is not of such size and depth that life preservers or flotation means would be
                        required for the survival of its occupants in the event the flight terminates in that
                        water.


121.341 Equipment for Operations in Icing Conditions
                        Except as permitted in paragraph (c)(2) of this section, unless an airplane is type
                        certificated under the transport category airworthiness requirements relating to ice
                        protection, or unless an airplane is a non-transport category airplane type certificated                                            N/A by category
                        after December 31, 1964, that has the ice protection provisions that meet section 34
   121.341(a)
                        of appendix A of part 135 of this chapter, no person may operate an airplane in icing
                        conditions unless it is equipped with means for the prevention or removal of ice on                             The ERJ-170 is certified to standards of FAR 25.1419
                        windshields, wings, empennage, propellers, and other parts of the airplane where ice
                        formation will adversely affect the safety of the airplane.
                        No person may operate an airplane in icing conditions at night unless means are                                 Complied with by virtue of FAR Part 25.1403 at
                        provided for illuminating or otherwise determining the formation of ice on the parts of
                                                                                                                        TCDS            manufacture
   121.341(b)           the wings that are critical from the standpoint of ice accumulation. Any illuminating
                        that is used must be of a type that will not cause glare or reflection that would            GMM 6.15.4(51)
                        handicap crewmembers in the performance of their duties.                                                        Verified at conformity inspection (conformity checklist)
                        Non-transport category airplanes type certificated after December 31, 1964. Except
                        for an airplane that has ice protection provisions that meet section 34 of appendix A
   121.341(c)
                        of part 135 of this chapter, or those for transport category airplane type certification,                                           N/A by category
                        no person may operate -
  121.341(c)(1)         Under IFR into known or forecast light or moderate icing conditions;                                                                N/A by category
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                                                                                                                                                                                                 RA
FAR/SRR


                        Under VFR into known light or moderate icing conditions; unless the airplane has
                        functioning deicing anti-icing equipment protecting each propeller, windshield, wing,
  121.341(c)(2)
                        stabilizing or control surface, and each airspeed, altimeter, rate of climb, or flight                                            N/A by category
                        attitude instrument system; or
  121.341(c)(3)         Into known or forecast severe icing conditions.                                                                                   N/A by category
                        If current weather reports and briefing information relied upon by the pilot in
                        command indicate that the forecast icing condition that would otherwise prohibit the
   121.341(d)           flight will not be encountered during the flight because of changed weather                                            N/A by virtue of FAR Part 121.341(c)
                        conditions since the forecast, the restrictions in paragraph (c) of this section based
                        on forecast conditions do not apply.


121.342 Pitot Heat Indication Systems
                        No person may operate a transport category airplane or, after December 20, 1999, a                            Complied with by virtue of FAR Part 25.1426 at
                        nontransport category airplane type certificated after December 31, 1964, that is             TCDS
                                                                                                                                      manufacture
   § 121.342            equipped with a flight instrument pitot heating system unless the airplane is also         GMM 6.15.4(43)
                        equipped with an operable pitot heat indication system that complies § 25.1326 of          GMM 6.15.4(147)
                        this chapter in effect on April 12, 1978.                                                                     Verified at conformity inspection (conformity checklist)

121.343 Flight Recorders
                        Except as provided in paragraphs (b), (c), (d), (e), and (f) of this section, no person
                        may operate a large airplane that is certificated for operations above 25,000 feet
                        altitude or is turbine engine powered unless it is equipped with one or more
   121.343(a)
                        approved flight recorders that record data from which the following may be                                          N/A The ERJ-170 is equipped with a DFDR
                        determined within the ranges, accuracies, and recording intervals specified in
                        Appendix B of this part:
  121.343(a)(1)         Time;                                                                                                               N/A The ERJ-170 is equipped with a DFDR
  121.343(a)(2)         Altitude;                                                                                                           N/A The ERJ-170 is equipped with a DFDR
  121.343(a)(3)         Airspeed;                                                                                                           N/A The ERJ-170 is equipped with a DFDR
  121.343(a)(4)         Vertical acceleration;                                                                                              N/A The ERJ-170 is equipped with a DFDR
  121.343(a)(5)         Heading; and                                                                                                        N/A The ERJ-170 is equipped with a DFDR
  121.343(a)(6)         Time of each radio transmission either to or from air traffic control.                                              N/A The ERJ-170 is equipped with a DFDR
                        No person may operate a large airplane type certificated up to and including
                        September 30, 1969, for operations above 25,000 feet altitude, or a turbine engine
                        powered airplane certificated before the same date, unless it is equipped before May
   121.343(b)           26, 1989 with one or more approved flight recorders that utilize a digital method of                                N/A The ERJ-170 is equipped with a DFDR
                        recording and storing data and a method of readily retrieving that data from the
                        storage medium. The following information must be able to be determined within the
                        ranges, accuracies, and recording intervals specified in Appendix B of this part:

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  121.343(b)(1)         Time;                                                                                                       N/A The ERJ-170 is equipped with a DFDR
  121.343(b)(2)         Altitude;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(b)(3)         Airspeed;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(b)(4)         Vertical acceleration;                                                                                      N/A The ERJ-170 is equipped with a DFDR
  121.343(b)(5)         Heading; and                                                                                                N/A The ERJ-170 is equipped with a DFDR
  121.343(b)(6)         Time of each radio transmission either to or from air traffic control.                                      N/A The ERJ-170 is equipped with a DFDR
                        Except as provided in paragraph (l) of this section, no person may operate an
                        airplane specified in paragraph (b) of this section unless it is equipped, before May
                        26, 1994 with one or more approved flight recorders that utilize a digital method of
   121.343(c)
                        recording and storing data and a method of readily retrieving that data from the                            N/A The ERJ-170 is equipped with a DFDR
                        storage medium. The following information must be able to be determined within the
                        ranges, accuracies and recording intervals specified in Appendix B of this part:
  121.343(c)(1)         Time;                                                                                                       N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(2)         Altitude;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(3)         Airspeed;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(4)         Vertical acceleration;                                                                                      N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(5)         Heading;                                                                                                    N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(6)         Time of each radio transmission either to or from air traffic control;                                      N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(7)         Pitch attitude;                                                                                             N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(8)         Roll attitude;                                                                                              N/A The ERJ-170 is equipped with a DFDR
  121.343(c)(9)         Longitudinal acceleration;                                                                                  N/A The ERJ-170 is equipped with a DFDR
 121.343(c)(10)         Control column or pitch control surface position; and                                                       N/A The ERJ-170 is equipped with a DFDR
 121.343(c)(11)         Thrust of each engine.                                                                                      N/A The ERJ-170 is equipped with a DFDR
                        No person may operate an airplane specified in paragraph (b) of this section that is
                        manufactured after May 26, 1989, as well as airplanes specified in paragraph (a) of
                        this section that have been type certificated after September 30, 1969, unless it is
   121.343(d)           equipped with one or more approved flight recorders that utilize a digital method of                        N/A The ERJ-170 is equipped with a DFDR
                        recording and storing data and a method of readily retrieving that data from the
                        storage medium. The following information must be able to be determined within the
                        ranges, accuracies, and recording intervals specified in Appendix B of this part:
  121.343(d)(1)         Time;                                                                                                       N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(2)         Altitude;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(3)         Airspeed;                                                                                                   N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(4)         Vertical acceleration;                                                                                      N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(5)         Heading;                                                                                                    N/A The ERJ-170 is equipped with a DFDR
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FAR/SRR


  121.343(d)(6)         Time of each radio transmission either to or from air traffic control;                                      N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(7)         Pitch attitude;                                                                                             N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(8)         Roll attitude;                                                                                              N/A The ERJ-170 is equipped with a DFDR
  121.343(d)(9)         Longitudinal acceleration;                                                                                  N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(10)         Pitch trim position;                                                                                        N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(11)         Control column or pitch control surface position;                                                           N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(12)         Control wheel or lateral control surface position;                                                          N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(13)         Rudder pedal or yaw control surface position;                                                               N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(14)         Thrust of each engine;                                                                                      N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(15)         Position of each thrust reverser;                                                                           N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(16)         Trailing edge flap or cockpit flap control position; and                                                    N/A The ERJ-170 is equipped with a DFDR
 121.343(d)(17)         Leading edge flap or cockpit flap control position.                                                         N/A The ERJ-170 is equipped with a DFDR
                        For the purpose of this section, "manufactured" means the point in time at which the
   121.343(d)           airplane inspection acceptance records reflect that the airplane is complete and                            N/A The ERJ-170 is equipped with a DFDR
                        meets the FAA-approved type design data.
                        After October 11, 1991, no person may operate a large airplane equipped with a
                        digital data bus and ARINC 717 digital flight data acquisition unit (DFDAU) or
                        equivalent unless it is equipped with one or more approved flight recorders that
   121.343(e)           utilize a digital method of recording and storing data and a method of readily                              N/A The ERJ-170 is equipped with a DFDR
                        retrieving that data from the storage medium. Any parameters specified in Appendix
                        B of this part that are available on the digital data bus must be recorded within the
                        ranges, accuracies, resolutions, and sampling intervals specified.
                        After October 11, 1991, no person may operate an airplane specified in paragraph
                        (b) of this section that is manufactured after October 11, 1991, nor an airplane
                        specified in paragraph (a) of this section that has been type certificated after
                        September 30, 1969, and manufactured after October 11, 1991, unless it is
   121.343(f)
                        equipped with one or more flight recorders that utilize a digital method of recording                       N/A The ERJ-170 is equipped with a DFDR
                        and storing data and a method of readily retrieving that data from the storage
                        medium. The parameters specified in Appendix B of this part must be recorded
                        within the ranges, accuracies, resolutions, and sampling intervals specified.
                        Whenever a flight recorder required by this section is installed, it must be operated
   121.343(g)           continuously from the instant the airplane begins the takeoff roll until it has                             N/A The ERJ-170 is equipped with a DFDR
                        completed the landing roll at an airport.




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                                                                                                                                                                                 RA
FAR/SRR


                        Except as provided in paragraph (i) of this section, and except for recorded data
                        erased as authorized in this paragraph, each certificate holder shall keep the
                        recorded data prescribed in paragraph (a), (b), (c), or (d) of this section, as
                        appropriate, until the airplane has been operated for at least 25 hours of the
   121.343(h)           operating time specified in § 121.359(a). A total of 1 hour of recorded data may be                            N/A The ERJ-170 is equipped with a DFDR
                        erased for the purpose of testing the flight recorder or the flight recorder system. Any
                        erasure made in accordance with this paragraph must be of the oldest recorded data
                        accumulated at the time of testing. Except as provided in paragraph (i) of this
                        section, no record need be kept more than 60 days.
                        In the event of an accident or occurrence that requires immediate notification of the
                        National Transportation Safety Board under Part 830 of its regulations and that
                        results in termination of the flight, the certificate holder shall remove the recording
   121.343(i)
                        media from the airplane and keep the recorded data required by paragraph (a), (b),                             N/A The ERJ-170 is equipped with a DFDR
                        (c), or (d) of this section, as appropriate, for at least 60 days or for a longer period
                        upon the request of the Board or the Administrator.
                        Each flight recorder required by this section must be installed in accordance with the
                        requirements of § 25.1459 of this chapter in effect on August 31, 1977. The
   121.343(j)
                        correlation required by § 25.1459(c) of this chapter need be established only on one                           N/A The ERJ-170 is equipped with a DFDR
                        airplane of any group of airplanes -
  121.343(j)(1)         That are of the same type;                                                                                     N/A The ERJ-170 is equipped with a DFDR
  121.343(j)(2)         On which the model flight recorder and its installation are the same; and                                      N/A The ERJ-170 is equipped with a DFDR
                        On which there is no difference in the type design with respect to the installation of
                        those first pilot's instruments associated with the flight recorder. The most recent
  121.343(j)(3)
                        instrument calibration, including the recording medium from which this calibration is                          N/A The ERJ-170 is equipped with a DFDR
                        derived, and the recorder correlation must be retained by the certificate holder.
                        Each flight recorder required by this section that records the data specified in
   121.343(k)           paragraph (a), (b), (c), or (d) of this section, as appropriate, must have an approved                         N/A The ERJ-170 is equipped with a DFDR
                        device to assist in locating that recorder under water.
                        No person may operate an airplane specified in paragraph (b) of this section that
                        meets the Stage 2 noise levels of part 36 of this chapter and is subject to § 91.801(c)
                        of this chapter unless it is equipped with one or more approved flight data recorders
                        that utilize a digital method of recording and storing data and a method of readily
   121.343(l)
                        retrieving that data from the storage medium. The information specified in                                     N/A The ERJ-170 is equipped with a DFDR
                        paragraphs (c)(1) through (c)(11) of this section must be able to be determined
                        within the ranges, accuracies and recording intervals specified in appendix B of this
                        part. In addition -
                        This flight data recorder must be installed at the next heavy maintenance check after
                        May 26, 1994, but no later than May 26, 1995. A heavy maintenance check is
  121.343(l)(1)
                        considered to be any time an aircraft is scheduled to be out of service for 4 or more                          N/A The ERJ-170 is equipped with a DFDR
                        days.



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                        By June 23, 1994, each carrier must submit to the FAA Flight Standards Service, Air
                        Transportation Division (AFS-200), documentation listing those airplanes covered
  121.343(l)(2)
                        under this paragraph and evidence that it has ordered a sufficient number of flight                                 N/A The ERJ-170 is equipped with a DFDR
                        data recorders to meet the May 26, 1995, compliance date for all aircraft on that list.
                        After May 26, 1994, any aircraft that is modified to meet Stage 3 noise levels must
  121.343(l)(3)         have the flight data recorder described in paragraph (c) of this section installed                                  N/A The ERJ-170 is equipped with a DFDR
                        before operating under this part.


