2A553B Vol. 5 Pretest
Settings
Pretest for CDC 2A553B Upgrade.
- 1.(801) On the C-5, what converts the input signal from the aileron cable system to a proportional output signal to the flight spoilers?
- A.
Centering device.
- B.
Override bungee.
- C.
Mix box.
- D.
Flaps.
- 2.(801) On the C-5 roll control system, what provides positive system centering with no force applied to the control wheel?
- A.
Spring.
- B.
Servo.
- C.
Cable.
- D.
Beam.
- 3.(801) On the C-5, maximum torque of the pilot assist cable servo is adjusted to provide approximately how much assistance in percent to the pitch and roll axes, respectively?
- A.
95; 80.
- B.
75; 60.
- C.
50; 40.
- D.
20; 15.
- 4.(802) What component of the C-5 elevator control system provides the pilot with feel forces as a function of normal acceleration?
- A.
Variable feel unit.
- B.
Centering spring.
- C.
Bob weight.
- D.
Cable.
- 5.(802) What component of the C-5 elevator control system provides the pilot with feel forces as a function of impact pressure?
- A.
Variable feel unit.
- B.
Centering spring.
- C.
Bob weight.
- D.
Cable.
- 6.(802) What component of the C-5 elevator control system assists the pilot in overcoming cable system friction?
- A.
Pilot assist cable servo.
- B.
Centering spring.
- C.
Bob weight.
- D.
Cable.
- 7.(803) On the C-5, what repositions the neutral point of the preloaded centering bungee after the C-5 rudder pedals have been displaced to a desired trim position?
- A.
Centering bungee.
- B.
Toggle switches.
- C.
Trim actuator.
- D.
Crank.
- 8.(803) On the C-5, simultaneous operation of the rudder trim control switches is required to provide...
- A.
Two power sources to the trim actuator.
- B.
Power and ground to the trim actuator.
- C.
A discrete pulse to the yaw computer.
- D.
Two grounds to the yaw damper.
- 9.(804) What part of a helicopter is designed to counter the tendency of the aircraft to spin about the vertical axis?
- A.
Rudder.
- B.
Ailerons.
- C.
Tail rotor.
- D.
Main rotor.
- 10.(804) What effect does raising the collective have on the main rotor of a helicopter?
- A.
Lift increases.
- B.
Lift decreases.
- C.
Airspeed increases.
- D.
Airspeed decreases.
- 11.(804) Which flight control is used to maneuver the helicopter left or right, and forward or aft, while hovering?
- A.
Yoke.
- B.
Cyclic.
- C.
Collective.
- D.
Foot pedals.
- 12.(804) What do the cyclic and collective flight controls use to change the pitch of the rotor blades?
- A.
Swash plate.
- B.
Foot pedals.
- C.
Rudder.
- D.
Cyclic.
- 13.(805) Each C-5 slat surface is extended and retracted by two...
- A.
Variable flap drive roller carriages.
- B.
Variable slat drive roller carriages.
- C.
Telescoping ballscrew actuators.
- D.
Telescoping slat drive limiters.
- 14.(805) The four positions called out on the C-5 flap handle console are...
- A.
DOWN, T/O 40, T/O AND APP, and LANDING.
- B.
DOWN, T/O 80, T/O AND APP, and LANDING.
- C.
UP, T/O 40, T/O AND APP, and LANDING.
- D.
UP, T/O 80, T/O AND APP, and LANDING.
- 15.(805) The flap position indicator on the C-5 is a dial-type instrument that shows flap position in...
- A.
Degrees; 0-60.
- B.
Degrees; 0-100.
- C.
Percentage; 0-60.
- D.
Percentage; 0-100.
- 16.(806) What safety device in the wing spoiler cable system of the C-5 aircraft closes the affected spoiler panels when a cable or pushrod is disconnected?
- A.
Switch.
- B.
Spring.
- C.
Valve.
- D.
Cam.
- 17.(807) On the C-5 horizontal stabilizer pitch trim system, hydraulic motor torque is transferred to the nut and screw drives through a...
