2a533b Volume 5

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1. What part of a helicopter is designed to counter the tendency of the aircraft to spin about the vertical axis?

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Quiz for 2a533b volume 5

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2. What effect does raisint the collective have on the main rotor of a helicopter?

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

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4. On the c-5 horizontal stabilizer pitch trim system, hydraulic motor torque is transferred to the nut and screw drives through a

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

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6. If a failure should occur in the output channel A, the C-5 Stability augmentation system

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7. What do the cyclic and collective flight controls use to change the pitch of the rotor blades

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8. Each c-5 slat surface is extended and retracted by two

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9. All three augmentation systems on the C-5 are

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10. The hydraulic manifold on the C-5 yaw augmentation system is equipped with

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11. 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?

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12. The C-5 yaw augmentation (Y/A) system provies yaw damping, turn coordination, Y/A manual rudder trim, and

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13. On the c-5, simultaneous operation of the rudder trim control switches is required to provide

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14. On the KC-135, what type of output device is used by the flight control set flight controller turn knob

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15. On the KC-135, the erection time of the gyro in the flight control set is

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16. 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

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17. 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?

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18. Which flight control is used to maneuver the helicopter left or right or forward or aft, while hovering?

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

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20. On the KC-135 a change on the pressure input of the air control unit sensor pressure data converter is represented on the output as a change in

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21. The four positions called out on the c-5 flap handle console are

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22. When the electric trim switches for the c-5 horizontal stabilizer are actuated together, electrical continuity is provided by

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23. What type filter is used in the yaw augmentation system to block any rate gyro signals developed as a result of the nomal bending of the c-5 aircraft body occuring during flight

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24. On the KC-135, the output of the angular accelerometer in the flight control set processor is used for damping what oscillations

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25. On the KC-135 flight control set, the GLIDE SLOPE ARM annunciator remains illuminated until

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26. In the C-17A electronic flight control system, control surface position feedback is provided by dual

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27. The Maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to

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28. Which is not a c-5 lateral augmentation system interface?

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29. The rudder power on the KC-135 flight control set must be on before the

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

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31. On the b-1b, hydraulic power to the left and right inboard spoiler servo cylinders is supplied by the

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32. What determines the direction the motor is driven to position the yaw trim bellcrank on the b-1b

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33. In the b-1b mechanical pitch control subsystem, normal mechanical control of the horizontal stabilzers is accomplished

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34. On the KC-135, the flight control set servomotors are connected to the aircraft conrol cables via the

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35. Which component of the H-60 altitude hold/hover stabilization system tells the system interface unit what mode has been selected?

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36. On the KC-135, the flight control set processor roll command module provides outputs to roll the aircraft in response to inputs from the

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37. When the autopilote (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

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38. Before the b-1b mechanical yaw limiter system can be placed in the limited mode, the

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39. Lengthening of the pitch cable in the b-1b mechanical pitch control system due to thermal changes is compensated for by the

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40. On the H-60 altitude hold/hover stabilization system, what mode uses all three axes accelerometers and the copilots vertical gyro for reference?

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41. On the KC-135, the primary function of the status/test panel is to test the flight control set at what level?

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42. What safety device in the wing spoiler cable system of the c-5 aircraft closes the affected spolier panels when a cable or pushrod is disconnected?

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43. The condition that allows the fairings on the B-1B to move up and down automatically are a wing sweep

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44. On the b-1b mechanical yaw control system, the two sets of rudder control pedals are interconnected

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45. 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

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46. On the KC-135, a vertical velocity of 3,500 feet per minute automatically inhibits engagement of what flight control set mode of operation?

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47. When do inboard spoilers on the B-1B roll trim system provide roll trim?

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48. What is the rudder movement of the b-1b during normal aircraft flight

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49. During manual flight, the roll damping gain of the lateral augmentation system on the c-5 is

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50. The KC-135 flight control set maintains a set Mach number by varying

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51. On the b-1b pitch control subsystem, the leading edge surface travel of the horizontal stabilizers is limited to

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52. On the KC-135 which status/test panel button allows the operator to bypass recording a failure?

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53. 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

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

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55. To initiate self-test of the c-5 pitch augmentation system, the four inboard elevator hydraulic power switches on the pilots overhead panel must be

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

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57. 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

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58. What component of the C-5 elevator control system provies the pilot with feel forces as a function of impact pressure

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59. The mechanical yaw control system on the b-1b is

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60. The lateral augmentation system on the c-5 provides roll damping, dutch roll damping, and

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61. 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

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62. To provide automatic pitch trim for the C-130, the trim tab adapter of the E-4 automatic flight control system moves the

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63. What component of the C-5 elevator control system assists the pilot in overcoming cable system friction

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64. On the B-1B, which indication on the surface position/comand indicator uses a single window for display of position information?

