2A852 CDC Volume 5

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Air Force Quizzes & Trivia

Questions and Answers
  • 1. 

    The pilot’s elevator input system is connected to the

    • A.

      Outboard elevators

    • B.

      Inboard elevators

    • C.

      Upper rudder

    • D.

      Lower rudder

    Correct Answer
    B. Inboard elevators
    Explanation
    The pilot's elevator input system is connected to the inboard elevators. This means that when the pilot moves the control input, it will directly affect the movement of the inboard elevators. The inboard elevators are the control surfaces located closer to the center of the aircraft, and they play a crucial role in controlling the pitch of the aircraft. By connecting the pilot's input system to the inboard elevators, the pilot has direct control over the pitch of the aircraft.

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  • 2. 

    The copilot’s elevator input system is connected to the

    • A.

      Outboard elevators

    • B.

      Inboard elevators

    • C.

      Upper rudder

    • D.

      Lower rudder

    Correct Answer
    A. Outboard elevators
    Explanation
    The copilot's elevator input system is connected to the outboard elevators. This means that the copilot has control over the outboard elevators, which are the elevators located on the outer edges of the aircraft's wings. This allows the copilot to adjust the pitch of the aircraft by moving the outboard elevators up or down. The inboard elevators, on the other hand, are located closer to the center of the aircraft and are controlled by the pilot. The upper and lower rudders are not connected to the copilot's elevator input system and are used for controlling the aircraft's yaw.

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  • 3. 

    Control of the aircraft in the yaw axis is accomplished by the

    • A.

      Elevators

    • B.

      Ailerons

    • C.

      Rudders

    • D.

      Spoilers

    Correct Answer
    C. Rudders
    Explanation
    The control of the aircraft in the yaw axis is achieved through the use of rudders. The rudders are located on the vertical stabilizer at the tail of the aircraft. By deflecting the rudders, the pilot can change the direction of the aircraft's nose left or right. This is important for maintaining stability and controlling the aircraft during turns or when dealing with crosswinds. The elevators control the aircraft's pitch, the ailerons control the roll, and the spoilers are used to decrease lift and increase drag.

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  • 4. 

    What type of cable system does the rudder input system incorporate that run from the flight station to the upper and lower rudder servo input quadrants?

    • A.

      Triple cable system.

    • B.

      Single cable system.

    • C.

      Double cable system.

    • D.

      Quadruple cable system

    Correct Answer
    B. Single cable system.
    Explanation
    The rudder input system incorporates a single cable system that runs from the flight station to the upper and lower rudder servo input quadrants. This means that there is only one cable used for transmitting the rudder inputs, providing a simpler and more efficient system compared to multiple cable systems.

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  • 5. 

    When are leading-edge slats and trailing-edge flaps used

    • A.

      Coordinated turns.

    • B.

      Landings and takeoffs

    • C.

      Aileron augmentation

    • D.

      Pitch and yaw maneuvers

    Correct Answer
    B. Landings and takeoffs
    Explanation
    Leading-edge slats and trailing-edge flaps are used during landings and takeoffs. These devices are deployed to increase the lift generated by the wings at lower speeds, allowing the aircraft to maintain lift and control at slower speeds during these critical phases of flight. The increased lift provided by the slats and flaps helps to reduce the aircraft's stall speed, allowing for safer landings and takeoffs.

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  • 6. 

    The slat surface is extended and retracted by

    • A.

      Two telescoping ballscrew actuators.

    • B.

      Three telescoping ballscrew actuators

    • C.

      Two variable slat drive roller carriages

    • D.

      Three variable slat drive roller carriages

    Correct Answer
    A. Two telescoping ballscrew actuators.
    Explanation
    The correct answer is two telescoping ballscrew actuators. These actuators are responsible for extending and retracting the slat surface. The use of two actuators ensures stability and control over the movement of the slat surface. Having only two actuators is sufficient for the task at hand, and there is no need for three actuators or variable slat drive roller carriages.

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  • 7. 

    The flap and slat power package receives hydraulic pressure from the

    • A.

      Number one and number two hydraulic systems

    • B.

      Number one and number four hydraulic systems

    • C.

      Number two and number four hydraulic systems

    • D.

