Flight Control System Flashcards
What is the maximum flap extension altitude?
() 10,000 ft.
() 20,000 ft.
() 25,000 ft.
() 20,000 ft.
_____________ hydraulic system is capable of providing full power control to the ailerons.
() Only the A
() Only the B
() Either
() Either
In the event of total hydraulic power failure, rotation of the pilots’ controls wheels _________ positions the ailerons.
() mechanically
() electrically
() pneumatically
() mechanically
If the spoiler system is jammed, force applied to the _____ control wheel provides roll control from the ailerons.
() Captain’s
() First Officer’s
() Captain’s
If the aileron system is jammed, force applied to the _____ control wheel provides roll control from the spoilers.
() Captain’s
() First Officer’s
() First Officer’s
Any ______ trim applied when the autopilot is engaged can result in an out of trim condition and an abrupt ________ movement when the autopilot is disconnected.
() aileron; rolling
() rudder; yawing
() elevator; pitching
() aileron; rolling
The flight spoilers rise on the wing with the up aileron and remain faired on the wing with the down aileron. When the control wheel is displaced more than approximately ____, spoiler deflection is initiated.
() 15 degrees
() 10 degrees
() 5 degrees
() 10 degrees
Where is the aileron trim indicator located?
() on the aft overhead panel
() on the center pedal stool
() on top of the control wheel
() on top of the control wheel
__________ Aileron Trim Switch(es) repositions the aileron neutral control position.
() Movement of either
() Movement of both
() Movement of the required (Left or Right)
() Movement of both
The pitch control surfaces consist of _______ powered elevators and an _______ powered stabilizer.
() hydraulically; electrically
() electrically; hydraulically
() hydraulically; hydraulically
() hydraulically; electrically
In the event of a control column jam, an override mechanism allows ___________.
() the captains control column to override the first officer’s control column
() the control columns to be physically separated
() for pneumatic separation of the control column
() the control columns to be physically separated
Illumination of the FEEL DIFF PRESS light indicates _______.
() the elevator trim system is inoperative
() excessive differential hydraulic pressure is sensed in the elevator feel computer
() an emergency situation exists due to a complete electrical failure
() excessive differential hydraulic pressure is sensed in the elevator feel computer
Engagement and disengagement of the Mach Trim System is accomplished _____________.
() automatically as a function of pressure altitude
() manually by use of the Mach Trim Cutout Switch
() automatically as a function of airspeed
() automatically as a function of airspeed
What has occurred when the MACH TRIM FAIL light is illuminated only when the Master Caution Annunciator recall is activated?
() a single channel failure of the mach trim system
() a dual channel failure of the mach trim system
() the mach trim cutout switch has failed
() a single channel failure of the mach trim system
The main electric and autopilot stabilizer trim have two modes: high speed with flaps _________ and low speed with flaps _________.
() extended; retracted
() retracted; extended
() extended; retracted
If the autopilot is engaged, actuating either pair of stabilizer trim switches ______________.
() overrides the autopilot
() automatically disengages the autopilot
() renders the elevator trim system inoperative
() automatically disengages the autopilot
___________ if takeoff is attempted with the stabilizer trim outside the takeoff trim range.
() The Master Caution light illuminates
() The Master Warning light illuminates
() An intermittent horn sounds
() An intermittent horn sounds
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 ____________________.
() disconnected from the single stabilizer trim motor
() disconnected from their respective stabilizer trim motor
() to override to opposing stabilizer trim motor
() disconnected from the single stabilizer trim motor
When control column movement opposes trim direction, what occurs?
() The control column actuated stabilizer trim cutout switches stop operation of the main electric only
() The control column actuated stabilizer trim cutout switches stop operation of the autopilot trim only
() The control column actuated stabilizer trim cutout switches stop operation of the main electric and autopilot trim
() The control column actuated stabilizer trim cutout switches stop operation of the main electric and autopilot trim
Placing the STAB TRIM override switch to OVERRIDE ____________.
() deactivates the autopilot STAB TRIM system
() electric trim can be used regardless of control column position
() deactivates the main STAB TRIM system
() electric trim can be used regardless of control column position
While inflight the SPEED TRIM FAIL light illuminates. What has occurred?
() a single channel failure of the speed trim system
() a dual channel failure of the speed trim system
() the speed trim is operating
() a dual channel failure of the speed trim system
___________ operates the rudder.
() Only the A hydraulic system
() Only the B hydraulic system
() Either hydraulic system
() Either hydraulic system
Operation of the Rudder Trim Control switch electrically repositions the _______________, which results in a shift in the rudder neutral position.
() rudder pedals
() rudder trim tabs
() rudder feel and centering unit
() rudder feel and centering unit
__________ movement results from yaw damper coordination.
() A maximum of 5 degrees of rudder pedal
() A maximum of 10 degrees of rudder pedal
() No rudder pedal
() No rudder pedal
On the B737-800, the yaw damper uses _____________.
