2a533b Volume 5
Quiz for 2a533b volume 5
- 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
Correct Answer
C. Mix Box -
- 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
Correct Answer
A. Spring -
- 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
Correct Answer
C. 50:40 -
- 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
Correct Answer
C. Bob weight -
- 5.
What component of the C-5 elevator control system provies the pilot with feel forces as a function of impact pressure
- A.
Variable feel unit
- B.
Centering spring
- C.
Bob weight
- D.
Cable
Correct Answer
A. Variable feel unit -
- 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
Correct Answer
A. Pilot assist cable servo -
- 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
Correct Answer
C. Trim actuator -
- 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 signal to the yaw computer
- D.
Two grounds to the yaw damper
Correct Answer
B. Power and ground to the trim actuator -
- 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
Correct Answer
C. Tail rotor -
- 10.
What effect does raisint the collective have on the main rotor of a helicopter?
- A.
Lift increases
- B.
Lift decreases
- C.
Airspeed increases
- D.
Airspeed decreases
Correct Answer
A. Lift increases -
- 11.
Which flight control is used to maneuver the helicopter left or right or forward or aft, while hovering?
- A.
Yoke
- B.
Cyclic
- C.
Collective
- D.
Foot pedals
Correct Answer
B. Cyclic -
- 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
Correct Answer
A. Swash plate -
- 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 slate drive limiters
Correct Answer
C. Telescoping ballscrew actuators -
- 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
Correct Answer
C. UP, T/O 40, 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, 0-60
- C.
Percent 0-60
- D.
Percent, 0-100
Correct Answer
D. Percent, 0-100 -
- 16.
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?
- A.
Switch
- B.
Spring
- C.
Valve
- D.
Cam
Correct Answer
B. Spring -
- 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
Correct Answer
C. Gear train -
- 18.
With flaps up, the limit switches cut off electrical power to the screw frive 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
Correct Answer
D. 1.5 degrees aircraft NOSE DOWN or 6.0 degrees aircraft NOSE UP -
- 19.
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
Correct Answer
B. Power and ground -
- 20.
The co-pilot stick controls the B-1B aircraft roll by using the stability augmentation system and
- A.
Inboard spoilers
- B.
Outboard spoilers
- C.
Mechanical linkage
- D.
Roll gyro differential signals
Correct Answer
B. Outboard spoilers -
- 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
Correct Answer
D. Rudder pedals and yaw-trim -
- 22.
The condition that allows 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 degrees and airspeed less than 70 knots
Correct Answer
A. Greater than 61 degrees and airspeed greater than 60 knots -
- 23.
On the B-1B, which indication on the surface position/comand indicator uses a single window for display of position information?
- A.
Slats
- B.
Flaps
- C.
Spoilers
- D.
Speedbrakes
Correct Answer
A. Slats -
- 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 places in the full up position
- C.
Inboard spoilers are forced into the down position
- D.
Pilot control stick is forced to the center position
Correct Answer
C. Inboard spoilers are forced into the down 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 sstems
- C.
1,2 and 4 hydraulic systems
- D.
2,3 and 4 hydraulic systems
Correct Answer
C. 1,2 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>35degrees or Mach>0.5 degrees
- C.
Wing sweep>15degrees or Mach>1.0 degrees
- D.
Roll rate and wing sweep > 35 degrees
Correct Answer
B. Wing sweep>35degrees or Mach>0.5 degrees -
- 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
Correct Answer
D. Outboard spoilers retract to full down position -
- 28.
To activate the actual roll trim command 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
Correct Answer
D. Position the roll trim switch laterally -
- 29.
When do 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
Correct Answer
A. Mach -
- 30.
The Maximum output of the B-1B speedbrake/spoiler roll trim actuator is limited to
- A.
53 degrees, 55 minutes
- B.
56 degrees, 37 minutes
- C.
57 degrees, 57 minutes
- D.
61 degrees, 57 minutes
Correct Answer
C. 57 degrees, 57 minutes -
- 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
Correct Answer
C. Mechanically controlled and hydromechanically actuated -
- 32.
On the B-1b mechanical yaw control system, the rudder pedals provide electrical positioning information for the
- A.
Yaw stability control augementation sytem (scas) and brakes.
- B.
Mechanical yaw, yaw SCAS, and nosewheel steering
- C.
Nosewheel steering, yaw SCAS, and brakes
- D.
Yaw SCAS and nosewheel steering
Correct Answer
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
Correct Answer
B. Through two bellcranks 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
Correct Answer
B. Slats in and left/right main gear must be uplocked -
- 35.
What is the rudder movement of the b-1b during normal aircraft flight
- A.
Limitemd to +-10 degrees
- B.
Unlimited to +- 25 degrees
- C.
Unlimited to +- 26 degrees
- D.
Limited to +-10 degrees or +-25degrees, depending on the mode of operation
Correct Answer
A. Limitemd to +-10 degrees -
- 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
Correct Answer
B. Brake -
- 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
Correct Answer
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
Correct Answer
A. 2453A06 -
- 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.
Wether the brake is engaged or disengaged
- C.
The signal from the proximity switch assemblies
- D.
Which power control assembly relay is energized or deenergized
Correct Answer
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 stabilzers 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
Correct Answer
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 mechanical pitch control system is isolated due to a failure in the linkage
- A.
Mechanical control of the horizontal stabilzers 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
Correct Answer
B. Electrical 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 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
Correct Answer
A. Tension regulator bungees -
- 43.
On the b-1b mechanical pitch system, the pitch control command is amplifies 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 assembly 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
Correct Answer
B. Overcome friction in the mechanical push-pull system -
- 44.
If the pitch master hydraulic servo cylinder in the b-1b mechanical pitch control system is disconnected, the
- A.
Stabilizers are places 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 positon
Correct Answer
D. Pitch centering bungees place the horizontal stabilizers into the center positon -
- 45.
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 max travel rate of 25 degrees per second.
- B.
20 degrees up and down at a max travel rate of 25 degrees per second
- C.
25 degrees up and 15 degrees down at a max travel rate of 20 degrees per second
- D.
25 degrees up and down at a maximum travel rate of 20 degrees per second
Correct Answer
A. 20 degrees up and 10 degrees down at a max travel rate of 25 degrees 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 the power is applied to the aircraft
- D.
After the electrical multiplexing system enables power control assembly 2454A06
Correct Answer
B. After the aircraft is in flight -
- 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
Correct Answer
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, byt 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 stabiity control augementation system controllers
Correct Answer
A. Is disabled -
- 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 control panel
- C.
Contacts of the control stick pitch trim switch
- D.
Trim switch on the flight control power panel
Correct Answer
B. Trim switch on the flight control auxiliary control panel -
- 50.
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
- A.
Control stick
- B.
Flight control trim panel
- C.
Flight control power panel
- D.
Flight control auxiliary panel
Correct Answer
D. Flight control auxiliary panel -
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Jan 21, 2013Quiz Edited by
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Nov 23, 2010Quiz Created by
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