- A.
Step-down transformer.
- B.
Torque synchro.
- C.
Gear train.
- D.
Lever.
- 18.(807) With flaps up, the limit switches cut off electrical power to the screw drive unit when the horizontal stabilizer on a C-5 reaches...
- A.
8 percent aircraft NOSE DOWN or 15 percent aircraft NOSE UP.
- B.
5 percent aircraft NOSE DOWN or 12 percent aircraft NOSE UP.
- C.
2.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP.
- D.
1.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP.
- 19.(807) When the electric trim switches for the C-5 horizontal stabilizer are actuated together, electrical continuity is provided by...
- A.
Dual power relays.
- B.
Power and ground.
- C.
Backup battery power.
- D.
Bipolar synchro transmitters.
- 20.(808) The co-pilot stick controls the B-1B aircraft roll by using the stability control augmentation system and...
- A.
Inboard spoilers.
- B.
Outboard spoilers.
- C.
Mechanical linkage.
- D.
Roll gyro differential signals.
- 21.(808) During stability control augmentation system (SCAS) operation, the B-1B upper and intermediate rudders get their primary position signals from the...
- A.
Control sticks.
- B.
SCAS and yaw-trim.
- C.
SCAS and control stick.
- D.
Rudder pedals and yaw-trim.
- 22.(808) The conditions that allow the fairings on the B-1B to move up and down automatically are a wing sweep...
- A.
Greater than 61 degrees and airspeed greater than 60 knots.
- B.
Less than 61 degrees and airspeed greater than 60 knots.
- C.
Greater than 62 degrees and airspeed less than 70 knots.
- D.
Less than 62 degress and airspeed less than 70 knots.
- 23.(808) On the B-1B, which indication on the surface position/command indicator uses a single window for display of position information?
- A.
Slats.
- B.
Flaps.
- C.
Spoilers.
- D.
Speedbrakes.
- 24.(809) When the roll master servo cylinder output linkage in the mechanical roll control system on the B-1B is disconnected, the...
- A.
Inboard and outboard spoilers are forced into the full down position.
- B.
Outboard spoilers are placed in the full up position.
- C.
Inboard spoilers are forced into the down position.
- D.
Pilot control stick is forced to the center position.
- 25.(809) On the B-1B, hydraulic power to the left and right inboard spoiler servo cylinders is supplied by the...
- A.
1 and 4 hydraulic systems.
- B.
2 and 3 hydraulic systems.
- C.
1,2, and 4 hydraulic systems.
- D.
2,3, and 4 hydraulic systems.
- 26.(810) On the B-1B, what signals are combined with the roll command signals inside the spoiler controller to produce the "dead-band" signal?
- A.
Weight-on-wheels, roll rate, and Mach >0.5.
- B.
Wing sweep >35 degrees or Mach >0.5.
- C.
Wing sweep >15 degrees or Mach >1.0.
- D.
Roll rate and wing sweep >35 degrees.
- 27.(810) In the B-1B roll control-outboard spoilers system, what is the result of placing the spoiler switch in the OFF position?
- A.
Speedbrakes are disengaged if weight-on-wheels (WOW) is present.
- B.
Inboard and outboard spoilers retract to full down position.
- C.
Speedbrakes are engaged if WOW is not present.
- D.
Outboard spoilers retract to full down position.
- 28.(811) To activate the actual roll trim commands on the B-1B, you...
- A.
Place the roll trim mode select switch to norm.
- B.
Place the roll trim mode select switch to alter.
- C.
Position the roll trim switch longitudinally.
- D.
Position the roll trim switch laterally.
- 29.(811) When do the inboard spoilers on the B-1B roll trim system provide roll trim?
- A.
Mach
- B.
Mach = 1.0 and Norm mode selected.
- C.
Mach = 0.5 and Norm mode selected.
- D.
Mach >0.99 and Alter mode selected.
- 30.(811) The maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to...
- A.
53 degrees, 55 minutes (').
- B.
56 degrees, 37'.
- C.
57 degrees, 57'.
- D.
61 degrees, 57'.