121.344 Digital Flight Data Recorders for Transport Category Airplanes
                        Except as provided in paragraph (l) of this section, no person may operate under this
                        part a turbine-engine-powered transport category airplane unless it is equipped with
                        one or more approved flight recorders that use a digital method of recording and                              Aircraft conformity inspection Aircraft equipped with
                        storing data and a method of readily retrieving that data from the storage medium.         GMM 6.15.4(26)     Honeywell DFDR that meets the mandatory parameter
   121.344(a)
                        The operational parameters required to be recorded by digital flight data recorders        GMM 6.15.4(72)     requirements of 121.344 See Honeywell report
                        required by this section are as follows: the phrase "when an information source is
                                                                                                                                      number 170EBD047
                        installed" following a parameter indicates that recording of that parameter is not
                        intended to require a change in installed equipment:
  121.344(a)(1)         Time;                                                                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(2)         Pressure altitude;                                                                         GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(3)         Indicated airspeed;                                                                        GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Heading -- primary flight crew reference (if selectable, record discrete, true or
  121.344(a)(4)
                        magnetic);                                                                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(5)         Normal acceleration (Vertical);                                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(6)         Pitch attitude;                                                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(7)         Roll attitude;                                                                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(8)         Manual radio transmitter keying, or CVR/DFDR synchronization reference;                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
  121.344(a)(9)         Thrust/power of each engine -- primary flight crew reference;                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(10)         Autopilot engagement status;                                                               GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(11)         Longitudinal acceleration;                                                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(12)         Pitch control input;                                                                       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(13)         Lateral control input;                                                                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(14)         Rudder pedal input;                                                                        GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(15)         Primary pitch control surface position;                                                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(16)         Primary lateral control surface position;                                                  GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(17)         Primary yaw control surface position;                                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)

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 121.344(a)(18)         Lateral acceleration;                                                                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Pitch trim surface position or parameters of paragraph (a)(82) of this section if
 121.344(a)(19)
                        currently recorded;                                                                  GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Trailing edge flap or cockpit flap control selection (except when parameters of
 121.344(a)(20)
                        paragraph (a)(85) of this section apply);                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Leading edge flap or cockpit flap control selection (except when parameters of
 121.344(a)(21)
                        paragraph (a)(86) of this section apply);                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(22)         Each Thrust reverser position (or equivalent for propeller airplane);                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Ground spoiler position or speed brake selection (except when parameters of
 121.344(a)(23)
                        paragraph (a)(87) of this section apply);                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(24)         Outside or total air temperature;                                                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Automatic Flight Control System (AFCS) modes and engagement status, including
 121.344(a)(25)
                        autothrottle;                                                                        GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(26)         Radio altitude (when an information source is installed);                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(27)         Localizer deviation, MLS Azimuth;                                                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(28)         Glideslope deviation, MLS Elevation;                                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(29)         Marker beacon passage;                                                               GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(30)         Master warning;                                                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(31)         Air/ground sensor (primary airplane system reference nose or main gear);             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(32)         Angle of attack (when information source is installed);                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(33)         Hydraulic pressure low (each system);                                                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(34)         Ground speed (when an information source is installed);                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(35)         Ground proximity warning system;                                                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(36)         Landing gear position or landing gear cockpit control selection;                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(37)         Drift angle (when an information source is installed);                               GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(38)         Wind speed and direction (when an information source is installed);                  GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(39)         Latitude and longitude (when an information source is installed);                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(40)         Stick shaker/pusher (when an information source is installed);                       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(41)         Windshear (when an information source is installed);                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(42)         Throttle/power lever position;                                                       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(43)         Additional engine parameters (as designated in Appendix M of this part);             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(44)         Traffic alert and collision avoidance system;                                        GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(45)         DME 1 and 2 distances;                                                               GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(46)         Nav 1 and 2 selected frequency;                                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
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FAR/SRR


 121.344(a)(47)         Selected barometric setting (when an information source is installed);                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(48)         Selected altitude (when an information source is installed);                          GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(49)         Selected speed (when an information source is installed);                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(50)         Selected mach (when an information source is installed);                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(51)         Selected vertical speed (when an information source is installed);                    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(52)         Selected heading (when an information source is installed);                           GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(53)         Selected flight path (when an information source is installed);                       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(54)         Selected decision height (when an information source is installed);                   GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(55)         EFIS display format;                                                                  GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(56)         Multi-function/engine/alerts display format;                                          GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(57)         Thrust command (when an information source is installed);                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(58)         Thrust target (when an information source is installed);                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(59)         Fuel quantity in CG trim tank (when an information source is installed);              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(60)         Primary Navigation System Reference;                                                  GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(61)         Icing (when an information source is installed);                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(62)         Engine warning each engine vibration (when an information source is installed);       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(63)         Engine warning each engine over temp. (when an information source is installed);      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                        Engine warning each engine oil pressure low (when an information source is
 121.344(a)(64)
                        installed);                                                                           GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(65)         Engine warning each engine over speed (when an information source is installed);      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(66)         Yaw trim surface position;                                                            GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(67)         Roll trim surface position;                                                           GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(68)         Brake pressure (selected system);                                                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(69)         Brake pedal application (left and right);                                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(70)         Yaw or sideslip angle (when an information source is installed);                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(71)         Engine bleed valve position (when an information source is installed);                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(72)         De-icing or anti-icing system selection (when an information source is installed);    GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(73)         Computed center of gravity (when an information source is installed);                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(74)         AC electrical bus status;                                                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(75)         DC electrical bus status;                                                             GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(76)         APU bleed valve position (when an information source is installed);                   GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(77)         Hydraulic pressure (each system);                                                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
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FAR/SRR


 121.344(a)(78)            Loss of cabin pressure;                                                                     GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(79)            Computer failure;                                                                           GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(80)            Heads-up display (when an information source is installed);                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a (81)            Para-visual display (when an information source is installed);                              GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(82)            Cockpit trim control input position -- pitch;                                               GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(83)            Cockpit trim control input position -- roll;                                                GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(84)            Cockpit trim control input position -- yaw;                                                 GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(85)            Trailing edge flap and cockpit flap control position;                                       GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(86)            Leading edge flap and cockpit flap control position;                                        GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(87)            Ground spoiler position and speed brake selection; and                                      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
 121.344(a)(88)            All cockpit flight control input forces (control wheel, control column, rudder pedal).      GMM 6.15.4(26)     Verified at conformity inspection (conformity checklist)
                           For all turbine-engine powered transport category airplanes manufactured on or
   121.344(b)
                           before October 11, 1991, by August 20, 2001.                                                                                         N/A by date
                           For airplanes not equipped as of July 16, 1996, with a flight data acquisition unit
                           (FDAU), the parameters listed in paragraphs (a)(1) through (a)(18) of this section
  121.344(b)(1)
                           must be recorded within the ranges and accuracies specified in Appendix B of this                                                    N/A by date
                           part, and --
                           For airplanes with more than two engines, the parameter described in paragraph
 121.344(b)(1)(i)          (a)(18) is not required unless sufficient capacity is available on the existing recorder                                             N/A by date
                           to record that parameter;
                           Parameters listed in paragraphs (a)(12) through (a)(17) each may be recorded from
 121.344(b)(1)(ii)
                           a single source.                                                                                                                     N/A by date
                           For airplanes that were equipped as of July 16, 1996, with a flight data acquisition
                           unit (FDAU), the parameters listed in paragraphs (a)(1) through (a)(22) of this
  121.344(b)(2)            section must be recorded within the ranges, accuracies, and recording intervals                                                      N/A by date
                           specified in Appendix M of this part. Parameters listed in paragraphs (a)(12) through
                           (a)(17) each may be recorded from a single source.
                           The approved flight recorder required by this section must be installed at the earliest
                           time practicable, but no later than the next heavy maintenance check after August                              The ER-170 is equipped with a DFDR meeting these
  121.344(b)(3)            18, 1999 and no later than August 20, 2001. A heavy maintenance check is                                       requirements when manufactured
                           considered to be any time an airplane is scheduled to be out of service for 4 or more                          See Honeywell report number 170EBD047
                           days and is scheduled to include access to major structural components.
                           For all turbine-engine powered transport category airplanes manufactured on or
   121.344(c)
                           before October 11, 1991 -                                                                                                            N/A by date




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                        That were equipped as of July 16, 1996, with one or more digital data bus(es) and
                        an ARINC 717 digital flight data acquisition unit (DFDAU) or equivalent, the
                        parameters specified in paragraphs (a)(1) through (a)(22) of this section must be
  121.344(c)(1)
                        recorded within the ranges, accuracies, resolutions, and sampling intervals specified                                              N/A by date
                        in Appendix M of this part by August 20, 2001. Parameters listed in paragraphs
                        (a)(12) through (a)(14) each may be recorded from a single source.
                        Commensurate with the capacity of the recording system (DFDAU or equivalent and
                        the DFDR), all additional parameters for which information sources are installed and
  121.344(c)(2)         which are connected to the recording system must be recorded within the ranges,                                                    N/A by date
                        accuracies, resolutions, and sampling intervals specified in Appendix M of this part
                        by August 20, 2001.
                        That were subject to § 121.343(e) of this part, all conditions of § 121.343(e) must
  121.344(c)(3)         continue to be met until compliance with paragraph (c)(1) of this section is                                                       N/A by date
                        accomplished.
                        For all turbine-engine-powered transport category airplanes that were manufactured
   121.344(d)
                        after October 11, 1991 -
                        The parameters listed in paragraph (a)(1) through (a)(34) of this section must be                            Complied with by virtue of FAR Part 121.344(f)
                        recorded within the ranges, accuracies, resolutions, and recording intervals specified
  121.344(d)(1)
                        in Appendix M of this part by August 20, 2001. Parameters listed in paragraphs            GMM 6.15.4(26)
                        (a)(12) through (a)(14) each may be recorded from a single source.                                           Verified at conformity inspection (conformity checklist)
                        Commensurate with the capacity of the recording system, all additional parameters                            Complied with by virtue of FAR Part 121.344(f)
                        for which information sources are installed and which are connected to the recording
  121.344(d)(2)
                        system must be recorded within the ranges, accuracies, resolutions, and sampling          GMM 6.15.4(26)
                        intervals specified in Appendix M of this part by August 20, 2001.                                           Verified at conformity inspection (conformity checklist)
                                                                                                                                     Complied with by virtue of FAR Part 121.344(f)
                        For all turbine-engine-powered transport category airplanes that are manufactured
   121.344(e)
                        after August 18, 2000 -                                                                   GMM 6.15.4(26)
                                                                                                                                     Verified at conformity inspection (conformity checklist)
                        The parameters listed in paragraph (a)(1) through (57) of this section must be                               Complied with by virtue of FAR Part 121.344(f)
  121.344(e)(1)         recorded within the ranges, accuracies, resolutions, and recording intervals specified    GMM 6.15.4(26)
                        in Appendix M of this part.                                                                                  Verified at conformity inspection (conformity checklist)
                        Commensurate with the capacity of the recording system, all additional parameters                            Complied with by virtue of FAR Part 121.344(f)
                        for which information sources are installed and which are connected to the recording
  121.344(e)(2)
                        system, must be recorded within the ranges, accuracies, resolutions, and sampling         GMM 6.15.4(26)
                        intervals specified in Appendix M of this part.                                                              Verified at conformity inspection (conformity checklist)
                                                                                                                                     Aircraft equipped with Honeywell DFDR that meets the
                        For all turbine-engine-powered transport category airplanes that are manufactured                            mandatory parameter requirements of 121.344 See
                        after August 19, 2002 the parameters listed in paragraph (a)(1) through (a)(88) of
   121.344(f)
                        this section must be recorded within the ranges, accuracies, resolutions, and             GMM 6.15.4(26)     Honeywell report number 170EBD047
                        recording intervals specified in Appendix M of this part.
                                                                                                                                     Verified at conformity inspection (conformity checklist)

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                                                                                                                                                                                                    RA
FAR/SRR


