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									2007 POPA Convention

Technical Walk Around on Your PC-12



   This presentation is for familiarization purposes only and is not meant to supplement the P.O.H. or any other approved Pilatus manual
2007 POPA Convention




Welcome:


•   Technical Walk Around of your PC-12 featuring:
        –   Helpful tips/Do’s and Don’ts
        –   Post-Flight vs. Pre-Flight
        –   Upgrades as the Fleet Matures
        –   Web links
        –   Information Leaflets




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2007 POPA Convention




Interior


•   Cockpit/Cabin Items
        –   Please leave CD’s in the Aircraft (AMM/IPC/WDM)
        –   Switch Caps/Master Caution
        –   Light bulb spares for your aircraft
        –   Required equipment and not grounding your aircraft
        –   Upgrading your interior
        –   Care of leather, cabinets, fire blocking concerns, Placards




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2007 POPA Convention




Electronically Recorded Engine Parameters

•   ITT
•   Torque
•   Gas Generator Speed
•   Propeller Speed
•   Fuel Flow
•   Engine Oil Pressure
•   Engine Oil Temperature
•   Weight on Wheels (discrete)                              Recorded but not
•   P2.5 / P3 (discrete)                                     indicated on EIS
•   Inertial Separator Door Open/Closed (discrete)
•   Pressure Altitude
•   Computed Airspeed
•   Outside Air Temperature
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Auto Trending Mode


•   Auto trending occurs only during flight when the following
    conditions are met for greater than 2 minutes stability:
        –   600C < ITT < 800C
        –   15psi < Tq < 44.4 psi
        –   10,000ft < Alt < 35000ft
•   Data is stored every 2 minutes
•   The “store” light on the EIS panel will illuminate during storing
    of data
•   This data is designed to be used for trending, and is compatible
    with the Pratt ECTM or Web-ECTM programs


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Manual Data Recording


•   Occurs when the “store” button on the front of the EIS is pushed
    during an engine run condition
•   Upon pressing the “store” button, the EIS will store 20 seconds
    of data that can be retrieved later from the data card
•   “store” light illuminates while the EIS is storing the manual data
•   This mode is useful if you notice something peculiar on the EIS
    parameters and want to avoid having to write down all of the
    parameters manually




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Exceedence Data Recording


•   An exceedence occurs when any of the Pratt defined normal
    operating limits are exceeded
•   The EIS recognizes these exceedences and will begin recording
    data every second that the exceedences exist
•   In addition, the EIS will store the engine parameters for the 2
    minutes prior to the exceedence
•   Excellent data is produced for troubleshooting purposes; the
    engine parameters can be graphed in Excel to determine such
    information as time duration of the exceedence and what caused
    the exceedence
•   Data chip can hold 15 hours of exceedence data

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Downloading the Data Chip


•   Software and instructions for downloading the data chip is
    located at www.pilatus-aircraft.com , under Engine Instrument
    System Data Download
•   Overview:
        –   Remove data chip from EIS
        –   Insert chip into the appropriate card reader for you
            computer
        –   Run the download software and download the data files to
            you computer
        –   Send the data off for analysis or analyze in-house


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Control Lock Removal

•   Caution must be taken when removing the flight control lock in order to prevent damaging
    the EHSI
•   When removing the lock grasp the bottom of the lock and raise vertically
•   Many people are simply grabbing the control lock at the top and pulling
•   As a result, with the tight fit of the lock, operators have mistakenly damaged the EFIS tubes

                                                                     YES




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Cockpit Lighting


•   Most of the annunciator and push
    button switches have easily replaceable
    bulbs by simply pulling the fixture from
    the socket




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Cockpit Lighting


•   Removal process is simplified by the use of an extraction tool




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Cockpit Lighting


•   This type of switch/annunciator is identified by ridges on the
    housing




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Cockpit Lighting

•   The locking type requires the use of a .005 - .009 feeler gauge to disengage the tab on the
    left side of the unit
•   Simply slide the feeler gauge into the left side of the housing down approximately one inch
    then grasp the unit with the feeler gauge and finger and slide out
•   This type is identified by being completely smooth having no ridges around the switch face



