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									     MlTSUBlSHl                    AIRPLANE FLIGHT MANUAL                     SECTION 3
     MU-25-60                             MARQU I SE               EMERGENCY PROCEDURES


                             SECTION 3 EMERGENCY PROCEDURES
                                        CONTENTS
     ENGINE FAILURE ..........................................................      3-1
         ENGINE FAILURE DURING TAKEOFF PRIOR TO LIFTOFF .................... 3-1
         ENGINE FAILURE AFTER LIFTOFF .GEAR DOWN OR IN TRANSIT TO UP ...... 3 - 1
         ENGINE FAILURE IN TAKEOFF CLIMB .GEAR FULLY RETRACTED ............ 3 - 1
         LH OR RH BETA RANGE ANNUNCIATOR ILLUMINATED IN FLIGHT ............. 3 - 2
R        AUTO-IGNITION RELIGHT FAILURE ..................................... 3-3
         ENGINE SHUTDOWN PROCEDURE ......................................... 3-3
R        DRIFTDOWN PROCEDURE ............................................... 3- fi
                         .................................................
     SINGLE ENGINE LANDING                                                    3-d
  SINGLE ENGINE GO AROUND ...............................................     3-5
  ENGINE FIRE ...........................................................      3-6
R AIRSTART ..............................................................     3-7

R FUEL BOOST PUMP FAILURE ...............................................     3-8
R SMOKE AND FUME ELIMINATION .....................................     3- 8-1/3- 8-2
  LANDING GEAR EMERGENCY OPERATIONS .....................................     3-9
      RECYCLING OF LANDING GEAR SYSTEM ..................................     3-9
      LANDING GEAR EMERGENCY EXTENSION ..................................     3-10
  AIR CONDITIONING AND PRESSURIZATION SYSTEM FAILURE ....................     3-10
      CABIN PRESS LOW ANNUNCIATOR ILLUMINATES ...........................     3-10
      AIR CON0 SYS FAIL ANNUNCIATOR ILLUMINATES .........................     3-10
      DEFOG OVER TEMP ANNUNCIATOR ILLUMINATES ...........................     3-11
  EMERGENCY DESCENT .....................................................     3-11
  BATTERY OVERHEAT ......................................................     3-11




    FAA APPROVED 3-2-78
    REISSUED 09-24-85                                                            Page 3-7
    REVISION 6 03-09-95
 HITSUBISHI                   AIRPLANE FLIGKT MANUAL                    SECTION 3
 MU-2B-60                            MARQUISE                EMERGENCY PROCEDURES


                          SECTION 3 EMERGENCY PROCEDURES
                                     CONTENTS
 ELECTRICAL FAILURE  .......,................................*.......,,..,,....
                                                                              3-12
      L OR R DC GEN OUT ANNUNCIATOR ILLUMINATES ............................  3-12
      INVERTER FAIL ANNUNCIATOR CYCLES ON AND OFF
      (Applicable to S/N 700SA, 731SA Through 798SA) .......................  3-14
      INVERTER FAIL ANNUNCIATOR ILLUMINATES
      (Applicable t o S/N A700SA, 731SA Through 798SA) ...................... 3-15
      INVERTER FAIL ANNUNCIATOR ILLUMINATES AFTER SELECTING STANDBY  ..as.... 3-15
      INVERTER FAIL ANNUNCIATOR ILLUMINATES
      (Applicable to S/N 799SA, 1501SA And Subsequent) .....................  3-16
      INVERTER FAIL ANNUNCIATOR ILLUMINATES AFTER SELECTING STANDBY
      (Applicable to S/N 799SA, 1501SA And Subsequent) .....................  3-16
      L FEEDER OUT ANNUNCIATOR ILLUMINATES ................................   3-17
      R FEEDER OUT ANNUNCIATOR ILLUMINATES ...
                                           ...
                                           ..
                                            ..
                                            ..
                                             I                                3-18




FAA APPROVED 3-2-78
REISSUED 09-24-85                                                               3-ii
 I41TSUBISHI                                    AIRPLANE FLIGHT MANUAL                                        SECTIm 3
 MU-ZB-60                                              MARQUISE                                    EMERGENCY PROCEDURES



 ENGINE FAILURE

ENGINE FAILURE DURING TAKEOFF PRIOR TO LIFTOFF

       1.
       2.
             Power L e v e r s
             Brakes...
                                  ................. AS NECESSARY (REVERSE AS REQUIRED)
                                                     GROUND I D L E
                             ..................... AS REQUIRED TO MAINTAIN DIRECTIONAL
       3.    Reverse Thrust          ...............            CONTROL
 L

                ON OTHER THAN DRY, HARD SURFACE RUNWAYS, I T I S POSSIBLE TO APPLY
                MORE REVERSE THRUST THAN CAN BE COUWTERACTEO B Y RUDDER, BRAKES, AND
                NOSEWHEEL STEERING.