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

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66. Which power control assembly supplies the operating power to the yaw trim actuators on the b-1b?

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67. 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

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68. On the C-130, the altitude control on the E-4 automatic flight control system maintains a fixed altitude by controlling the

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69. During the STANDBY mode of operation of the b-1b pitch control subsytem, the actual co-pilot pitch trim commands to the stabilizers are provided by the

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70. Placing th epitch trim switch to the pitch trim-up position during STANDBY mode of operation of the b-1b pitch control subsystem causes the

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71. On the KC-135, which button on the status/test panel allows the operator to record an indicated failure in memory?

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72. On the b-1b what signals are combined with the roll command signals inside the spoiler controller to produce the "dead-band" signal?

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73. On the B-1b mechanical yaw control system, the rudder pedals provide electrical positioning information for the

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74. On the C-130 the gyro erection system in the E-4 automatic flight control system roll and pitch control

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75. In the c-17A aircraft electronic flight control system, the flight control computers directly control the ailerons,

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76. During alternate mode of operation of the b-1b pitch trim system, the trim controller in the automatic flight control system

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77. With flaps up, the limit switches cut off electrical power to the screw frive unit when the horizontal stabilizer on a c-5 reaches

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78. 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

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79. On the b-1b mechanical pitch system, the pitch control command is amplifies by the pitch master hydraulic servo cylinder to

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80. On the KC-135, which flight control set mode disengages if the turn knob is turned out of detent after engagement?

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81. The co-pilot stick controls the B-1B aircraft roll by using the stability augmentation system and

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

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83. On the KC-135, the turn knob on the flight control set must be in detent before the

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

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85. To activate the actual roll trim command on the B-1B, you

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86. In the B-1b roll control-outboard spoilers system, what is the result of placing the spoiler switch in the OFF position?

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87. The maximum rudder displacement the c-5 yaw augmentation system can command from reference is

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88. On the KC-135, the flight control set modes available when the pitch axis is engaged include ALT HOLD, MACH HOLD, and

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89. The pitch control subsystem linkage shaker motors on the b-1b are enabled

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90. Automatic disengagement of all three axes of the KC-135 flight control set occurs if an error is detected in the

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91. 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

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92. In the C-17A electronic flight control system, the primary pitch input originates in the

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93. In the rudder control loop of the E-4 automatic flight control system, the heading reference of the C-130 aircraft is locked by

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

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95. If the pitch master hydraulic servo cylinder in the b-1b mechanical pitch control system is disconnected, the

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96. On the KC-135, inputs provided by the inertial navigation system to the flight control set include pitch attitude, roll attitude, and

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97. During ALTER mode on the b-1b, the yaw trim signals applied to the actuators originate

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98. On the C-130 the trim indicators on the pedestal controller of the E-4 automatic flight control system represent the output of each

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99. 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