                        Whenever a flight data recorder required by this section is installed, it must be                                FDR system records data from the when the engines
   121.344(g)           operated continuously from the instant the airplane begins its takeoff roll until it has   AMM I chapter 31.31   are started or the aircraft is airborne as shown by the
                        completed its landing roll.                                                                                      weight on wheels switches
                        Except as provided in paragraph (i) of this section, and except for recorded data
                        erased as authorized in this paragraph, each certificate holder shall keep the
                        recorded data prescribed by this section, as appropriate, until the airplane has been
                        operated for at least 25 hours of the operating time specified in § 121.359(a) of this
                                                                                                                                         TransGlobal Airlines will keep a minimum of 25 hours
   121.344(h)           part. A total of 1 hour of recorded data may be erased for the purpose of testing the        GMM 6.13.1.1A
                        flight recorder or the flight recorder system. Any erasure made in accordance with                               of recorded data
                        this paragraph must be of the oldest recorded data accumulated at the time of
                        testing. Except as provided in paragraph (i) of this section, no record need be kept
                        more than 60 days.
                        In the event of an accident or occurrence that requires immediate notification of the
                        National Transportation Safety Board under 49 CFR 830 of its regulations and that                                In the event of an accident, the NTSB is notified
                        results in termination of the flight, the certificate holder shall remove the recorder
   121.344(i)
                        from the airplane and keep the recorder data prescribed by this section, as                    GMM 6.13.7
                                                                                                                                         The DFDR is stored for a minimum of 60 days or
                        appropriate, for at least 60 days or for a longer period upon the request of the Board
                                                                                                                                         longer if directed by the FAA or the NTSB
                        or the Administrator.
                        Each flight data recorder system required by this section must be installed in
                        accordance with the requirements of § 25.1459 (a), (b), (d), and (e) of this chapter. A
                        correlation must be established between the values recorded by the flight data                                   TransGlobal Airlines will generate a single correlation
                        recorder and the corresponding values being measured. The correlation must
                                                                                                                                         report of the DFDR data and the corresponding
   121.344(j)           contain a sufficient number of correlation points to accurately establish the                  GMM 6.13.5
                        conversion from the recorded values to engineering units or discrete state over the                              values. Complied with by virtue of certification Part
                        full operating range of the parameter. Except for airplanes having separate altitude                             25.1459
                        and airspeed sensors that are an integral part of the flight data recorder system, a
                        single correlation may be established for any group of airplanes -
                                                                                                                                         All ERJ-170 aircraft are considered to be the same
  121.344(j)(1)         That are of the same type;                                                                     GMM 6.13.5
                                                                                                                                         type
  121.344(j)(2)         On which the flight recorder system and its installation are the same; and                     GMM 6.13.5        All ERJ-170 aircraft have the same installation
                        On which there is no difference in the type design with respect to the installation of
                        those sensors associated with the flight data recorder system. Documentation
  121.344(j)(3)
                        sufficient to convert recorded data into the engineering units and discrete values             GMM 6.13.5        The type design for each aircraft is the same
                        specified in the applicable appendix must be maintained by the certificate holder.
                                                                                                                                         Verified at conformity inspection (conformity checklist)
                        Each flight data recorder required by this section must have an approved device to           GMM 6.15.4(73)
   121.344(k)
                        assist in locating that recorder under water.                                              AMM 31-31-00 page 6
                                                                                                                                         AMM gives the location of the locating device
                        The following airplanes that were manufactured before August 18, 1997 need not
   121.344(l)           comply with this section, but must continue to comply with applicable paragraphs of
                        § 121.343 of this chapter, as appropriate:

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                        Airplanes that meet the State 2 noise levels of part 36 of this chapter and are subject
                        to § 91.801(c) of this chapter, until January 1, 2000. On and after January 1, 2000,
  121.344(l)(1)         any Stage 2 airplane otherwise allowed to be operated under Part 91 of this chapter             TCDS          N/A The ERJ-170 meets stage 3 noise requirements
                        must comply with the applicable flight data recorder requirements of this section for
                        that airplane.
                        {New-2003-17 (l)(2) revised July 18, 2003, effective August 18, 2003}
                        British Aerospace 1-11, General Dynamics Convair 580, General Dynamics Convair
                        600, General Dynamics Convair 640, deHavilland Aircraft Company Ltd. DHC-7,
                        Fairchild Industries FH 227, Fokker F-27 (except Mark 50), F-28 Mark 1000 and
                        Mark 4000, Gulfstream Aerospace G-159, Jetstream 4100 Series, Lockheed Aircraft
  121.344(l)(2)         Corporation Electra 10-A, Lockheed Aircraft Corporation Electra 10-B, Lockheed                                               N/A by aircraft model
                        Aircraft Corporation Electra 10-E, Lockheed Aircraft Corporation Electra L-188,
                        Lockheed Martin Model 382 (L-100) Hercules, Maryland Air Industries, Inc. F27,
                        Mitsubishi Heavy Industries, Ltd. YS-11, Short Bros. Limited SD3-30, Short Bros.
                        Limited SD3-60.
                        {Beginning of old text revised July 18, 2003, effective August 18, 2003}
                        General Dynamics Convair 580, General Dynamics Convair 600, General Dynamics
                        Convair 640, deHavilland Aircraft Company Ltd. DHC-7, Fairchild Industries FH 227,
                        Fokker F-27 (except Mark 50), F-28 Mark 1000 and Mark 4000, Gulfstream
                        Aerospace G-159, Lockheed Aircraft Corporation Electra 10-A, Lockheed Aircraft
  121.344(l)(2)
                        Corporation Electra 10-B, Lockheed Aircraft Corporation Electra 10-E, Lockheed                                               N/A by aircraft model
                        Aircraft Corporation Electra L-188, Maryland Air Industries, Inc. F27, Mitsubishi
                        Heavy Industries, Ltd. YS-11, Short Bros. Limited SD3-30, Short Bros. Limited SD3-
                        60.


121.344a Digital Flight Data Recorders for 10-19 Seat Airplanes
                        Except as provided in paragraph (f) of this section, no person may operate under this
                        part a turbine-engine-powered airplane having a passenger seating configuration,
                        excluding any required crewmember seat, of 10 to 19 seats, that was brought onto
                        the U.S. register after, or was registered outside the United States and added to the
                        operator's U.S. operations specifications after, October 11, 1991, unless it is
  121.344a(a)           equipped with one or more approved flight recorders that use a digital method of                                          N/A by seating configuration
                        recording and storing data and a method of readily retrieving that data from the
                        storage medium. On or before August 20, 2001, airplanes brought onto the U.S.
                        register after October 11, 1991, must comply with either the requirements in this
                        section or the applicable paragraphs in § 135.152 of this chapter. In addition, by
                        August 20, 2001.
                        The parameters listed in §§ 121.344(a)(1) through 121.344(a)(18) of this part must
 121.344a(a)(1)         be recorded with the ranges, accuracies, and resolutions specified in Appendix B of                                       N/A by seating configuration
                        part 135 of this chapter, except that -


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                            Either the parameter listed in § 121.344 (a)(12) or (a)(15) of this part must be
                            recorded; either the parameters listed in § 121.344(a)(13) or (a)(16) of this part must
 121.344a(a)(1)(i)
                            be recorded; and either the parameter listed in § 121.344(a)(14) or (a)(17) of this                              N/A by seating configuration
                            part must be recorded.
                            For airplanes with more than two engines, the parameter described in §
 121.344a(a)(1)(ii)         121.344(a)(18) of this part must also be recorded if sufficient capacity is available on                         N/A by seating configuration
                            the existing recorder to record that parameter;
                            Parameters listed in §§ 121.344(a)(12) through 121.344(a)(17) of this part each may
121.344a(a)(1)(iii)
                            be recorded from a single source;                                                                                N/A by seating configuration
                            Any parameter for which no value is contained in Appendix B of part 135 of this
121.344a(a)(1)(iv)          chapter must be recorded within the ranges, accuracies, and resolutions specified in                             N/A by seating configuration
                            Appendix M of this part.
                            Commensurate with the capacity of the recording system (FDAU or equivalent and
                            the DFDR), the parameters listed in §§ 121.344(a)(19) through 121.344(a)(22) of this
  121.344a(a)(2)
                            part also must be recorded within the ranges, accuracies, resolutions, and recording                             N/A by seating configuration
                            intervals specified in Appendix B of part 135 of this chapter.
                            The approved flight recorder required by this section must be installed as soon as
                            practicable, but no later than the next heavy maintenance check or equivalent after
  121.344a(a)(3)            August 18, 1999. A heavy maintenance check is considered to be any time an                                       N/A by seating configuration
                            airplane is scheduled to be out of service for 4 more days and is scheduled to
                            include access to major structural components.
                            For a turbine-engine-powered airplanes having a passenger seating configuration,
   121.344a(b)              excluding any required crewmember seat, of 10 to 19 seats, that are manufactured                                 N/A by seating configuration
                            after August 18, 2000.
                            The parameters listed in §§ 121.344(a)(1) through 121.344(a)(57) of this part, must
  121.344a(b)(1)            be recorded within the ranges, accuracies, resolutions, and recording intervals                                  N/A by seating configuration
                            specified in Appendix M of this part.
                            Commensurate with the capacity of the recording system, all additional parameters
                            listed in § 121.344(a) of this part for which information sources are installed and
  121.344a(b)(2)            which are connected to the recording system, must be recorded within the ranges,                                 N/A by seating configuration
                            accuracies, resolutions, and sampling intervals specified in Appendix M of this part
                            by August 20, 2001.
                            For all turbine-engine-powered airplanes having a passenger seating configuration,
                            excluding any required crewmember seats, of 10 to 19 seats, that are manufactured
   121.344a(c)              after August 19, 2002, the parameters listed in § 121.344(a)(1) through (a)(88) of                               N/A by seating configuration
                            this part must be recorded within the ranges, accuracies, resolutions, and recording
                            intervals specified in Appendix M of this part.




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                        Each flight data recorder system required by this section must be installed in
                        accordance with the requirements of § 23.1459 (a), (b), (d), and (e) of this chapter. A
                        correlation must be established between the values recorded by the flight data
                        recorder and the corresponding values being measured. The correlation must
  121.344a(d)
                        contain a sufficient number of correlation points to accurately establish the                                              N/A by seating configuration
                        conversion from the recorded values to engineering units or discrete state over the
                        full operating range of the parameter. A single correlation may be established for any
                        group of airplanes -
 121.344a(d)(1)         That are of the same type;                                                                                                 N/A by seating configuration
 121.344a(d)(2)         On which the flight recorder system and its installation are the same; and                                                 N/A by seating configuration
                        On which there is no difference in the type design with respect to the installation of
 121.344a(d)(3)         those sensors associated with the flight data recorder system. Correlation                                                 N/A by seating configuration
                        documentation must be maintained by the certificate holder.
                        All airplanes subject to this section are also subject to the requirements and
  121.344a(e)
                        exceptions stated in §§ 121.344(g) through 121.344(k) of this part.                                                        N/A by seating configuration
                        {New-2003-17 (f) revised July 18, 2003, effective August 18, 2003}                                                         N/A by seating configuration
                        For airplanes that were manufactured before August 18, 1997, the following airplane
                        types need not comply with this section, but must continue to comply with applicable
                        paragraphs of § 135.152 of this chapter, as appropriate: Beech Aircraft-99 Series,
  121.344a(f)
                        Beech Aircraft 1300, Beech Aircraft 1900C, Construcciones Aeronauticas, S.A.                                               N/A by seating configuration
                        (CASA) C-212, deHavilland DHC-6, Dornier 228, HS-748, Embraer EMB 110,
                        Jetstream 3101, Jetstream 3201, Fairchild Aircraft SA-226, Fairchild Metro SA-227.
                        {Beginning of old text revised July 18, 2003, effective August 18, 2003}                                                   N/A by seating configuration
                        For airplanes that were manufactured before August 18, 1997, the following airplane
                        types need not comply with this section, but must continue to comply with applicable
                        paragraphs of § 135.152 of this chapter, as appropriate: Beech Aircraft-99 Series,
  121.344a(f)
                        Beech Aircraft 1300, Beech Aircraft 1900C, Construcciones Aeronauticas, S.A.                                               N/A by seating configuration
                        (CASA) C-212, deHavilland DHC-6, Dornier 228, HS-748, Embraer EMB 110,
                        Jetstream 3101, Jetstream 3201, Fairchild Aircraft SA-226.


121.345 Radio Equipment
                                                                                                                                      TransGlobal Airlines verifies that each aircraft has the
                        No person may operate an airplane unless it is equipped with radio equipment                                  required radio equipment by performing an aircraft
   121.345(a)
                        required for the kind of operation being conducted.                                          GMM 6.15.4
                                                                                                                                      conformity inspection prior to the aircraft being added
                                                                                                                                      to the aircraft listing Ops Spec
                        Where two independent (separate and complete) radio systems are required by §§
                        121.347 and 121.349, each system must have an independent antenna installation
   121.345(b)
                        except that, where rigidly supported nonwire antennas or other antenna installations       GMM 6.15.4(117)    Verified at conformity inspection (conformity checklist)
                        of equivalent reliability are used, only one antenna is required.

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                            ATC transponder equipment installed within the time periods indicated below must
    121.345(c)
                            meet the performance and environmental requirements of the following TSOs:                   GMM 6.15.4(117)    Verified at conformity inspection (conformity checklist)
  121.345(c)(1)             Through January 1, 1992:                                                                                                        N/A by applicable date
                            Any class of TSO-C74b or any class of TSO-C74c as appropriate, provided that the
 121.345(c)(1)(i)
                            equipment was manufactured before January 1, 1990; or                                                                           N/A by applicable date
 121.345(c)(1)(ii)          The appropriate class of TSO-C112 (Mode S).                                                                                     N/A by applicable date
                            After January 1, 1992: The appropriate class of TSO-C112 (Mode S). For purposes
 121.345(c)(2)(ii)
                            of paragraph (c) (2) of this section, "installation" does not include -                      GMM 6.15.4(121)    Verified at conformity inspection (conformity checklist)
                            Temporary installation of TSO-C74b or TSO-C74c substitute equipment, as
 121.345(c)(2)(i)
                            appropriate, during maintenance of the permanent equipment;                                                             N/A Equipment is permanently installed
 121.345(c)(2)(ii)          Reinstallation of equipment after temporary removal for maintenance; or                                                 N/A Equipment is permanently installed
                            For fleet operations, installation of equipment in a fleet aircraft after removal of the
 121.345(c)(2)(iii)
                            equipment for maintenance from another aircraft in the same operator's fleet.                                           N/A Equipment is permanently installed


121.347 Radio Equipment for Operations Under VFR Over Routes Navigated by Pilotage
                                                                                                                                            Aircraft is equipped with the required radio equipment
                            No person may operate an airplane under VFR over routes that can be navigated by
                                                                                                                         GMM 6.15.4(117)    by virtue of FAR Part 121.345
    121.347(a)              pilotage, unless it is equipped with the radio equipment necessary under normal
                            operating conditions to fulfill the following:                                               GMM 6.15.4(119)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
                            Communicate with at least one appropriate ground station from any point on the               GMM 6.15.4(117)
  121.347(a)(1)
                            route.                                                                                                          Verified at conformity inspection (conformity checklist)
                                                                                                                         GMM 6.15.4(119)
                            Communicate with appropriate traffic control facilities from any point within the lateral
                                                                                                                         GMM 6.15.4(117)
  121.347(a)(2)             boundaries of the surface areas of Class B, Class C, Class D, or Class E airspace                               Verified at conformity inspection (conformity checklist)
                            designated for an airport in which flights are intended.                                     GMM 6.15.4(119)
                            Receive meteorological information from any point enroute by either of two
                                                                                                                         GMM 6.15.4(117)
  121.347(a)(3)             independent systems. One of the means provided to comply with this subparagraph                                 Verified at conformity inspection (conformity checklist)
                            may be used to comply with paragraphs (a)(1) and (2) of this section.                        GMM 6.15.4(119)
                            No person may operate an airplane at night under VFR over routes than can be
                            navigated by pilotage unless that airplane is equipped with the radio equipment
                                                                                                                         GMM 6.15.4(117)
    121.347(b)              necessary under normal operating conditions to fulfill the functions specified in                               Verified at conformity inspection (conformity checklist)
                            paragraph (a) of this section and to receive radio navigational signals applicable to        GMM 6.15.4(119)
                            the route flown, except that a marker beacon receiver or ILS receiver is not required.




