2A553B Vol. 5 Pretest

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| By Kotadod

Kotadod

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Quizzes Created: 6 | Total Attempts: 2,788

Questions: 100 | Attempts: 367 | Updated: Mar 22, 2023

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Questions and Answers

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.
Correct Answer
C. 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.

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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.
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.

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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.
Correct Answer
C. 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.

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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.
Correct Answer
C. Bob weight.

Explanation
The bob weight is a component of the C-5 elevator control system that provides the pilot with feel forces as a function of normal acceleration. It is responsible for simulating the sensation of the aircraft's movement and acceleration, allowing the pilot to have a better sense of control and responsiveness. The bob weight adjusts its position based on the aircraft's acceleration, creating the appropriate force feedback for the pilot. This helps the pilot in making precise adjustments and maintaining control of the aircraft during flight.

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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.
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.

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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.
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.

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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.
Correct Answer
C. Trim actuator.

Explanation
The trim actuator is responsible for repositioning the neutral point of the preloaded centering bungee after the C-5 rudder pedals have been displaced to a desired trim position. The centering bungee alone cannot perform this task. Toggle switches and crank are not mentioned in the question and are therefore not relevant to the explanation.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
C. Tail rotor.

Explanation
The tail rotor of a helicopter is designed specifically to counteract the tendency of the aircraft to spin about the vertical axis. This is known as the helicopter's yawing motion. The tail rotor produces a sideways force that counteracts the torque generated by the main rotor, allowing the helicopter to maintain its heading and prevent unwanted spinning. The other options, such as the rudder and ailerons, are control surfaces used in fixed-wing aircraft and do not directly counteract the spinning motion of a helicopter.

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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.
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.

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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.
Correct Answer
B. 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.

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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.
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.

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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.
Correct Answer
C. 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.

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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.
Correct Answer
C. 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.

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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.
Correct Answer
D. 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.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
C. 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.

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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.
Correct Answer
D. 1.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP.

Explanation
The correct answer is 1.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP. This answer indicates the specific angles at which the limit switches on the screw drive unit of a C-5 aircraft will cut off electrical power. When the horizontal stabilizer reaches 1.5 degrees nose down or 6.0 degrees nose up, the limit switches will activate and stop the power flow to the screw drive unit.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
C. Mechanical linkage.

Explanation
The co-pilot stick controls the B-1B aircraft roll by using a mechanical linkage. This means that the co-pilot's input on the stick is directly transmitted to the control surfaces of the aircraft, allowing them to roll in the desired direction. The stability control augmentation system and other components may assist in maintaining stability and enhancing the co-pilot's control, but the primary mechanism for controlling the roll is the mechanical linkage.

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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.
Correct Answer
D. Rudder pedals and yaw-trim.

Explanation
During stability control augmentation system (SCAS) operation, the B-1B upper and intermediate rudders get their primary position signals from the rudder pedals and yaw-trim. This means that the position of the rudders is determined by the input from the pilot's rudder pedals and the yaw-trim system. The SCAS system then uses this information to provide additional control and stability to the aircraft. The control sticks and SCAS also play a role in the overall control of the aircraft, but they are not directly responsible for providing the primary position signals for the rudders.

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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.
Correct Answer
A. Greater than 61 degrees and airspeed greater than 60 knots.

Explanation
The fairings on the B-1B can move up and down automatically when the wing sweep is greater than 61 degrees and the airspeed is greater than 60 knots. This means that at a certain wing sweep angle and airspeed, the fairings will be activated to move.

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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.
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.

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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.
Correct Answer
C. Inboard spoilers are forced into the down position.

Explanation
When the roll master servo cylinder output linkage in the mechanical roll control system on the B-1B is disconnected, the inboard spoilers are forced into the down position. This means that the spoilers located closer to the center of the aircraft are pushed downward. This action helps to increase the drag on the wing, which in turn helps to reduce the lift and roll the aircraft in the desired direction. Disconnecting the roll master servo cylinder output linkage disables the normal control of the inboard spoilers, causing them to be forced into the down position.

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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.
Correct Answer
C. 1,2, and 4 hydraulic systems.

Explanation
The correct answer is 1, 2, and 4 hydraulic systems. This means that hydraulic power to the left and right inboard spoiler servo cylinders on the B-1B is supplied by hydraulic systems 1, 2, and 4.

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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.
Correct Answer
B. Wing sweep >35 degrees or Mach >0.5.