      Number two and number three hydraulic systems

    Correct Answer
    B. Number one and number four hydraulic systems
    Explanation
    The flap and slat power package receives hydraulic pressure from the number one and number four hydraulic systems.

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  • 8. 

    What is not included in the mechanical flight control system?

    • A.

      Cables.

    • B.

      Torque tubes

    • C.

      Push-pull tubes

    • D.

      Electrically powered actuators.

    Correct Answer
    D. Electrically powered actuators.
    Explanation
    The mechanical flight control system includes cables, torque tubes, and push-pull tubes, which are all mechanisms used to transmit control inputs from the pilot to the control surfaces of an aircraft. Electrically powered actuators, on the other hand, are not part of the mechanical system as they use electrical power to move the control surfaces.

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  • 9. 

    Some aircraft incorporate flight control systems that automatically revert to servo-tab control

    • A.

      In case of total electrical system failure

    • B.

      In case of total hydraulic system failure

    • C.

      To limit the external wind forces from damaging the aircraft while it is parked.

    • D.

      To limit the external wind forces from damaging the aircraft while it is tied down.

    Correct Answer
    B. In case of total hydraulic system failure
    Explanation
    In case of total hydraulic system failure, some aircraft incorporate flight control systems that automatically revert to servo-tab control. This means that if the hydraulic system fails, the servo-tabs on the aircraft's control surfaces will take over and provide limited control to the pilot. This is important because without hydraulic power, the pilot would not be able to control the aircraft's movements effectively. The servo-tabs help to maintain some level of control and allow the pilot to safely maneuver the aircraft in such situations.

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  • 10. 

    Hydraulic powered actuators convert hydraulic pressure into

    • A.

      Control surface movements

    • B.

      Artificial stall warning.

    • C.

      Gust lock limit

    • D.

      Fly-by-wire.

    Correct Answer
    A. Control surface movements
    Explanation
    Hydraulic powered actuators are designed to convert hydraulic pressure into mechanical force, allowing them to control the movement of various control surfaces on an aircraft. These control surfaces, such as ailerons, elevators, and rudders, are responsible for maneuvering the aircraft and maintaining stability during flight. By converting hydraulic pressure into controlled movements of these surfaces, hydraulic powered actuators play a crucial role in the overall control and maneuverability of the aircraft.

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  • 11. 

    Artificial feel systems provide

    • A.

      Increased resistance to the flight controls at lower speeds

    • B.

      Decreased resistance to the flight controls at lower speeds.

    • C.

      Increased resistance to the flight controls at higher speeds

    • D.

      Decreased resistance to the flight controls at higher speeds

    Correct Answer
    C. Increased resistance to the flight controls at higher speeds
    Explanation
    Artificial feel systems are designed to provide pilots with a sense of the aerodynamic forces acting on the aircraft. At higher speeds, the aerodynamic forces are stronger, and therefore, the artificial feel system increases resistance to the flight controls. This increased resistance allows pilots to have a better feel of the aircraft's response and improves their ability to make precise control inputs.

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  • 12. 

    Electronic flight control computers can be programmed to prevent undesirable and dangerous characteristics, such as

    • A.

      Stalling.

    • B.

      Gust lock.

    • C.

      Aileron trim.

    • D.

      Artificial feel.

    Correct Answer
    A. Stalling.
    Explanation
    Electronic flight control computers can be programmed to prevent stalling, which is an undesirable and dangerous characteristic in an aircraft. Stalling occurs when the airflow over the wings is disrupted, causing a loss of lift and a sudden decrease in altitude. By detecting the conditions that lead to a stall, the flight control computers can automatically adjust the aircraft's control surfaces and engine power to prevent it from happening. This programming ensures that the aircraft remains within safe flight parameters and reduces the risk of accidents.

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  • 13. 

    On the 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 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 torque and motion from one part of a machine to another. In this case, the gear train is responsible for transferring the torque from the hydraulic motor to the nut and screw drives, allowing for the adjustment of the pitch trim on the horizontal stabilizer.

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  • 14. 

    With flaps up, limit switches cut off electrical power to the screw drive unit when the horizontal stabilizer reaches

    • A.

