2A553B Vol. 5 Pretest

100 Questions | Total Attempts: 363

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CDC Quizzes & Trivia

Pretest for CDC 2A553B Upgrade.


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.

  • 2. 
    (801) On the C-5 roll control system, what provides positive system centering with no force applied to the control wheel?
    • A. 

      Spring.

    • B. 

      Servo.

    • C. 

      Cable.

    • D. 

      Beam.

  • 3. 
    (801) On the C-5, maximum torque of the pilot assist cable servo is adjusted to provide approximately how much assistance in percent to the pitch and roll axes, respectively?
    • A. 

      95; 80.

    • B. 

      75; 60.

    • C. 

      50; 40.

    • D. 

      20; 15.

  • 4. 
    (802) What component of the C-5 elevator control system provides the pilot with feel forces as a function of normal acceleration?
    • A. 

      Variable feel unit.

    • B. 

      Centering spring.

    • C. 

      Bob weight.

    • D. 

      Cable.

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

      Variable feel unit.

    • B. 

      Centering spring.

    • C. 

      Bob weight.

    • D. 

      Cable.

  • 6. 
    (802) What component of the C-5 elevator control system assists the pilot in overcoming cable system friction?
    • A. 

      Pilot assist cable servo.

    • B. 

      Centering spring.

    • C. 

      Bob weight.

    • D. 

      Cable.

  • 7. 
    (803) On the C-5, what repositions the neutral point of the preloaded centering bungee after the C-5 rudder pedals have been displaced to a desired trim position?
    • A. 

      Centering bungee.

    • B. 

      Toggle switches.

    • C. 

      Trim actuator.

    • D. 

      Crank.

  • 8. 
    (803) On the C-5, simultaneous operation of the rudder trim control switches is required to provide...
    • A. 

      Two power sources to the trim actuator.

    • B. 

      Power and ground to the trim actuator.

    • C. 

      A discrete pulse to the yaw computer.

    • D. 

      Two grounds to the yaw damper.

  • 9. 
    (804) What part of a helicopter is designed to counter the tendency of the aircraft to spin about the vertical axis?
    • A. 

      Rudder.

    • B. 

      Ailerons.

    • C. 

      Tail rotor.

    • D. 

      Main rotor.

  • 10. 
    (804) What effect does raising the collective have on the main rotor of a helicopter?
    • A. 

      Lift increases.

    • B. 

      Lift decreases.

    • C. 

      Airspeed increases.

    • D. 

      Airspeed decreases.

  • 11. 
    (804) Which flight control is used to maneuver the helicopter left or right, and forward or aft, while hovering?
    • A. 

      Yoke.

    • B. 

      Cyclic.

    • C. 

      Collective.

    • D. 

      Foot pedals.

  • 12. 
    (804) What do the cyclic and collective flight controls use to change the pitch of the rotor blades?
    • A. 

      Swash plate.

    • B. 

      Foot pedals.

    • C. 

      Rudder.

    • D. 

      Cyclic.

  • 13. 
    (805) Each C-5 slat surface is extended and retracted by two...
    • A. 

      Variable flap drive roller carriages.

    • B. 

      Variable slat drive roller carriages.

    • C. 

      Telescoping ballscrew actuators.

    • D. 

      Telescoping slat drive limiters.

  • 14. 
    (805) The four positions called out on the C-5 flap handle console are...
    • A. 

      DOWN, T/O 40, T/O AND APP, and LANDING.

    • B. 

      DOWN, T/O 80, T/O AND APP, and LANDING.

    • C. 

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

    • D. 

      UP, T/O 80, T/O AND APP, and LANDING.

  • 15. 
    (805) The flap position indicator on the C-5 is a dial-type instrument that shows flap position in...
    • A. 

      Degrees; 0-60.

    • B. 

      Degrees; 0-100.

    • C. 

      Percentage; 0-60.

    • D. 

      Percentage; 0-100.

