2A852 CDC Volume 5

71 Questions | Total Attempts: 88

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2A852 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

  • 2. 
    The copilot’s elevator input system is connected to the
    • A. 

      Outboard elevators

    • B. 

      Inboard elevators

    • C. 

      Upper rudder

    • D. 

      Lower rudder

  • 3. 
    Control of the aircraft in the yaw axis is accomplished by the
    • A. 

      Elevators

    • B. 

      Ailerons

    • C. 

      Rudders

    • D. 

      Spoilers

  • 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

  • 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

  • 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

  • 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

  • 8. 
    What is not included in the mechanical flight control system?
    • A. 

      Cables.

    • B. 

      Torque tubes

    • C. 

      Push-pull tubes

    • D. 

      Electrically powered actuators.

  • 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.

  • 10. 
    Hydraulic powered actuators convert hydraulic pressure into
    • A. 

      Control surface movements

    • B. 

      Artificial stall warning.

    • C. 

      Gust lock limit

    • D. 

      Fly-by-wire.

  • 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

  • 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.

  • 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.

  • 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.

  • 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.

  • 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.

  • 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°.

  • 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).

  • 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

  • 20. 
    Synchro position indicating systems convert mechanical shaft angles to
    • A. 

      Mechanical shaft degrees

    • B. 

      Electrical shaft degrees

    • C. 

      Mechanical signals.

    • D. 

      Electrical signals

  • 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.

  • 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

  • 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).

  • 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).

  • 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).

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