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121.349 Radio Equipment for Operations Under VFR Over Routes Not Navigated by Pilotage or for Operations Under IFR or
Over the Top
                       No person may operate an airplane under VFR over routes that cannot be navigated
                       by pilotage or for operations conducted under IFR or over the top, unless the
                       airplane is equipped with that radio equipment necessary under normal operating                                   Aircraft is equipped with the required radio equipment
                       conditions to fulfill the functions specified in § 121.347(a) and to receive satisfactorily
                                                                                                                      GMM 6.15.4(117)    by virtue of FAR Part 121.345
   121.349(a)          by either of two independent systems radio navigational signals from all primary
                       enroute and approach navigational facilities intended to be used. However, only one            GMM 6.15.4(119)
                       marker beacon receiver providing visual and aural signals and one ILS receiver need                               Verified at conformity inspection (conformity checklist)
                       be provided. Equipment provided to receive signals enroute may be used to receive
                       signals on approach, if it is capable of receiving both signals.
                       In the case of operation over routes on which navigation is based on low frequency
                       radio range or automatic direction finding, only one low frequency radio range or
                       ADF receiver need be installed if the airplane is equipped with two VOR receivers,
                                                                                                                      GMM 6.15.4(117)
   121.349(b)          and VOR navigational aids are so located and the airplane is so fueled that, in the                               Verified at conformity inspection (conformity checklist)
                       case of failure of the low frequency radio range receiver or ADF receiver, the flight          GMM 6.15.4(119)
                       may proceed safely to a suitable airport, by means of VOR aids, and complete an
                       instrument approach by use of the remaining airplane radio system.
                       Whenever VOR navigational receivers are required by paragraph (a) or (b) of this
                       section, at least one approved distance measuring equipment unit (DME) capable of
                                                                                                                      GMM 6.15.4(117)
   121.349(c)          receiving and indicating distance information from VORTAC facilities must be                                      Verified at conformity inspection (conformity checklist)
                       installed on each airplane when operated in the 50 states and the District of                  GMM 6.15.4(119)
                       Columbia.
                       If the distance measuring equipment (DME) becomes inoperative enroute, the pilot               GMM 6.15.4(117)
   121.349(d)
                       shall notify ATC of that failure as soon as it occurs.                                                            Verified at conformity inspection (conformity checklist)
                                                                                                                      GMM 6.15.4(119)
                       No person may operate an airplane having a passenger seat configuration of 10 to
                       30 seats, excluding each crewmember seat, and a payload of 7,500 pounds or less
                       under IFR or in extended overwater operations unless it has, in addition to any other
                                                                                                                      GMM 6.15.4(117)
   121.349(e)          required radio communications and navigational equipment appropriate to the                                       Verified at conformity inspection (conformity checklist)
                       facilities to be used which are capable of transmitting to, and receiving from, at any         GMM 6.15.4(119)
                       place on the route to be flown, at least one ground facility, two microphones, and two
                       headsets or one headset and one speaker.


121.351 Radio and Navigation Equipment for Extended Overwater Operations and for Certain Other Operations
                       Except as provided in paragraph (c) of this section, no person may conduct an
                       extended overwater operation unless the airplane is equipped with the radio
                       communication equipment necessary to comply with § 121.349, an independent                                          N/A TransGlobal Airlines will not conduct extended
   121.351(a)
                       system that complies with § 121.347(a)(1), and two long-range navigation systems                                                 overwater operations
                       when VOR or ADF radio navigation equipment is unusable along a portion of the
                       route.

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                        No certificate holder conducting a flag or supplemental operation or a domestic
                        operation within the State of Alaska may conduct an operation without the equipment
   121.351(b)           specified in paragraph (a) of this section, if the Administrator finds that equipment to                              N/A by Area of Operations
                        be necessary for search and rescue operations because of the nature of the terrain
                        to be flown over.
                        Notwithstanding the requirements of paragraph (a) of this section, installation and
                        use of a single LRNS and a single LRCS may be authorized by the Administrator
   121.351(c)           and approved in the certificate holder's operations specifications for operations and                                 N/A by Area of Operations
                        routes in certain geographic areas. The following are among the operational factors
                        the Administrator may consider in granting an authorization:
                        The ability of the flightcrew to reliably fix the position of the airplane within the
  121.351(c)(1)
                        degree of accuracy required by ATC,                                                                                   N/A by Area of Operations
  121.351(c)(2)         The length of the route being flown, and                                                                              N/A by Area of Operations
  121.351(c)(3)         The duration of the very high frequency communications gap.                                                           N/A by Area of Operations

121.353 Emergency Equipment for Operations Over Uninhabited Terrain Areas: Flag, Supplemental, and Certain Domestic
Operations
                        Unless the airplane has the following equipment, no person may conduct a flag or
                        supplemental operation or a domestic operation within the States of Alaska or
   § 121.353            Hawaii over an uninhabited area or any other area that (in its operations                                             N/A by Area of Operations
                        specifications) the Administrator specifies required equipment for search and rescue
                        in case of an emergency:
   121.353(a)           Suitable pyrotechnic signaling devices.                                                                               N/A by Area of Operations
                        An approved survival type emergency locator transmitter. Batteries used in this
                        transmitter must be replaced (or recharged, if the battery is rechargeable) when the
                        transmitter has been in use for more than 1 cumulative hour, or when 50 percent of
                        their useful life (or for rechargeable batteries, 50 percent of their useful life of charge)
   121.353(b)           has expired, as established by the transmitter manufacturer under its approval. The                                   N/A by Area of Operations
                        new expiration date for replacing (or recharging) the battery must be legibly marked
                        on the outside of the transmitter. The battery useful life (or useful life of charge)
                        requirements of this paragraph do not apply to batteries (such as water activated
                        batteries) that are essentially unaffected during probable storage intervals.
                        Enough survival kits, appropriately equipped for the route to be flown for the number
   121.353(c)
                        of occupants of the airplane.                                                                                         N/A by Area of Operations




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121.354 Terrain Awareness and Warning System
                        Airplanes manufactured after March 29, 2002. No person may operate a turbine-                              TransGlobal Airlines verifies that each aircraft has the
                        powered airplane unless that airplane is equipped with an approved terrain
                                                                                                                                   required terrain awareness and warning system by
   121.354(a)           awareness and warning system that meets the requirements for Class A equipment            GMM 6.15.4
                        in Technical Standard Order (TSO)-C151. The airplane must also include an                                  performing an aircraft conformity inspection prior to the
                        approved terrain situational awareness display.                                                            aircraft being added to the aircraft listing Ops Spec
                        Airplanes manufactured on or before March 29, 2002. No person may operate a
                        turbine-powered airplane after March 29, 2005, unless that airplane is equipped with
   121.354(b)           an approved terrain awareness and warning system that meets the requirements for                                        N/A by type certification date
                        Class A equipment in Technical Standard Order (TSO)-C151. The airplane must
                        also include an approved terrain situational awareness display.
                        (Approved by the Office of Management and Budget under control number 2120-
                        0631)
                        Airplane Flight Manual. The Airplane Flight Manual shall contain appropriate
   121.354(c)
                        procedures for--
                                                                                                                                   AOM1 Section 4 contains guidance on using the
  121.354(c)(1)         The use of the terrain awareness and warning system; and                                  170-SOP 4.5
                                                                                                                                   TAWS (EGPWS)
                        Proper flight crew reaction in response to the terrain awareness and warning system                        AOM1 Section 4.5 contains flight crew reactions in
  121.354(c)(2)
                        audio and visual warnings.                                                              170-SOP 4.5.3.1
                                                                                                                                   response to the TAWS (EGPWS) system warnings

121.355 Equipment for Operations on Which Specialized Means of Navigation are Used
   121.355(a)           No certificate holder may conduct an operation -
                        Using Doppler Radar or an Inertial Navigation System outside the 48 contiguous
  121.355(a)(1)         States and the District of Columbia, unless such systems have been approved in                                           N/A by Area of Operations
                        accordance with Appendix G to this part; or
                        Using Doppler Radar or an Inertial Navigation System within the 48 contiguous
                        States and the District of Columbia, or any other specialized means of navigation,
  121.355(a)(2)
                        unless it shows that an adequate airborne system is provided for the specialized                                     N/A This equipment is not installed
                        navigation authorized for the particular operation.
                        Notwithstanding paragraph (a) of this section, Doppler Radar and Inertial Navigation
                        Systems, and the training programs, maintenance programs, relevant operations
   121.355(b)           manual material, and minimum equipment lists prepared in accordance therewith,                                       N/A This equipment is not installed
                        approved before April 29, 1972, are not required to be approved in accordance with
                        that paragraph.




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121.356 (existing)                    Collision Avoidance System
                           Unless otherwise authorized by the Administrator, each certificate holder operating a                              TransGlobal Airlines verifies that each aircraft has the
                           large airplane that has a passenger seating configuration, excluding any pilot seat, of
                                                                                                                                              required collision avoidance system by performing an
   121.356(a)              more than 30 seats, shall equip its airplanes with an approved TCAS II traffic alert            GMM 6.15.4(120)
                           and collision avoidance system and the appropriate class of Mode S transponder                                     aircraft conformity inspection prior to the aircraft being
                           according to the following schedule:                                                                               added to the aircraft listing Ops Spec
                             Date                               Required equipage
                             December 30, 1990                  At least 20% of all covered
                                                                airplanes, if the certificate
   121.356(a)                                                   holder operates more than 30
                                                                such airplanes.
                             December 30, 1991                  50% of all covered airplanes.
                             December 30, 1993                  100% of all covered airplanes.
                           Unless otherwise authorized by the Administrator, after December 31, 1995, no
                           person may operate a passenger or combination cargo/passenger (combi) airplane
                           that has a passenger seat configuration, excluding any pilot seat, of 10 to 30 seats
   121.356(b)
                           unless it is equipped with an approved traffic alert and collision avoidance system. If                                          N/A by seating configuration
                           a TCAS II system is installed, it must be capable of coordinating with TCAS units
                           that meet TSO C-119.
                           The appropriate manuals required by § 121.131 shall contain the following
   121.356(c)              information on the TCAS II System or TCAS I System, as appropriate, as required by
                           this section:
  121.356(c)(1)            Appropriate procedures for -
                                                                                                                                              The AOM contains procedures to operate the TCAS
 121.356(c)(1)(i)          The operation of the equipment; and                                                              170-SOP 4.6.1
                                                                                                                                              system
                                                                                                                                              AOM1 Section 4 contains proper flight crew actions for
                                                                                                                                              TA and RA advisories
                                                                                                                            170-SOP 4.6.3
 121.356(c)(1)(ii)         Proper flightcrew action with respect to the equipment.                                          170-SOP 4.6.4
                                                                                                                                              The FOM contains TransGlobal Airlines general policy
                                                                                                                             FOM 13.3.1
                                                                                                                                              on the use of TCAS and the reactions flight crews
                                                                                                                                              should pursue with respect to TCAS warnings
                           An outline of all input sources that must be operative for the TCAS to function
  121.356(c)(2)
                           properly.                                                                                        170-SOP 4.6.2
                           Effective May 1, 2003, if TCAS II is installed in an airplane for the first time after April
   121.356(d)              30, 2003, and before January 1, 2005, no person may operate that airplane without               GMM 6.15.4(120)    Verified at conformity inspection (conformity checklist)
                           TCAS II that meets TSO C-119b (version 7.0), or a later version.