  • 16. 
    (806) What safety device in the wing spoiler cable system of the C-5 aircraft closes the affected spoiler panels when a cable or pushrod is disconnected?
    • A. 

      Switch.

    • B. 

      Spring.

    • C. 

      Valve.

    • D. 

      Cam.

  • 17. 
    (807) On the C-5 horizontal stabilizer pitch trim system, hydraulic motor torque is transferred to the nut and screw drives through a...
    • A. 

      Step-down transformer.

    • B. 

      Torque synchro.

    • C. 

      Gear train.

    • D. 

      Lever.

  • 18. 
    (807) With flaps up, the limit switches cut off electrical power to the screw drive unit when the horizontal stabilizer on a C-5 reaches...
    • A. 

      8 percent aircraft NOSE DOWN or 15 percent aircraft NOSE UP.

    • B. 

      5 percent aircraft NOSE DOWN or 12 percent aircraft NOSE UP.

    • C. 

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

    • D. 

      1.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP.

  • 19. 
    (807) When the electric trim switches for the C-5 horizontal stabilizer are actuated together, electrical continuity is provided by...
    • A. 

      Dual power relays.

    • B. 

      Power and ground.

    • C. 

      Backup battery power.

    • D. 

      Bipolar synchro transmitters.

  • 20. 
    (808) The co-pilot stick controls the B-1B aircraft roll by using the stability control augmentation system and...
    • A. 

      Inboard spoilers.

    • B. 

      Outboard spoilers.

    • C. 

      Mechanical linkage.

    • D. 

      Roll gyro differential signals.

  • 21. 
    (808) During stability control augmentation system (SCAS) operation, the B-1B upper and intermediate rudders get their primary position signals from the...
    • A. 

      Control sticks.

    • B. 

      SCAS and yaw-trim.

    • C. 

      SCAS and control stick.

    • D. 

      Rudder pedals and yaw-trim.

  • 22. 
    (808) The conditions that allow the fairings on the B-1B to move up and down automatically are a wing sweep...
    • A. 

      Greater than 61 degrees and airspeed greater than 60 knots.

    • B. 

      Less than 61 degrees and airspeed greater than 60 knots.

    • C. 

      Greater than 62 degrees and airspeed less than 70 knots.

    • D. 

      Less than 62 degress and airspeed less than 70 knots.

  • 23. 
    (808) On the B-1B, which indication on the surface position/command indicator uses a single window for display of position information?
    • A. 

      Slats.

    • B. 

      Flaps.

    • C. 

      Spoilers.

    • D. 

      Speedbrakes.

  • 24. 
    (809) When the roll master servo cylinder output linkage in the mechanical roll control system on the B-1B is disconnected, the...
    • A. 

      Inboard and outboard spoilers are forced into the full down position.

    • B. 

      Outboard spoilers are placed in the full up position.

    • C. 

      Inboard spoilers are forced into the down position.

    • D. 

      Pilot control stick is forced to the center position.

  • 25. 
    (809) On the B-1B, hydraulic power to the left and right inboard spoiler servo cylinders is supplied by the...
    • A. 

      1 and 4 hydraulic systems.

    • B. 

      2 and 3 hydraulic systems.

    • C. 

      1,2, and 4 hydraulic systems.

    • D. 

      2,3, and 4 hydraulic systems.

  • 26. 
    (810) On the B-1B, what signals are combined with the roll command signals inside the spoiler controller to produce the "dead-band" signal?
    • A. 

      Weight-on-wheels, roll rate, and Mach >0.5.

    • B. 

      Wing sweep >35 degrees or Mach >0.5.

    • C. 

      Wing sweep >15 degrees or Mach >1.0.

    • D. 

      Roll rate and wing sweep >35 degrees.

  • 27. 
    (810) In the B-1B roll control-outboard spoilers system, what is the result of placing the spoiler switch in the OFF position?
    • A. 

      Speedbrakes are disengaged if weight-on-wheels (WOW) is present.