Explanation
The correct answer is "Wing sweep >35 degrees or Mach >0.5." This means that in order to produce the "dead-band" signal on the B-1B, the wing sweep must be greater than 35 degrees or the Mach number must be greater than 0.5. The "dead-band" signal is a combination of signals from the spoiler controller and these specific conditions must be met for it to be produced.

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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.
Correct Answer
D. Outboard spoilers retract to full down position.

Explanation
Placing the spoiler switch in the OFF position in the B-1B roll control-outboard spoilers system results in the outboard spoilers retracting to the full down position.

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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.
Correct Answer
D. Position the roll trim switch laterally.

Explanation
To activate the actual roll trim commands on the B-1B, you need to position the roll trim switch laterally. This means that you need to move the switch left or right in order to adjust the roll trim. The other options mentioned, such as placing the switch to norm or alter, or positioning the switch longitudinally, are not correct methods for activating the roll trim commands on the B-1B.

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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.
Correct Answer
A. Mach

Explanation
The inboard spoilers on the B-1B roll trim system provide roll trim when Mach = 1.0 and Norm mode is selected.

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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'.
Correct Answer
C. 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.

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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.
Correct Answer
C. Mechanically controlled and hydromechanically actuated.

Explanation
The correct answer is mechanically controlled and hydromechanically actuated. This means that the yaw control system on the B-1B bomber aircraft is controlled by mechanical means, such as cables and linkages, and is actuated using a combination of mechanical and hydraulic systems. The mechanical control allows for precise manipulation of the yaw control surfaces, while the hydromechanical actuation provides the necessary power and force to move these surfaces effectively.

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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.
Correct Answer
D. Yaw SCAS and nosewheel steering.

Explanation
The rudder pedals on the B-1B mechanical yaw control system provide electrical positioning information for the yaw stability control augmentation system (SCAS) and nosewheel steering. This means that the movement of the rudder pedals is used to determine the desired direction of the aircraft and to control the yaw stability through the SCAS. Additionally, the positioning information from the rudder pedals is also used for nosewheel steering, which allows the pilot to steer the aircraft on the ground.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
A. Limited to +/- 10 degrees.

Explanation
The rudder movement of the B-1B during normal aircraft flight is limited to +/- 10 degrees.

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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.
Correct Answer
B. 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.

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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.
Correct Answer
D. From the flight control trim panel yaw trim left/right switch.

Explanation
During ALTER mode on the B-1B, the yaw trim signals applied to the actuators originate from the flight control trim panel yaw trim left/right switch.

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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.
Correct Answer
A. 2453A06.

Explanation
The correct answer is 2453A06.

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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.
Correct Answer
D. 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.

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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.
Correct Answer
D. 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.

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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.
Correct Answer
B. Electrical control of the horizontal stabilizers in pitch and roll.

Explanation
The correct answer is "Electrical control of the horizontal stabilizers in pitch and roll." This means that if the pilot's stick in the mechanical pitch control system is isolated due to a failure in the linkage, the co-pilot can still fly the B-1B aircraft using electrical controls to adjust the horizontal stabilizers in both pitch and roll.

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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.
Correct Answer
A. Tension regulator bungees.

Explanation
The correct answer is tension regulator bungees. In the B-1B mechanical pitch control system, thermal changes can cause the pitch cable to lengthen. The tension regulator bungees are designed to compensate for this lengthening by maintaining the proper tension in the cable. This ensures that the pitch control system remains responsive and accurate, allowing for effective control of the aircraft's pitch.

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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.
Correct Answer
B. Overcome friction in the mechanical push-pull system.

Explanation
The correct answer is overcome friction in the mechanical push-pull system. In the B-1B mechanical pitch system, the pitch control command is transmitted through a mechanical push-pull system. Friction can occur in this system, which can make it difficult to move the control stick. The pitch master hydraulic servo cylinder amplifies the control command to overcome this friction and ensure smooth movement of the control stick. This allows for easier and more precise control of the aircraft's pitch.

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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.
Correct Answer
D. Pitch centering bungees place the horizontal stabilizers into the center position.

Explanation
If the pitch master hydraulic servo cylinder in the B-1B mechanical pitch control system is disconnected, the pitch centering bungees will take over and place the horizontal stabilizers into the center position. This is because the pitch centering bungees are designed to automatically center the horizontal stabilizers when there is no hydraulic input from the pitch master servo cylinder.

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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.
Correct Answer
A. 20 degrees up and 10 degrees down at a maximum travel rate of 25 degrees per second.

