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99 Cards in this Set
- Front
- Back
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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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Mix Box
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On the C-5 roll control system, what provides positive system centering with no force applied to the control wheel?
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Spring
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On the C-5, maximum torque of the pilot assist cable servo is adjusted to provide approx. how much assistance in percent to the pitch and roll axes, respectively?
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50% ; 40%
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What compmnent of the C-5 elevator control system provides the pilot with feel forces as a function of normal acceleration?
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Bob Weight
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What component of the C-5 elevator control system provides the pilot with feel forces as a function of impact pressure?
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Variable feel unit.
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What component of the C-5 elevator control system assists the pilot in overcoming cable system friction?
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Pilot assist servo cable.
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On the C-5, what repositions the neutral point of the preloaded centering bungee after the rudder pedals have been displaced to a desired trim position.
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Trim actuator.
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On the C-5, simultaneous operation of the rudder trim control switches is required to provide what?
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Power and ground to the trim actuator.
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What part of a helicopter is designed to counter the tendancy of the aircraft to spin about the vertical axis?
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Tail rotor.
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What effect does raising the collective have on the main rotor of a helicopter?
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Lift increases.
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Which flight control is used to maneuver the helicopter left or right, and forward or aft, while hovering?
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Cyclic control.
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What do the cyclic and collective flight controls use to change the pitch of the rotor blades?
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Swash plate.
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Each C-5 slat surface is extended and retracted by two of these.
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Telescoping ballscrew actuators.
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The four positions called out on the C-5 flap handle console are?
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UP, T/O 40, T/O AND APP, and LANDING.
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The flap position indicator on the C-5 is a dial type instrument that shows flap position in
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percentage; 0-100.
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What safety in the wing spoiler cable system of the c-5 closes the affected spoiler panels when a cable or pushrod is disconnected?
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spring
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On the C-5 horizontal stabilizer pitch tim system, hydraulic motor torque is transferred to the nut and screw drives through what?
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A gear train.
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With the flaps up, the limit switches cut off electrical power to the screw drive unit when the horizontal stabilizer on a c-5 reaches
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1.5' aircraft nose down or 6.0' aircraft nose up.
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when the electric trim switches for the c-5 horizontal stabilizer are actuated together, electrical continuity is provided by
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power and ground
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The co-pilot stick controls the B-1B aircraft roll by using the stability control augmentation system and
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outboard spoilers.
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During SCAS operation, the b-1b upper and intermediate rudders get their primary position signals from the
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rudder pedals and yaw-trim.
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the conditions that allow the fairings on the b-1b to move up and down automatically are a wing sweep
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greater than 61' and airspeed greater than 60 knots.
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on the b-1b, which indication on the surface position/command indicator uses a single window for display of position information?
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slats
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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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inboard spoilers are forced the the full down position.
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on the b-1b, hydraulic power to the left and right inboard spoiler servo cylinders is supplied by the
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1,2, and 4 hydraulic systems
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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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Wing sweep >35' or Mach >0.5
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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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outboard spoilers retract to the full down position.
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to activate the actual roll trim commands on the b-1b, you
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position the roll trim switch laterally.
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when do the inboard spoilers on the b-1b roll trim system provide roll trim?
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mach <0.99 and trim norm selected.
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the max output of the b-1b speedbrake/spoiler roll trim actuator is limited to
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57', 57 minutes.
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The mechanical yaw control system on the b-1b is
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mechanically controlled and hydromechanically actuated.
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on the b-1b mechanical yaw control system, the rudder pedals provide electrical positioning information for the
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yaw scas and nosewheel steering.
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on the b-1b mechanical yaw contro system, the two sets of rudder control pedals are interconnected
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throught two bellcranks and push-pull rods.
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befor the b-1b mechanical yaw limiter system can be placed in the limited mode, the
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slats in and left/right main landing gear must be uplocked.
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what is the rudder movement of the b-1b during normal aircraft flight?
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limited to + or - 10'
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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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brake
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during ALTER mode on the b-1b, the yaw trim signals applied to the actuators originate
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from the flight control trim panel yaw trim left/right switch.
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which PCA supplies the operating power to the yaw trim actuators on the b-1b?
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2453A06
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What determines the direction the motor is driven to position the yaw trim bellcrank on the b-1b?
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which PCA is energized or deenergized.
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in the b-1b mechanical pitch control subsystem, normal mechanical control of the horizontal stabilizers is accomplished
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symmetrically by the pilot and copilot control sticks.
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what control(s) is/are available for the copilot to fly the b-1b aircraft if the pilots stick in the mechanical pitch control system is isolated due to a failure in the linkage?
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electrical control of the horizontal stabilizers in pitch and roll.
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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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tension regulator bungees.
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on the b-1b mechanical pitch system, the pitch control command is amplified by the pitch master hydraulic servo cylinder to
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overcome friction in the mechanical push-pull system.
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if the pitch master hydraulic servo cylinder in the b-1b mechanical pitch control system is disconnected, the
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pitch centering bungees place the horizontal stabilizers into the center position.
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on the b-1b pitch control subsystem, the leading edge surface travel of the horizontal stabilizers is limited to
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20' up and 10' down at a max travel rate of 25' per min.
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the pitch control subsystem linkage shaker motors on the b-1b are enabled
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after the aircraft is in flight.
