Flight Controls Flashcards
At radio altitudes less than _________do not deploy the speed brakes in flight.
A. 1,000 feet
B. 2,000 feet
C. 1,500 feet
A. 1,000 feet
Full power control to the ailerons is provided by _____________ hydraulic system.
A. Either
B. Only the A
C. Only the B
A. Either
If you have a total hydraulic power failure, rotation of the control wheels _________ positions the ailerons.
A. electrically
B. pneumatically
C. mechanically
C. mechanically
If you have a jammed spoiler system, force applied to the _____ control wheel provides roll control from the ailerons.
A. Captain’s
B. First Officer’s
A. Captain’s
If you have a jammed aileron system, force applied to the _____ control wheel provides roll control from the spoilers.
A. Captain’s
B. First Officer’s
B. First Officer’s
If the autopilot is engaged, any ______ trim applied can result in an out of trim condition and an abrupt ______ movement when the autopilot is disconnected.
A. aileron; rolling
B. rudder; yawing
C. elevator; pitching
A. aileron; rolling
When the control wheel is displaced more than approximately ____, spoiler deflection is initiated and the flight spoilers rise on the wing with the up aileron and remain faired on the wing with the down aileron.
A. 5 degrees
B. 15 degrees
C. 10 degrees
C. 10 degrees
Where is the aileron trim indicator located on the 737?
A. on top of the control wheel
B. on the aft overhead panel
C. on the center pedal stool
A. on top of the control wheel
On the 737, __________ Aileron Trim Switch(es) repositions the aileron neutral control position.
A. Movement of either
B. Movement of both
C. Movement of the required (Left or Right)
B. Movement of both
Looking at the the pitch control surfaces, these consist of _______ powered elevators and an _______ powered stabilizer.
A. electrically; hydraulically
B. hydraulically; electrically
C. hydraulically; hydraulically
B. hydraulically; electrically
If you have a control column jam, an override mechanism allows ___________.
A. the captains control column to override the first officer’s control column
B. for pneumatic separation of the control column
C. the control columns to be physically separated
C. the control columns to be physically separated
If the FEEL DIFF PRESS light Illuminates, this indicates _______.
A. excessive differential hydraulic pressure is sensed in the elevator feel computer
B. the elevator trim system is inoperative
C. an emergency situation exists due to a complete electrical failure
A. excessive differential hydraulic pressure is sensed in the elevator feel computer
If the FEEL DIFF PRESS light Illuminates, this indicates _______.
A. excessive differential hydraulic pressure is sensed in the elevator feel computer
B. the elevator trim system is inoperative
C. an emergency situation exists due to a complete electrical failure
A. excessive differential hydraulic pressure is sensed in the elevator feel computer
What has occurred when the MACH TRIM FAIL light is illuminated only when the Master Caution Annunciator recall is activated?
A. a dual channel failure of the mach trim system
B. the mach trim cutout switch has failed
C. a single channel failure of the mach trim system
C. a single channel failure of the mach trim system
The Elevator Feel Shift module increases hydraulic system A pressure to the elevator feel and centering unit during a stall. This actually increases the _________ force to approximately four times the normal feel pressure.
A. forward control column
B. aft control column
C. aileron control column
A. forward control column
There are two modes on the main electric and autopilot stabilizer trim: high speed with flaps _________ and low speed with flaps_______.
A. extended; retracted
B. retracted; extended
A. extended; retracted
Actuating either pair of stabilizer trim switches ______________ if the autopilot is engaged.
A. automatically disengages the autopilot
B. overrides the autopilot
C. renders the elevator trim system inoperative
A. automatically disengages the autopilot
With the stabilizer trim outside the takeoff trim range ___________ if takeoff is attempted.
A. An intermittent horn sounds
B. The Master Caution light illuminates
C. The Master Warning light illuminates
A. An intermittent horn sounds
_______________ may be used to return the stabilizer to electrical trim units if manual trim is used to position the stabilizer beyond the electrical trim limits.