ENGINE FAILURE AFTER LIFTOFF                    -  GEAR DOW OR I N TRANSIT TO UP
I f t h e e n g i n e f a i l u r e o c c u r s a f t e r l i f t o f f b u t b e f o r e t h e l a n d i n g g e a r C Y C ~ Fi s
f u l l y c o m p l e t e ( g e a r UP, d o o r s CLOSED) a n d c o n t i n u e d f l i g h t i s n o t p o s s i b l e

                                ................. DOWN AS REQUIRED
      1.
      2.
      3.

      4.
             L a n d i n g Gear
                                     ............. POWER
             O p e r a t i n g Engs'ne
             Flaps     ........................ LEAVE I N SELECTED TAKEOFF POSITION
             L a n d s t r a i g h t ahead u s i n g a i r s p e e d a p p r o p r i a t e f o r t h e a i r p l a n e weight,
             b u t n o t l e s s t h a n 105 KCAS
                                                                                                                              I
               I F FLAPS 20" TAKEOFF IS SELECTED AND ENGINE FAILURE OCCURS AFTER
               LIFTOFF, COMTINUED CLIMB PERFORWNCE I S NOT ASSURED UNLESS THE
               LANDING GEAR HAS COMPLETELY RETRACTED, THE GEAR DOORS ARE CLOSED,
               AND THE FLAPS ARE AT 5 O OR LESS.

ENGINE FAILURE I N TAKEOFF CLIMB                    - GEAR FULLY RETRACTED
      1.    Airspeed      .....................
                      ........................                 140 KCAS MINIMUM



i
 3.
 4.
      2.    Flaps
            F a i l e d Engine C o n d i t i o n Lever.
            F a i l e d E n g i n e Power L e v e r    ....
                                                               5"
                                                               EMERGENCY STOP
                                                               TAKEOFF                                                       1
               IDENTIFY FAILED ENGINE BY POWER ASYMMETRY AND ENGINE INSTRUMENTS.
               DO NOT RETARD FAILED ENGINE POWER LEVER.      PLACE FAILED ENGINE
               POWER LEVER TO TAKEOFF POSITION DURING FEATHERING OF PROPELLER AND
               LEAVE THERE FOR THE REMAINDER OF THE FLIGHT.



               RUN-CRANK-STOP SWITCH MUST REMAIN I N RUN POSITION.



FAA APPROVED 3-2-78
REISSUED 09-24-85
 flITSUBISHI                             AIRPLANE FLIGHT MANUAL                                       SECTION 3
 MU-28-60                                       MARQUISE                                   EMERGENCY PROCEDURES


 ENGINE FAILURE (CONT)
 ENGINE FAILURE I TAKEOFF CLIMB
                N                          -
     5. Flaps
     6. Airspeed
                   ........................ GEAR UFULLY RETRACTED
                       ..................... ASP REQUIRED
                                                                                     (CONT)

     7. Operating E n g i n e Power       ....... 150 KCAS
             AIR CONDITIONING AND PRESSURIZATION SYSTEM M S REMAIN OFF
                                                         UT
             TO ATTAIN FULL CLIMB CAPABILITY.
     8.     Engine Shutdown Procedure           .... COMPLETE
                                                (NOTEJ
             Single engine climb rates a r e best a t t a i n e d w i t h wings
             level by use o f rudder t o c o r r e c t for yawing tendency and
             u s i n g t h e m i n i m u m amount of s p o i l e r necessary t o m a i n t a i n
             lateral control.



                         0" (UP)                      140                  150   *
                                                      130                  140
             I
                         5 O

                        20                 I          125
                                                                   I       135         I
             *VISE,   Maximum Takeoff Gross Weight, Sea Level Standard
             day, Flaps 0" i s 152 KCAS. 150 KCAS i s recommended f o r
             a l l weights.
LH OR RH BETA RANGE ANNUNCIATOR ILL\IMINATED IN FLIGHT
Should e i t h e r BETA RANGE annunciator i l l u m i n a t e i n f l i g h t i n o t h e r than a f u l l
s t a l l condition and no control problem i s p r e s e n t i n rpm o r yaw:
1. Affected Engine           ...................... SECURE P R I O R TO LANDING (USE ENGINE
                                                    SHUTDOWN PROCEDURE)
                                                           or
I f airplane control o r rpm problem e x i s t s :
1. Affected Engine       ......................    SECURE
                                                                 HTO N
                                                                          IMMEDIATELY
                                                                S U D W PROCEDURE)
                                                                                        (USE   ENGINE
2.   Land   .................................                   USE SINGLE ENGINE LANDING PROCEDURES

                                               CAUTION                 1
             ILLUMINATION OF EITHER BETA RANGE-ANNUNCIATOR IN FLIGHT
                                                       '



             MAY BE AN INDICATION OF A PROPELLER CONTROL MALFUNCTION.
             I T MAY BE IMPOSSIBLE TO REDUCE THRUST ON THE AFFECTED
             ENGINE DURING LANDING OR AFTER TOUCHDOWN.




