Growler systems: Engine

The flashcards below were created by user dcbailo on FreezingBlue Flashcards.

  1. The engine turbofans
         a. 
         b. 
         c. 
         d.
    • a. low bypass
    • b. axial-flow
    • c. twin-spool
    • d. with after burner
  2. How many compressor stages
    • 3 stage low pressure
    • 7 stage high pressure
  3. MIL thrust
    13,900 lb
  4. MAX thrust
    20,700 lb
  5. FADEC, what does it stand for
    full authority digital engine control
  6. When the throttle is at or above IDLE, the FADEC transfers control to the other channel only if...
    the requested channel's health is no worse than the channel in control.
  7. FADEC power source prior to engine start
    Battery powers CH A of both FADEC's
  8. When N2 reaches ... rpm during start,the ... comes online and powers both channels of its corresponding FADEC
    When N2 reaches 10% rpm during start,the engine driven alternator comes online and powers both channels of its corresponding FADEC
  9. With both engines operating, each ... is the primary source of FADEC power with the aircraft's ... as backup.
    With both engines operating, each engine driven alternator is the primary source of FADEC power with the aircraft's 28 vdc essential bus as backup.
  10. When both channels of a FADEC are powered after initial start, the FADEC automatically switches operation to ...
    When both channels of a FADEC are powered after initial start, the FADEC automatically switches operation to the channel which was not in control during the last flight/engine run.
  11. ... seconds after reaching idle power, the FADEC attempts to switch to the ... to verify that backup power is available. If backup power is inadequate/inoperative, the FADEC declares a ... and sets a 6A8 or 6C8 MSP code
    Ten seconds after reaching idle power, the FADEC attempts to switch to the 28 vdc essential bus to verify that backup power is available. If backup power is inadequate/inoperative, the FADEC declares a channel degrade (dual channel line out) and sets a 6A8 or 6C8 MSP code
  12. These degrade indications appear if the first engine is started with the corresponding ... OFF, and requires a FADEC reset to restore normal engine indications.
    These degrade indications appear if the first engine is started with the corresponding GEN switch OFF, and requires a FADEC reset to restore normal engine indications.
  13. Engine status NORM
    Engine performance is normal.
  14. Engine status PERF90
    10% or less thrust loss and/or slower engine transients. Afterburner is not inhibited.
  15. Engine status AB FAIL
    No afterburner capability
  16. Engine status THRUST
    Engine thrust is limited to between 40% and 90% and significantly slower transients.
  17. Engine status IDLE
    Engine is limited to idle power only.
  18. Engine status SHUTDOWN
    Engine automatically shut down.
  19. FADEC/ Engine degrade advisories:
    Inflight:
         1. 
         2. .
         3. 

    On the ground or below 80 KCAS after landing:
         1. 
         2. 
         3. 
         4.
    • Inflight:
    •      1. FADEC and BIT advisories.
    •      2. ENG STATUS — NORM.
    •      3. OP GO indication for the affected engine channel on the BIT/HYDRO MECH display.

    • On the ground or below 80 KCAS after landing:
    •      1. FADEC and BIT advisories.
    •      2. ENG STATUS — NORM.
    •      3. DEGD replaces OP GO for the affected engine channel on the BIT/HYDRO MECH display.
    •      4. Both CH A and CH B lined out on the ENG display.
  20. FADEC OP GO inflight should be considered ...
    FADEC OP GO inflight should be considered informative and should not mandate a mission abort.
  21. FADEC reset
    When a throttle is OFF, the corresponding FADEC uses a channel change request as a FADEC software reset.
  22. a FADEC reset (should/should not) be attempted, particularly airborne, as any degrade in ENG STATUS is most likely indicative of ...
    a FADEC reset should not be attempted, particularly airborne, as any degrade in ENG STATUS is most likely indicative of the failure of a mechanical component.
  23. The FADEC provides simultaneous control of the main and afterburner igniters via the engine driven alternator and ignition exciter. Ignition (both main engine and afterburner) is commanded whenever:
         1.
         2.
         3.
         4.
    • The FADEC provides simultaneous control of the main and afterburner igniters via the engine driven alternator and ignition exciter. Ignition (both main engine and afterburner) is commanded whenever:
    •      1. N2 rpm is between 10% and 45% during engine start.
    •      2. Flameout occurs.
    •      3. Throttle is advanced into afterburner, remaining on until afterburner light off is sensed.
    •      4. Any wing pylon mounted A/A or forward firing A/G weapon is launched. Ignition remains on for 5 seconds.
  24. Oil pressure transducer and oil pressure switch, what do they do
    The transducer provides an oil pressure value for display in the cockpit.

