Embraer 190 - Auxiliary Power Unit

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Embraer 190 - Auxiliary Power Unit - Quiz

AUXILIARY POWER UNIT QUESTIONS MADE FROM THE AOM VOL. 2GOOD LUCK! SANTIAGO STOCKER.


Questions and Answers
  • 1. 
    The Auxiliary Power Unit (APU) is a gas turbine engine located in the airplane tailcone, which provides pneumatic and electrical AC power. The pneumatic power is used for engine starting and to supply bleed air to the air conditioning packs of the Environmental Control System (ECS). An electrical AC generator supplies _____________ to the electrical system.
    • A. 

      220 V 40 kVA

    • B. 

      115 V 40 kVA

  • 2. 
    The APU is automatically monitored and controlled through a dedicated _______ ________ ________ ________ ______ (FADEC) unit.
  • 3. 
    APU EMERGENCY STOP BUTTON (GUARDED) PUSH IN: closes the APU ______________, shutting down the APU with no cooldown period. A white striped bar illuminates on the lower half of the button.
    • A. 

      Fuel shutoff valve

    • B. 

      Air bleed valve

  • 4. 
    When only DC power is available, the DC fuel pump, located in the ______ _____ _____ , provides fuel to the APU.
    • A. 

      Left wing tank

    • B. 

      Right wing tank

  • 5. 
    If AC power is available and the engine is not running, fuel will be provided by the __________ .
    • A. 

      AC fuel pump

    • B. 

      DC fuel pump

  • 6. 
    When the engine is running, the _____ _____ _____ provides fuel to the APU from the right wing tank. However, it is also possible to provide fuel to the APU from the left wing tank via a crossfeed valve.
    • A. 

      Ejector fuel pump

    • B. 

      AC fuel pump

  • 7. 
    The APU supplies bleed air on the ____________. However, it is used primarily as a ground pneumatic source for the air conditioning packs (ECS) and engine starting. The Air Management System (AMS) controls the operation of the APU and engine bleed valves.
    • A. 

      Inflight only

    • B. 

      Ground only

    • C. 

      Ground or inflight

  • 8. 
    A dedicated Full Authority Digital Electronic Control (FADEC) monitors and controls the _______________ sequence, fault detection and APU status.
    • A. 

      Start

    • B. 

      Shutdown

    • C. 

      Start and shutdown

  • 9. 
    The APU is able to supply electrical AC power up to ...
    • A. 

      33000 ft.

    • B. 

      21000 ft.

    • C. 

      15000 ft.

    • D. 

      30000 ft.

  • 10. 
    The APU is able to supply bleed air for engine starting up to ...
    • A. 

      33000 ft.

    • B. 

      21000 ft.

    • C. 

      15000 ft.

    • D. 

      30000 ft.

  • 11. 
    The APU is able to supply bleed air for air conditioning and pressurization up to ...
    • A. 

      33000 ft.

    • B. 

      21000 ft.

    • C. 

      15000 ft.

    • D. 

      30000 ft.

  • 12. 
    Maximum altitude for APU start is ....
    • A. 

      33000 ft.

    • B. 

      21000 ft.

    • C. 

      15000 ft.

    • D. 

      30000 ft.

  • 13. 
    Rotating the APU master switch to ON powers the FADEC and APU fuel shutoff valve opens. NOTE: The SPDA sends power to APU FADEC energization only _____ after its power-up, so APU start is not available before this time period.
    • A. 

      15 s

    • B. 

      30 s

    • C. 

      60 s

  • 14. 
    _______ seconds after APU speed has reached 95%, electrical and pneumatic loading are available. If the APU does not reach proper speed or acceleration rate within the starting cycle time, the APU will automatically shut down.
    • A. 

      Three

    • B. 

      Six

  • 15. 
    GROUND START The FADEC initiates ignition at approximately ____ rpm and the fuel flow after 0.5 s.
    • A. 

      6 %

    • B. 

      30 %

  • 16. 
    The battery ____ energizes the electronic starter controller. After a light off occurs, the FADEC commands the starter to cutout at approximately 50% rpm.
    • A. 

      #1

    • B. 

      #2

  • 17. 
    IN FLIGHT START The FADEC initiates ignition at approximately ____________and the fuel flow after 0.5 s. After a light off occurs, the FADEC commands the starter to cutout at approximately 50% rpm.
    • A. 

      7% to 17% rpm

    • B. 

      17% to 27% rpm

  • 18. 
    Rotating the APU selector knob from ON to OFF initiates a normal APU shutdown, which is monitored and controlled by the FADEC. During a normal shutdown sequence, the APU pneumatic power is removed immediately and the electrical power is removed at the end of a _________ cooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of that period. 
    • A. 

      1 minutes

    • B. 

      2 minutes

    • C. 

      3 minutes

  • 19. 
    The cooldown period is _________ , followed by a spooldown period. The EICAS message APU SHUTTING DOWN disappears at the end of spooldown period.
    • A. 

      1 minute

    • B. 

      3 minutes

  • 20. 
    Turning the APU selector knob back to ON position during the shutdown sequence cancels the shutdown.
    • A. 

      True

    • B. 

      False

  • 21. 
    The FADEC provides automatic APU shutdown protection on ground as follows.
    • A. 

      Overspeed

    • B. 

      Underspeed

    • C. 

      FADEC critical fault

    • D. 

      APU fire

    • E. 

      APU EGT overtemperature

    • F. 

      APU high oil temperature

    • G. 

      APU low oil pressure

    • H. 

      Sensor fail

  • 22. 
    The FADEC provides automatic APU shutdown protection on in flight as follows.
    • A. 

      Overspeed

    • B. 

      Underspeed

    • C. 

      FADEC critical fault

    • D. 

      APU fire

    • E. 

      APU EGT overtemperature

    • F. 

      APU high oil temperature

    • G. 

      APU low oil pressure

    • H. 

      Sensor fail

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