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121.356 (new as of 1/1/05)                       Collision Avoidance System
                                                                                                                         TransGlobal Airlines verifies that each aircraft has the
                       Effective January 1, 2005, any airplane you operate under this part must be                       required collision avoidance system by performing an
   § 121.356
                       equipped and operated according to the following table:                          GMM 6.15.4
                                                                                                                         aircraft conformity inspection prior to the aircraft being
                                                                                                                         added to the aircraft listing Ops Spec




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                       Collision Avoidance Systems
                       If you operate any--            Then you must operate that
                                                       airplane with--
                       121.356(a) Turbine-powered      121.356(a)(1) An appropriate
                       airplane of more than 33,000    class of Mode S transponder        GMM 6.15.4(120)    Verified at conformity inspection (conformity checklist)
                       pounds maximum certificated     that meets Technical
                       takeoff weight.                 Standard Order (TSO) C-112,
                                                       or a later version, and one of
                                                       the following approved units:
                                                       121.356(a)(1)(i) TCAS II that
                                                       meets TSO C-119b (version
                                                       7.0), or takeoff weight a later
                                                       version.
                                                       121.356(a)(1)(ii) TCAS II that
                                                       meets TSO C-119a (version
                                                       6.04A Enhanced) that was
                                                       installed in that airplane
                                                       before May 1, 2003. If that
                                                       TCAS II version 6.04A
                                                       Enhanced no longer can be
                                                       repaired to TSO C-119a
                                                       standards, it must be replaced
                                                       with a TCAS II that meets
                                                       TSO C-119b (version 7.0), or
                                                       a later version.
                                                       121.356(a)(1)(iii) A collision
                                                       avoidance system equivalent
                                                       to TSO C-119b (version 7.0),
                                                       or a later version, capable of
                                                       coordinating with units that
    121.356
                                                       meet TSO C-119a (version
                                                       6.04A Enhanced), or a later
                                                       version.
                       121.356(b) Passenger or         121.356(b)(1) TCAS I that
                       combination cargo/passenger     meets TSO C-118, or a later
                       (combi) airplane that has a     version, or
                       passenger seat configuration
                       of 10-30 seats.
                                                       121.356(b)(2) A collision
                                                       avoidance system equivalent
                                                       to has a TSO C-118, or a later
                                                       version, or
                                                       121.356(b)(3) A collision
                                                       avoidance system and Mode
                                                       S transponder that meet
Page 97 of 115                                         paragraph (a)(1) of this
                                                       section.
                       121.356(c) Piston-powered       121.356(c)(1) TCAS I that
                       airplane of more than 33,000    meets TSO C-118, or a later
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121.357 Airborne Weather Radar Equipment Requirements
                                                                                                                                         TransGlobal Airlines verifies that each aircraft has the
                        No person may operate any transport category airplane (except C-46 type airplanes)
                                                                                                                                         required airborne weather radar equipment by
   121.357(a)           or a nontransport category airplane certificated after December 31, 1964, unless              GMM 6.15.4(122)
                        approved airborne weather radar equipment has been installed in the airplane.                                    performing an aircraft conformity inspection prior to the
                                                                                                                                         aircraft being added to the aircraft listing Ops Spec
   121.357(b)            [Reserved]
                        Each person operating an airplane required to have approved airborne weather
   121.357(c)           radar equipment installed shall, when using it under this part, operate it in
                        accordance with the following:
                        Dispatch. No person may dispatch an airplane (or begin the flight of an airplane in
                        the case of a certificate holder, that does not use a dispatch system) under IFR or                              Radar is required anytime a flight will be conducted
                        night VFR conditions when current weather reports indicate that thunderstorms, or               DPM 24.2.1A      under IMC or night VMC conditions, and there is
  121.357(c)(1)
                        other potentially hazardous weather conditions that can be detected with airborne               FOM 13.4.3       forecasted or reported convective activity along the
                        weather radar, may reasonably be expected along the route to be flown, unless the
                                                                                                                                         intended route of flight
                        airborne weather radar equipment is in satisfactory operating condition.
                                                                                                                                         If the radar fails after dispatch, advise ATC and SOC
                                                                                                                                         of the failure and obtain the latest convective weather
                        If the airborne weather radar becomes inoperative enroute, the airplane must be                                  information from appropriate sources
                                                                                                                        DPM 24.2.1B
  121.357(c)(2)         operated in accordance with the approved instructions and procedures specified in
                        the operations manual for such an event.                                                        FOM 13.4.5B
                                                                                                                                         The flight may continue provided an alternate route
                                                                                                                                         clear of thunderstorm or hazardous weather conditions
                                                                                                                                         can be flown
                        This section does not apply to airplanes used solely within the State of Hawaii or
   121.357(d)           within the State of Alaska and that part of Canada west of longitude 130° W,                                                   N/A by Area of Operations
                        between latitude 70° N, and latitude 53° N, or during any training, test, or ferry flight.
                        Notwithstanding any other provision of this chapter, an alternate electrical power
   121.357(e)
                        supply is not required for airborne weather radar equipment.


121.358 Low Altitude Windshear System Equipment Requirements
                        Airplanes manufactured after January 2, 1991. No person may operate a turbine                                    TransGlobal Airlines verifies that each aircraft has the
                        powered airplane manufactured after January 2, 1991, unless it is equipped with
                                                                                                                                         required low altitude windshear system equipment by
   121.358(a)           either an approved airborne windshear warning and flight guidance system, an                  GMM 6.15.4(123)
                        approved airborne detection and avoidance system, or an approved combination of                                  performing an aircraft conformity inspection prior to the
                        these systems.                                                                                                   aircraft being added to the aircraft listing Ops Spec
                        Airplanes manufactured before January 3, 1991. Except as provided in paragraph (c)
                        of this section, after January 2, 1991, no person may operate a turbine powered
   121.358(b)
                        airplane manufactured before January 3, 1991 unless it meets one of the following                                             N/A by type certification date
                        requirements as applicable.
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                            The makes/models/series listed below must be equipped with either an approved
  121.358(b)(1)             airborne windshear warning and flight guidance system, an approved airborne
                            detection and avoidance system, or an approved combination of these systems:
 121.358(b)(1)(i)           A-300-600;                                                                                                            N/A by aircraft model
 121.358(b)(1)(ii)          A-310 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(iii)         A-320 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(iv)          B-737-300, 400, and 500 series;                                                                                       N/A by aircraft model
 121.358(b)(1)(v)           B-747-400;                                                                                                            N/A by aircraft model
 121.358(b)(1)(vi)          B-757 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(vii)         B-767 - all series;                                                                                                   N/A by aircraft model
121.358(b)(1)(viii)         F-100 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(v)           B-747-400;                                                                                                            N/A by aircraft model
 121.358(b)(1)(vi)          B-757 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(vii)         B-767 - all series;                                                                                                   N/A by aircraft model
121.358(b)(1)(viii)         F-100 - all series;                                                                                                   N/A by aircraft model
 121.358(b)(1)(ix)          MD-11 - all series; and                                                                                               N/A by aircraft model
                            MD-80 series equipped with an EFIS and Honeywell-970 digital flight guidance
 121.358(b)(1)(x)
                            computer.                                                                                                             N/A by aircraft model
                            All other turbine powered airplanes not listed above must be equipped with as a
                            minimum requirement, an approved airborne windshear warning system. These                                         N/A by type certification date
  121.358(b)(2)
                            airplanes may be equipped with an approved airborne windshear detection and                                        Reference FAR 121.358(b)
                            avoidance system, or an approved combination of these systems.
                            Extension of the compliance date. A certificate holder may obtain an extension of the
                            compliance date in paragraph (b) of this section if it obtains FAA approval of a retrofit
    121.358(c)
                            schedule. To obtain approval of a retrofit schedule and show continued compliance                                  N/A Extension not required
                            with that schedule, a certificate holder must do the following:
                            Submit a request for approval of a retrofit schedule by June 1, 1990, to the Flight
  121.358(c)(1)
                            Standards Division Manager in the region of the certificate holding district office.                               N/A Extension not required
                            Show that all of the certificate holder's airplanes required to be equipped in
  121.358(c)(2)             accordance with this section will be equipped by the final compliance date                                         N/A Extension not required
                            established for TCAS II retrofit.
                            Comply with its retrofit schedule and submit status reports containing information
                            acceptable to the Administrator. The initial report must be submitted by January 2,
  121.358(c)(3)             1991, and subsequent reports must be submitted every six months thereafter until                                   N/A Extension not required
                            completion of the schedule. The reports must be submitted to the certificate holder's
                            assigned Principal Avionics Inspector.
    121.358(d)              Definitions. For the purposes of this section the following definitions apply -

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                           "Turbine powered airplane" includes, e.g., turbofan, turbojet, propfan, and ultrahigh
  121.358(d)(1)            bypass fan powered airplanes. The definition specifically excludes turbopropeller
                           powered airplanes.
                           An airplane is considered manufactured on the date the inspection acceptance
  121.358(d)(2)            records reflect that the airplane is complete and meets the FAA Approved Type
                           Design data.


121.359 Cockpit Voice Recorders
                                                                                                                                            Complied with by virtue of FAR Part 25.1457 at
                                                                                                                                            manufacture
                           No certificate holder may operate a large turbine engine powered airplane or a large
                           pressurized airplane with four reciprocating engines unless an approved cockpit
                                                                                                                       GMM 6.15.4(71)       Verified at conformity inspection (conformity checklist)
   121.359(a)              voice recorder is installed in that airplane and is operated continuously from the start
                           of the use of the checklist (before starting engines for the purpose of flight), to        AMM I chapter 31-31
                           completion of the final checklist at the termination of the flight.                                              CVR/FDR system records data from the when the
                                                                                                                                            engines are started or the aircraft is airborne as shown
                                                                                                                                            by the weight on wheels switches
   121.359(b)               [Removed and Reserved]
                           The cockpit voice recorder required by paragraph (a) of this section must meet the
   121.359(c)
                           following application standards:
                                                                                                                                            Complied with by virtue of FAR Part 25.1457 at
                                                                                                                           TCDS             manufacture
  121.359(c)(1)            The requirements of Part 25 of this chapter in affect on August 31, 1977.
                                                                                                                        GMM 6.15.4(71)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
                                                                                                                                            Complied with by virtue of FAR Part 25.1457 at
                                                                                                                           TCDS             manufacture
  121.359(c)(2)            After September 1, 1980, each recorder container must -
                                                                                                                        GMM 6.15.4(71)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
                                                                                                                                            Complied with by virtue of FAR Part 25.1457 at
                                                                                                                           TCDS             manufacture
 121.359(c)(2)(i)          Be either bright orange or bright yellow;
                                                                                                                        GMM 6.15.4(71)
                                                                                                                                            Verified at conformity inspection (conformity checklist)
                                                                                                                                            Complied with by virtue of FAR Part 25.1457 at
                           Have reflective tape affixed to the external surface to facilitate its location under           TCDS             manufacture
 121.359(c)(2)(ii)
                           water; and                                                                                   GMM 6.15.4(71)
                                                                                                                                            Verified at conformity inspection (conformity checklist)

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                            Have an approved underwater locating device on or adjacent to the container which
                            is secured in such a manner that they are not likely to be separated during crash
 121.359(c)(2)(iii)         impact, unless the cockpit voice recorder, and the flight recorder required by §                  GMM 6.15.4(73)      Verified at conformity inspection (conformity checklist)
                            121.343, are installed adjacent to each other in such a manner that they are not
                            likely to be separated during crash impact.
                            No person may operate a multiengine, turbine-powered airplane having a passenger
    121.359(d)              seat configuration of 10-19 seats unless it is equipped with an approved cockpit                                                   N/A by seating configuration
                            voice recorder that:
                            Is installed in compliance with § 23.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g); §
  121.359(d)(1)
                            25.1457(a) (1) and (2), (b), (c), (d), (e), (f), and (g) of this chapter, as applicable; and                                       N/A by seating configuration
                            Is operated continuously from the use of the checklist before the flight to completion
  121.359(d)(2)
                            of the final checklist at the end of the flight.                                                                                   N/A by seating configuration
                            No person may operate a multiengine, turbine-powered airplane having a passenger
    121.359(e)              seat configuration of 20 to 30 seats unless it is equipped with an approved cockpit                                                N/A by seating configuration
                            voice recorder that -
                            Is installed in compliance with § 23.1457 or § 25.1457 of this chapter, as applicable;
  121.359(e)(1)
                            and                                                                                                                                N/A by seating configuration
                            Is operated continuously from the use of the checklist before the flight to completion
  121.359(e)(2)
                            of the final checklist at the end of the flight.                                                                                   N/A by seating configuration
                            In complying with this section, an approved cockpit voice recorder having an erasure                                  Verified at conformity inspection (conformity checklist)
                            feature may be used, so that at any time during the operation of the recorder,                    GMM 6.15.4(73)
    121.359(f)
                            information recorded more than 30 minutes earlier may be erased or otherwise                    AMM 31-31-00 page 4   The CVR system does not allow audio data to erased
                            obliterated.
                                                                                                                                                  when the aircraft is in flight
                                                                                                                                                  Complied with by virtue of FAR Part 25.1457 at
                            For those aircraft equipped to record the uninterrupted audio signals received by a                                   manufacture
                            boom or a mask microphone, the flight crewmembers are required to use the boom
                            microphone below 18,000 feet mean sea level. No person may operate a large                           TCDS
                            turbine engine powered airplane or a large pressurized airplane with four                                             Verified at conformity inspection (conformity checklist)
    121.359(g)
                            reciprocating engines manufactured after October 11, 1991, or on which a cockpit                  GMM 6.15.4(71)
                            voice recorder has been installed after October 11, 1991, unless it is equipped to                 FOM 4.20.4B        When operating below 18,000 feet MSL, each
                            record the uninterrupted audio signal received by a boom or mask microphone in                                        pilot will use the aircraft’s boom microphone or his
                            accordance with § 25.1457(c)(5) of this chapter.                                                                      personal boom microphone provided it meets
                                                                                                                                                  TSO standards