    • B. 

      Inboard and outboard spoilers retract to full down position.

    • C. 

      Speedbrakes are engaged if WOW is not present.

    • D. 

      Outboard spoilers retract to full down position.

  • 28. 
    (811) To activate the actual roll trim commands on the B-1B, you...
    • A. 

      Place the roll trim mode select switch to norm.

    • B. 

      Place the roll trim mode select switch to alter.

    • C. 

      Position the roll trim switch longitudinally.

    • D. 

      Position the roll trim switch laterally.

  • 29. 
    (811) When do the inboard spoilers on the B-1B roll trim system provide roll trim?
    • A. 

      Mach

    • B. 

      Mach = 1.0 and Norm mode selected.

    • C. 

      Mach = 0.5 and Norm mode selected.

    • D. 

      Mach >0.99 and Alter mode selected.

  • 30. 
    (811) The maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to...
    • A. 

      53 degrees, 55 minutes (').

    • B. 

      56 degrees, 37'.

    • C. 

      57 degrees, 57'.

    • D. 

      61 degrees, 57'.

  • 31. 
    (812) The mechanical yaw control system on the B-1B is...
    • A. 

      Electrically and mechanically controlled and actuated.

    • B. 

      Electrically controlled and hydromechanically actuated.

    • C. 

      Mechanically controlled and hydromechanically actuated.

    • D. 

      Hydromechanically controlled and hydroelectrically actuated.

  • 32. 
    (812) On the B-1B mechanical yaw control system, the rudder pedals provide electrical positioning information for the...
    • A. 

      Yaw stability control augmentation system (SCAS) and brakes.

    • B. 

      Mechanical yaw, yaw SCAS, and nosewheel steering.

    • C. 

      Nosewheel steering, yaw SCAS, and brakes.

    • D. 

      Yaw SCAS and nosewheel steering.

  • 33. 
    (812) On the B-1B mechanical yaw control system, the two sets of rudder control pedals are interconnected...
    • A. 

      With one bellcrank and two push-pull rods.

    • B. 

      Through two bellcranks and push-pull rods.

    • C. 

      With tension regulator bungees and bellcranks.

    • D. 

      To one another with idler arms and push-pull rods.

  • 34. 
    (813) Before the B-1B mechanical yaw limiter system can be placed in the limited mode, the...
    • A. 

      Slats in or left/right main gear must be uplocked.

    • B. 

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

    • C. 

      Flaps out or left/right main gear must be downlocked.

    • D. 

      Flaps out and left/right main gear must be downlocked.

  • 35. 
    (813) What is the rudder movement of the B-1B during normal aircraft flight?
    • A. 

      Limited to +/- 10 degrees.

    • B. 

      Unlimited to +/- 25 degress.

    • C. 

      Unlimited to +/- 26 degrees.

    • D. 

      Limited to +/- 10 degrees or +/- 25 degrees, depending on the mode of operation.

  • 36. 
    (813) On the B-1B, which component of the yaw limiter actuator motor B restricts the movement of the motor from movement during excessive aircraft vibrations?
    • A. 

      Cam.

    • B. 

      Brake.

    • C. 

      Bellcrank.

    • D. 

      Output shaft.

  • 37. 
    (814) During ALTER mode on the B-1B, the yaw trim signals applied to the actuators originate...
    • A. 

      From the control stick trim switch.

    • B. 

      In the central integrated test system.

    • C. 

      In the yaw stability control augmentation system.

    • D. 

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

  • 38. 
    (814) Which power control assembly supplies the operating power to the yaw trim actuators on the B-1B?
    • A. 

      2453A06.

    • B. 

      2454A06.

    • C. 

      2455A05.

    • D. 

      2455A06.

  • 39. 
    (814) What determines the direction the motor is driven to position the yaw trim bellcrank on the B-1B?
    • A. 

      The position of the travel limit switches.

    • B. 

      Whether the brake is engages or disengaged.