A. the stabilizer trim switches
B. only manual trim
C. only Mach Trim
A. the stabilizer trim switches
The stabilizer trim main electric cutout switch and the stabilizer trim autopilot cutout switch are provided to allow the autopilot or main electrical trim inputs to be ____________________.
A. disconnected from their respective stabilizer trim motor
B. disconnected from the single stabilizer trim motor
C. to override to opposing stabilizer trim motor
B. disconnected from the single stabilizer trim motor
When control column movement opposes the trim direction, what will occur?
A. The control column actuated stabilizer trim cutout switches stop operation of the main electric and autopilot trim
B. The control column actuated stabilizer trim cutout switches stop operation of the main electric only
C. The control column actuated stabilizer trim cutout switches stop operation of the autopilot trim only
A. The control column actuated stabilizer trim cutout switches stop operation of the main electric and autopilot trim
Switching the STAB TRIM override switch to OVERRIDE ____________.
A. deactivates the main STAB TRIM system
B. deactivates the autopilot STAB TRIM system
C. electric trim can be used regardless of control column position
C. electric trim can be used regardless of control column position
The speed trim system (STS) is a speed stability augmentation system designed to improve the flight characteristics during any operation with a low gross weight, aft center of gravity, and high thrust when the autopilot _______ engaged.
A. is
B. is not
B. is not
While inflight and there is an illuminated SPEED TRIM FAIL light, what has occurred?
A. a dual channel failure of the speed trim system
B. a single channel failure of the speed trim system
C. the speed trim is operating
A. a dual channel failure of the speed trim system
___________ operates the rudder system.
A. Only the B hydraulic system
B. Only the A hydraulic system
C. Either hydraulic system
C. Either hydraulic system
The Rudder Trim Control switch electrically repositions the _______________, which results in a shift in the rudder neutral position.
A. rudder pedals
B. rudder feel and centering unit
C. rudder trim tabs
B. rudder feel and centering unit
__________ movements results from the yaw damper coordination.
A. A maximum of 5 degrees of rudder pedal
B. No rudder pedal
C. A maximum of 10 degrees of rudder pedal
B. No rudder pedal
B737-800, the yaw damper uses the _____________.
A. hydraulic system B or standby hydraulic system pressure
B. hydraulic system A or standby hydraulic system pressure
C. hydraulic system A or B
A. hydraulic system B or standby hydraulic system pressure
Above approximately 135 knots, there is a reduction in both hydraulic system A and B pressure. This function limits full rudder authority __________,.
A. only before landing
B. on the ground
C. in flight after takeoff and before landing
C. in flight after takeoff and before landing
The rudder pedals permit limited nose gear steering up to ______ degrees each side of center for steering.
A. 7
B. 10
C. 15
A. 7
The OFF Flag with the Rudder Trim indicates the rudder trim __________.
A. indicator is inoperative
B. is inoperative
C. is operative
A. indicator is inoperative
If you rotate the rudder trim control knob, this __________.
A. pneumatically trims the rudder
B. electrically trims the rudder
C. hydraulically trims the rudder
B. electrically trims the rudder
Which hydraulic system powers the ground spoilers?
A. A & B
B. B
C. A
C. A
When the SPEED BRAKE lever is actuated all of the spoilers will__________.
A. extend in the air
B. extend on the ground and in the air
C. extend on the ground and only the flight spoilers extend when the aircraft is in the air
C. extend on the ground and only the flight spoilers extend when the aircraft is in the air
If you use the flight spoilers during a turn ___________.
A. greatly increase the roll rate
B. greatly decrease the roll rate
C. decrease rate of descent
A. greatly increase the roll rate
All flight and ground spoilers will automatically rise to the full extension on landing if the speed brake lever is in the ARMED position and __________.
A. either thrust lever is at IDLE
B. both thrust levers are at IDLE
B. both thrust levers are at IDLE
A SPEED BRAKE DO NOT ARM illuminated light indicates ___________.
