2A553B Vol. 5 Pretest

Reviewed by Editorial Team

The ProProfs editorial team is comprised of experienced subject matter experts. They've collectively created over 10,000 quizzes and lessons, serving over 100 million users. Our team includes in-house content moderators and subject matter experts, as well as a global network of rigorously trained contributors. All adhere to our comprehensive editorial guidelines, ensuring the delivery of high-quality content.

Learn about Our Editorial Process

| By Kotadod

Kotadod

Community Contributor

Quizzes Created: 6 | Total Attempts: 2,788

| Attempts: 367

Questions

Feedback

During the Quiz End of Quiz

Difficulty

Easy First Hard First Sequential

1/100 Questions

(804) What part of a helicopter is designed to counter the tendency of the aircraft to spin about the vertical axis?
- Rudder.
- Ailerons.
- Tail rotor.
- Main rotor.

About This Quiz

This pretest assesses knowledge of the C-5 aircraft's control systems, including aileron cable systems, roll control, elevator control, and pilot assistance mechanisms.

Quiz Preview

2.

(801) On the C-5, what converts the input signal from the aileron cable system to a proportional output signal to the flight spoilers?
- Centering device.
- Override bungee.
- Mix box.
- Flaps.
Correct Answer

A. Mix box.

Explanation

The mix box is responsible for converting the input signal from the aileron cable system to a proportional output signal to the flight spoilers. It is a crucial component that helps to control and coordinate the movement of the spoilers based on the pilot's input through the aileron system. The mix box ensures that the spoilers move in proportion to the aileron input, allowing for precise control and stabilization of the aircraft during flight.

Rate this question:
3.

(804) What effect does raising the collective have on the main rotor of a helicopter?
- Lift increases.
- Lift decreases.
- Airspeed increases.
- Airspeed decreases.
Correct Answer

A. Lift increases.

Explanation

Raising the collective of a helicopter increases the pitch angle of the rotor blades. This increased pitch angle creates more lift by increasing the angle of attack of the blades, allowing the helicopter to generate more upward force and lift. Consequently, raising the collective increases the overall lift produced by the main rotor of the helicopter.

Rate this question:
4.

(804) What do the cyclic and collective flight controls use to change the pitch of the rotor blades?
- Swash plate.
- Foot pedals.
- Rudder.
- Cyclic.
Correct Answer

A. Swash plate.

Explanation

The cyclic and collective flight controls use the swash plate to change the pitch of the rotor blades. The swash plate is a mechanism that allows the pilot to tilt the rotor blades asymmetrically (cyclic control) or collectively (collective control) to control the pitch and lift of the helicopter. By manipulating the swash plate, the pilot can change the angle of attack of the rotor blades, thereby changing the pitch and controlling the helicopter's movement in different directions.

Rate this question:
5.

(805) Each C-5 slat surface is extended and retracted by two...
- Variable flap drive roller carriages.
- Variable slat drive roller carriages.
- Telescoping ballscrew actuators.
- Telescoping slat drive limiters.
Correct Answer

A. Telescoping ballscrew actuators.

Explanation

The correct answer is telescoping ballscrew actuators. These actuators are responsible for extending and retracting each C-5 slat surface. They use a combination of telescoping mechanisms and ballscrew technology to achieve this movement. The ballscrew actuators provide precise control and reliable operation for the slat surfaces.

Rate this question:
6.

(818) If a failure should occur in the output channel A, the C-5 stability augmentation system...
- Switches to channel B and remains engaged.
- Remains in channel A with reduced accuracy.
- Remains in channel A and disengages the system.
- Switches to channel B and disengages the system.
Correct Answer

A. Switches to channel B and remains engaged.

Explanation

If a failure should occur in the output channel A, the C-5 stability augmentation system switches to channel B and remains engaged. This means that if there is a problem with channel A, the system automatically switches to channel B to ensure the stability augmentation system continues to function. It does not disengage the system but rather remains engaged to provide the necessary stability.

Rate this question:
7.