- 31.(812) The mechanical yaw control system on the B-1B is...
- A.
Electrically and mechanically controlled and actuated.
- B.
Electrically controlled and hydromechanically actuated.
- C.
Mechanically controlled and hydromechanically actuated.
- D.
Hydromechanically controlled and hydroelectrically actuated.
- 32.(812) On the B-1B mechanical yaw control system, the rudder pedals provide electrical positioning information for the...
- A.
Yaw stability control augmentation system (SCAS) and brakes.
- B.
Mechanical yaw, yaw SCAS, and nosewheel steering.
- C.
Nosewheel steering, yaw SCAS, and brakes.
- D.
Yaw SCAS and nosewheel steering.
- 33.(812) On the B-1B mechanical yaw control system, the two sets of rudder control pedals are interconnected...
- A.
With one bellcrank and two push-pull rods.
- B.
Through two bellcranks and push-pull rods.
- C.
With tension regulator bungees and bellcranks.
- D.
To one another with idler arms and push-pull rods.
- 34.(813) Before the B-1B mechanical yaw limiter system can be placed in the limited mode, the...
- A.
Slats in or left/right main gear must be uplocked.
- B.
Slats in and left/right main gear must be uplocked.
- C.
Flaps out or left/right main gear must be downlocked.
- D.
Flaps out and left/right main gear must be downlocked.
- 35.(813) What is the rudder movement of the B-1B during normal aircraft flight?
- A.
Limited to +/- 10 degrees.
- B.
Unlimited to +/- 25 degress.
- C.
Unlimited to +/- 26 degrees.
- D.
Limited to +/- 10 degrees or +/- 25 degrees, depending on the mode of operation.
- 36.(813) On the B-1B, which component of the yaw limiter actuator motor B restricts the movement of the motor from movement during excessive aircraft vibrations?
- A.
Cam.
- B.
Brake.
- C.
Bellcrank.
- D.
Output shaft.
- 37.(814) During ALTER mode on the B-1B, the yaw trim signals applied to the actuators originate...
- A.
From the control stick trim switch.
- B.
In the central integrated test system.
- C.
In the yaw stability control augmentation system.
- D.
From the flight control trim panel yaw trim left/right switch.
- 38.(814) Which power control assembly supplies the operating power to the yaw trim actuators on the B-1B?
- A.
2453A06.
- B.
2454A06.
- C.
2455A05.
- D.
2455A06.
- 39.(814) What determines the direction the motor is driven to position the yaw trim bellcrank on the B-1B?
- A.
The position of the travel limit switches.
- B.
Whether the brake is engages or disengaged.
- C.
The signal from the proximity switch assemblies.
- D.
Which power control assembly relay is energized or deenergized.
- 40.(815) In the B-1B mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished...
- A.
Symmetrically by the pilot control stick only.
- B.
Asymmetrically by the pilot control stick only.
- C.
Asymmetrically by the co-pilot control stick only.
- D.
Symmetrically by the pilot and co-pilot control sticks.
- E.
- 41.(815) What control(s) is/are available for the co-pilot to fly the B-1B aircraft if the pilot's stick in the mechanical pitch control system is isolated due to a failure in the linkage?
- A.
Mechanical control of the horizontal stabilizers in pitch only.
- B.
Electrical control of the horizontal stabilizers in pitch and roll.
- C.
Mechanical and electrical control of the horizontal stabilizers in pitch only.
- D.
Electrical and hydromechanical control of the horizontal stabilizers in pitch and roll.
- 42.(815) Lengthening of the pitch cable in the B-1B mechanical pitch control system due to thermal changes is compensated for by the...
- A.
Tension regulator bungees.
- B.
Forward and aft feel bungees.
- C.
Pitch master hydraulic servo cylinder.
- D.
Left and right override regulator bungees.
- 43.(815) On the B-1B mechanical pitch system, the pitch control command is amplified by the pitch master hydraulic servo cylinder to...
- A.
Isolate the control stick from the pitch SCAS function.
- B.
Overcome friction in the mechanical push-pull system.