      1.5° aircraft NOSE DOWN or 6.0° aircraft NOSE UP

    • B.

      1.5° aircraft NOSE DOWN or 8.0° aircraft NOSE UP.

    • C.

      2.5° aircraft NOSE DOWN or 6.0° aircraft NOSE UP.

    • D.

      2.5° aircraft NOSE DOWN or 8.0° aircraft NOSE UP.

    Correct Answer
    A. 1.5° aircraft NOSE DOWN or 6.0° aircraft NOSE UP
    Explanation
    The limit switches are responsible for cutting off electrical power to the screw drive unit when the horizontal stabilizer reaches certain angles. In this case, with the flaps up, the limit switches will cut off power when the aircraft is at 1.5° nose down or 6.0° nose up. This means that if the horizontal stabilizer reaches either of these angles, the power to the screw drive unit will be cut off, ensuring that the stabilizer does not move any further in that direction.

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  • 15. 

    What is energized by simultaneous actuation of the horizontal stabilizer trim control wheel switches?

    • A.

      Flap direction solenoid

    • B.

      Trim direction solenoid

    • C.

      Rudder direction solenoid

    • D.

      Aileron direction solenoid.

    Correct Answer
    B. Trim direction solenoid
    Explanation
    The correct answer is the Trim direction solenoid. The simultaneous actuation of the horizontal stabilizer trim control wheel switches energizes the Trim direction solenoid. This solenoid is responsible for adjusting the trim of the aircraft's horizontal stabilizer, which helps to maintain the desired pitch attitude of the aircraft.

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  • 16. 

    Horizontal stabilizer pitch trim, console switches provide a means of operating the actuator

    • A.

      Generator drive.

    • B.

      Synchro drive

    • C.

      Screw drive.

    • D.

      Nut drive.

    Correct Answer
    C. Screw drive.
    Explanation
    The correct answer is screw drive. Horizontal stabilizer pitch trim console switches use a screw drive mechanism to operate the actuator. This means that the switches control the movement of the actuator by rotating a screw, which in turn moves the stabilizer to adjust the pitch. This type of drive mechanism is commonly used in aircraft systems for its precision and reliability.

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  • 17. 

    Pitch trim position is displayed by a dial-type indicator, incorporating a scale graduated in degrees from

    • A.

      –5° to +15°.

    • B.

      –6° to +14°.

    • C.

      –7° to +13°.

    • D.

      –8° to +12°.

    Correct Answer
    B. –6° to +14°.
    Explanation
    The correct answer is –6° to +14°. This means that the pitch trim position can be displayed on the dial-type indicator within a range of -6° to +14°. This range allows for a greater degree of adjustment in the pitch trim position, allowing for more precise control of the aircraft's pitch.

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  • 18. 

    The pitch trim actuator screw drive and nut drive receive hydraulic power from

    • A.

      Two hydraulic systems operating at 2000 pounds per square inch (PSI).

    • B.

      Two hydraulic systems operating at 3000 pounds per square inch (PSI).

    • C.

      Three hydraulic systems operating at 2000 pounds per square inch (PSI).

    • D.

      Three hydraulic systems operating at 3000 pounds per square inch (PSI).

    Correct Answer
    B. Two hydraulic systems operating at 3000 pounds per square inch (PSI).
    Explanation
    The pitch trim actuator screw drive and nut drive receive hydraulic power from two hydraulic systems operating at 3000 pounds per square inch (PSI). This high pressure allows for efficient and reliable operation of the pitch trim actuator, ensuring precise control of the aircraft's pitch trim. The use of two hydraulic systems adds redundancy and enhances safety, as the failure of one system would still allow the other system to provide power to the actuator.

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  • 19. 

    What flight control surface indicator is designed to display percentage of surface extension?

    • A.

      Flap position indicator

    • B.

      Rudder trim position indicator

    • C.

      Aileron trim position indicator

    • D.

      Horizontal stabilizer trim position indicator

    Correct Answer
    A. Flap position indicator
    Explanation
    The flap position indicator is designed to display the percentage of surface extension. Flaps are used to increase lift and drag during takeoff and landing, and their position can be adjusted to different degrees. The flap position indicator allows pilots to visually monitor the extension of the flaps, ensuring they are set correctly for the desired flight phase.