    • C. 

      The signal from the proximity switch assemblies.

    • D. 

      Which power control assembly relay is energized or deenergized.

  • 40. 
    (815) In the B-1B mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished...
    • A. 

      Symmetrically by the pilot control stick only.

    • B. 

      Asymmetrically by the pilot control stick only.

    • C. 

      Asymmetrically by the co-pilot control stick only.

    • D. 

      Symmetrically by the pilot and co-pilot control sticks.

    • E. 

  • 41. 
    (815) What control(s) is/are available for the co-pilot to fly the B-1B aircraft if the pilot's stick in the mechanical pitch control system is isolated due to a failure in the linkage?
    • A. 

      Mechanical control of the horizontal stabilizers in pitch only.

    • B. 

      Electrical control of the horizontal stabilizers in pitch and roll.

    • C. 

      Mechanical and electrical control of the horizontal stabilizers in pitch only.

    • D. 

      Electrical and hydromechanical control of the horizontal stabilizers in pitch and roll.

  • 42. 
    (815) Lengthening of the pitch cable in the B-1B mechanical pitch control system due to thermal changes is compensated for by the...
    • A. 

      Tension regulator bungees.

    • B. 

      Forward and aft feel bungees.

    • C. 

      Pitch master hydraulic servo cylinder.

    • D. 

      Left and right override regulator bungees.

  • 43. 
    (815) On the B-1B mechanical pitch system, the pitch control command is amplified by the pitch master hydraulic servo cylinder to...
    • A. 

      Isolate the control stick from the pitch SCAS function.

    • B. 

      Overcome friction in the mechanical push-pull system.

    • C. 

      Prevent vibrations induced by the linkage shaker assemby from effecting the stabilizer position.

    • D. 

      Reduce the effort required by the co-pilot to move the control stick when the pilot stick is disconnected.

  • 44. 
    (815) If the pitch master hydraulic servo cylinder in the B-1B mechanical pitch control system is disconnected, the...
    • A. 

      Stabilizers are placed in a +10 degree up position.

    • B. 

      Stabilizers are forced to a -10 degree down position.

    • C. 

      Pitch master servo cylinder output is forced to the center position.

    • D. 

      Pitch centering bungees place the horizontal stabilizers into the center position.

  • 45. 
    (815) On the B-1B pitch control subsystem, the leading-edge surface travel of the horizontal stabilizers is limited to...
    • A. 

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

    • B. 

      20 degrees up and down at a maximum travel rate of 25 degrees per second.

    • C. 

      25 degrees up and 15 degrees down at a maximum travel rate of 20 degrees per second.

    • D. 

      25 degrees up and down at a maximum travel rate of 20 degrees per second.

  • 46. 
    (816) The pitch control subsystem linkage shaker motors on the B-1B are enabled...
    • A. 

      When pitch trim is selected.

    • B. 

      After the aircraft is in flight.

    • C. 

      When power is applied to the aircraft.

    • D. 

      After the electrical multiplexing system enables power control assembly 2454A06.

  • 47. 
    (816) The B-1B central integrated test system monitors the speed of the pitch control subsystem likage shaker motors through...
    • A. 

      Data acquisition units (DAU) 1 and 2.

    • B. 

      DAUs 2 and 4.

    • C. 

      DAU 2.

    • D. 

      DAU 4.

  • 48. 
    (817) During alternate mode of operation of the B-1B pitch trim system, the trim controller in the automatic flight control system...
    • A. 

      Is disabled.

    • B. 

      Is enabled, but does not control the pitch trim actuator.

    • C. 

      Receives electrical multiplexing system pitch trim-up and pitch trim-down.

    • D. 

      Processes the pitch trim-up/down commands for application to the stability control augmentation system controllers.

  • 49. 
    (817) During the STANDBY mode of operation of the B-1B pitch control subsystem, the pitch trim actuator receives the pitch trim-up command from the STANDBY...
    • A. 