FAA APPROVED 3-2-78
REISSUED 09-24-85                                                                                        3-2
-




     M ITSUBISH I                      AIRPLANE FLIGHT M A N U A L             SECTION 3
     M U -28- 6 0                           MAROUISE               ElVERGENCY PRcxlEDUREs



     ENGINE FAILURE (CONT)

     AUTO-IGNITION RELIGHT FAILURE (Applicable               to airplanes equipped with Auto-
    Ignition System)
R   Ignition Annunciator Light illminates with Auto-Ignition selected, engine
    fails to accelerate properly:


     r
                                                                                           -
R         1.    Failed Engine ITT and RPM    .......
                                              CHECK
R                                             (If ITT increases toward red line
                                              and RPM is not increasing normally)
         2. Failed Engine Condition Lever _..EMERGENCY STOP
     i   3. Failed Engine Power Lever ....... TAKEOFF
         4. Engine Shutdown Procedure        .......   COMPLETE
                                                                                           -


R
R
R
R                 IF ACTUATION OF THE AUTO-IGNITION WAS DUE TO ICE INGESTION,
R                 ENSURE THAT APPROPRIATE PROCEDURES ARE EXECUTED FOR FLIGHT
R                 IN ICING CONDITIONS.
    ENGINE SHUTDOWN PROCEDURE

    If engine failure occurs, or if a sudden l o s s or significant fluctuation
    ( * 7.5%) of indicated torque pressure occurs, as indicated by airplane yaw,
    promptly shutdown the affected engine and determine the cause prior to further
    operation.
         1. Failed Engine Condition Lever --. EMERGENCY STDP
         2. Failed Engine Power Lever ....... TAKEOFF
                                                                                           i
                                          WARN1 NG

                 IDENTIFY FAILED EAlGIEE BY POWER ASYMETRY AND ENGINE
                 INSTRUMENTS. DO NOT RETARD FAILED ENGINE POWER LEVER.
                 PLACE FAILED ENGINE FElwER LEVER TO TAKEQFF POSITION DURING
                 THE FEATHERING OF mapELLm AND LEAVE THERE FOR THE
                 REMAINDER O THE F f f W .
                            F




                      RUN-CRANK-STOP SWITCH MUST REMAIN IN RUN POSITION.
         3. Trim    ............................       SET
         4. Power    ...........................       PIS REQUIRED
         5.    Failed Engine DC Generator
                 Switch ........................       OFF
    FAA APPROVED 3-2-78
    REISSUED 09-24-85                                                               Page 3-3
    REVISION 7 11-30-95
    MI TSU B ISH I                 AIRPLANE F L I G H T MANUAL           SECTION 3
    MU-2B-60                            MARQUISE               ENERGENCY wIoc8)wIEs



    ENGINE FAILURE (CONT)

R   ENGINE SHUTDOWN PROCEDURE (CONT)
        6. Ignition Switch ................. OFF (Affected engine)
        7. Air Conditioning and Pressurization
             System ........................ SELECT OPERATING ENGINE BLEED AIR OR
                                             RAM AIR (IF THRUST CRITICAL)
                                        /NOTE/
               Ram Air Position will depressurize Cabin. Oxygen may be
               required.
        8. Operating Engine Power Lever .... SET AS REQUIRE0
        9. Operating Engine DC Generator
               Load   ..........................  REDUCE   TO ESSENTIAL ITEMS
       10. Synchrophaser      ................... OFF
    DRIFTDOWN PROCEDURE

    Following an engine failure at altitudes above 25,000 feet pressure altitude:
        1. Failed Engine ................... SECURE (USE ENGINE SHUTDOWN PROCE-
                                              DURE)
        2. Operating Engine Power Setting .. AS REQUIRED
        3. Pressurization System ........... SELECT OPERATING ENGINE BLEED AIR

                                       1   NOTE/
              For prolonged descent above 25,000 feet pressure altitude,
              it may be necessary to utilize oxygen. Observe cabin
              altitude warning light. Recommended airspeed for prolonged
              descent is 135 KCAS with operating engine at maximum
              continuous power setting.
    SINGLE ENGINE LANDING



              THE USE OF 40" FLAPS WITH A N ENGINE INOPERATIVE IS NOT
              RECOMMENDED. ALWAYS MAINTAIN AIRSPEED ABOVE V X S E FOR
              FLAP SETTING BEING USED UNTIL LANDING IS ASSURED.
    Before Landing Checklist - Use normal procedures except as follows:
        1. Inoperative Engine .............. SECURED (USE ENGINE SHUTDOWN PROCE-
                                              DURE)
        2. Fuel Quantity and Balance ....... CHECK WITHIN LIMITATIONS
        3. Cabin Air Selector Switch ....... OFF OR RAM
        4. Condition Lever (Operating
              Engine) ....................... TAKEOFF LAND

    FAA APPROVED 3-2-78
    REISSUED 09-24-85                                                           Page 3-4
    REVISION 7 11-30-95

								
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