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  • 20. 

    Synchro position indicating systems convert mechanical shaft angles to

    • A.

      Mechanical shaft degrees

    • B.

      Electrical shaft degrees

    • C.

      Mechanical signals.

    • D.

      Electrical signals

    Correct Answer
    D. Electrical signals
    Explanation
    Synchro position indicating systems convert mechanical shaft angles to electrical signals. This means that the system takes the position of a mechanical shaft and converts it into an electrical signal. This conversion allows for the transmission and processing of the shaft position data in an electrical form, which can be more easily utilized and interpreted by other electronic systems.

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  • 21. 

    What type of operating power is required by a selsyn position indicating system?

    • A.

      26 VAC.

    • B.

      28 VDC.

    • C.

      115 VAC.

    • D.

      120 VDC.

    Correct Answer
    B. 28 VDC.
    Explanation
    A selsyn position indicating system requires 28 VDC (Volts Direct Current) as the operating power.

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  • 22. 

    The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned how many degrees apart?

    • A.

      45

    • B.

      90

    • C.

      120

    • D.

      180

    Correct Answer
    C. 120
    Explanation
    The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned 120 degrees apart. This means that each tap is separated from the other by 120 degrees on the circular resistance winding. This arrangement allows for accurate and precise position indication in the system.

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  • 23. 

    Manual pitch and roll axis attitude adjustments are allowed by the

    • A.

      Flight control augmentation system (FCAS).

    • B.

      Stability augmentation system (SAS).

    • C.

      Flight management system (FMS).

    • D.

      Flight control set (FCS).

    Correct Answer
    D. Flight control set (FCS).
    Explanation
    The correct answer is Flight control set (FCS). The FCS allows for manual pitch and roll axis attitude adjustments. This system is responsible for controlling the aircraft's flight surfaces and ensuring stability and control during flight. It allows the pilot to make precise adjustments to the aircraft's attitude, improving maneuverability and handling. The Flight control augmentation system (FCAS) and Stability augmentation system (SAS) are not responsible for manual adjustments, and the Flight management system (FMS) is not directly involved in controlling the aircraft's attitude.

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  • 24. 

    The flight control set (FCS) roll axis must be engaged for selection of heading select (HDG SEL) or

    • A.

      Mach number hold (MACH HOLD).

    • B.

      Navigation/localizer (NAV/LOC).

    • C.

      Altitude hold (ALT HOLD).

    • D.

      Glide slope (G/S).

    Correct Answer
    B. Navigation/localizer (NAV/LOC).
    Explanation
    The flight control set (FCS) roll axis must be engaged for selection of navigation/localizer (NAV/LOC). This means that in order to select the NAV/LOC mode, the roll axis of the FCS must be engaged. This mode is used for following a selected navigation course or localizer signal, allowing the aircraft to maintain a specific track or follow a specific instrument approach. It is important for the roll axis to be engaged in order to accurately track the desired navigation course or localizer signal.

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  • 25. 

    The flight control set (FCS) pitch axis must be engaged for selection of altitude hold (ALT HOLD) or

    • A.

      Mach number hold (MACH HOLD).

    • B.

      Tactical Air Navigation (TACAN).

    • C.

      Navigation/localizer (NAV/LOC).

    • D.

      Heading select (HDG SEL).

    Correct Answer
    A. Mach number hold (MACH HOLD).
    Explanation
    The flight control set (FCS) pitch axis must be engaged for selection of Mach number hold (MACH HOLD) because this mode allows the aircraft to maintain a specific Mach number, which is the ratio of the aircraft's true airspeed to the speed of sound. The pitch axis of the FCS controls the aircraft's pitch attitude, which is necessary to adjust the aircraft's speed and maintain the desired Mach number. Altitude hold (ALT HOLD), Tactical Air Navigation (TACAN), navigation/localizer (NAV/LOC), and heading select (HDG SEL) are not directly related to controlling the aircraft's Mach number.

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  • 26. 

    Which is not one of the navigation signals that can be selected in the flight control set (FCS) navigation/localizer (NAV/LOC) mode?