      Circuit of the automatic flight control system trim controller.

    • B. 

      Trim switch on the flight control auxiliary panel.

    • C. 

      Contacts of the control stick pitch trim switch.

    • D. 

      Trim switch on the flight control power panel.

  • 50. 
    (817) During the STANDBY mode of operation of the B-1B pitch control subsystem, the actual co-pilot pitch trim commands to the stabilizers are provided by the...
    • A. 

      Control stick.

    • B. 

      Flight control trim panel.

    • C. 

      Flight control power panel.

    • D. 

      Flight control auxiliary panel.

  • 51. 
    (817) Placing the pitch trim switch to the pitch trim-up position during STANDBY mode of operation of the B-1B pitch control subsystem causes the...
    • A. 

      Stability control augmentation system (SCAS) controllers to command the pitch SCAS servo actuators.

    • B. 

      Automatic flight control system pitch trim controller to enable the pitch trim actuator motor.

    • C. 

      Power control assembly 2455A06 to enable the pitch trim actuator motor.

    • D. 

      SCAS controllers to command the pitch trim actuator motor.

  • 52. 
    (817) On the B-1B, what signals are summed by the electrical multiplexing system to illuminate the trim-for-takeoff (TTO) annunciator?
    • A. 

      Roll, yaw, and normal.

    • B. 

      TTO position signals and TTO command.

    • C. 

      Pitch trim and pitch TTO command signals.

    • D. 

      TTO command and pitch trim TTO position.

  • 53. 
    (818) All three augmentation systems on the C-5 are...
    • A. 

      Single channel failure protected.

    • B. 

      Fail-operational and fail-safe.

    • C. 

      Fail-operational only.

    • D. 

      Fail-safe only.

  • 54. 
    (818) If a failure should occur in the output channel A, the C-5 stability augmentation system...
    • A. 

      Switches to channel B and remains engaged.

    • B. 

      Remains in channel A with reduced accuracy.

    • C. 

      Remains in channel A and disengages the system.

    • D. 

      Switches to channel B and disengages the system.

  • 55. 
    (819) The C-5 yaw augmentation (Y/A) system provides yaw damping, turn coordination, Y/A manual rudder trim, and...
    • A. 

      Attitude hold.

    • B. 

      Altitude hold.

    • C. 

      Dutch roll damping.

    • D. 

      Divergence control.

  • 56. 
    (819) The hydraulic manifold on the C-5 yaw augmentation system is equipped with...
    • A. 

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

    • B. 

      An SOV, automatic throttle system, EHV, and LVDT.

    • C. 

      A pressure data converter, HPS, EHV, and LVDT.

    • D. 

      And SOV, HPS, EHV, and pilot assist cable servo.

  • 57. 
    (819) What type filter is used in the yaw augmentation system to block any rate gyro signals developed as a result of the normal bending of the C-5 aircraft body from occuring during flight?
    • A. 

      High-pass.

    • B. 

      Low-pass.

    • C. 

      Greenfield.

    • D. 

      Body-bend.

  • 58. 
    (819) The maximum rudder displacement the C-5 yaw augmentation system can command from reference is...
    • A. 

      +/- 20 degrees.

    • B. 

      +/- 15 degrees.

    • C. 

      +/- 12 degrees.

    • D. 

      +/- 10 degrees.

  • 59. 
    (820) The lateral augmentation system on the C-5 provides roll damping, dutch roll damping, and...
    • A. 

      Wing camber control.

    • B. 

      Vertical lift distribution.

    • C. 

      Spiral divergence control.

    • D. 

      Roll coriolis compensation.

  • 60. 
    (820) During manual flight, the roll damping gain of the lateral augmentation system on the C-5 is...
    • A. 

      0.

    • B. 

      1.

    • C. 

      2.

    • D. 

      3.

  • 61. 
    (820) Which is not a C-5 lateral augmentation system interface?
    • A. 