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                                                                                                                                            In the event of an accident, the NTSB is notified
                            In the event of an accident or occurrence requiring immediate notification of the
                            National Transportation Safety Board under Part 830 of its regulations, which results
                            in the termination of the flight, the certificate holder shall keep the recorded                                The CVR is stored for a minimum of 60 days or longer
                                                                                                                          GMM 6.13.6
                            information for at least 60 days or, if requested by the Administrator or the Board, for                        if directed by the FAA or the NTSB
    121.359(h)
                            a longer period. Information obtained from the record is used to assist in determining        GMM 6.13.7
                            the cause of accidents or occurrences in connection with investigations under Part            FOM 20.6.5
                                                                                                                                            In the event of a reportable accident or occurrence, the
                            830. The Administrator does not use the record in any civil penalty or certificate
                            action.                                                                                                         flight crew will deactivate the CVR if the event occurs
                                                                                                                                            within 30 minutes of landing

121.360 Ground Proximity Warning/Glide Slope Deviation Alerting System
                            No person may operate a turbine-powered airplane unless it is equipped with a                                   TransGlobal Airlines verifies that each aircraft has the
                            ground proximity warning system that meets the performance and environmental                                    required ground proximity warning/glide slope
    121.360(a)              standards of TSO-C92 (available from the FAA, 800 Independence Avenue SW.,                  GMM 6.15.4(124)     deviation alerting system by performing an aircraft
                            Washington, DC 20591) or incorporates TSO-approved ground proximity warning                                     conformity inspection prior to the aircraft being added
                            equipment.
                                                                                                                                            to the aircraft listing Ops Spec
                            For the ground proximity warning system required by this section, the Airplane Flight
    121.360(b)
                            Manual shall contain -
  121.360(b)(1)             Appropriate procedures for -
                                                                                                                                            This section describes the normal procedures for the
 121.360(b)(1)(i)           The use of the equipment;                                                                    170-SOP 4.5.2
                                                                                                                                            EGPWS
 121.360(b)(1)(ii)          Proper flightcrew action with respect to the equipment;                                     170-SOP 4.5.3.1     Recovery actions for the applicable warnings
                                                                                                                                            These numbers reference pages in the QRH that
 121.360(b)(1)(iii)         Deactivation for planned abnormal and emergency conditions;                                   QRH 1, 2, 76
                                                                                                                                            contain procedures on deactivation
                            Inhibition of Mode 4 warnings based on flaps being in other than the landing                                    These numbers reference pages in the QRH that
 121.360(b)(1)(iv)
                            configuration if the system incorporates a Mode 4 flap warning inhibition control; and     QRH 24, 25, 43, 81
                                                                                                                                            contain procedures on deactivation
  121.360(b)(2)             An outline of all input sources that must be operating.                                      170-SOP 4.5.1      All of the input sources for the EGPWS are listed
                            No person may deactivate a ground proximity warning system required by this
                                                                                                                                               N/A The AFM does not require the system to be
    121.360(c)              section except in accordance with the procedures contained in the Airplane Flight
                            Manual.                                                                                                                           deactivated.
                                                                                                                                                 N/A MEL does not require the system to be
                            Whenever a ground proximity warning system required by this section is deactivated,
                                                                                                                                               deactivated. Any permanent deactivation will be
    121.360(d)              an entry shall be made in the airplane maintenance record that includes the date and
                            time of deactivation.                                                                                           documented on an E.O. and the date and time of such
                                                                                                                                            deactivation will be documented in the aircraft logbook


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                        No person may operate a turbine-powered airplane unless it is equipped with a
                        ground proximity warning / glide slope deviation alerting system that meets the
   121.360(e)           performance and environmental standards contained in TSO-C92a or TSO-C92b or               GMM 6.15.4(124)    Verified at conformity inspection (conformity checklist)
                        incorporates TSO-approved ground proximity warning-glide slope deviation alerting
                        equipment.
                        No person may operate a turbojet powered airplane equipped with a system required
                        by paragraph (e) of this section, that incorporates equipment that meets the
   121.360(f)
                        performance and environmental standards of TSO-C92b or is approved under that              GMM 6.15.4(124)    Verified at conformity inspection (conformity checklist)
                        TSO, using other than Warning Envelopes 1 or 3 for Warning Modes 1 and 4.
   121.360(g)           This section expires on March 29, 2005.


Subpart L – MAINTENANCE, PREVENTIVE MAINTENANCE, AND ALTERATIONS
121.361 Applicability
                        Except as provided by paragraph (b) of this section, this subpart prescribes
   121.361(a)           requirements for maintenance, preventive maintenance, and alternations for all                                This Subpart applies to TransGlobal Airlines
                        certificate holders.
                        The Administrator may amend a certificate holder's operations specifications to
                        permit deviation from those provisions of this subpart that would prevent the return to
                        service and use of airframe components, powerplants, appliances, and spare parts
                        thereof because those items have been maintained, altered, or inspected by persons                            TransGlobal Airlines is requesting no deviations from
   121.361(b)
                        employed outside the United States who do not hold U.S. airman certificates. Each                             Subpart L
                        certificate holder who uses parts under this deviation must provide for surveillance of
                        facilities and practices to assure that all work performed on these parts is
                        accomplished in accordance with the certificate holder's manual.


121.363 Responsibility for Airworthiness
   121.363(a)           Each certificate holder is primarily responsible for -
                                                                                                                        GMM5
                                                                                                                       GMM 5A
                                                                                                                       GMM 5B         TransGlobal Airlines recognizes it is responsible for
                        The airworthiness of its aircraft, including airframes, aircraft engines, propellers,          GMM 5C         the airworthiness of the aircraft and will comply with
  121.363(a)(1)
                        appliances, and parts thereof; and                                                             GMM 5D         the procedures stated in the maintenance portions of
                                                                                                                      GMM 5.1A        the manual system
                                                                                                                      GMM 5.1B
                                                                                                                      GMM 6.1

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                                                                                                                             GMM 5A
                                                                                                                             GMM 5B
                        The performance of the maintenance, preventive maintenance, and alteration of its                                        TransGlobal Airlines recognizes it is responsible for
                                                                                                                             GMM 5C
                        aircraft, including airframes, aircraft engines, propellers, appliances, emergency                                       the airworthiness of the aircraft and will comply with
  121.363(a)(2)
                        equipment, and parts thereof, in accordance with its manual and the regulations of                   GMM 5D
                                                                                                                                                 the procedures stated in the maintenance portions of
                        this chapter.                                                                                       GMM 5.1A
                                                                                                                                                 the manual system
                                                                                                                            GMM 5.1B
                                                                                                                            GMM 6.1
                        A certificate holder may make arrangements with another person for the                                                   TransGlobal Airlines may make arrangements with
                        performance of any maintenance, preventive maintenance, or alterations. However,                   GMM 5.22A
   121.363(b)
                        this does not relieve the certificate holder of the responsibility specified in paragraph                                another person for the performance of any
                                                                                                                           GMM 5.22B
                        (a) of this section.                                                                                                     maintenance, preventive maintenance, or alterations

121.365 Maintenance, Preventive Maintenance, and Alteration Organization
                        Each certificate holder that performs any of its maintenance (other than required                                        TransGlobal Airlines has an adequate organization to
                        inspections), preventive maintenance, or alterations, and each person with whom it                 GMM Chpt 4
   121.365(a)
                        arranges for the performance of that work must have an organization adequate to                                          maintain the highest degree of safety See organization
                                                                                                                           GMM 4.1.3G
                        perform the work.                                                                                                        structure and job descriptions
                        Each certificate holder that performs any inspections required by its manual in                   GMM Chpt 4
                                                                                                                                                 TransGlobal Airlines has an adequate organization to
                        accordance with § 121.369(b)(2) or (3) (in this subpart referred to as "required                  GMM 4.1.3G
   121.365(b)
                        inspections") and each person with whom it arranges for the performance of that                                          maintain the highest degree of safety See organization
                                                                                                                          GMM 6.3.1B
                        work must have an organization adequate to perform that work.                                                            structure and job descriptions
                                                                                                                          GMM 6.6.3 A
                        Each person performing required inspections in addition to other maintenance,
                        preventive maintenance, or alterations, shall organize the performance of those                                          TransGlobal Airlines will ensure that it maintains an
                        functions so as to separate the required inspection functions from the other                     GMM 6.3.1C
                                                                                                                                                 adequate organization and separates the functions of
   121.365(c)           maintenance, preventive maintenance, and alteration functions. The separation shall            GMM 10.9 RAF-261
                        be below the level of administrative control at which overall responsibility for the                                     the inspection department from those of the
                        required inspection functions and other maintenance, preventive maintenance, and                                         maintenance department
                        alteration functions are exercised.


121.367 Maintenance, Preventive Maintenance, and Alterations Programs
                        Each certificate holder shall have an inspection program and a program covering
   § 121.367
                        other maintenance, preventive maintenance, and alterations that ensures that -
                                                                                                                    GMM 10.9 Checklist 1 and 6
                        Maintenance, preventive maintenance, and alterations performed by it, or by other                 (section 1)            CASS will audit the performance of this requirement to
   121.367(a)
                        persons, are performed in accordance with the certificate holder's manual;                    GMM 10.9 RAF-261           ensure compliance
                                                                                                                          (section 4)

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                        Competent personnel and adequate facilities and equipment are provided for the               GMM 5.24
   121.367(b)
                        proper performance of maintenance, preventive maintenance, and alterations; and                              Responsibility of the President and CEO
                                                                                                                    GMM 4.2.1A
                                                                                                                                     Accomplished through the airworthiness
                        Each aircraft released to service is airworthy and has been properly maintained for
   121.367(c)
                        operation under this part.                                                                  GMM 5.9.1A       release/maintenance logbook entry process
                                                                                                                                     Maintenance Control procedures.

121.368 Aging Airplane Inspections and Records Reviews
                        Applicability. This section applies to all airplanes operated by a certificate holder                         N/A per Op Spec D485 para C4. TransGlobal will be
   121.368(a)           under this part, except for those airplanes operated between any point within the                             operating aircraft less than one year old and will list
                        State of Alaska and any other point within the State of Alaska.                                                        each aircraft on Ops Spec D485
                        Operation after inspection and records review. After the dates specified in this
                        paragraph, a certificate holder may not operate an airplane under this part unless the
                        Administrator has notified the certificate holder that the Administrator has completed                        N/A per Op Spec D485 para C4. TransGlobal will be
                        the aging airplane inspection and records review required by this section. During the
   121.368(b)
                        inspection and records review, the certificate holder must demonstrate to the                                 operating aircraft less than one year old and will list
                        Administrator that the maintenance of age-sensitive parts and components of the                                        each aircraft on Ops Spec D485
                        airplane has been adequate and timely enough to ensure the highest degree of
                        safety.
                        Airplanes exceeding 24 years in service on December 8, 2003; initial and repetitive                           N/A per Op Spec D485 para C4. TransGlobal will be
                        inspections and records reviews. For an airplane that has exceeded 24 years in
  121.368(b)(1)
                        service on December 8, 2003, no later than December 5, 2007, and thereafter at                                operating aircraft less than one year old and will list
                        intervals not to exceed 7 years.                                                                                       each aircraft on Ops Spec D485
                        Airplanes exceeding 14 years in service but not 24 years in service on December 8,                            N/A per Op Spec D485 para C4. TransGlobal will be
                        2003; initial and repetitive inspections and records reviews. For an airplane that has
  121.368(b)(2)
                        exceeded 14 years in service but not 24 years in service on December 8, 2003, no                              operating aircraft less than one year old and will list
                        later than December 4, 2008, and thereafter at intervals not to exceed 7 years.                                        each aircraft on Ops Spec D485
                        Airplanes not exceeding 14 years in service on December 8, 2003; initial and                                  N/A per Op Spec D485 para C4. TransGlobal will be
                        repetitive inspections and records reviews. For an airplane that has not exceeded 14
  121.368(b)(3)
                        years in service on December 8, 2003, no later than 5 years after the start of the                            operating aircraft less than one year old and will list
                        airplane's 15th year in service and thereafter at intervals not to exceed 7 years.                                     each aircraft on Ops Spec D485
                        Unforeseen schedule conflict. In the event of an unforeseen scheduling conflict for a                         N/A per Op Spec D485 para C4. TransGlobal will be
   121.368(c)           specific airplane, the Administrator may approve an extension of up to 90 days                                operating aircraft less than one year old and will list
                        beyond an interval specified in paragraph (b) of this section.                                                         each aircraft on Ops Spec D485
                        Airplane and records availability. The certificate holder must make available to the                          N/A per Op Spec D485 para C4. TransGlobal will be
                        Administrator each airplane for which an inspection and records review is required
   121.368(d)
                        under this section, in a condition for inspection specified by the Administrator,                             operating aircraft less than one year old and will list
                        together with records containing the following information:                                                            each aircraft on Ops Spec D485


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                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(1)             Total years in service of the airplane;                                                                       operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(2)             Total flight hours of the airframe;                                                                           operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(3)             Total flight cycles of the airframe;                                                                          operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(4)             Date of the last inspection and records review required by this section;                                      operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(5)             Current status of life-limited parts of the airframe;                                                         operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
                            Time since the last overhaul of all structural components required to be overhauled
  121.368(d)(6)
                            on a specific time basis;                                                                                     operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
                            Current inspection status of the airplane, including the time since the last inspection
  121.368(d)(7)
                            required by the inspection program under which the airplane is maintained;                                    operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(8)             Current status of the following, including the method of compliance:                                          operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
 121.368(d)(8)(i)           Airworthiness directives;                                                                                     operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
 121.368(d)(8)(ii)          Corrosion Prevention and Control Programs; and                                                                operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485
                                                                                                                                          N/A per Op Spec D485 para C4. TransGlobal will be
 121.368(d)(8)(iii)         Inspections and procedures required by § 121.370a of this part;                                               operating aircraft less than one year old and will list
                                                                                                                                                   each aircraft on Ops Spec D485

