Ifcs 5 Level Cdc's Volume 5

Front 1

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

Back 1

Mix box

Front 2

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

Back 2

Spring

Front 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?

Back 3

50; 40

Front 4

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

Back 4

Bob weight

Front 5

What component of the C-5 elevator control system provides the pilot with feel forces as a function of impact pressure?

Back 5

Variable feel unit

Front 6

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

Back 6

Pilot assist cable servo

Front 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?

Back 7

Trim actuator

Front 8

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

Back 8

power and ground to the trim actuator.

Front 9

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

Back 9

Tail rotor.

Front 10

What effect does raising the collective have on the main rotor of a helicopter?

Back 10

Lift increase

Front 11

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

Back 11

Cyclic

Front 12

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

Back 12

Swash plate

Front 13

Each C-5 slat surface is extended and retracted by two

Back 13

telescoping ballscrew actuators

Front 14

The four positions called out on the C-5 flap handle console are

Back 14

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

Front 15

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

Back 15

percentage; 0-100

Front 16

What safety device in the wing spoiler cable system on the C-5 aircraft closes the affected spoiler panels when a cable or pushrod is disconnected?

Back 16

Spring

Front 17

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

Back 17

gear train

Front 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

Back 18

1.5º aircraft NOSE DOWN or 6.0º aircraft NOSE UP

Front 19

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

Back 19

power and ground

Front 20

The copilot stick controls the B-1B aircraft roll by using the stability control augmentation system and

Back 20

outboard spoilers

Front 21

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

Back 21

rudder pedals and yaw-trim

Front 22

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

Back 22

greater than 61º and airspeed greater then 60 knots.

Front 23

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

Back 23

Slats

Front 24

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

Back 24

inboard spoilers are forced into the down position

Front 25

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

Back 25

1, 2, and 4 hydraulic systems

Front 26

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

Back 26

Wing sweep >35º or Mach >0.5

Front 27

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

Back 27

Outboard spoilers retract to full down position

Front 28

To activate the actual roll trim commands on the B-1B, you

Back 28

position the roll trim switch laterally

Front 29

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

Back 29

Mach <0.99 and Trim Norm selected

Front 30

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

Back 30

57º, 57'

Front 31

The mechanical yaw control system on the B-1B is

Back 31

mechanically controlled and hydromechanically actuated

Front 32

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

Back 32

yaw SCAS and nosewheel steering

Front 33

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

Back 33

through bellcranks and push-pull rods.

Front 34

Before the B-1B mechanical yaw limiter system can be placed in the limited mode, the

Back 34

slats in and left/right main gear must be uplocked

Front 35

What is the rudder movement of the B-1B during normal aircraft flight?

Back 35

Limited to +/- 10º

Front 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?

Back 36

Brake

Front 37

During ALTER mode on the B-1B, the yaw trim signals applied to the actuators originate

Back 37

from the flight control trim panel yaw trim left/right switch

Front 38

Which power control assembly supplies the operating power to the yaw trim actuators on the B-1B?

Back 38

2453A06

Front 39

What determines the direction the motor is driven to position the yaw trim bellcrank on the B-1B?

Back 39

Which power control assembly relay is energized or deenergized

Front 40

In the B-1B mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished

Back 40

symmetrically by the pilot and co-pilot sticks

Front 41

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?

Back 41

Electrical control of the horizontal stabilizers in pitch and roll.

Front 42

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

Back 42

tension regulator bungees.

Front 43

On the B-1B mechanical pitch system, the pitch control command is amplified by the pitch master hydraulic servo cylinder to

Back 43

overcome friction in the mechanical push-pull system

Front 44

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

Back 44

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

Front 45

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

Back 45

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

Front 46

The pitch control subsystem linkage shaker motors on the B-1B are enabled

Back 46

after the aircraft is in flight

Front 47

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

Back 47

DAU 4

Front 48

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

Back 48

is disabled

Front 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

Back 49

trim switch on the flight control auxiliary panel

Front 50

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

Back 50

flight control auxiliary panel

Front 51

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

Back 51

power control assembly 2455A06 to enable the pitch trim actuator motor

Front 52

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

Back 52

Roll, yaw, and normal

Front 53

All three augmentation systems on the C-5 are

Back 53

fail-operational and fail-safe

Front 54

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

Back 54

switches to channel B and remains engaged.

Front 55

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

Back 55

dutch roll damping

Front 56

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

Back 56

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

Front 57

What type filter is used in the yaw augmentation system to clock any rate gyro signals developed as a result of the normal bending of the C-5 aircraft body from occurring during flight?

Back 57

Body-bend

Front 58

The maximum rudder displacement the C-5 yaw augmentation system can command from reference is

Back 58

+/- 20º

Front 59

The lateral augmentation system on the C-5 provides roll damping, dutch roll damping, and

Back 59

spiral divergence control

Front 60

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

Back 60

0

Front 61

Which is not a C-5 lateral augmentation system interface?

Back 61

Very-high frequency control panel

Front 62

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

Back 62

in the OFF position

Front 63

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

Back 63

roll axis in engaged

Front 64

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

Back 64

yaw axis is engaged

Front 65

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

Back 65

yaw servo loop.

Front 66

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

Back 66

FCS VG

Front 67

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

Back 67

an axis hardover

Front 68

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

Back 68

roll steering.

Front 69

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

Back 69

GLIDE SCOPE

Front 70

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?

Back 70

Continuous

Front 71

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

Back 71

Dutch roll

Front 72

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

Back 72

Organizational

Front 73

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

Back 73

right arrow

Front 74

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

Back 74

Verify

Front 75

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

Back 75

processor

Front 76

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

Back 76

HDG SEL

Front 77

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

Back 77

variable resistor

Front 78

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

Back 78

drum and bracket assembly

Front 79

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

Back 79

frequency

Front 80

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

Back 80

1-1½ minutes

Front 81

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

Back 81

turn knob

Front 82

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

Back 82

CAPTURE and TRACK submodes

Front 83

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

Back 83

ALT HOLD

Front 84

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

Back 84

the pitch of the aircraft

Front 85

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

Back 85

the GLIDE SLOPE beam is captured

Front 86

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

Back 86

elevators

Front 87

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

Back 87

is cut out during commanded turns

Front 88

On the C-130, the trim indicators on the pedestal controller of the E-4 automatic flight control system represents the output of each

Back 88

servo control generator

Front 89

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

Back 89

AIL trim knob

Front 90

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

Back 90

trim tab

Front 91

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

Back 91

shorting the output of the turn motor amplifier

Front 92

In the C-17A aircraft's electronic flight control system, the flight control computers directly control the ailerons,

Back 92

elevators, rudders, and horizontal stabilizer

Front 93

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

Back 93

rudder pedals

Front 94

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

Back 94

linear variable displacement transducers (LVDT) in the hydraulic actuators

Front 95

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

Back 95

pitch stick position sensor

Front 96

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

Back 96

airspeed

Front 97

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

Back 97

engages into the same mode as the F/D

Front 98

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

Back 98

AHHS system control unit

Front 99

Which control panel on the H-60 altitude hold/hover stabilization system, what mode uses all three axes accelerometers and the copilot's vertical gyro for reference?

Back 99

HOV

Front 100

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

Back 100

System control unit