- C.
Prevent vibrations induced by the linkage shaker assemby from effecting the stabilizer position.
- D.
Reduce the effort required by the co-pilot to move the control stick when the pilot stick is disconnected.
- 44.(815) If the pitch master hydraulic servo cylinder in the B-1B mechanical pitch control system is disconnected, the...
- A.
Stabilizers are placed in a +10 degree up position.
- B.
Stabilizers are forced to a -10 degree down position.
- C.
Pitch master servo cylinder output is forced to the center position.
- D.
Pitch centering bungees place the horizontal stabilizers into the center position.
- 45.(815) On the B-1B pitch control subsystem, the leading-edge surface travel of the horizontal stabilizers is limited to...
- A.
20 degrees up and 10 degrees down at a maximum travel rate of 25 degrees per second.
- B.
20 degrees up and down at a maximum travel rate of 25 degrees per second.
- C.
25 degrees up and 15 degrees down at a maximum travel rate of 20 degrees per second.
- D.
25 degrees up and down at a maximum travel rate of 20 degrees per second.
- 46.(816) The pitch control subsystem linkage shaker motors on the B-1B are enabled...
- A.
When pitch trim is selected.
- B.
After the aircraft is in flight.
- C.
When power is applied to the aircraft.
- D.
After the electrical multiplexing system enables power control assembly 2454A06.
- 47.(816) The B-1B central integrated test system monitors the speed of the pitch control subsystem likage shaker motors through...
- A.
Data acquisition units (DAU) 1 and 2.
- B.
DAUs 2 and 4.
- C.
DAU 2.
- D.
DAU 4.
- 48.(817) During alternate mode of operation of the B-1B pitch trim system, the trim controller in the automatic flight control system...
- A.
Is disabled.
- B.
Is enabled, but does not control the pitch trim actuator.
- C.
Receives electrical multiplexing system pitch trim-up and pitch trim-down.
- D.
Processes the pitch trim-up/down commands for application to the stability control augmentation system controllers.
- 49.(817) During the STANDBY mode of operation of the B-1B pitch control subsystem, the pitch trim actuator receives the pitch trim-up command from the STANDBY...
- A.
Circuit of the automatic flight control system trim controller.
- B.
Trim switch on the flight control auxiliary panel.
- C.
Contacts of the control stick pitch trim switch.
- D.
Trim switch on the flight control power panel.
- 50.(817) During the STANDBY mode of operation of the B-1B pitch control subsystem, the actual co-pilot pitch trim commands to the stabilizers are provided by the...
- A.
Control stick.
- B.
Flight control trim panel.
- C.
Flight control power panel.
- D.
Flight control auxiliary panel.
- 51.(817) Placing the pitch trim switch to the pitch trim-up position during STANDBY mode of operation of the B-1B pitch control subsystem causes the...
- A.
Stability control augmentation system (SCAS) controllers to command the pitch SCAS servo actuators.
- B.
Automatic flight control system pitch trim controller to enable the pitch trim actuator motor.
- C.
Power control assembly 2455A06 to enable the pitch trim actuator motor.
- D.
SCAS controllers to command the pitch trim actuator motor.
- 52.(817) On the B-1B, what signals are summed by the electrical multiplexing system to illuminate the trim-for-takeoff (TTO) annunciator?
- A.
Roll, yaw, and normal.
- B.
TTO position signals and TTO command.
- C.
Pitch trim and pitch TTO command signals.
- D.
TTO command and pitch trim TTO position.
- 53.(818) All three augmentation systems on the C-5 are...
- A.
Single channel failure protected.
- B.
Fail-operational and fail-safe.
- C.
Fail-operational only.
- D.
Fail-safe only.
- 54.(818) If a failure should occur in the output channel A, the C-5 stability augmentation system...
- A.
Switches to channel B and remains engaged.
- B.
Remains in channel A with reduced accuracy.
- C.
Remains in channel A and disengages the system.
- D.
Switches to channel B and disengages the system.