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                                                                                                                                                    N/A per Op Spec D485 para C4. TransGlobal will be
  121.368(d)(9)         A list of major structural alterations; and                                                                                 operating aircraft less than one year old and will list
                                                                                                                                                             each aircraft on Ops Spec D485
                                                                                                                                                    N/A per Op Spec D485 para C4. TransGlobal will be
                        A report of major structural repairs and the current inspection status for those
 121.368(d)(10)
                        repairs.                                                                                                                    operating aircraft less than one year old and will list
                                                                                                                                                             each aircraft on Ops Spec D485
                        Notification to Administrator. Each certificate holder must notify the Administrator at                                     N/A per Op Spec D485 para C4. TransGlobal will be
   121.368(e)           least 60 days before the date on which the airplane and airplane records will be                                            operating aircraft less than one year old and will list
                        made available for the inspection and records review.                                                                                each aircraft on Ops Spec D485

121.369 Manual Requirements
                        The certificate holder shall put in its manual a chart or description of the certificate            GMM 4.1.4
                        holder's organization required by § 121.365 and a list of persons with whom it has
   121.369(a)
                        arranged for the performance of any of its required inspections, other maintenance,                GMM 5.22.2
                        preventive maintenance, or alterations, including a general description of that work.             Ops Spec D091
                        The certificate holder's manual must contain the programs required by § 121.367                                            TransGlobal Airlines CAMP consist of the GMM,
                        that must be followed in performing maintenance, preventive maintenance, and
                                                                                                                     TransGlobal Airlines Manual   MTLM, MTM, aircraft, engine and component
   121.369(b)           alterations of that certificate holder's airplanes, including airframes, aircraft engines,
                        propellers, appliances, emergency equipment, and parts thereof, and must include at                   System               maintenance manuals, IPC, TCDS, SB, AD, MEL and
                        least the following:                                                                                                       CDL
                                                                                                                               AMM
                        The method of performing routine and nonroutine maintenance (other than required
  121.369(b)(1)
                        inspections), preventive maintenance, and alterations.                                               Job Cards             Method of performance
                                                                                                                            GMM Chpt 5
                        A designation of the items of maintenance and alteration that must be inspected
                        (required inspections), including at least those that could result in a failure,
  121.369(b)(2)
                        malfunction, or defect endangering the safe operation of the aircraft, if not performed              GMM 6.3.2             RII Item List
                        properly or if improper parts or materials are used.
                        The method of performing required inspections and a designation by occupational
  121.369(b)(3)
                        title of personnel authorized to perform each required inspection.                                   GMM 6.3.2             RII Item List
                        Procedures for the reinspection of work performed pursuant to previous required
  121.369(b)(4)
                        inspection findings ("buy-back procedures").                                                          GMM 6.4              Buy back procedures
                        Procedures, standards, and limits necessary for required inspections and                          GMM 5.5.1
                                                                                                                                                   Calibration of tools, measuring devices, and test
  121.369(b)(5)         acceptance or rejection of the items required to be inspected and for periodic                   GMM 5.5.10.1C
                        inspection and calibration of precision tools, measuring devices, and test equipment.                                      equipment.
                                                                                                                          GMM 6.3.2B
                                                                                                                          GMM 6.3.4
                                                                                                                                                   Identification of RII items
  121.369(b)(6)         Procedures to ensure that all required inspections are performed.                              GMM 10.9 Checklist 2
                                                                                                                                                   Audit of RII
                                                                                                                           (Section1)
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                            Instructions to prevent any person who performs any item of work from performing            GMM 6.3.5
  121.369(b)(7)
                            any required inspection of that work.                                                                         Separation of maintenance and inspection
                                                                                                                     (Explanatory Note)
                            Instructions and procedures to prevent any decision of an inspector, regarding any
                            required inspection from being countermanded by persons other than supervisory
                            personnel of the inspection unit, or a person at that level of administrative control        GMM 6.4.2
  121.369(b)(8)
                            that has overall responsibility for the management of both the required inspection                            Countermand procedures
                                                                                                                         GMM 6.4.3
                            functions and the other maintenance, preventive maintenance, and alterations
                            functions.
                            Procedures to ensure that required inspections, other maintenance, preventive
                            maintenance, and alterations that are not completed as a result of shift changes or        GMM 5.11.3.1B
  121.369(b)(9)
                            similar work interruptions are properly completed before the aircraft is released to                          Turnover procedures
                                                                                                                         GMM 5.6
                            service.
                            The certificate holder must set forth in its manual a suitable system (which may
    121.369(c)              include a coded system) that provides for preservation and retrieval of information in
                            a manner acceptable to the Administrator and that provides -
                            A description (or reference to data acceptable to the Administrator) of the work          GMM 5.1.2.1(4)
  121.369(c)(1)
                            performed;                                                                                                    Forms completion
                                                                                                                      GMM 5.8.3(37)
                                                                                                                        GMM 5.3.1
                            The name of the person performing the work if the work is performed by a person            GMM 5.3.2.3
  121.369(c)(2)
                            outside the organization of the certificate holder; and                                                       Forms completion
                                                                                                                      GMM 5.1.2.1(8)
                                                                                                                      GMM 5.8.3(42)
                                                                                                                      GMM 5.1.2.1( 3)
                                                                                                                        GMM 5.3.1
  121.369(c)(3)             The name or other positive identification of the individual approving the work.                               Forms completion
                                                                                                                        GMM 5.3.2
                                                                                                                      GMM 5.8.3(42)

121.370 Flight Cycle Implementation Times
                            For the Airbus Model A300 (excluding the -600 series), the flight cycle
  121.370(a)(1)
                            implementation time is:                                                                                                       N/A by aircraft model
 121.370(a)(1)(i)           Model B2: 36,000 flights.                                                                                                     N/A by aircraft model
                            Model B4-100 (including Model B4-2C): 30,000 flights above the window line, and
 121.370(a)(1)(ii)
                            36,000 flights below the window line.                                                                                         N/A by aircraft model
                            Model B4-200: 25,500 flights above the window line, and 34,000 flights below the
 121.370(a)(1)(iii)
                            window line.                                                                                                                  N/A by aircraft model
                            For all models of the British Aerospace BAC 1-11, the flight cycle implementation
  121.370(a)(2)
                            time is 60,000 flights.                                                                                                       N/A by aircraft model
                            For all models of the Boeing 707, the flight cycle implementation time is 15,000
  121.370(a)(3)
                            flights.                                                                                                                      N/A by aircraft model
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                        For all models of the Boeing 720, the flight cycle implementation time is 23,000
  121.370(a)(4)
                        flights.                                                                                                                   N/A by aircraft model
                        For all models of the Boeing 727, the flight cycle implementation time is 45,000
  121.370(a)(5)
                        flights.                                                                                                                   N/A by aircraft model
                        For all models of the Boeing 737, the flight cycle implementation time is 60,000
  121.370(a)(6)
                        flights.                                                                                                                   N/A by aircraft model
                        For all models of the Boeing 747, the flight cycle implementation time is 15,000
  121.370(a)(7)
                        flights.                                                                                                                   N/A by aircraft model
                        For all models of the McDonnell Douglas DC-8, the flight cycle implementation time
  121.370(a)(8)
                        is 30,000 flights.                                                                                                         N/A by aircraft model
                        For all models of the McDonnell Douglas DC-9/MD-80, the flight cycle
  121.370(a)(9)
                        implementation time is 60,000 flights.                                                                                     N/A by aircraft model
                        For all models of the McDonnell Douglas DC-10, the flight cycle implementation time
 121.370(a)(10)
                        is 30,000 flights.                                                                                                         N/A by aircraft model
                        For all models of the Lockheed L-1011, the flight cycle implementation time is 27,000
 121.370(a)(11)
                        flights.                                                                                                                   N/A by aircraft model
                        For the Fokker F-28 Mark 1000, 2000, 3000, and 4000, the flight cycle
 121.370(a)(12)
                        implementation time is 60,000 flights.                                                                                     N/A by aircraft model
                        After December 6, 2004, no certificate holder may operate a turbine-powered
                        transport category airplane with a type certificate issued after January 1, 1958, and
                        either a maximum type certificated passenger capacity of 30 or more, or a maximum
                        type certificated payload capacity of 7,500 pounds or more, unless instructions for
                        maintenance and inspection of the fuel tank system are incorporated in its
                        maintenance program. These instructions must address the actual configuration of
                        the fuel tank systems of each affected airplane and must be approved by the FAA
                        Aircraft Certification Office (ACO), or office of the Transport Airplane Directorate,                       N/A Currently not applicable due to compliance date.
   121.370(b)           having cognizance over the type certificate for the affected airplane. Operators must                       These instructions will be reviewed and submitted for
                        submit their request through an appropriate FAA Principal Maintenance Inspector,                                    approval prior to December 16, 2008
                        who may add comments and then send it to the manager of the appropriate office.
                        Thereafter, the approved instructions can be revised only with the approval of the
                        FAA Aircraft Certification Office (ACO), or office of the Transport Airplane
                        Directorate, having cognizance over the type certificate for the affected airplane.
                        Operators must submit their requests for revisions through an appropriate FAA
                        Principal Maintenance Inspector, who may add comments and then send it to the
                        manager of the appropriate office.




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121.370a Supplemental Inspections
                                                                                                                                                    The TransGlobal Airlines Maintenance Time Limits
                                                                                                                                                    Manual has incorporated the damage tolerance
                        Applicability and general requirements. After December 5, 2007, a certificate holder
                        may not operate an airplane under this part unless the maintenance program for that                                         inspections required by this section
                        airplane includes damage-tolerance-based inspections and procedures. Paragraphs              MTLM Part II Chapter 7
  121.370a(a)           (b), (c), and (d) of this section list the exceptions to this requirement. This section      Airworthiness Limitation       For the Embraer 170, based on the current fatigue test
                        does not apply to an airplane operated by a certificate holder under this part                     Inspections              and according to RBHA/FAR 25.571 (b), the ALI list
                        between any point within the State of Alaska and any other point within the State of
                        Alaska.                                                                                                                     will not be included in the MTLM until revision 2 of the
                                                                                                                                                    MRB. The airplane operation is limited to 2,500 FC
                                                                                                                                                    until the ALI are issued. Currently not required by date
                        New model added through type certificate amendment. This paragraph applies to                                               For the Embraer 170, based on the current fatigue test
                        each airplane added to a type certificate after December 8, 2003, that has a                                                and according to RBHA/FAR 25.571 (b), the ALI list
                        certification basis that does not include a requirement for damage-tolerance-based               MRB Appendix B
                                                                                                                                                    will not be included in the MTLM until revision 2 of the
  121.370a(b)           inspections and procedures. A certificate holder may not operate that airplane more           Airworthiness Limitation
                        than 4 years after the date of the type certificate amendment unless the                                                    MRB. The airplane operation is limited to 2,500 FC
                                                                                                                   Inspections (ALI) - Structures
                        maintenance program for that airplane includes damage-tolerance-based                                                       until the ALI are issued. Currently not required less
                        inspections and procedures.                                                                                                 than four years of operation
                        Design-life goal airplanes. If on or after December 5, 2007, the time in service of an
                        airplane reaches the design-life goal listed in appendix N to this part, the certificate                                    For the Embraer 170, based on the current fatigue test
                        holder may operate that airplane until the date the airplane's time in service reaches           MRB Appendix B             and according to RBHA/FAR 25.571 (b), the ALI list
  121.370a(c)           the design-life goal or until December 20, 2010, whichever occurs sooner. After that          Airworthiness Limitation      will not be included in the MTLM until revision 2 of the
                        date, the certificate holder may not operate the airplane unless the maintenance           Inspections (ALI) - Structures   MRB. The airplane operation is limited to 2,500 FC
                        program for that airplane includes damage-tolerance-based inspections and
                        procedures.                                                                                                                 until the ALI are issued. Currently not required by date
                        Airworthiness directive-mandated service-history-based inspections. Until December                                          For the Embraer 170, based on the current fatigue test
                        20, 2010, a certificate holder may operate an airplane for which an airworthiness                MRB Appendix B             and according to RBHA/FAR 25.571 (b), the ALI list
                        directive requires the maintenance program to include service-history-based
  121.370a(d)
                        inspections and procedures. After that date, the certificate holder may not operate           Airworthiness Limitation      will not be included in the MTLM until revision 2 of the
                        the airplane unless the maintenance program for that airplane includes damage-             Inspections (ALI) - Structures   MRB. The airplane operation is limited to 2,500 FC
                        tolerance-based inspections and procedures.                                                                                 until the ALI are issued. Currently not required by date
                        Approvals. The inspections and procedures required by this section to be included in
                        the certificate holder's maintenance program for an airplane must be approved by                 MRB Appendix B             As the MRB document is revised and approved by the
  121.370a(e)           the FAA Aircraft Certification Office or office of the Small Airplane Directorate or          Airworthiness Limitation      ACO. The revisions will be incorporated into the MTLM
                        Transport Airplane Directorate having cognizance over the type certificate for the         Inspections (ALI) - Structures   as required
                        affected airplane.