      Very-high frequency control panel.

    • B. 

      Inertial navigation system.

    • C. 

      Master caution.

    • D. 

      Autopilot.

  • 62. 
    (821) To initiate self-test of the C-5 pitch augmentation system, the four inboard elevator hydraulic power switches on the pilot's overhead panel must be...
    • A. 

      Reset to TEST.

    • B. 

      In the ON position.

    • C. 

      In the OFF position.

    • D. 

      In the NORM position.

  • 63. 
    (822) On the KC-135, the turn knob on the flight control set must be in detent before the...
    • A. 

      Roll axis is engaged.

    • B. 

      Yaw axis is engaged.

    • C. 

      Pitch axis is engaged.

    • D. 

      Lateral axis is engaged.

  • 64. 
    (822) The rudder power on the KC-135 flight control set must be on before the...
    • A. 

      Roll axis is engaged.

    • B. 

      Yaw axis is engaged.

    • C. 

      Pitch axis is engaged.

    • D. 

      Lateral axis is engaged.

  • 65. 
    (822) Automatic disengagement of all three axes of the KC-135 flight control set occurs if an error is detected in the...
    • A. 

      Roll servo loop.

    • B. 

      Yaw servo loop.

    • C. 

      Pitch servo loop.

    • D. 

      Lateral servo loop.

  • 66. 
    (822) On the KC-135, the sources of the flight control set (FCS) gyro 1 signals are the INS and...
    • A. 

      Automatic flight control system vertical gyro (VG).

    • B. 

      Pilot's attitude director indicator.

    • C. 

      Flight director.

    • D. 

      FCS VG.

  • 67. 
    (823) On the KC-135, cross-channel monitoring in the flight control set processor of the flight control set (FCS) prevents a single processor failure from causing...
    • A. 

      A shaker signal.

    • B. 

      An axis hardover.

    • C. 

      An FCS shutdown.

    • D. 

      An axis disengagement.

  • 68. 
    (823) On the KC-135, inputs provided by the inertial navigation system to the flight control set include pitch attitude, roll attitude, and...
    • A. 

      Altitude.

    • B. 

      Heading.

    • C. 

      Airspeed.

    • D. 

      Roll steering.

  • 69. 
    (823) On the KC-135, the flight control set modes available when the pitch axis is engaged include ALT HOLD, MACH HOLD, and...
    • A. 

      LOC.

    • B. 

      HDG SEL.

    • C. 

      NAV/LOC.

    • D. 

      GLIDE SLOPE.

  • 70. 
    (823) On the KC-135, which built-in test is designed to detect a fault and shut down the flight control set before a hardover occurs?
    • A. 

      Maintenance.

    • B. 

      Continuous.

    • C. 

      Postflight.

    • D. 

      Preflight.

  • 71. 
    (823) On the KC-135, the output of the angular accelerometer in the flight control set processor is used for damping what oscillations?
    • A. 

      Aileron.

    • B. 

      Elevator.

    • C. 

      Dutch roll.

    • D. 

      Trim stabilizer.

  • 72. 
    (824) On the KC-135, the primary function of the status/test panel is to test the flight control set at what level?
    • A. 

      Field.

    • B. 

      Depot.

    • C. 

      Intermediate.

    • D. 

      Organizational.

  • 73. 
    (824) On the KC-135, which button on the status/test panel allows the operator to record an indicated failure in memory?
    • A. 

      VERIFY.

    • B. 

      Up arrow.

    • C. 

      Left arrow.

    • D. 

      Right arrow.

  • 74. 
    (824) On the KC-135, which status/test panel button allows the operator to bypass recording a failure?
    • A. 

      VERIFY.

    • B. 

      Up arrow.

    • C. 

      Left arrow.

    • D. 

      Right arrow.

  • 75. 
    (825) On the KC-135, the voltage required to hold the flight control set control panel mode switches in the ON position is supplied by the flight control set...
    • A. 

      Processor.