- 55.(819) The C-5 yaw augmentation (Y/A) system provides yaw damping, turn coordination, Y/A manual rudder trim, and...
- A.
Attitude hold.
- B.
Altitude hold.
- C.
Dutch roll damping.
- D.
Divergence control.
- 56.(819) The hydraulic manifold on the C-5 yaw augmentation system is equipped with...
- A.
A solenoid-operated shutoff valve (SOV), hydraulic pressure switch (HPS), electrohydraulic valve (EHV), and linear variable differential transformer (LVDT).
- B.
An SOV, automatic throttle system, EHV, and LVDT.
- C.
A pressure data converter, HPS, EHV, and LVDT.
- D.
And SOV, HPS, EHV, and pilot assist cable servo.
- 57.(819) What type filter is used in the yaw augmentation system to block any rate gyro signals developed as a result of the normal bending of the C-5 aircraft body from occuring during flight?
- A.
High-pass.
- B.
Low-pass.
- C.
Greenfield.
- D.
Body-bend.
- 58.(819) The maximum rudder displacement the C-5 yaw augmentation system can command from reference is...
- A.
+/- 20 degrees.
- B.
+/- 15 degrees.
- C.
+/- 12 degrees.
- D.
+/- 10 degrees.
- 59.(820) The lateral augmentation system on the C-5 provides roll damping, dutch roll damping, and...
- A.
Wing camber control.
- B.
Vertical lift distribution.
- C.
Spiral divergence control.
- D.
Roll coriolis compensation.
- 60.(820) During manual flight, the roll damping gain of the lateral augmentation system on the C-5 is...
- A.
0.
- B.
1.
- C.
2.
- D.
3.
- 61.(820) Which is not a C-5 lateral augmentation system interface?
- A.
Very-high frequency control panel.
- B.
Inertial navigation system.
- C.
Master caution.
- D.
Autopilot.
- 62.(821) To initiate self-test of the C-5 pitch augmentation system, the four inboard elevator hydraulic power switches on the pilot's overhead panel must be...
- A.
Reset to TEST.
- B.
In the ON position.
- C.
In the OFF position.
- D.
In the NORM position.
- 63.(822) On the KC-135, the turn knob on the flight control set must be in detent before the...
- A.
Roll axis is engaged.
- B.
Yaw axis is engaged.
- C.
Pitch axis is engaged.
- D.
Lateral axis is engaged.
- 64.(822) The rudder power on the KC-135 flight control set must be on before the...
- A.
Roll axis is engaged.
- B.
Yaw axis is engaged.
- C.
Pitch axis is engaged.
- D.
Lateral axis is engaged.
- 65.(822) Automatic disengagement of all three axes of the KC-135 flight control set occurs if an error is detected in the...
- A.
Roll servo loop.
- B.
Yaw servo loop.
- C.
Pitch servo loop.
- D.
Lateral servo loop.
- 66.(822) On the KC-135, the sources of the flight control set (FCS) gyro 1 signals are the INS and...
- A.
Automatic flight control system vertical gyro (VG).
- B.
Pilot's attitude director indicator.
- C.
Flight director.
- D.
FCS VG.
- 67.(823) On the KC-135, cross-channel monitoring in the flight control set processor of the flight control set (FCS) prevents a single processor failure from causing...
- A.
A shaker signal.
- B.
An axis hardover.
- C.
An FCS shutdown.
- D.
An axis disengagement.
- 68.(823) On the KC-135, inputs provided by the inertial navigation system to the flight control set include pitch attitude, roll attitude, and...
- A.
Altitude.
- B.
Heading.
- C.
Airspeed.
- D.
Roll steering.
- 69.(823) On the KC-135, the flight control set modes available when the pitch axis is engaged include ALT HOLD, MACH HOLD, and...
- A.
LOC.
- B.
HDG SEL.
- C.
NAV/LOC.
- D.
GLIDE SLOPE.
- 70.(823) On the KC-135, which built-in test is designed to detect a fault and shut down the flight control set before a hardover occurs?
- A.
Maintenance.
- B.
Continuous.
- C.
Postflight.
- D.
