Volume 5 Section 1

52 Questions

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Volume 5 Section 1

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Questions and Answers
  • 1. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    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. 
    What safety dfevice 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. 
    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. 
    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 deg aircraft NOSE DOWN or 6.0 deg aircraft NOSE UP

    • D. 

      1.5 deg aircraft NOSE DOWN or 6.0 deg aircraft NOSE UP

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

      Dual power relays

    • B. 

      Power and ground

    • C. 

      Backup battery power

    • D. 

      Bipolar synchro transmitters

  • 20. 
    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. 
    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. 
    The conditions that allow the fairings on the B-1B to move up and down automatically are a wing sweep
    • A. 

      Greater than 61 deg and airspeed greater than 60 knots

    • B. 

      Less than 61 deg and airspeed greater than 60 knots

    • C. 

      Greater than 62 deg and airspeed less than 70 knots

    • D. 

      Less than 62 deg and airspeed less than 70 knots

  • 23. 
    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. 
    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. 
    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. 
    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 deg or Mach >0.5

    • C. 

      Wing sweep>15 deg or Mach>1.0

    • D. 

      Roll rate and wing sweep>35 deg

  • 27. 
    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. 
    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. 
    When do the inboard spoilers on the B-1B roll trim system provide roll trim?
    • A. 

      Mach < 0.99 and Trim Norm selected

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

      53 deg, 55 minutes (')

    • B. 

      56 deg, 37 '

    • C. 

      57 deg, 57 '

    • D. 

      61 deg, 57 '

  • 31. 
    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. 
    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. 
    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. 
    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. 
    What is the rudder movement of the B-1B during noraml aircraft flight?
    • A. 

      Limited to + - 10 deg

    • B. 

      Unlimited to + - 25 deg

    • C. 

      Unlimited to + - 26 deg

    • D. 

      Limited to + - 10 deg or + - 25 deg, depending on the mode of operation

  • 36. 
    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. 
    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. 
    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. 
    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 engaged or disengaged

    • C. 

      The signal from the proximity switch assemblies

    • D. 

      Which power control assembly relay is energized or deenergized

  • 40. 
    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

  • 41. 
    What control(s) is / are available for the co-pilot to fly the B-1B aircraft if the pilot's stick in the mechancial 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. 
    Lengthening of the pitch cable in the B-1B mechanical pitch control system due to thermal chagnes 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. 
    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 vibration induced by the linkage shaker assembly from effecting the stabilizer

    • D. 

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

  • 44. 
    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 deg up position

    • B. 

      Stabilizers are forced in a -10 deg 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. 
    On the B-1B pitch control subsystem, the leading-edge surface travel of the horizontal stabilizers is limited to
    • A. 

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

    • B. 

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

    • C. 

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

    • D. 

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

  • 46. 
    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. 
    The B-1B central integrated test system monitors the speed of the pitch control subsystem linkage shaker motors through
    • A. 

      Data acquisition units (DAU) 1 and 2

    • B. 

      DAUs 2 and 4

    • C. 

      DAU 2

    • D. 

      DAU 4

  • 48. 
    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. 
    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. 
    During the STANDBY mode of operation of the B-1B pitch control subsystem, the actual co-pilot trim commands to the stabilizer are provided by the
    • A. 

      Control stick

    • B. 

      Flight control trim panel

    • C. 

      Flight control power panel

    • D. 

      Flight control auxiliary panel

  • 51. 
    Placing the pitch trim switch to the pitch trim-up position during STANDBY mode of operation of the B-1B pitch control susbsystem 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. 
    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