Explanation
The correct answer is 20 degrees up and 10 degrees down at a maximum travel rate of 25 degrees per second. This means that the leading-edge surface travel of the horizontal stabilizers on the B-1B pitch control subsystem can move up to 20 degrees in the upward direction and 10 degrees in the downward direction. The maximum travel rate is 25 degrees per second, indicating the speed at which the stabilizers can move.

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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.
Correct Answer
B. After the aircraft is in flight.

Explanation
The correct answer is "after the aircraft is in flight." This means that the pitch control subsystem linkage shaker motors on the B-1B are only enabled once the aircraft has taken off and is airborne. It suggests that these motors are not active on the ground or during pre-flight preparations.

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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.
Correct Answer
D. DAU 4.

Explanation
The B-1B central integrated test system monitors the speed of the pitch control subsystem linkage shaker motors through DAU 4. This means that DAU 4 is responsible for collecting and transmitting data related to the speed of the motors. The other options (DAUs 1, 2, and 2 and 4) are not mentioned in relation to monitoring the speed of the motors, indicating that they are not the correct answer.

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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.
Correct Answer
A. Is disabled.

Explanation
During alternate mode of operation of the B-1B pitch trim system, the trim controller in the automatic flight control system is disabled. This means that the trim controller is not functioning or active during this mode. The reason for this could be to allow manual control of the pitch trim or to prevent any interference or conflict with other systems or controls. Without the trim controller being enabled, the pitch trim actuator would not be controlled automatically and any adjustments would need to be made manually by the pilot or flight crew.

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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.
Correct Answer
B. Trim switch on the flight control auxiliary panel.

Explanation
During the STANDBY mode of operation, the pitch trim actuator receives the pitch trim-up command from the trim switch on the flight control auxiliary panel. This indicates that the trim switch on the flight control auxiliary panel is responsible for sending the pitch trim-up command to the pitch trim actuator during the STANDBY mode.

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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.
Correct Answer
D. Flight control auxiliary panel.

Explanation
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 flight control auxiliary panel.

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Current Version
Mar 22, 2023

Quiz Edited by
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Jun 22, 2009

Quiz Created by
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2A553B Vol. 5 Pretest

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

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

(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?

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

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

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

(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?

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

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

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

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

(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...

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

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

(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?

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

(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...

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

(808) The co-pilot stick controls the B-1B aircraft roll by using the stability control augmentation system and...

(808) During stability control augmentation system (SCAS) operation, the B-1B upper and intermediate rudders get their primary position signals from the...

(808) The conditions that allow the fairings on the B-1B to move up and down automatically are a wing sweep...

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

(809) When the roll master servo cylinder output linkage in the mechanical roll control system on the B-1B is disconnected, the...

(809) On the B-1B, hydraulic power to the left and right inboard spoiler servo cylinders is supplied by the...

(810) On the B-1B, what signals are combined with the roll command signals inside the spoiler controller to produce the "dead-band" signal?

(810) In the B-1B roll control-outboard spoilers system, what is the result of placing the spoiler switch in the OFF position?

(811) To activate the actual roll trim commands on the B-1B, you...

(811) When do the inboard spoilers on the B-1B roll trim system provide roll trim?

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

(812) The mechanical yaw control system on the B-1B is...

(812) On the B-1B mechanical yaw control system, the rudder pedals provide electrical positioning information for the...

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

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

(813) What is the rudder movement of the B-1B during normal aircraft flight?

(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?

(814) During ALTER mode on the B-1B, the yaw trim signals applied to the actuators originate...

(814) Which power control assembly supplies the operating power to the yaw trim actuators on the B-1B?

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

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

(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?

(815) Lengthening of the pitch cable in the B-1B mechanical pitch control system due to thermal changes is compensated for by the...

(815) On the B-1B mechanical pitch system, the pitch control command is amplified by the pitch master hydraulic servo cylinder to...

(815) If the pitch master hydraulic servo cylinder in the B-1B mechanical pitch control system is disconnected, the...

(815) On the B-1B pitch control subsystem, the leading-edge surface travel of the horizontal stabilizers is limited to...

(816) The pitch control subsystem linkage shaker motors on the B-1B are enabled...

(816) The B-1B central integrated test system monitors the speed of the pitch control subsystem likage shaker motors through...

(817) During alternate mode of operation of the B-1B pitch trim system, the trim controller in the automatic flight control system...

(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...

(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...