2A553B Cumulative CDC Pretest

270 Questions | Total Attempts: 292

SettingsSettingsSettings
CDC Quizzes & Trivia

Cumulative Pretest containing information from Volumes 1-5 of 2A553B CDCs.


Questions and Answers
  • 1. 
    (839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?
    • A. 

      System control unit.

    • B. 

      Weight-on-wheels.

    • C. 

      Digital remote unit.

    • D. 

      Forward relay unit.

  • 2. 
    (838) On the H-60 altitude hold/hover stabilization system, what mode uses all three axes' accelerometers and the copilot's vertical gyro for reference?
    • A. 

      HOV/RA.

    • B. 

      RAD/ALT.

    • C. 

      HOV.

    • D. 

      BAR/ALT.

  • 3. 
    (837) Which control panel on the H-60 altitude hold/hover stabilization (AHHS) system contains an altitude select knob?
    • A. 

      Hover engage panel.

    • B. 

      Auto flight control panel.

    • C. 

      AHHS mode select panel.

    • D. 

      AHHS system control unit.

  • 4. 
    (836) When the autopilot (A/P) of the electronic flight control system on a C-17A aircraft is engaged after the flight director (F/D) is already engaged, the A/P...
    • A. 

      Automatically disengaged the F/D mode.

    • B. 

      Causes the F/D to switch to the A/P mode.

    • C. 

      Engages into the same mode as the F/D.

    • D. 

      Engages into the mode the pilot has selected.

  • 5. 
    (836) To reduce structural loads on the C-17A vertical stabilizer, the flight control computers of the electronic flight control system limit rudder deflection as a function of...
    • A. 

      Airspeed and altitude.

    • B. 

      Static pressure.

    • C. 

      Airspeed.

    • D. 

      Altitude.

  • 6. 
    (835) In the C-17A electronic flight control system, the primary pitch input originates in the...
    • A. 

      Control stick sensor assembly.

    • B. 

      Flight control computer.

    • C. 

      Pitch stick position sensor.

    • D. 

      Pitch autopilot actuator.

  • 7. 
    (834) In the C-17A electronic flight control system, control surface position feedback is provided by dual...
    • A. 

      Rotary variable displacement transducers (RVDT) in the hydraulic actuators.

    • B. 

      Linear variable displacement transducers (LVDT) in the hydraulic actuators.

    • C. 

      RVDTs in the integrated flight control module.

    • D. 

      LVDTs in the integrated flight control module.

  • 8. 
    (834) In response to rudder trim commands, the rudder trim acutator of the C-17A electronic flight control system moves the rudder, as well as the...
    • A. 

      Ailerons.

    • B. 

      Ailerons and spoilers.

    • C. 

      Rudder pedals.

    • D. 

      Force transducer.

  • 9. 
    (834) In the C-17A aircraft's electronic flight control system, the flight control computers directly control the ailerons,...
    • A. 

      Spoilers, elevators, and rudders.

    • B. 

      Spoilers, elevators, rudders, and horizontal stabilizer.

    • C. 

      Elevators, rudders, and horizontal stabilizer.

    • D. 

      Flaps, slats, spoilers, elevators, and rudders.

  • 10. 
    (833) In the rudder control loop of the E-4 automatic flight control system, the heading reference of the C-130 aircraft is locked by...
    • A. 

      Shorting the output of the turn motor amplifier.

    • B. 

      Shorting the output of the heading synchro.

    • C. 

      Driving the rudder synchro to follow the output of the heading synchro.

    • D. 

      Aligning the rudder synchro with the heading synchro.

  • 11. 
    (832) To provide automatic pitch trim for the C-130, the trim tab adapter of the E-4 automatic flight control system moves the...
    • A. 

      Aileron.

    • B. 

      Trim tab.

    • C. 

      Elevator.

    • D. 

      Stabilizer.

  • 12. 
    (831) If the C-130 aircraft is not wings-level during operation of the E-4 automatic flight control system, the aircraft can be returned to wings-level by using the...
    • A. 

      TURN knob.

    • B. 