(807) On the C-5 horizontal stabilizer pitch trim system, hydraulic motor torque is transferred to the nut and screw drives through a...
- Step-down transformer.
- Torque synchro.
- Gear train.
- Lever.
Correct Answer

A. Gear train.

Explanation

The correct answer is gear train. In the C-5 horizontal stabilizer pitch trim system, the hydraulic motor torque is transferred to the nut and screw drives through a gear train. A gear train is a system of gears that transmit power and motion from one component to another. In this case, the gear train helps to transfer the torque from the hydraulic motor to the nut and screw drives, allowing for the adjustment of the horizontal stabilizer pitch trim.

Rate this question:
8.

(819) The hydraulic manifold on the C-5 yaw augmentation system is equipped with...
- A solenoid-operated shutoff valve (SOV), hydraulic pressure switch (HPS), electrohydraulic valve (EHV), and linear variable differential transformer (LVDT).
- An SOV, automatic throttle system, EHV, and LVDT.
- A pressure data converter, HPS, EHV, and LVDT.
- And SOV, HPS, EHV, and pilot assist cable servo.
Correct Answer

A. A solenoid-operated shutoff valve (SOV), hydraulic pressure switch (HPS), electrohydraulic valve (EHV), and linear variable differential transformer (LVDT).

Explanation

The correct answer is the first option, which states that the hydraulic manifold on the C-5 yaw augmentation system is equipped with a solenoid-operated shutoff valve (SOV), hydraulic pressure switch (HPS), electrohydraulic valve (EHV), and linear variable differential transformer (LVDT). This means that the manifold has components that allow for the control and regulation of hydraulic pressure, as well as the measurement of linear variable differential. The other options do not include all of these necessary components.

Rate this question:
9.

(801) On the C-5 roll control system, what provides positive system centering with no force applied to the control wheel?
- Spring.
- Servo.
- Cable.
- Beam.
Correct Answer

A. Spring.

Explanation

The correct answer is Spring. In the C-5 roll control system, the spring provides positive system centering with no force applied to the control wheel. This means that the spring helps to keep the control wheel in a neutral or centered position, without any external force being applied. The spring acts as a mechanical component that ensures the control wheel returns to its neutral position when not being actively manipulated by the pilot.

Rate this question:
10.

(803) On the C-5, simultaneous operation of the rudder trim control switches is required to provide...
- Two power sources to the trim actuator.
- Power and ground to the trim actuator.
- A discrete pulse to the yaw computer.
- Two grounds to the yaw damper.
Correct Answer

A. Power and ground to the trim actuator.

Explanation

Simultaneous operation of the rudder trim control switches is required to provide power and ground to the trim actuator. This means that both switches need to be activated at the same time in order to supply the necessary electrical power and ground connection to the trim actuator. This ensures that the trim actuator receives the correct signals to adjust the rudder trim properly.

Rate this question:
11.

(818) All three augmentation systems on the C-5 are...
- Single channel failure protected.
- Fail-operational and fail-safe.
- Fail-operational only.
- Fail-safe only.
Correct Answer

A. Fail-operational and fail-safe.

Explanation

The correct answer is fail-operational and fail-safe. This means that all three augmentation systems on the C-5 are designed to continue operating even in the event of a failure, ensuring the safety and reliability of the aircraft.

Rate this question:
12.

(820) Which is not a C-5 lateral augmentation system interface?
- Very-high frequency control panel.
- Inertial navigation system.
- Master caution.
- Autopilot.
Correct Answer

A. Very-high frequency control panel.

Explanation

The very-high frequency control panel is not a C-5 lateral augmentation system interface. The other options, such as the inertial navigation system, master caution, and autopilot, are all components that can be part of a C-5 lateral augmentation system interface. However, the very-high frequency control panel is not directly related to the lateral augmentation system interface.

Rate this question:
13.

(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?
- Maintenance.
- Continuous.
- Postflight.
- Preflight.
Correct Answer

A. Continuous.

Explanation

Continuous built-in test is designed to detect a fault and shut down the flight control set before a hardover occurs on the KC-135. This means that the test is continuously monitoring the system during flight and will take action to prevent a hardover, which is a sudden and uncontrollable movement of the flight controls. The continuous built-in test is an important safety feature that helps to ensure the proper functioning of the flight control system and prevent potential accidents or malfunctions.