    • A.

      Instrument Landing System (ILS).

    • B.

      Tactical Air Navigation (TACAN).

    • C.

      Flight Management System (FMS).

    • D.

      Automatic Direction Finder (ADF).

    Correct Answer
    D. Automatic Direction Finder (ADF).
    Explanation
    The correct answer is Automatic Direction Finder (ADF). In the flight control set (FCS) navigation/localizer (NAV/LOC) mode, the navigation signals that can be selected include Instrument Landing System (ILS), Tactical Air Navigation (TACAN), and Flight Management System (FMS). However, Automatic Direction Finder (ADF) is not one of the navigation signals that can be selected in this mode. ADF is a radio navigation system that determines the direction of a radio signal, but it is not typically used for precision approach and landing guidance like ILS, TACAN, and FMS.

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  • 27. 

    The continuous built-in-test (BIT) monitors and records errors within each axis of operation while the aircraft

    • A.

      Is in flight and the flight control set (FCS) is engaged

    • B.

      Is in flight and the flight control set (FCS) is disengaged

    • C.

      Is on the ground and the flight control set (FCS) is engaged

    • D.

      Is on the ground and the flight control set (FCS) is disengaged.

    Correct Answer
    A. Is in flight and the flight control set (FCS) is engaged
    Explanation
    The continuous built-in-test (BIT) monitors and records errors within each axis of operation while the aircraft is in flight and the flight control set (FCS) is engaged. This means that the BIT system is active and functioning while the aircraft is in motion and the flight control set is being used. This allows for real-time monitoring and detection of any errors or issues that may arise during flight, ensuring the safety and proper functioning of the aircraft's flight control system.

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  • 28. 

    All analog signals that come into the flight control set processor (FCSP) are converted to

    • A.

      Digital.

    • B.

      Pitot-static.

    • C.

      Positional feedback.

    • D.

      Electromagnetic pulse.

    Correct Answer
    A. Digital.
    Explanation
    All analog signals that come into the flight control set processor (FCSP) need to be converted to digital format in order to be processed by the digital system. This conversion allows for easier manipulation, storage, and transmission of the signals, as well as providing better accuracy and reliability in the flight control system. Therefore, the correct answer is digital.

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  • 29. 

    Which component provides all switch holding voltages to the flight control set (FCS) control panel?

    • A.

      Flight control set controller.

    • B.

      Flight control set processor

    • C.

      Horizontal position sensor

    • D.

      Status/test panel

    Correct Answer
    B. Flight control set processor
    Explanation
    The flight control set processor provides all switch holding voltages to the flight control set (FCS) control panel. This component is responsible for regulating and supplying the necessary voltages to ensure proper functioning of the switches on the control panel. It plays a crucial role in the overall operation and control of the flight control system.

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  • 30. 

    Which condition is required to engage the flight control set (FCS) pitch axis?

    • A.

      Valid heading signal

    • B.

      Turn knob must be in detent.

    • C.

      Valid selected gyro #1 and gyro #2 signals.

    • D.

      Series yaw damper system must be engaged.

    Correct Answer
    C. Valid selected gyro #1 and gyro #2 signals.
    Explanation
    To engage the flight control set (FCS) pitch axis, it is necessary to have valid selected gyro #1 and gyro #2 signals. This means that the gyroscopes, which are responsible for measuring and indicating the aircraft's attitude and movement, must be functioning properly and providing accurate information to the flight control system. Without valid signals from these gyroscopes, the FCS pitch axis cannot be engaged, potentially compromising the aircraft's stability and control.

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  • 31. 

    What condition is not required for flight control set roll axis engagement?

    • A.

      Valid heading signal

    • B.

      Turn knob must be in detent.

    • C.

      Valid selected gyro #1 signal.

    • D.

      Valid selected gyro #2 signal

    Correct Answer
    D. Valid selected gyro #2 signal
    Explanation
    The condition that is not required for flight control set roll axis engagement is a valid selected gyro #2 signal. This means that even if the selected gyro #2 signal is not valid, the flight control can still engage the roll axis. The other conditions mentioned, such as a valid heading signal, turn knob in detent, and a valid selected gyro #1 signal, are still necessary for the roll axis engagement.