Preflight.
- 71.(823) On the KC-135, the output of the angular accelerometer in the flight control set processor is used for damping what oscillations?
- A.
Aileron.
- B.
Elevator.
- C.
Dutch roll.
- D.
Trim stabilizer.
- 72.(824) On the KC-135, the primary function of the status/test panel is to test the flight control set at what level?
- A.
Field.
- B.
Depot.
- C.
Intermediate.
- D.
Organizational.
- 73.(824) On the KC-135, which button on the status/test panel allows the operator to record an indicated failure in memory?
- A.
VERIFY.
- B.
Up arrow.
- C.
Left arrow.
- D.
Right arrow.
- 74.(824) On the KC-135, which status/test panel button allows the operator to bypass recording a failure?
- A.
VERIFY.
- B.
Up arrow.
- C.
Left arrow.
- D.
Right arrow.
- 75.(825) On the KC-135, the voltage required to hold the flight control set control panel mode switches in the ON position is supplied by the flight control set...
- A.
Processor.
- B.
Control panel.
- C.
Flight controller.
- D.
Status/test panel.
- 76.(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.
- 77.(825) On the KC-135, what type of output device is used by the flight control set flight controller turn knob?
- A.
Synchro.
- B.
Solenoid switch.
- C.
Variable resistor.
- D.
Control transformer.
- 78.(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.
- 79.(827) On the KC-135, a change on the pressure input of the air control unit sensor pressure data converter is represented on the ouput as a change in...
- A.
Parity.
- B.
Polarity.
- C.
Amplitude.
- D.
Frequency.
- 80.(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.
- 81.(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.
- 82.(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.
- 83.(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.
ALT HOLD.
- B.
LOCALIZER.
- C.
MACH HOLD.
- D.
GLIDE SLOPE.
- 84.(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.
- 85.(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.
- 86.(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.
- 87.(830) On the C-130, the gyro erection system in the E-4 automatic flight control system roll and pitch control...
- A.
Operates at a slow rate during initial warm-up.
- B.
Operates at a fast rate after initial warm-up.
- C.
Erects the gyro during all phases of flight.
- D.
Is cut out during commanded turns.
- 88.(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.
Servo control generator.
- B.
Repeatback synchro.
- C.
Servoamplifier.
- D.
Servomotor.
- 89.(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.
PITCH knob.
- C.
Control wheel.
- D.
AIL trim knob.
- 90.(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.
- 91.(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 heading synchro.
- B.
Shorting the output of the turn motor amplifier.
- C.
Aligning the rudder synchro with the heading synchro.
- D.
Driving the rudder synchro to follow the output of the heading synchro.
- 92.(834) In the C-17A aircraft's electronic flight control system, the flight control computers directly control the ailerons,...
- A.
Spoilers, elevators, rudders, and horizontal stabilizer.
- B.
Elevators, rudders, and horizontal stabilizer.
- C.
Flaps, slats, spoilers, elevators, and rudders.
- D.
Spoilers, elevators, and rudders.
- 93.(834) In response to rudder trim commands, the rudder trim actuator of the C-17A electronic flight control system moves the rudder, as well as the...
- A.
Ailerons.
- B.
Rudder pedals.
- C.
Force transducer.
- D.
Ailerons and spoilers.
- 94.(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.
- 95.(835) In the C-17A electronic flight control system, the primary pitch input originates in the...
- A.
Control stick sensor assembly.
- B.
Pitch stick position sensor.
- C.
Pitch autopilot actuator.
- D.
Flight control computer.
- 96.(835) 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.
- 97.(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.
Engages into the mode the pilot has selected.
- B.
Causes the F/D to switch to the A/P mode.
- C.
Automatically disengaged the F/D mode.
- D.
Engages into the same mode as the F/D.
- 98.(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.
- 99.(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.
- B.
HOV/RA.
- C.
RAD/ALT.
- D.
BAR/ALT.
- 100.(839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?
- A.
Weight-on-wheels.
- B.
Forward relay unit.
- C.
Digital remote unit.
- D.
System control unit.
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