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the b-1b CITS monitors the speed of the pitch control subsystem linkage shaker motors through
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DAU 4
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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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is disabled
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during the standby mode of operation of the b-1b piutch control subsystem, the pitch trim actuator recieves the pitch trim-up command from the standby
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trim switch on the flight control aux. panel.
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During the standby mode of operation of the b-1b pitch control subsystem, the actual copilot pitch trim commands to the stabilizers are provided by the
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flight control aux panel.
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placing the pitch trim switch to the the pitch trim -up position during standby mode of operation of the b-1b pitch control subsytem causes the
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PCA 2455A06 to enable the pitch trim actuator motor.
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on the b-1b what signals are summed by the electrical multiplexing system to illuminate the TTO annunciator?
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Roll, yaw, and normal.
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all three augmentation systems on the c-5 are
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fail-operational and fail-safe
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if a failure should occur in output channel A, the c-5 stability augmentation system
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switches to channel B and remains engaged.
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the c-5 yaw augmentation system provides yaw damping, turn coordination, Y/A manual rudder trim, and
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dutch roll damping
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the hydraulic manifold on the c-5 yaw augmentation system is equipped with
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a SOV, HPS, EHV, and LVDT.
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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?
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body-bend filter.
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the max. rudder displacement the c-5 yaw augmentation system can command from reference is
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+ or - 20 degrees
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the lateral augmentation system on the c-5 providfes roll damping, dutch roll damping, and
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spiral divergance control.
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during manual flight, the roll damping gain of the lateral augmentation system on the c-5 is
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0
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which is not a c-5 lateral augmentation system interface?
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Very-high frequency control panel.
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to initiate self-test of the c-5 pitch augmenttion system, the four inboard elevator hydraulic power switches on the pilots overhead panel must be
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in the off position.
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on the kc-135, the turn knob on the flight control set must be in detent before the
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yaw axis is engaged.
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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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yaw servo loop.
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on the kc-135, cross channel monitoring in the flight control set processor of the flight control set prevents a single processor failure from causing
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an axis hardover
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on the kc-135, the sources of the flight control set gyro 1 signals are the INS and
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FCS VG
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on the kc-135, inputs provided by the INS to the flight control set include pitch attitude, roll attitude, and
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roll steering
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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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GLIDE SLOPE
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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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Continuous
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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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Dutch roll
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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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organizational.
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on the kc-135, which button on the ststus/test panel allows the operator to record an indicated failure in memory?
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right arrow.
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on the kc-135, which status/test panel button allows the operator to bypass recording a failure?
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VERIFY
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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 FCS
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processor (FCSP)
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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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HDG SEL
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on the kc-135, what type of output device is used by the flight control set flight controller turn knob?
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Variable resistor.
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on the kc-135, the flight control set servomotors are connected to the aircraft control cables via the
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drum and bracket assembly
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on the kc-135, a chang on the pressure inpt of the air control unit sensor pressure data converter is represented on the output as a change in
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frequency.
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on the kc-135, the erection time of the gyro in the flight control set is
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1-1 1/2 minutes
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on the kc-135, the FCSP roll command module provides outputs to roll the aircraft in response to inputs from the
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turn knob.
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on the kc-135, placing the turn knob out of detentcauses the NAV/LOC switch on the flight control set tactical air navigation to disengage during the
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CAPTURE and TRACK submodes
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on the kc-135, a vertical velocity of 3,500 fpm automatically inhibits engagement of what flight control set mode of operation?
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ALT HOLD
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the kc-135 flight control set maintains a set mach number by varying
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the pitch of the aircraft.
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on the kc-135 FCS, the GLIDE SLOPE ARM annunciator remains illuminated until
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the GLIDE SLOPE beam is captured.
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on the c-130, the altitude control on the e-4 AFCS maintains a fixed altitude by controlling the
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elevators
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on the c-130, the altitude control on the e-4 automatic flight control system roll and pitch control
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is cut out during commanded turns.
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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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servo control generator.
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if the c-130 is not wings level during operation of the e-4 AFCS, the aircraft can be returned to wings-level by using the
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AIL trim knob
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To provide automatic pitch trim for the c-130, the trim tab aapter of the e-4 AFCS moves the
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trim tab
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in the rudder control loop of the e-4 AFCS, the heading reference of the c-130 is locked by
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shorting the output of the turn motor amplifier.
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in the c-17 EFCS, the flight control computers directly control the ailerons,
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elevators, rudders, and horizontal stabilizer
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in response to rudder trim commands, the rudder trim actuator of the c-17 EFCS moves the rudder as well as the
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rudder pedals
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in the c-17 EFCS, control surface position feedback is provided by dual
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LVDT's in the hydraulic actuators.
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in the c-17 EFCS, the primary pitch input originates in the
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pitch stick position sensor
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to reduce structural loads on the c-17 vertical stabilizer, the flight control computers of the EFCS limit rudder movement as a function of
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airspeed
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when the a/p of the EFCS on a c-17 aircraft is engaged after the f/d is already engaged, the a/p
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engages into the same mode as the f/d.
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which control panel on the H-60 AHHS system contains an altitude select knob?
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AHHS system control unit.
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on the H-60 AHHS, what mode uses all three axes accelerometers and the copilots VG for reference?
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HOV
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Which component of the H-60 AHHS system tells the system interface unit what mode has been selected?
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System control unit.
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