1.
(839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?
A. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
3.
(837) Which control panel on the H-60 altitude hold/hover stabilization (AHHS) system contains an altitude select knob?
A. 
B. 
Auto flight control panel.
C. 
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. 
B. 
C. 
D. 
6.
(835) In the C-17A electronic flight control system, the primary pitch input originates in the...
A. 
Control stick sensor assembly.
B. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
21.
(827) On the KC-135, the erection time of the gyro in the flight control set is...
A. 
B. 
C. 
D. 
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. 
B. 
C. 
D. 
23.
(826) On the KC-135, the flight control set servomotors are connected to the aircraft control cables via the...
A. 
B. 
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. 
B. 
C. 
D. 
25.
(825) On the KC-135, which flight control set mode disengages if the turn knob is turned out of detent after engagement?
A. 
B. 
C. 
D.