Rate this question:
14.

(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...
- Ailerons.
- Rudder pedals.
- Force transducer.
- Ailerons and spoilers.
Correct Answer

A. Rudder pedals.

Explanation

In the C-17A electronic flight control system, the rudder trim actuator is responsible for moving the rudder in response to rudder trim commands. Additionally, it also moves the rudder pedals. This means that when the pilot adjusts the rudder trim, not only does the rudder move, but the position of the rudder pedals also changes. The rudder pedals are an important control surface that allow the pilot to control the yawing motion of the aircraft, so it makes sense that they would be affected by rudder trim commands.

Rate this question:
15.

(805) The flap position indicator on the C-5 is a dial-type instrument that shows flap position in...
- Degrees; 0-60.
- Degrees; 0-100.
- Percentage; 0-60.
- Percentage; 0-100.
Correct Answer

A. Percentage; 0-100.

Explanation

The flap position indicator on the C-5 is a dial-type instrument that shows flap position in percentage from 0 to 100.

Rate this question:
16.

(807) When the electric trim switches for the C-5 horizontal stabilizer are actuated together, electrical continuity is provided by...
- Dual power relays.
- Power and ground.
- Backup battery power.
- Bipolar synchro transmitters.
Correct Answer

A. Power and ground.

Explanation

When the electric trim switches for the C-5 horizontal stabilizer are actuated together, electrical continuity is provided by power and ground. This means that both the power source and the ground connection are necessary for the electric trim switches to function properly. The power source supplies the necessary electrical energy, while the ground connection completes the circuit and allows the current to flow. Without both power and ground, the switches would not be able to provide the electrical continuity needed for their operation.

Rate this question:
17.

(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?
- 95; 80.
- 75; 60.
- 50; 40.
- 20; 15.
Correct Answer

A. 50; 40.

Explanation

The correct answer is 50; 40. This means that the maximum torque of the pilot assist cable servo provides approximately 50% assistance to the pitch axis and 40% assistance to the roll axis.

Rate this question:
18.

(804) Which flight control is used to maneuver the helicopter left or right, and forward or aft, while hovering?
- Yoke.
- Cyclic.
- Collective.
- Foot pedals.
Correct Answer

A. Cyclic.

Explanation

The cyclic control is used to maneuver the helicopter left or right, and forward or aft, while hovering. It is a control stick located between the pilot's legs and is used to tilt the rotor disc in the desired direction. By tilting the cyclic, the pilot can change the pitch of the rotor blades at different points in their rotation, allowing for control of the helicopter's movement in all directions while hovering. The yoke is typically used in fixed-wing aircraft, the collective controls the overall pitch of the rotor blades, and the foot pedals control the tail rotor for yaw control.

Rate this question:
19.

(811) The maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to...
- 53 degrees, 55 minutes (').
- 56 degrees, 37'.
- 57 degrees, 57'.
- 61 degrees, 57'.
Correct Answer

A. 57 degrees, 57'.

Explanation

The correct answer is 57 degrees, 57'. This means that the maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to 57 degrees, 57 minutes.

Rate this question:
20.

(815) In the B-1B mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished...
- Symmetrically by the pilot control stick only.
- Asymmetrically by the pilot control stick only.
- Asymmetrically by the co-pilot control stick only.
- Symmetrically by the pilot and co-pilot control sticks.
Correct Answer

A. Symmetrically by the pilot and co-pilot control sticks.

Explanation

In the B-1B mechanical pitch control subsystem, the normal mechanical control of the horizontal stabilizers is achieved symmetrically by both the pilot and co-pilot control sticks. This means that both the pilot and co-pilot have the ability to control the horizontal stabilizers simultaneously and in the same manner.

Rate this question:
21.

(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?
- High-pass.
- Low-pass.
- Greenfield.
- Body-bend.
Correct Answer

A. Body-bend.

Explanation

The correct answer is "Body-bend." The yaw augmentation system uses a filter to block any rate gyro signals that may be developed due to the normal bending of the C-5 aircraft body during flight. This filter is specifically designed to address the issue of body bending and prevent it from affecting the yaw augmentation system.