      AIL trim knob.

    • C. 

      PITCH knob.

    • D. 

      Control wheel.

  • 13. 
    (830) On the C-130, the trim indicators on the pedestal controller of the E-4 automatic flight control system represent the output of each...
    • A. 

      Servomotor.

    • B. 

      Servoamplifier.

    • C. 

      Repeatback synchro.

    • D. 

      Servo control generator.

  • 14. 
    (830) On the C-130, the gyro erection system in the E-4 automatic flight control system roll and pitch control...
    • A. 

      Is cut out during commanded turns.

    • B. 

      Operates at a slow rate during initial warm-up.

    • C. 

      Operates at a fast rate after initial warm-up.

    • D. 

      Erects the gyro during all phases of flight.

  • 15. 
    (830) On the C-130, the altitude control on the E-4 automatic flight control system maintains a fixed altitude by controlling the...
    • A. 

      Ailerons.

    • B. 

      Elevators.

    • C. 

      Trim tabs.

    • D. 

      Stabilizer.

  • 16. 
    (829) On the KC-135 flight control set, the GLIDE SLOPE ARM annunciator remains illuminated until...
    • A. 

      The GLIDE SLOPE CAP annunciator goes out.

    • B. 

      ALT HOLD or MACH HOLD are engaged.

    • C. 

      The GLIDE SLOPE beam is captured.

    • D. 

      The localizer beam is captured.

  • 17. 
    (829) The KC-135 flight control set maintains a set Mach number by varying...
    • A. 

      The position of the throttles.

    • B. 

      Fuel flow to the engines.

    • C. 

      The position of the flaps.

    • D. 

      The pitch of the aircraft.

  • 18. 
    (829) On the KC-135, a vertical velocity of 3,500 feet per minute automatically inhibits engagement of what flight control set mode of operation?
    • A. 

      LOCALIZER.

    • B. 

      ALT HOLD.

    • C. 

      MACH HOLD.

    • D. 

      GLIDE SLOPE.

  • 19. 
    (828) On the KC-135, placing the turn knob out of detent causes the NAV/LOC switch on the flight control set tactical air navigation to disengage during the...
    • A. 

      ARM and CAPTURE submodes.

    • B. 

      CAPTURE and TRACK submodes.

    • C. 

      ARM and OVERSTATION submodes.

    • D. 

      TRACK and OVERSTATION submodes.

  • 20. 
    (828) On the KC-135, the flight control set processor roll command module provides outputs to roll the aircraft in response to inputs from the...
    • A. 

      Turn knob.

    • B. 

      Pitch wheel.

    • C. 

      Air control unit sensor.

    • D. 

      Angular accelerometer.

  • 21. 
    (827) On the KC-135, the erection time of the gyro in the flight control set is...
    • A. 

      1 - 1 1/2 minutes.

    • B. 

      2 - 3 minutes.

    • C. 

      5 - 10 minutes.

    • D. 

      More than 10 minutes.

  • 22. 
    (827) On the KC-135, a change on the pressure input of the air control unit sensor pressure data converter is represented on the output as a change in...
    • A. 

      Parity.

    • B. 

      Amplitude.

    • C. 

      Frequency.

    • D. 

      Polarity.

  • 23. 
    (826) On the KC-135, the flight control set servomotors are connected to the aircraft control cables via the...
    • A. 

      Trim actuator.

    • B. 

      Jackscrew assembly.

    • C. 

      Surface control assembly.

    • D. 

      Drum and bracket assembly.

  • 24. 
    (825) On the KC-135, what type of output device is used by the flight control set flight controller turn knob?
    • A. 

      Synchro.

    • B. 

      Variable resistor.

    • C. 

      Solenoid switch.

    • D. 

      Control transformer.

  • 25. 
    (825) On the KC-135, which flight control set mode disengages if the turn knob is turned out of detent after engagement?
    • A. 

      HDG SEL.

    • B. 

      ALT HOLD.

    • C. 

      ROLL AXIS.

    • D. 

      MACH HOLD.

Back to Top Back to top