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

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What part of a helicopter is designed to counter the tendency of the...
What effect does raisint the collective have on the main rotor of a...
The flap position indicator on the C-5 is a dial type instrument that...
On the c-5 horizontal stabilizer pitch trim system, hydraulic motor...
On the C-5, what converts the input signal from the aileron cable...
If a failure should occur in the output channel A, the C-5 Stability...
What do the cyclic and collective flight controls use to change the...
Each c-5 slat surface is extended and retracted by two
All three augmentation systems on the C-5 are
The hydraulic manifold on the C-5 yaw augmentation system is equipped...
On the KC-135, which built in test is designed to detect a fault and...
The C-5 yaw augmentation (Y/A) system provies yaw damping, turn...
On the c-5, simultaneous operation of the rudder trim control switches...
On the KC-135, what type of output device is used by the flight...
On the KC-135, the erection time of the gyro in the flight control set...
In response to rudder trim commands, the rudder trim actuator of the...
On the C-5, maximum torque of the pilot assist cable servo is adjusted...
Which flight control is used to maneuver the helicopter left or right...
On the KC-135, cross-channel monitoring in the flight control...
On the KC-135 a change on the pressure input of the air control unit...
The four positions called out on the c-5 flap handle console are
When the electric trim switches for the c-5 horizontal stabilizer are...
What type filter is used in the yaw augmentation system to block any...
On the KC-135, the output of the angular accelerometer in the flight...
On the KC-135 flight control set, the GLIDE SLOPE ARM annunciator...
In the C-17A electronic flight control system, control surface...
The Maximum output of the B-1B speedbrake/spoiler roll trim actuator...
Which is not a c-5 lateral augmentation system interface?
The rudder power on the KC-135 flight control set must be on before...
On the C-5 roll control system, what provides positive system...
On the b-1b, hydraulic power to the left and right inboard spoiler...
What determines the direction the motor is driven to position the yaw...
In the b-1b mechanical pitch control subsystem, normal mechanical...
On the KC-135, the flight control set servomotors are connected to the...
Which component of the H-60 altitude hold/hover stabilization system...
On the KC-135, the flight control set processor roll command module...
When the autopilote (A/P) of the electronic flight control system on a...
Before the b-1b mechanical yaw limiter system can be placed in the...
Lengthening of the pitch cable in the b-1b mechanical pitch control...
On the H-60 altitude hold/hover stabilization system, what mode uses...
On the KC-135, the primary function of the status/test panel is to...
What safety device in the wing spoiler cable system of the c-5...
The condition that allows the fairings on the B-1B to move up and down...
On the b-1b mechanical yaw control system, the two sets of rudder...
On the kc-135, the voltage required to hold the flight control set...
On the KC-135, a vertical velocity of 3,500 feet per minute...
When do inboard spoilers on the B-1B roll trim system provide roll...
What is the rudder movement of the b-1b during normal aircraft flight
During manual flight, the roll damping gain of the lateral...
The KC-135 flight control set maintains a set Mach number by varying
On the b-1b pitch control subsystem, the leading edge surface travel...
On the KC-135 which status/test panel button allows the operator to...
On the b-1b, which component of the yaw limiter actuator motor B...
On the B-1b, what signals are summed by the electrical multiplexing...
To initiate self-test of the c-5 pitch augmentation system, the four...
On the KC-135, the sources of the flight control set (FCS) gyro 1...
To reduce structural loads on the C-17A vertical stabilizer, the...
What component of the C-5 elevator control system provies the pilot...
The mechanical yaw control system on the b-1b is
The lateral augmentation system on the c-5 provides roll damping,...
On the KC-135 placing the turn knob out of detent causes the NAV/LOC...
To provide automatic pitch trim for the C-130, the trim tab adapter of...
What component of the C-5 elevator control system assists the pilot in...
On the B-1B, which indication on the surface position/comand indicator...
The B-1b central integrated test system monitors the speed of the...
Which power control assembly supplies the operating power to the yaw...
During the STANDBY mode of operation of the B-1b pitch control...
On the C-130, the altitude control on the E-4 automatic flight control...
During the STANDBY mode of operation of the b-1b pitch control...
Placing th epitch trim switch to the pitch trim-up position during...
On the KC-135, which button on the status/test panel allows the...
On the b-1b what signals are combined with the roll command signals...
On the B-1b mechanical yaw control system, the rudder pedals provide...
On the C-130 the gyro erection system in the E-4 automatic flight...
In the c-17A aircraft electronic flight control system, the flight...
During alternate mode of operation of the b-1b pitch trim system, the...
With flaps up, the limit switches cut off electrical power to the...
If the C-130 aircraft is not wings-level during operation of the E-4...
On the b-1b mechanical pitch system, the pitch control command is...
On the KC-135, which flight control set mode disengages if the turn...
The co-pilot stick controls the B-1B aircraft roll by using the...
During stability control augmentation system (SCAS) operation, the...
On the KC-135, the turn knob on the flight control set must be in...
What component of the C-5 elevator control system provides the pilot...
To activate the actual roll trim command on the B-1B, you
In the B-1b roll control-outboard spoilers system, what is the result...
The maximum rudder displacement the c-5 yaw augmentation system can...
On the KC-135, the flight control set modes available when the pitch...
The pitch control subsystem linkage shaker motors on the b-1b are...
Automatic disengagement of all three axes of the KC-135 flight control...
What control(s) is/are available for the co-pilot to fly the b-1b...
In the C-17A electronic flight control system, the primary pitch input...
In the rudder control loop of the E-4 automatic flight control system,...
Which control panel on the H-60 altitude hold/hover stabilization...
If the pitch master hydraulic servo cylinder in the b-1b mechanical...
On the KC-135, inputs provided by the inertial navigation system to...
During ALTER mode on the b-1b, the yaw trim signals applied to the...
On the C-130 the trim indicators on the pedestal controller of the E-4...
On the c-5, what repositions the neutral point of the preloaded...
When the roll master servo cylinder output linkage in the mechanical...
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