2A553B Cumulative CDC Pretest
Cumulative Pretest containing information from Volumes 1-5 of 2A553B CDCs.
- 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.
Questions: 266 | Attempts: 9547 | Last updated: Mar 22, 2022
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