Rate this question:
22.

(823) On the KC-135, the output of the angular accelerometer in the flight control set processor is used for damping what oscillations?
- Aileron.
- Elevator.
- Dutch roll.
- Trim stabilizer.
Correct Answer

A. Dutch roll.

Explanation

The output of the angular accelerometer in the flight control set processor on the KC-135 is used to dampen Dutch roll oscillations. Dutch roll is an undesirable yawing and rolling oscillation that can occur in aircraft, particularly those with swept wings. Damping these oscillations helps to stabilize the aircraft and improve its handling characteristics.

Rate this question:
23.

(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...
- Turn knob.
- Pitch wheel.
- Air control unit sensor.
- Angular accelerometer.
Correct Answer

A. Turn knob.

Explanation

The flight control set processor roll command module on the KC-135 provides outputs to roll the aircraft in response to inputs from the turn knob. This suggests that the turn knob is used to control the roll movement of the aircraft. The other options, such as the pitch wheel, air control unit sensor, and angular accelerometer, are not mentioned in relation to the roll command module, indicating that they are not directly involved in controlling the roll of the aircraft.

Rate this question:
24.

(819) The C-5 yaw augmentation (Y/A) system provides yaw damping, turn coordination, Y/A manual rudder trim, and...
- Attitude hold.
- Altitude hold.
- Dutch roll damping.
- Divergence control.
Correct Answer

A. Dutch roll damping.

Explanation

The C-5 yaw augmentation (Y/A) system provides various functions including yaw damping, turn coordination, Y/A manual rudder trim, and dutch roll damping. Dutch roll is an oscillatory motion that can occur in aircraft, characterized by a combination of yawing and rolling movements. The yaw augmentation system helps to dampen this motion, reducing its effects and improving the stability and control of the aircraft. Therefore, the correct answer is dutch roll damping.

Rate this question:
25.

(829) On the KC-135 flight control set, the GLIDE SLOPE ARM annunciator remains illuminated until...
- The GLIDE SLOPE CAP annunciator goes out.
- ALT HOLD or MACH HOLD are engaged.
- The GLIDE SLOPE beam is captured.
- The localizer beam is captured.
Correct Answer

A. The GLIDE SLOPE beam is captured.

Explanation

The correct answer is "the GLIDE SLOPE beam is captured." This means that the GLIDE SLOPE ARM annunciator will remain illuminated until the aircraft has successfully captured the GLIDE SLOPE beam. Once the beam is captured, the annunciator will go out. This is an important indication for the pilots to know that the aircraft is properly aligned with the glide slope and can continue the approach safely.

Rate this question:
26.

(802) What component of the C-5 elevator control system assists the pilot in overcoming cable system friction?
- Pilot assist cable servo.
- Centering spring.
- Bob weight.
- Cable.
Correct Answer

A. Pilot assist cable servo.

Explanation

The pilot assist cable servo is a component of the C-5 elevator control system that helps the pilot overcome cable system friction. It is designed to reduce the effort required by the pilot to control the elevator by compensating for any friction in the cable system. This servo system assists in providing smooth and responsive control of the elevator, making it easier for the pilot to maneuver the aircraft.

Rate this question:
27.

(822) The rudder power on the KC-135 flight control set must be on before the...
- Roll axis is engaged.
- Yaw axis is engaged.
- Pitch axis is engaged.
- Lateral axis is engaged.
Correct Answer

A. Yaw axis is engaged.

Explanation

The correct answer is yaw axis is engaged. The rudder power on the KC-135 flight control set needs to be on before the yaw axis is engaged. The yaw axis controls the left and right movement of the aircraft's nose, which is primarily controlled by the rudder. Therefore, it is important to have the rudder power on before engaging the yaw axis to ensure proper control and maneuverability of the aircraft.

Rate this question:
28.