    The oil pressure switch provides an additional source to confirm the presence of oil pressure if the oil pressure transducer fails.
  25. If a L or R OIL PR caution is set with a valid cockpit readout, ... .If the cockpit readout is zero with no caution set, ...
    If a L or R OIL PR caution is set with a valid cockpit readout, actual engine oil pressure is below scheduled limits.If the cockpit readout is zero with no caution set, the oil pressure transducer has failed and the pressure switch is inhibiting the caution.
  26. With ... and ..., the FADEC commands ground idle by reducing the engine compressor discharge pressure (CDP) (typically a slight decrease in N2 rpm) from the inflight idle setting.
    With WonW and airspeed below 80 knots, the FADEC commands ground idle by reducing the engine compressor discharge pressure (CDP) (typically a slight decrease in N2 rpm) from the inflight idle setting.
  27. Alternate idle schedules are deactivated with...
         1. 
         2.
         3.
         4.
    • 1. WonW
    • 2. when spin recovery mode is engaged
    • 3. inflight refueling probe extended
    • 4. landing gear are extended
  28. The fan speed lockup system prevents inlet instability (buzz) at high Mach by holding engine speed and airflow at military power levels when the throttle(s) are retarded below MIL. Speed lockup is activated when the aircraft accelerates above Mach ... and deactivated when the aircraft decelerates below Mach ...
    The fan speed lockup system prevents inlet instability (buzz) at high Mach by holding engine speed and airflow at military power levels when the throttle(s) are retarded below MIL. Speed lockup is activated when the aircraft accelerates above Mach 1.23 and deactivated when the aircraft decelerates below Mach 1.18.
  29. If the FADEC detects a stall or flameout condition, ... terminates afterburner operation in both engines when airspeed is greater than ...
    If the FADEC detects a stall or flameout condition, supersonic engine thrust limiting (SETLIM) terminates afterburner operation in both engines when airspeed is greater than 1.7M
  30. The reduced authority thrust system (RATS) reduces the wind‐over‐deck required for carrier landings by ...
    The reduced authority thrust system (RATS) reduces the wind‐over‐deck required for carrier landings by rapidly reducing thrust at the beginning of a successful arrestment, reducing the energy absorbed by the arresting gear. 
  31. RATS operation can be overridden by ...
    RATS operation can be overridden by advancing the throttles to full afterburner (THA within 2° of the MAX stop).
  32. ABLIM will reduce MAX fuel flow from ... to about ...
    ABLIM will reduce MAX fuel flow from 35,000 to 45,000 pph to about 25,000 pph
  33. When anti‐ice air is flowing, N2 rpm increases approximately ..., and EGT increases approximately...
    When anti‐ice air is flowing, N2 rpm increases approximately 2%, and EGT increases approximately 5 °C.
  34. During engine start, advancing the throttles from OFF to IDLE opens the ... and, when commanded by the ..., provides fuel flow to the engines.
    During engine start, advancing the throttles from OFF to IDLE opens the engine fuel control shutoff valves and, when commanded by the FADEC, provides fuel flow to the engines.
  35. The ATC system has two operating modes: ...
    The ATC system has two operating modes: approach and cruise.
  36. The system automatically modulates engine thrust between ... power in order to maintain ... in the approach mode or ... in the cruise mode.
    The system automatically modulates engine thrust between flight IDLE and MIL power in order to maintain on‐speed angle of attack (AOA) in the approach mode or calibrated airspeed (existing at the time of engagement) in the cruise mode.
  37. Pressing and releasing the ATC button on the left throttle engages the approach mode with ... and the cruise mode with ....
    Pressing and releasing the ATC button on the left throttle engages the approach mode with the FLAP switch in HALF or FULL and the cruise mode with the FLAP switch in AUTO.
  38. ATC automatically disengages for...
    • Either mode:
    •    *Any ATC system internal failure.
    •    *ATC button failure. FADEC failure.
    •    *FCC CH 2 or CH 4 failure.
    •    *Backdrive failure.
    •    *THA split greater than 3° for more than 1 second.
    •    *FLAP switch position change between AUTO and HALF or FULL.

    • Approach mode only:
    •    *AOA, pitch rate, or NZ sensor failure.
    •    *Bank angle in excess of 70°.
    •    *Flap blowup at 250 KCAS.
    •    *Gain ORIDE selection.
    •    *Weight‐on‐wheels.

    • Cruise mode only:
    •    *FCC calibrated airspeed failure.
Author
ID
317847
Card Set
Growler systems: Engine
Description
Engine system
Updated
Show Answers