    • B. 

      Control panel.

    • C. 

      Flight controller.

    • D. 

      Status/test panel.

  • 76. 
    (825) On the KC-135, which flight control set mode disengages if the turn knob is turned out of detent after engagement?
    • A. 

      HDG SEL.

    • B. 

      ALT HOLD.

    • C. 

      ROLL AXIS.

    • D. 

      MACH HOLD.

  • 77. 
    (825) On the KC-135, what type of output device is used by the flight control set flight controller turn knob?
    • A. 

      Synchro.

    • B. 

      Solenoid switch.

    • C. 

      Variable resistor.

    • D. 

      Control transformer.

  • 78. 
    (826) On the KC-135, the flight control set servomotors are connected to the aircraft control cables via the...
    • A. 

      Trim actuator.

    • B. 

      Jackscrew assembly.

    • C. 

      Surface control assembly.

    • D. 

      Drum and bracket assembly.

  • 79. 
    (827) On the KC-135, a change on the pressure input of the air control unit sensor pressure data converter is represented on the ouput as a change in...
    • A. 

      Parity.

    • B. 

      Polarity.

    • C. 

      Amplitude.

    • D. 

      Frequency.

  • 80. 
    (827) On the KC-135, the erection time of the gyro in the flight control set is...
    • A. 

      1 - 1 1/2 minutes.

    • B. 

      2 - 3 minutes.

    • C. 

      5 - 10 minutes.

    • D. 

      More than 10 minutes.

  • 81. 
    (828) On the KC-135, the flight control set processor roll command module provides outputs to roll the aircraft in response to inputs from the...
    • A. 

      Turn knob.

    • B. 

      Pitch wheel.

    • C. 

      Air control unit sensor.

    • D. 

      Angular accelerometer.

  • 82. 
    (828) On the KC-135, placing the turn knob out of detent causes the NAV/LOC switch on the flight control set tactical air navigation to disengage during the...
    • A. 

      ARM and CAPTURE submodes.

    • B. 

      CAPTURE and TRACK submodes.

    • C. 

      ARM and OVERSTATION submodes.

    • D. 

      TRACK and OVERSTATION submodes.

  • 83. 
    (829) On the KC-135, a vertical velocity of 3,500 feet per minute automatically inhibits engagement of what flight control set mode of operation?
    • A. 

      ALT HOLD.

    • B. 

      LOCALIZER.

    • C. 

      MACH HOLD.

    • D. 

      GLIDE SLOPE.

  • 84. 
    (829) The KC-135 flight control set maintains a set Mach number by varying...
    • A. 

      The position of the throttles.

    • B. 

      Fuel flow to the engines.

    • C. 

      The position of the flaps.

    • D. 

      The pitch of the aircraft.

  • 85. 
    (829) On the KC-135 flight control set, the GLIDE SLOPE ARM annunciator remains illuminated until...
    • A. 

      The GLIDE SLOPE CAP annunciator goes out.

    • B. 

      ALT HOLD or MACH HOLD are engaged.

    • C. 

      The GLIDE SLOPE beam is captured.

    • D. 

      The localizer beam is captured.

  • 86. 
    (830) On the C-130, the altitude control on the E-4 automatic flight control system maintains a fixed altitude by controlling the...
    • A. 

      Ailerons.

    • B. 

      Elevators.

    • C. 

      Trim tabs.

    • D. 

      Stabilizer.

  • 87. 
    (830) On the C-130, the gyro erection system in the E-4 automatic flight control system roll and pitch control...
    • A. 

      Operates at a slow rate during initial warm-up.

    • B. 

      Operates at a fast rate after initial warm-up.

    • C. 

      Erects the gyro during all phases of flight.

    • D. 

      Is cut out during commanded turns.

  • 88. 
    (830) On the C-130, the trim indicators on the pedestal controller of the E-4 automatic flight control system represent the output of each...
    • A. 

      Servo control generator.

    • B. 