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  • 32. 

    The status/test panel (STP) allows maintenance personnel to initialize and step through flight control set tests which are controlled by

    • A.

      Air data computer software

    • B.

      Analog to digital conversion

    • C.

      Flight control set processor software

    • D.

      Flight control set controller software.

    Correct Answer
    C. Flight control set processor software
    Explanation
    The flight control set processor software is responsible for controlling the flight control set tests on the status/test panel (STP). It allows maintenance personnel to initialize and step through these tests. The software processes the inputs from the air data computer software, analog to digital conversion, and flight control set controller software to carry out the necessary tests.

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  • 33. 

    The secondary goal of the flight control set continuous built-in-test (CBIT) is to isolate failures to a particular line replaceable unit (LRU) and store the information in

    • A.

      Flight control set processor non-volatile memory.

    • B.

      Flight control set controller non-volatile memory

    • C.

      Flight control set processor volatile random access memory

    • D.

      Flight control set controller volatile random access memory

    Correct Answer
    A. Flight control set processor non-volatile memory.
    Explanation
    The secondary goal of the flight control set continuous built-in-test (CBIT) is to isolate failures to a particular line replaceable unit (LRU) and store the information in the flight control set processor non-volatile memory. This means that the CBIT is designed to identify and localize any failures that occur within the flight control set, specifically to a specific LRU. The information about these failures is then stored in the flight control set processor's non-volatile memory, which ensures that it is retained even when power is lost.

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  • 34. 

    The flight control set (FCS) status/test panel (STP) provides personnel with an interface to the

    • A.

      Flight control set disengage annunciator.

    • B.

      Flight control set control panel.

    • C.

      Flight control set controller

    • D.

      Flight control set processor

    Correct Answer
    D. Flight control set processor
    Explanation
    The flight control set (FCS) status/test panel (STP) is responsible for providing personnel with an interface to the flight control set processor. This means that the panel allows personnel to interact with and monitor the flight control set processor, which is a crucial component in the aircraft's flight control system. It is responsible for processing and executing commands from the flight control set control panel, ensuring the proper functioning of the flight control system.

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  • 35. 

    Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to record an indicated failure in memory?

    • A.

      POWER.

    • B.

      VERIFY.

    • C.

      Left arrow (←).

    • D.

      Right arrow (→).

    Correct Answer
    D. Right arrow (→).
    Explanation
    The right arrow (→) pushbutton switch on the flight control set (FCS) status/test panel (STP) allows personnel to record an indicated failure in memory. This switch is used to scroll through the various failure indicators and select the specific failure to be recorded. By pressing the right arrow button, the indicated failure is stored in the memory for further analysis and troubleshooting.

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  • 36. 

    Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to repeat a test?

    • A.

      POWER.

    • B.

      VERIFY.

    • C.

      Left arrow (←).

    • D.

      Right arrow (→).

    Correct Answer
    C. Left arrow (←).
    Explanation
    The left arrow (←) pushbutton switch on the flight control set (FCS) status/test panel (STP) allows personnel to repeat a test. This is because the left arrow is commonly used as a symbol for "previous" or "back," indicating that pressing this button will take the user back to a previous step or action, in this case, repeating the test.

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  • 37. 

    Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to bypass a report failure?

    • A.

      POWER

    • B.

      VERIFY

    • C.

      Left arrow (←).

    • D.

      Right arrow (→).

    Correct Answer
    B. VERIFY
    Explanation
    The correct answer is VERIFY because the VERIFY pushbutton switch on the flight control set (FCS) status/test panel (STP) allows personnel to confirm or verify the status or test results without bypassing any reported failures.

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  • 38. 

    Which component enables the flight crew to engage and disengage the flight control set (FCS)?

    • A.

      Flight control set processor

    • B.

      Flight control set controller

    • C.

      Flight control set control panel

    • D.

      Flight control set status/test panel

    Correct Answer
    C. Flight control set control panel
    Explanation
    The flight control set control panel is the component that enables the flight crew to engage and disengage the flight control set (FCS). This panel allows the crew to control and manage the various functions and settings of the FCS, such as activating or deactivating certain control modes or adjusting control parameters. It serves as the interface between the crew and the FCS, providing them with the necessary controls and indicators to effectively operate and monitor the aircraft's flight controls.