          Locking Tab




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Seats


•   Ipeco crew seats (3 Yr Chapter 5)
       – Ensure your MX facility is aware of
         the 3 yr replacement on the Ipeco
         crew seat foam and the correct p/n
         along with the regulatory
         requirements.
•   Seat Belt replacement (12 Yr)
       – SL 097
       – This Service letter contains all the
         information required to replace
         your crew and cabin seat belts on
         a timely matter with minimal
         inconvenience.
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2007 POPA Convention




In-flight Pusher Test


•   The in-flight test is not the same as the pre-flight test
•   The amber PUSHER caption on the CAWS display unit must remain off
    and the stick pusher must not operate
•   The stick pusher computer must receive all of these signals to do the
    in-flight test:
        –   Aircraft not on ground
        –   Engine torque more than 5 psi
        –   PCL not set to IDLE
        –   Flaps set to any angle




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2007 POPA Convention




In-flight Pusher Test


•   When the PUSHER switch is pressed and held in, the system goes
    through this sequence:
        –   The amber PUSHER ICE MODE caption on the CAWS display unit
            comes on
        –   The stick shaker and audio stall warning operate for two seconds
        –   The stick shaker and audio stall warning stop for one second
        –   The stick shaker and audio stall warning operate for two seconds
        –   The stick shaker and audio stall warning stop for one second
        –   The stick shaker and audio stall warning operate for as long as the
            PUSHER switch is pressed
•   At the end of the sequence, the PUSHER switch is released and the
    amber PUSHER ICE MODE caption on the CAWS display unit goes off

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Advantages of a Comprehensive Post-Flight


•   Not in a rush fueling, Checking Weather, flight planning, loading
    bags
•   Check engine oil level within recommended 10 – 20 min.
•   Visually inspect aircraft for Fuel, Oil, & Hydraulic leaks
•   Wipe down extended Struts w/5606 while light on fuel
•   Service Lav and re-stock cabinets
•   Address any interior/exterior cosmetic issues
•   Most importantly: time to obtain parts and address MX/servicing
    items in reasonable time prior to next flight



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Exterior Items


•   The Maturing Fleet & Corrosion Control
•   Lightning Strikes, Static wicks
•   De-Ice boot condition, pin holes
•   High Pressure wash concerns
•   Care of exterior, paint, boots, windows
•   After re-painting
        –   Bonding points
        –   Composites
        –   Flight controls
        –   Placards
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Passenger Door


•   Extremely important in Winter when salt and other corrosive de-
    ice materials are on the flightline
                                                             Lift and clean sill plate
                                                             regularly to prevent FOD &
                                                             corrosion damage to the door
                                                             hinge


                                                             Drain Holes must be clean to
                                                             prevent moisture build-up and
                                                             possible corrosion this is very
                                                             important in areas where salt
                                                             is used to de-ice ramps




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    Passenger Door


•   This corrosion was a direct result of salt that was used to de-ice
    the aircraft parking ramp being tracked into the aircraft from
    passenger/pilot shoes




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Passenger Door


•   1.25” strip in the center
    with dense foam under
    the door side and carpet
    on the step side
•   Maintenance Stand
•   Door seal condition



                                                                     8.25”
                                                                     8.25”

                                                             17.5”
                                                             17.5”




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Brakes


•   Brake wear pin indicator must be checked with brakes/parking
    brake applied




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Landing Gear Struts


•   Clean strut with 5606
    after each flight or prior
    to re-fueling




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Main Landing Gear


•   Tire condition and pressure
    60-63 psi
•   The proximity switch’s are
    susceptible to static
    discharge interference if
    corroded or poorly bonded