(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...
- Parity.
- Polarity.
- Amplitude.
- Frequency.
Correct Answer

A. Frequency.

Explanation

A change in pressure input on the air control unit sensor pressure data converter of the KC-135 aircraft is reflected as a change in frequency on the output. This means that the frequency of the output signal will vary depending on the pressure input.

Rate this question:
29.

(827) On the KC-135, the erection time of the gyro in the flight control set is...
- 1 - 1 1/2 minutes.
- 2 - 3 minutes.
- 5 - 10 minutes.
- More than 10 minutes.
Correct Answer

A. 1 - 1 1/2 minutes.

Explanation

The correct answer is 1 - 1 1/2 minutes. This means that the erection time of the gyro in the flight control set on the KC-135 is relatively quick, taking only around 1 to 1 1/2 minutes. This suggests that the process of setting up and aligning the gyro is efficient and does not require a significant amount of time.

Rate this question:
30.

(839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?
- Weight-on-wheels.
- Forward relay unit.
- Digital remote unit.
- System control unit.
Correct Answer

A. System control unit.

Explanation

The system control unit is responsible for telling the system interface unit what mode has been selected in the H-60 altitude hold/hover stabilization system. It acts as the central control unit for the system, receiving input from various components and providing the necessary commands to maintain the desired altitude or hover. The weight-on-wheels component detects whether the helicopter is on the ground or in the air, the forward relay unit controls the forward flight of the helicopter, and the digital remote unit allows for remote control of the system. However, none of these components specifically determine the selected mode.

Rate this question:
31.

(825) On the KC-135, what type of output device is used by the flight control set flight controller turn knob?
- Synchro.
- Solenoid switch.
- Variable resistor.
- Control transformer.
Correct Answer

A. Variable resistor.

Explanation

The flight control set flight controller turn knob on the KC-135 uses a variable resistor as its output device. A variable resistor is a type of electrical component that allows for the adjustment of resistance in a circuit. In this case, the variable resistor is used to control and adjust the flight controls of the aircraft.

Rate this question:
32.

(826) On the KC-135, the flight control set servomotors are connected to the aircraft control cables via the...
- Trim actuator.
- Jackscrew assembly.
- Surface control assembly.
- Drum and bracket assembly.
Correct Answer

A. Drum and bracket assembly.

Explanation

The flight control set servomotors on the KC-135 are connected to the aircraft control cables through the drum and bracket assembly. This assembly allows for the transfer of motion from the servomotors to the control cables, which in turn control the movement of the aircraft's flight control surfaces. The drum and bracket assembly ensures a smooth and efficient transfer of motion, allowing the pilot to manipulate the flight controls effectively.

Rate this question:
33.

(834) In the C-17A electronic flight control system, control surface position feedback is provided by dual...
- Rotary variable displacement transducers (RVDT) in the hydraulic actuators.
- Linear variable displacement transducers (LVDT) in the hydraulic actuators.
- RVDTs in the integrated flight control module.
- LVDTs in the integrated flight control module.
Correct Answer

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

Explanation

In the C-17A electronic flight control system, control surface position feedback is provided by linear variable displacement transducers (LVDT) in the hydraulic actuators. LVDTs are commonly used to measure linear displacement and are well-suited for this application. They provide accurate and reliable feedback on the position of the control surfaces, allowing the flight control system to make precise adjustments as needed. Using LVDTs in the hydraulic actuators ensures that the control surface position is accurately monitored and controlled during flight operations.

Rate this question:
34.

(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?
- Switch.
- Spring.
- Valve.
- Cam.
Correct Answer

A. Spring.

Explanation

The correct answer is Spring. In the wing spoiler cable system of the C-5 aircraft, the spring serves as a safety device that closes the affected spoiler panels when a cable or pushrod is disconnected. The spring provides tension and ensures that the spoiler panels are in the correct position for optimal aerodynamic performance and safety.

Rate this question:
35.