A. the speed brake lever has automatically stowed
B. an abnormal condition or during landing the wheel speed has dropped below 60kts and the speed brake lever
is not in the down position
C. the speed brake lever has automatically moved to full extend
B. an abnormal condition or during landing the wheel speed has dropped below 60kts and the speed brake lever
is not in the down position
The _______ position in the 737 indicates all flight spoilers are extended to their maximum position for inflight use, while the ________ indicates all flight and ground spoilers are extended to their maximum position for use on the ground.
A. FLIGHT DETENT; UP
B. UP; FLIGHT DETENT
C. UP; UP
A. FLIGHT DETENT; UP
A SPEED BRAKE ARMED illuminated light indicates ___________.
A. the speed brakes need to be armed
B. the speed brakes will remain stowed on landing
C. valid automatic speed brake system inputs
C. valid automatic speed brake system inputs
In the event of a total hydraulic system B failure, the trailing edge flaps ___________.
A. are inoperative
B. can be operated with hydraulic A system
C. can be operated electrically
C. can be operated electrically
____________ is provided through the electrical alternate flap drive system.
A. No asymmetry or skew protection
B. Asymmetry and skew protection
C. Asymmetry protection
A. No asymmetry or skew protection
The Flaps/Slats Electronic Unit (FSEU) monitors trailing edge flaps for _______________. If the Flaps/Slats Electronic Unit (FSEU) detects a trailing edge problem, it_______ the trailing edge flap bypass valve.
A. skew protection but no asymmetry protection; closes
B. asymmetry and skew conditions; closes
C. asymmetry protection but no skew protection; opens
B. asymmetry and skew conditions; closes
The TE flap load relief function protects the flaps from excessive air loads. When the flaps are set to 40 the TE flaps will _______ if airspeed exceeds 163 knots.
A. retract to 30
B. retract to 25
C. sound the configuration warning horn
A. retract to 30
The 737 FLAP Lever _______.
A. at flap positions 30 and 40 arms the flap load relief system
B. selects position of flap control valve, direction hydraulic pressure for flap drive unit, and selects the position of the LE devices by the determined TE flap position
C. all answers are correct
C. all answers are correct
Why are there mechanical Flap Gates positioned at the flaps 1 and flaps 15 detent?
A. for single engine and normal go-around
B. for takeoff flap settings
C. for standardization among fleets
A. for single engine and normal go-around
Where would a TE flaps asymmetry error or skew indication issue be seen?
A. The Aft Overhead Panel
B. The Flap Position Indicator
C. all answers are correct
B. The Flap Position Indicator
The 737 Leading edge devices are normally extended and retracted by ___________.
A. hydraulic power from system A
B. electric power
C. hydraulic power from system B
C. hydraulic power from system B
The 737 Leading edge devices _______ be retracted by the standby hydraulic system.
A. cannot
B. can
A. cannot
At flaps 1, the Auto Slat system _____________ as the aircraft approaches a stall condition.
A. automatically drives the slats to EXTEND
B. automatically drives the slats to FULL EXTEND
C. automatically retracts the slats from EXTEND to UP
B. automatically drives the slats to FULL EXTEND
Located on the aft overhead panel, on the Leading Edge Devices (LE DEVICES) Annunciator Panel, an extinguished LE light indicates ______.
A. the related LE device is extended
B. the related LE device has been manually extended
C. the related LE device is retracted
C. the related LE device is retracted
Located on the aft overhead panel, on the Leading Edge Devices (LE DEVICES) Annunciator Panel, pressing the Leading Edge Annunciator Panel TEST switch _________.
A. tests the FSEU
B. tests all annunciator panel lights
C. tests all trailing edge flap positions
B. tests all annunciator panel lights
An amber illuminated Leading Edge Devices Transit (LE FLAP TRANSIT) Light, indicates _________.
A. a LE slat skew condition exists
B. any LE device is in transit, or is not in its programmed position with respect to the trailing edge flaps
C. all answers are correct
C. all answers are correct
An green illuminated Leading Edge Devices Extended (LE FLAPS EXT) Light, indicates _________.
A. all leading edge devices are retracted
B. all leading flaps are extended
C. all trailing edge devices are retracted
B. all leading flaps are extended