      Repeatback synchro.

    • C. 

      Servoamplifier.

    • D. 

      Servomotor.

  • 89. 
    (831) If the C-130 aircraft is not wings-level during operation of the E-4 automatic flight control system, the aircraft can be returned to wings-level by using the...
    • A. 

      TURN knob.

    • B. 

      PITCH knob.

    • C. 

      Control wheel.

    • D. 

      AIL trim knob.

  • 90. 
    (832) To provide automatic pitch trim for the C-130, the trim tab adapter of the E-4 automatic flight control system moves the...
    • A. 

      Aileron.

    • B. 

      Trim tab.

    • C. 

      Elevator.

    • D. 

      Stabilizer.

  • 91. 
    (833) In the rudder control loop of the E-4 automatic flight control system, the heading reference of the C-130 aircraft is locked by...
    • A. 

      Shorting the output of the heading synchro.

    • B. 

      Shorting the output of the turn motor amplifier.

    • C. 

      Aligning the rudder synchro with the heading synchro.

    • D. 

      Driving the rudder synchro to follow the output of the heading synchro.

  • 92. 
    (834) In the C-17A aircraft's electronic flight control system, the flight control computers directly control the ailerons,...
    • A. 

      Spoilers, elevators, rudders, and horizontal stabilizer.

    • B. 

      Elevators, rudders, and horizontal stabilizer.

    • C. 

      Flaps, slats, spoilers, elevators, and rudders.

    • D. 

      Spoilers, elevators, and rudders.

  • 93. 
    (834) In response to rudder trim commands, the rudder trim actuator of the C-17A electronic flight control system moves the rudder, as well as the...
    • A. 

      Ailerons.

    • B. 

      Rudder pedals.

    • C. 

      Force transducer.

    • D. 

      Ailerons and spoilers.

  • 94. 
    (834) In the C-17A electronic flight control system, control surface position feedback is provided by dual...
    • A. 

      Rotary variable displacement transducers (RVDT) in the hydraulic actuators.

    • B. 

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

    • C. 

      RVDTs in the integrated flight control module.

    • D. 

      LVDTs in the integrated flight control module.

  • 95. 
    (835) In the C-17A electronic flight control system, the primary pitch input originates in the...
    • A. 

      Control stick sensor assembly.

    • B. 

      Pitch stick position sensor.

    • C. 

      Pitch autopilot actuator.

    • D. 

      Flight control computer.

  • 96. 
    (835) To reduce structural loads on the C-17A vertical stabilizer, the flight control computers of the electronic flight control system limit rudder deflection as a function of...
    • A. 

      Airspeed and altitude.

    • B. 

      Static pressure.

    • C. 

      Airspeed.

    • D. 

      Altitude.

  • 97. 
    (836) When the autopilot (A/P) of the electronic flight control system on a C-17A aircraft is engaged after the flight director (F/D) is already engaged, the A/P...
    • A. 

      Engages into the mode the pilot has selected.

    • B. 

      Causes the F/D to switch to the A/P mode.

    • C. 

      Automatically disengaged the F/D mode.

    • D. 

      Engages into the same mode as the F/D.

  • 98. 
    (837) Which control panel on the H-60 altitude hold/hover stabilization (AHHS) system contains an altitude select knob?
    • A. 

      Hover engage panel.

    • B. 

      Auto flight control panel.

    • C. 

      AHHS mode select panel.

    • D. 

      AHHS system control unit.

  • 99. 
    (838) On the H-60 altitude hold/hover stabilization system, what mode uses all three axes' accelerometers and the copilot's vertical gyro for reference?
    • A. 

      HOV.

    • B. 

      HOV/RA.

    • C. 

      RAD/ALT.

    • D. 

      BAR/ALT.

  • 100. 
    (839) Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?
    • A. 

      Weight-on-wheels.

    • B. 

      Forward relay unit.

    • C. 

      Digital remote unit.

    • D. 

      System control unit.