(813) Before the B-1B mechanical yaw limiter system can be placed in the limited mode, the...
- Slats in or left/right main gear must be uplocked.
- Slats in and left/right main gear must be uplocked.
- Flaps out or left/right main gear must be downlocked.
- Flaps out and left/right main gear must be downlocked.
Correct Answer

A. Slats in and left/right main gear must be uplocked.

Explanation

The correct answer is "slats in and left/right main gear must be uplocked." This means that both the slats and the left/right main gear must be in the uplocked position in order for the B-1B mechanical yaw limiter system to be placed in the limited mode.

Rate this question:
36.

(832) To provide automatic pitch trim for the C-130, the trim tab adapter of the E-4 automatic flight control system moves the...
- Aileron.
- Trim tab.
- Elevator.
- Stabilizer.
Correct Answer

A. Trim tab.

Explanation

The correct answer is trim tab. The trim tab adapter of the E-4 automatic flight control system moves the trim tab to provide automatic pitch trim for the C-130. The trim tab is a small surface attached to the trailing edge of the elevator. By adjusting the position of the trim tab, the system can help maintain the desired pitch attitude of the aircraft, reducing the need for constant manual control input from the pilot.

Rate this question:
37.

(802) What component of the C-5 elevator control system provides the pilot with feel forces as a function of impact pressure?
- Variable feel unit.
- Centering spring.
- Bob weight.
- Cable.
Correct Answer

A. Variable feel unit.

Explanation

The variable feel unit is the component of the C-5 elevator control system that provides the pilot with feel forces as a function of impact pressure. This means that it adjusts the resistance or force feedback that the pilot feels when operating the elevator controls based on the impact pressure experienced by the aircraft. The variable feel unit helps the pilot maintain control and awareness of the aircraft's movements by providing appropriate tactile feedback.

Rate this question:
38.

(805) The four positions called out on the C-5 flap handle console are...
- DOWN, T/O 40, T/O AND APP, and LANDING.
- DOWN, T/O 80, T/O AND APP, and LANDING.
- UP, T/O 40, T/O AND APP, and LANDING.
- UP, T/O 80, T/O AND APP, and LANDING.
Correct Answer

A. UP, T/O 40, T/O AND APP, and LANDING.

Explanation

The correct answer is UP, T/O 40, T/O AND APP, and LANDING. This is because the positions on the C-5 flap handle console are described in the order of their location from top to bottom. "UP" indicates that the flaps are fully retracted, "T/O 40" means that the flaps are set to a 40% takeoff position, "T/O AND APP" suggests that the flaps are set for both takeoff and approach, and "LANDING" indicates that the flaps are fully extended for landing.

Rate this question:
39.

(812) On the B-1B mechanical yaw control system, the two sets of rudder control pedals are interconnected...
- With one bellcrank and two push-pull rods.
- Through two bellcranks and push-pull rods.
- With tension regulator bungees and bellcranks.
- To one another with idler arms and push-pull rods.
Correct Answer

A. Through two bellcranks and push-pull rods.

Explanation

The correct answer is "through two bellcranks and push-pull rods." The explanation for this answer is that the B-1B mechanical yaw control system connects the two sets of rudder control pedals using two bellcranks and push-pull rods. This setup allows for synchronized movement of the rudder control pedals, ensuring coordinated yaw control during flight.

Rate this question:
40.

(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?
- Cam.
- Brake.
- Bellcrank.
- Output shaft.
Correct Answer

A. Brake.

Explanation

The correct answer is brake. On the B-1B, the brake component of the yaw limiter actuator motor B restricts the movement of the motor during excessive aircraft vibrations. This brake helps to stabilize the motor and prevent any unwanted movement that could be caused by vibrations.

Rate this question:
41.

(820) During manual flight, the roll damping gain of the lateral augmentation system on the C-5 is...
- 0.
- 1.
- 2.
- 3.
Correct Answer

A. 0.

Explanation

The roll damping gain of the lateral augmentation system on the C-5 during manual flight is 0. This means that the system does not provide any additional damping or stability assistance to the aircraft's roll motion. The pilot has full control over the roll movement without any automated assistance from the lateral augmentation system.

Rate this question:
42.