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  • 39. 

    Engagement of the control panel ROLL axis switch causes the flight control set (FCS) to maintain the aircraft in a wings-level condition and

    • A.

      Maintain the prevailing pitch attitude

    • B.

      Maintain the prevailing yaw attitude

    • C.

      Hold the existing heading

    • D.

      Hold the existing altitude

    Correct Answer
    C. Hold the existing heading
    Explanation
    When the control panel ROLL axis switch is engaged, the flight control set (FCS) will hold the existing heading of the aircraft. This means that regardless of any external factors or disturbances, the FCS will make adjustments to ensure that the aircraft maintains its current heading. This is important for maintaining the desired direction of flight and ensuring stability during maneuvers.

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  • 40. 

    When the control panel NAV LOC switch is in the ON position, the flight control set (FCS) automatically

    • A.

      Flies down the glide slope beam path

    • B.

      Navigates along the selected course

    • C.

      Achieves Mach.

    • D.

      Gains altitude.

    Correct Answer
    B. Navigates along the selected course
    Explanation
    When the control panel NAV LOC switch is in the ON position, it indicates that the flight control set (FCS) will automatically navigate the aircraft along the selected course. This means that the FCS will use the navigation systems onboard the aircraft to follow the desired flight path, ensuring that the aircraft stays on track and reaches its intended destination. The FCS will make adjustments to the aircraft's heading, altitude, and speed as necessary to maintain the selected course.

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  • 41. 

    What controls the flight control set (FCS) control panel LOC ARM/CAP and G/S ARM/CAP indicators?

    • A.

      Flight control set processor

    • B.

      Flight control set controller

    • C.

      Flight control set control panel

    • D.

      Flight control set status/test panel

    Correct Answer
    A. Flight control set processor
    Explanation
    The flight control set (FCS) control panel LOC ARM/CAP and G/S ARM/CAP indicators are controlled by the flight control set processor. This processor is responsible for receiving and processing signals related to the localizer (LOC) and glide slope (G/S) modes of the aircraft's flight control system. It ensures that the indicators accurately display the status of these modes, allowing the pilot to monitor and control the aircraft's approach and landing.

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  • 42. 

    When a flight control set (FCS) mode select switch is switched ON, a 28 VDC

    • A.

      Engage signal is sent to the flight control set processor.

    • B.

      Disengage signal is sent to the flight control set processor

    • C.

      Engage signal is sent to the flight control set servo drum and bracket

    • D.

      Disengage signal is sent to the flight control set servo drum and bracket

    Correct Answer
    A. Engage signal is sent to the flight control set processor.
    Explanation
    When the flight control set (FCS) mode select switch is switched ON, it sends a 28 VDC engage signal to the flight control set processor. This signal indicates that the FCS mode has been selected and activates the processor to initiate the desired control actions. The engage signal is crucial for the proper functioning of the flight control system, as it allows the processor to receive the necessary input and execute the appropriate commands.

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  • 43. 

    What is the degree rotation of the flight control set (FCS) controller thumbwheels ?

    • A.

      90

    • B.

      180

    • C.

      270

    • D.

      360

    Correct Answer
    D. 360
    Explanation
    The degree rotation of the flight control set (FCS) controller thumbwheels is 360. This means that the thumbwheels can be rotated a full 360 degrees, allowing for precise control and adjustment of the flight controls.

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  • 44. 

    What is the degree rotation of the flight control set (FCS) controller turn knob?

    • A.

      90

    • B.

      180

    • C.

      270

    • D.

      360

    Correct Answer
    C. 270
    Explanation
    The degree rotation of the flight control set (FCS) controller turn knob is 270. This means that the knob can be rotated 270 degrees in order to control the flight controls.

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  • 45. 

    The flight control set (FCS) uses one servo motor to move the ailerons and one to move the

    • A.

      Slats

    • B.

      Rudders

    • C.

      Spoilers

    • D.