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2007 POPA Convention




Cargo Door Area

          Check for coffee cup in                         Never close cargo door
          cupholder prior to opening                      unless handle is stowed




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2007 POPA Convention




Cargo Door Area


•   Cargo door hardware,
    frame & seal condition
    and security


•   Hydraulic Reservoir filler
    port


•   Caution
    System under pressure




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Empennage Access


•   Verify Drain Hole is
    un-obstructed
•   Check for evidence of
    debris or standing
    water
•   Visually inspect
    condition of the
    pressure dome and
    protective net




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2007 POPA Convention




Vertical Stabilizer



                                                              Crack area can
                                                             be on either side
                                                               and may be
                                                                covered by
                                                                  fairing


Wear between shear
plate (C) and strap
  (D) Could allow
vibration and cause
 Vert Stab skin to
        crack
                                  Vertical Stab Repairs
                                Recommended SB 55-002
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Lightning Strike


•   Obvious damage




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Lightning Strike


•   Hidden damage




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Composite Parts




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Composite Parts


•   Always have damaged
    composites repaired as
    soon as possible, to
    minimize repair cost
    and avoid complete
    replacement


•   Caution:
    Do not handle raw
    composites



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Miscellaneous

        De-ice boot Mx, Windows, Emer                Install propeller anchors, on -47 control
        Exit Pin, AOA/Pitot Probe covers                  lock removal is recommended




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Miscellaneous




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Wing De-Ice Boots Operation




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PT6A-67B Engine




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North America Corrosion Zones




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Inlet Case Corrosion




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Compressor & Turbine Wash


•   A motoring wash is done at 10 to 25% Ng
•   The water or the cleaning mixture, depending on ambient
    temperature is injected into the engine intake at a rate of 2 to 3
    gal/minute (7.6 to 11.3 l/minute)
•   Washing during a motoring cycle makes sure emulsion fluid
    remains in liquid form
•   Note: Watch your starter limitations




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2007 POPA Convention




Compressor & Turbine Wash
•   The 3 Types of Washes are:
     –Compressor desalination wash
       •   Essentially used to remove salt deposits, however, light dirt deposits may also be
           removed
       •   Wash fluid is drinking quality water, provided minimum standards are met. (Ref. P&W
           MM)
    –Compressor turbine desalination wash
      • Used to remove salt deposits from the blades
      • The wash fluid is the same as for a compressor wash
      • It is strongly recommended this procedure be done when operating in salt laden
        atmosphere
      • When desalination washes are done in conjunction with each other, it is essential that
        the compressor wash be done first
    –Compressor        performance recovery wash
       •   Uses approved chemical additives to remove more stubborn deposits which cannot be
           removed during normal desalination washes
       •   This method should only be done when engine performance loss is noticeable or trend
           monitoring dictates
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2007 POPA Convention




Engine Compartment


      Inspect Gen 2 belt for tension,                   Check engine oil on shut down
           condition & security                         and look for evidence of leaks

                                                             CT Wash
                                                              fitting




                                                        Fire LOOP




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2007 POPA Convention




Nose Section




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Nose Section




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Web sites & E-Handouts


•   MMEL
•   PDA performance calculator
•   EIS
•   Publication Revision status
•   De-Ice boot Care
•   Service Center list
•   P&W
•   Trend Group
•   CAMP
•   Pilatus web store
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Information Leaflets


•   High Altitude Field Performance
•   High Temperature Performance
•   Operations From Prepared Unpaved Surfaces




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In Closing


•   Know Thy Service provider
•   Anyone wanting the previous E-handouts please provide your
    Name and E-mail address
•   Any comments or suggestions how we may improve are always
    welcome
•   Thank You For Attending 2007 POPA Convention
•   As Always “Fly Safe”
•   Questions? and Answers


•   This presentation is for familiarization purposes only and is not meant to supplement the P.O.H. or any other approved Pilatus manual




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2007 POPA Convention




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