(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 shaker signal.
- An axis hardover.
- An FCS shutdown.
- An axis disengagement.
Correct Answer

A. An axis hardover.

Explanation

Cross-channel monitoring in the flight control set processor of the flight control set (FCS) on the KC-135 is designed to prevent a single processor failure from causing an axis hardover. This means that if one processor fails, the cross-channel monitoring system will detect the failure and prevent the control system from causing an uncommanded and potentially dangerous movement of one of the aircraft's control axes. This ensures the safety and stability of the aircraft during flight.

Rate this question:
43.

(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...
- Processor.
- Control panel.
- Flight controller.
- Status/test panel.
Correct Answer

A. Processor.

Explanation

The correct answer is processor. 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 processor. The processor is responsible for processing and controlling the flight control system, including maintaining the desired mode switches in the ON position. The control panel, flight controller, and status/test panel do not directly supply the voltage for this purpose.

Rate this question:
44.

(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?
- ALT HOLD.
- LOCALIZER.
- MACH HOLD.
- GLIDE SLOPE.
Correct Answer

A. ALT HOLD.

Explanation

When the KC-135 aircraft is experiencing a vertical velocity of 3,500 feet per minute, the engagement of the ALT HOLD mode of operation is automatically inhibited. This means that the aircraft's autopilot system will not be able to maintain a constant altitude during this particular vertical velocity condition. The ALT HOLD mode is designed to hold the aircraft at a specific altitude, but it is disabled when the vertical velocity reaches 3,500 feet per minute.

Rate this question:
45.

(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...
- Engages into the mode the pilot has selected.
- Causes the F/D to switch to the A/P mode.
- Automatically disengaged the F/D mode.
- Engages into the same mode as the F/D.
Correct Answer

A. Engages into the same mode as the F/D.

Explanation

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 engages into the same mode as the F/D. This means that the autopilot will follow the guidance and commands provided by the flight director, allowing for a seamless transition and coordination between the two systems. This ensures that the aircraft maintains the desired flight path and adheres to the pilot's instructions as indicated by the flight director.

Rate this question:
46.

(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?
- HOV.
- HOV/RA.
- RAD/ALT.
- BAR/ALT.
Correct Answer

A. HOV.

Explanation

The correct answer is HOV. On the H-60 altitude hold/hover stabilization system, the HOV mode uses all three axes' accelerometers and the copilot's vertical gyro for reference. This mode helps in maintaining a stable altitude and hover position by utilizing the data from these sensors.

Rate this question:
47.

(808) On the B-1B, which indication on the surface position/command indicator uses a single window for display of position information?
- Slats.
- Flaps.
- Spoilers.
- Speedbrakes.
Correct Answer

A. Slats.

Explanation

The correct answer is Slats. Slats are a type of high-lift device on the B-1B aircraft that are used to increase lift during takeoff and landing. The surface position/command indicator is a display that provides information about the position of various control surfaces on the aircraft. In this case, the slats indication on the surface position/command indicator uses a single window for display of position information. This means that the position of the slats can be easily monitored by the pilot using this indicator.

Rate this question:
48.

(814) What determines the direction the motor is driven to position the yaw trim bellcrank on the B-1B?
- The position of the travel limit switches.
- Whether the brake is engages or disengaged.
- The signal from the proximity switch assemblies.
- Which power control assembly relay is energized or deenergized.
Correct Answer

A. Which power control assembly relay is energized or deenergized.

Explanation

The direction in which the motor is driven to position the yaw trim bellcrank on the B-1B is determined by which power control assembly relay is energized or deenergized. This means that the relay being activated or deactivated controls the direction of the motor. The position of the travel limit switches, whether the brake is engaged or disengaged, and the signal from the proximity switch assemblies do not play a role in determining the direction of the motor.

Rate this question:
49.

(820) The lateral augmentation system on the C-5 provides roll damping, dutch roll damping, and...
- Wing camber control.
- Vertical lift distribution.
- Spiral divergence control.
- Roll coriolis compensation.
Correct Answer

A. Spiral divergence control.

Explanation

The lateral augmentation system on the C-5 provides roll damping and dutch roll damping, which help stabilize the aircraft during roll and yaw motions. Additionally, the system also provides spiral divergence control, which helps prevent the aircraft from entering a dangerous spiral dive. This control is crucial for maintaining the stability and safety of the aircraft during flight. Wing camber control, vertical lift distribution, and roll coriolis compensation are not directly related to the lateral augmentation system's functions.