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121.371 Required Inspection Personnel
                        No person may use any person to perform required inspections unless the person                      GMM 6.5.2
                                                                                                                                                TransGlobal Airlines will only use properly trained and
   121.371(a)           performing the inspection is appropriately certificated, properly trained, qualified, and            GMM 6.6
                        authorized to do so.                                                                                                    qualified personnel to conduct RII inspections
                                                                                                                            GMM 6.6.1
                                                                                                                             GMM 6.6
                                                                                                                            GMM 6.6.1B
                        No person may allow any person to perform a required inspection unless, at that
                                                                                                                            GMM 6.3.5
   121.371(b)           time, the person performing that inspection is under the supervision and control of an                                  RII personnel under the direction of the Director of QA
                        inspection unit.                                                                              (Exclamatory Statement)
                                                                                                                             GMM 6.6
                                                                                                                              (Note)
                                                                                                                            GMM 6.3.5
                        No person may perform a required inspection if he performed the item of work                                            Personnel may not perform required inspections on
   121.371(c)
                        required to be inspected.                                                                     (Exclamatory Statement)
                                                                                                                                                items where they have performed the work
                                                                                                                            GMM 6.6.1C
                        Each certificated holder shall maintain, or shall determine that each person with
                        whom it arranges to perform its required inspections maintains, a current listing of
                        persons who have been trained, qualified, and authorized to conduct required                                            TransGlobal Airlines and their contractors will maintain
                                                                                                                            GMM 6.6
                        inspections. The persons must be identified by name, occupational title, and the                                        an RII personnel list
                                                                                                                           GMM 6.6.1.1
   121.371(d)           inspections that they are authorized to perform. The certificated holder (or person                                     TransGlobal Airlines will notify the personnel in writing
                        with whom it arranges to perform its required inspections) shall give written                      GMM 6.6.3.1
                                                                                                                                                of Special Authorization by the Special Authorization
                        information to each person so authorized describing the extent of his responsibilities              GMM 6.2
                        authorities, and inspectional limitations. The list shall be made available for                                         Letter RAF-211
                        inspection by the Administrator upon request.


121.373 Continuing Analysis and Surveillance
                                                                                                                                                TransGlobal Airlines has established a Continuing
                        Each certificate holder shall establish and maintain a system for the continuing
                        analysis and surveillance of the performance and effectiveness of its inspection                                        Analysis and Surveillance System (CASS) program to
                        program and the program covering other maintenance, preventive maintenance, and                    GMM Chpt 10          monitor and analyze the performance and
   121.373(a)
                        alterations and for the correction of any deficiency in those programs, regardless of               GMM 10.1            effectiveness of its inspection and maintenance
                        whether those programs are carried out by the certificate holder or by another
                                                                                                                                                programs covering maintenance, preventative
                        person.
                                                                                                                                                maintenance and alterations
                        Whenever the Administrator finds that either or both of the programs described in
                        paragraph (a) of this section does not contain adequate procedures and standards to
                                                                                                                                                TransGlobal Airlines will make appropriate changes to
   121.373(b)           meet the requirements of this part, the certificate holder shall, after notification by the         GMM 10.1
                        Administrator, make any changes in those programs that are necessary to meet                                            the program when notified by the Administrator.
                        those requirements.



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                        A certificate holder may petition the Administrator to reconsider the notice to make a
                        change in a program. The petition must be filed with the FAA certificate-holding
                        district office charged with the overall inspection of the certificate holder's operations                       TransGlobal Airlines may file a petition to reconsider
   121.373(c)
                        within 30 days after the certificate holder receives the notice. Except in the case of           GMM 10.1
                                                                                                                                         but will abide by the final decision of the Administrator
                        an emergency requiring immediate action in the interest of safety, the filing of the
                        petition stays the notice pending a decision by the Administrator.


121.375 Maintenance and Preventive Maintenance Training Program
                        Each certificate holder or person performing maintenance or preventive maintenance                               TransGlobal Airlines maintains a training program for
                        functions for it shall have a training program to ensure that each person (including                             maintenance and inspection personnel to ensure that
                                                                                                                       GMM Chpt 11
   § 121.375            inspection personnel) who determines the adequacy of work done is fully informed                                 qualified personnel are assigned the responsibility of
                        about procedures and techniques and new equipment in use and is competent to                     MTM
                                                                                                                                         determining the adequacy of maintenance and/or
                        perform his duties.
                                                                                                                                         inspection work performed.

121.377 Maintenance and Preventive Maintenance Personnel Duty Time Limitations
                        Within the United States, each certificate holder (or person performing maintenance
                        or preventive maintenance functions for it) shall relieve each person performing                GMM 5.4          TransGlobal Airlines policy is to not allow anyone
   § 121.377            maintenance or preventive maintenance from duty for a period of at least 24                    GMM 5.4.1A        performing maintenance or preventative maintenance
                        consecutive hours during any seven consecutive days, or the equivalent thereof                 GMM 5.22.6.6      to exceed the duty times specified in FAR 121.377
                        within any one calendar month.


121.378 Certificate Requirements
                        Except for maintenance, preventive maintenance, alterations, and required                                        All personnel directly in charge of maintenance,
                        inspections performed by a certificated repair station that is located outside the              GMM 5.2.1A.      preventative maintenance, or alterations will be
   121.378(a)           United States, each person who is directly in charge of maintenance, preventive                 GMM 5.2.1 B.     appropriately certificated with the exception of foreign
                        maintenance, or alterations, and each person performing required inspections must              GMM 5.2.3.2(3)    repair stations. More stringent requirements of change
                        hold an appropriate airman certificate.
                                                                                                                                         effective 30 January 06 have been applied
                        For the purposes of this section, a person "directly in charge" is each person
                        assigned to a position in which he is responsible for the work of a shop or station
                        that performs maintenance, preventive maintenance, alterations, or other functions                               TransGlobal Airlines personnel directly in charge of
                                                                                                                        GMM 4.1.3H
   121.378(b)           affecting aircraft airworthiness. A person who is "directly in charge" need not                                  maintenance need not physically observe the work but
                        physically observe and direct each worker constantly but must be available for                  GMM 5.2.1B
                                                                                                                                         must be available for consultation
                        consultation and decision on matters requiring instruction or decision from higher
                        authority than that of the persons performing the work.




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121.379 Authority to Perform and Approve Maintenance, Preventive Maintenance, and Alterations
                            A certificate holder may perform, or it may make arrangements with other persons to
                            perform, maintenance, preventive maintenance, and alterations as provided in its                                TransGlobal Airlines recognizes it's authority to
                            continuous airworthiness maintenance program and its maintenance manual. In                    GMM Chpt 5       perform maintenance preventive maintenance, and
    121.379(a)
                            addition, a certificate holder may perform these functions for another certificate             GMM 9.4.3        alterations, in accordance with TransGlobal Airlines
                            holder as provided in the continuous airworthiness maintenance program and
                                                                                                                                            manuals and procedures
                            maintenance manual of the other certificate holder.
                            A certificate holder may approve any aircraft, airframe, aircraft engine, propeller, or
                            appliance for return to service after maintenance, preventive maintenance, or                    GMM 9.4        TransGlobal Airlines will ensure that all major repairs
    121.379(b)              alterations that are performed under paragraph (a) of this section. However, in the             GMM 9.4.2       and alterations performed on it’s aircraft are
                            case of a major repair or major alteration, the work must have been done in                     GMM 9.4.3       accomplished using approved data.
                            accordance with technical data approved by the Administrator.


121.380 Maintenance Recording Requirements
                                                                                                                                            TransGlobal Airlines will maintain and retain
                            Each certificate holder shall keep (using the system specified in the manual required
                                                                                                                           GMM Chpt 7       maintenance, repair, alteration, overhaul and
    121.380(a)              in § 121.369) the following records for the periods specified in paragraph (c) of this
                            section:                                                                                        GMM 7.1         inspection records in accordance with the
                                                                                                                                            requirements of FAR 121.380.
                                                                                                                                            All the records necessary to show that all requirements
                                                                                                                                            for the issuance of an Airworthiness Release under
                            All the records necessary to show that all requirements for the issuance of an                                  FAR 121.709 have been met shall be kept in a hard
  121.380(a)(1)
                            airworthiness release under § 121.709 have been met.                                            GMM 7.1.6
                                                                                                                                            copy file for each aircraft at TransGlobal Airlines’
                                                                                                                                            headquarters and maintained by the Records
                                                                                                                                            Department.
  121.380(a)(2)             Records containing the following information:
                                                                                                                            GMM 7.1.6
 121.380(a)(2)(i)           The total time in service of the airframe.                                                                      Records for total time in service
                                                                                                                             (Table)
                            Except as provided in paragraph (b) of this section, the total time in service of each          GMM 7.1.6
 121.380(a)(2)(ii)
                            engine and propeller.                                                                                           Total time in service for each engine
                                                                                                                             (Table)
                            The current status of life-limited parts of each airframe, engine, propeller, and               GMM 7.1.6
 121.380(a)(2)(iii)
                            appliance.                                                                                                      Current status of life limited parts
                                                                                                                             (Table)
                            The time since last overhaul of all items installed on the aircraft which are required to       GMM 7.1.6
 121.380(a)(2)(iv)
                            be overhauled on a specified time basis.                                                                        Time since last overhaul
                                                                                                                             (Table)
                            The identification of the current inspection status of the aircraft, including the times
                                                                                                                            GMM 7.1.6
 121.380(a)(2)(v)           since the last inspections required by the inspection program under which the aircraft                          Identification of current inspection status
                            and its appliances are maintained.                                                               (Table)
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                                                                                TransGlobal Airlines Letter of Compliance
                                                                                     Part 121 – Rev B Submission




                                                                                                                                                                                                         FAA
                      N/A                                      Requirement                                             Manual References              TransGlobal Policies/Comments




                                                                                                                                                                                                    RA
FAR/SRR


                            The current status of applicable airworthiness directives, including the date and              GMM 7.1.6
                                                                                                                                            Current status of applicable airworthiness directives
 121.380(a)(2)(vi)          methods of compliance, and, if the airworthiness directive involves recurring action,           (Table)
                            the time and date when the next action is required.                                                             AD summary
                                                                                                                          GMM 9.2.4
                                                                                                                           GMM 7.1.6
 121.380(a)(2)(vii)         A list of current major alterations to each airframe, engine, propeller, and appliance.                         List of current major alterations
                                                                                                                            (Table)
                            A certificate holder need not record the total time in service of an engine or propeller                                      N/A by type certificate date
                            on a transport category airplane that has a passenger seat configuration of more
    121.380(b)
                            than 30 seats or a nontransport category airplane type certificated before January 1,                             TransGlobal Airlines will record the TT as required
                            1958, until the following, whichever occurs first:
                                                                                                                                                                 electronically
                                                                                                                                                        N/A by type certificate date
  121.380(b)(1)             March 20, 1997; or
                                                                                                                                              TransGlobal Airlines will record the TT as required
                                                                                                                                                                 electronically
                                                                                                                                                        N/A by type certificate date
                            The date of the first overhaul of the engine or propeller, as applicable, after January
  121.380(b)(2)
                            19, 1996.                                                                                                         TransGlobal Airlines will record the TT as required
                                                                                                                                                                 electronically
                            Each certificate holder shall retain the records required to be kept by this section for
    121.380(c)
                            the following periods:
                            Except for the records of the last complete overhaul of each airframe, engine,
                            propeller, and appliance, the records specified in paragraph (a)(1) of this section            GMM 7.1.6
  121.380(c)(1)
                            shall be retained until the work is repeated or superseded by other work or for one                             Record retention
                                                                                                                            (Table)
                            year after the work is performed.
                            The records of the last complete overhaul of each airframe, engine, propeller, and
                                                                                                                           GMM 7.1.6
  121.380(c)(2)             appliance shall be retained until the work is superseded by work of equivalent scope                            Record retention
                            and detail.                                                                                     (Table)
                                                                                                                           GMM 7.1.6
                            The records specified in paragraph (a)(2) of this section shall be retained and
  121.380(c)(3)
                            transferred with the aircraft at the time the aircraft is sold.                             (Bottom of Table)   Record transferal
                                                                                                                           GMM 7.1.8
                            The certificate holder shall make all maintenance records required to be kept by this
                                                                                                                            GMM 7.1         TransGlobal Airlines will make all required records
    121.380(d)              section available for inspection by the Administrator or any authorized representative
                            of the National Transportation Safety Board (NTSB).                                            GMM 7.1.5        available to the FAA or NTSB

121.380a Transfer of Maintenance Records
    § 121.380a              Transfer of maintenance records.


Page 114 of 115
                                                                            TransGlobal Airlines Letter of Compliance
                                                                                 Part 121 – Rev B Submission




                                                                                                                                                                                                         FAA
                  N/A                                      Requirement                                              Manual References              TransGlobal Policies/Comments




                                                                                                                                                                                                    RA
FAR/SRR


                        Each certificate holder who sells a U.S. registered aircraft shall transfer to the
                        purchaser, at the time of sale, the following records of that aircraft, in plain language       GMM 7.1.6
                                                                                                                                         Current records retained at the time that an aircraft is
                        form or in coded form at the election of the purchaser, if the coded form provides for       (Bottom of Table)
                        the preservation and retrieval of information in a manner acceptable to the                                      sold shall be transferred with the aircraft
                                                                                                                        GMM 7.1.8
                        Administrator:
   121.380(a)           The record specified in § 121.380(a)(2).
                        The records specified in § 121.380(a)(1) which are not included in the records
                        covered by paragraph (a) of this section, except that the purchaser may permit the
                        seller to keep physical custody of such records. However, custody of records in the                              TransGlobal Airlines will transfer all records with the
   121.380(b)
                        seller does not relieve the purchaser of his responsibility under § 121.380(c) to make                           aircraft
                        the records available for inspection by the Administrator or any authorized
                        representative of the National Transportation Safety Board (NTSB).




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