      Elevators

    Correct Answer
    D. Elevators
    Explanation
    The flight control set (FCS) uses one servo motor to move the ailerons and one to move the elevators. The ailerons are control surfaces on the wings that help control the roll of the aircraft, while the elevators are control surfaces on the horizontal stabilizer that help control the pitch of the aircraft. The rudders are control surfaces on the vertical stabilizer that help control the yaw of the aircraft, and the spoilers are used to disrupt the airflow over the wings and reduce lift. Therefore, the correct answer is elevators.

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  • 46. 

    Which component provides a drive voltage to the flight control set (FCS) servo motor?

    • A.

      Flight control set processor.

    • B.

      Flight control set controller

    • C.

      Flight control set control panel

    • D.

      Flight control set status/test panel

    Correct Answer
    A. Flight control set processor.
    Explanation
    The flight control set processor is responsible for providing a drive voltage to the flight control set (FCS) servo motor. This component is specifically designed to process and control the flight control system, including the servo motor. It generates the necessary voltage to drive the motor, allowing for precise control and adjustment of the aircraft's flight controls. The other options mentioned, such as the controller, control panel, and status/test panel, may play important roles in the overall functioning of the FCS but do not directly provide the drive voltage to the servo motor.

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  • 47. 

    In the flight control set (FCS) system, control surface movement from a neutral position produces a synchro electrical output signal that is processed by the

    • A.

      Flight control set status/test panel

    • B.

      Flight control set control panel.

    • C.

      Flight control set controller.

    • D.

      Flight control set processor.

    Correct Answer
    D. Flight control set processor.
    Explanation
    In the flight control set (FCS) system, control surface movement from a neutral position produces a synchro electrical output signal. This signal needs to be processed in order to control the flight. The flight control set processor is responsible for processing this signal and translating it into appropriate control commands for the aircraft. The other options mentioned, such as the status/test panel, control panel, and controller, may have different functions within the FCS system but they do not specifically handle the processing of the synchro electrical output signal. Therefore, the flight control set processor is the correct answer.

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  • 48. 

    What provides the only mechanical connection from the flight control set (FCS) servo motor to the aircraft control cables?

    • A.

      Horizontal position sensor

    • B.

      Servo drum and bracket.

    • C.

      Jackscrew assembly.

    • D.

      Trim actuator.

    Correct Answer
    B. Servo drum and bracket.
    Explanation
    The servo drum and bracket provide the only mechanical connection from the flight control set (FCS) servo motor to the aircraft control cables. This connection allows for the transmission of mechanical force from the servo motor to the control cables, enabling the pilot to control the aircraft's movements. The horizontal position sensor, jackscrew assembly, and trim actuator are not directly involved in this mechanical connection.

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  • 49. 

    The flight control set (FCS) horizontal position sensor (HPS) consists of a

    • A.

      Trim actuator

    • B.

      Jackscrew assembly.

    • C.

      Servo drum and bracket.

    • D.

      Linear variable differential transformer

    Correct Answer
    D. Linear variable differential transformer
    Explanation
    The flight control set (FCS) horizontal position sensor (HPS) uses a linear variable differential transformer (LVDT). An LVDT is a type of sensor that converts linear displacement into an electrical signal. It consists of a primary coil, a secondary coil, and a core that moves within the coils. As the core moves, it induces a voltage in the secondary coil that is proportional to the displacement. In the case of the FCS HPS, the LVDT is used to measure the position of the trim actuator jackscrew assembly, allowing for precise control of the aircraft's horizontal position.

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  • 50. 

    The primary function of the flight control set (FCS) roll loop is to fly the aircraft at a wings level attitude while in

    • A.

      Heading hold mode.

    • B.

      Altitude hold mode

    • C.

      Glide slope mode.

    • D.

      Mach hold mode.

    Correct Answer
    A. Heading hold mode.
    Explanation
    The primary function of the flight control set (FCS) roll loop is to maintain the aircraft at a wings level attitude while in heading hold mode. In this mode, the FCS roll loop continuously adjusts the ailerons to counteract any roll deviations and keep the aircraft's wings level. This is essential for maintaining a stable flight and ensuring that the aircraft maintains its intended heading. The FCS roll loop does not directly control altitude, glide slope, or Mach hold modes, making heading hold mode the correct answer.

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