Rate this question:

Quiz Review Timeline (Updated): Mar 22, 2023 +

Our quizzes are rigorously reviewed, monitored and continuously updated by our expert board to maintain accuracy, relevance, and timeliness.

Current Version
Mar 22, 2023

Quiz Edited by
ProProfs Editorial Team
Jun 22, 2009

Quiz Created by
Kotadod

Recent Quizzes

Aircraft Pneumatic System and Bleed Air Management Quiz Aircraft Pneumatic System and Bleed Air Management Quiz

An APU Quiz for all aspiring pilots and plan technicians out there! An APU Quiz for all aspiring pilots and plan technicians out there!

Airbus A320 Engine System Quiz! Airbus A320 Engine System Quiz!

A 320 SYS HYDRAULIC , AND ICE / RAIN , LANDING GEAR. A 320 SYS HYDRAULIC , AND ICE / RAIN , LANDING GEAR.

A 320 SYS FUEL // FIGHT CONTROLS A 320 SYS FUEL // FIGHT CONTROLS

A 320 SYS PNEUMATIC AND COMMUNICATIONS A 320 SYS PNEUMATIC AND COMMUNICATIONS

Back to top

2A553B Vol. 5 Pretest

(804) What part of a helicopter is designed to counter the tendency of the aircraft to spin about the vertical axis?

Quiz Preview

(801) On the C-5, what converts the input signal from the aileron cable system to a proportional output signal to the flight spoilers?

(804) What effect does raising the collective have on the main rotor of a helicopter?

(804) What do the cyclic and collective flight controls use to change the pitch of the rotor blades?

(805) Each C-5 slat surface is extended and retracted by two...

(818) If a failure should occur in the output channel A, the C-5 stability augmentation system...

(807) On the C-5 horizontal stabilizer pitch trim system, hydraulic motor torque is transferred to the nut and screw drives through a...

(819) The hydraulic manifold on the C-5 yaw augmentation system is equipped with...

(801) On the C-5 roll control system, what provides positive system centering with no force applied to the control wheel?

(803) On the C-5, simultaneous operation of the rudder trim control switches is required to provide...

(818) All three augmentation systems on the C-5 are...

(820) Which is not a C-5 lateral augmentation system interface?

(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?

(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...

(805) The flap position indicator on the C-5 is a dial-type instrument that shows flap position in...

(807) When the electric trim switches for the C-5 horizontal stabilizer are actuated together, electrical continuity is provided by...

(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?

(804) Which flight control is used to maneuver the helicopter left or right, and forward or aft, while hovering?

(811) The maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to...

(815) In the B-1B mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished...

(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?

(823) On the KC-135, the output of the angular accelerometer in the flight control set processor is used for damping what oscillations?

(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...

(819) The C-5 yaw augmentation (Y/A) system provides yaw damping, turn coordination, Y/A manual rudder trim, and...

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

(802) What component of the C-5 elevator control system assists the pilot in overcoming cable system friction?

(822) The rudder power on the KC-135 flight control set must be on before the...

(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...

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

(839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?

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

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

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

(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?

(813) Before the B-1B mechanical yaw limiter system can be placed in the limited mode, the...

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

(802) What component of the C-5 elevator control system provides the pilot with feel forces as a function of impact pressure?

(805) The four positions called out on the C-5 flap handle console are...

(812) On the B-1B mechanical yaw control system, the two sets of rudder control pedals are interconnected...

(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?

(820) During manual flight, the roll damping gain of the lateral augmentation system on the C-5 is...

(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...

(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...

(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?

(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...

(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?

(808) On the B-1B, which indication on the surface position/command indicator uses a single window for display of position information?

(814) What determines the direction the motor is driven to position the yaw trim bellcrank on the B-1B?

(820) The lateral augmentation system on the C-5 provides roll damping, dutch roll damping, and...