() hydraulic system A or standby hydraulic system pressure
() hydraulic system B or standby hydraulic system pressure
() hydraulic system A or B
() hydraulic system B or standby hydraulic system pressure
The rudder pedals permit limited nose gear steering up to ______ degrees each side of center.
() 7
() 10
() 15
() 7
The Rudder Trim OFF Flag indicates the rudder trim __________.
() is inoperative
() is operative
() indicator is inoperative
() indicator is inoperative
Rotating the rudder trim control knob, __________.
() electrically trims the rudder
() hydraulically trims the rudder
() pneumatically trims the rudder
() electrically trims the rudder
When the SPEED BRAKE lever is actuated all the spoilers __________.
() extend on the ground and only the flight spoilers extend when the aircraft is in the air
() extend on the ground and in the air
() extend in the air
() extend on the ground and only the flight spoilers extend when the aircraft is in the air
Using the flight spoilers during a turn will ___________.
() greatly decrease the roll rate
() decrease rate of descent
() greatly increase the roll rate
() greatly increase the roll rate
All flight and ground spoilers will automatically rise to full extend on landing if the speed brake lever is in the ARMED position and __________.
() both thrust levers are at IDLE
() either thrust lever is at IDLE
() both thrust levers are at IDLE
An illuminated SPEED BRAKE DO NOT ARM light indicates ___________.
() the speed brake lever has automatically moved to full extend
() 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 speed brake lever has automatically stowed
() 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 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 ground use.
() UP; FLIGHT DETENT
() UP; UP
() FLIGHT DETENT; UP
() FLIGHT DETENT; UP
An illuminated SPEED BRAKE ARMED light indicates ___________.
() the speed brakes need to be armed
() valid automatic speed brake system inputs
() the speed brakes will remain stowed on landing
() valid automatic speed brake system inputs
In the event of hydraulic system B failure, the trailing edge flaps ___________.
() are inoperative
() can be operated electrically
() can be operated with hydraulic A system
() can be operated electrically
The Flaps/Slats Electronic Unit (FSEU) monitors trailing edge flaps for _______________. If the FSEU detects a trailing edge problem, it_______ the trailing edge flap bypass valve.
() asymmetry and skew conditions; closes
() skew protection but no asymmetry protection; closes
() asymmetry protection but no skew protection; opens
() asymmetry and skew conditions; closes
On the B737-800, 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.
() retract to 30
() retract to 25
() sound the configuration warning horn
() retract to 30
The FLAP Lever _______.
() 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
() at flap positions 30 and 40 arms the flap load relief system
() all answers are correct
() all answers are correct
() 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
() at flap positions 30 and 40 arms the flap load relief system
Why are there mechanical Flap Gates positioned at 1 and 15?
() for single engine and normal go-around
() for takeoff flap settings
() for standardization among fleets
() for single engine and normal go-around
Where would a TE flaps asymmetry or skew indication be seen?
() The Flap Position Indicator
() The Aft Overhead Panel
() all answers are correct
() The Flap Position Indicator
Leading edge devices _______ be retracted by the standby hydraulic system.
() can
() cannot
() cannot
On the Leading Edge Devices (LE DEVICES) Annunciator Panel, located on the aft overhead panel, an extinguished LE light indicates ______.
() the related LE device is extended
() the related LE device is retracted
() the related LE device has been manually extended
() the related LE device is retracted
On the Leading Edge Devices (LE DEVICES) Annunciator Panel, located on the aft overhead panel, pressing the Leading Edge Annunciator Panel TEST switch _________.
() tests all trailing edge flap positions
() tests all annunciator panel lights
() tests the FSEU
() tests all annunciator panel lights
An illuminated amber Leading Edge Devices Transit (LE FLAP TRANSIT) Light, indicates _________.
() any LE device is in transit, or is not in its programmed position with respect to the trailing edge flaps
() a LE slat skew condition exists
() all answers are correct
() all answers are correct
() any LE device is in transit, or is not in its programmed position with respect to the trailing edge flaps
() a LE slat skew condition exists
An illuminated green Leading Edge Devices Extended (LE FLAPS EXT) Light, indicates _________.
() all leading edge devices are retracted
() all trailing edge devices are retracted
() all leading flaps are extended
() all leading flaps are extended
The Flight SPOILER switches
() are in the OFF position for normal operating procedures
() are used for maintenance purposes only
() all answers are correct
() are used for maintenance purposes only
An illuminated amber YAW DAMPER Light indicates _________.
() the yaw damper is being operated by the standby hydraulic system
() the yaw damper switch needs to be positioned to OFF
() the yaw damper is not engaged
() the yaw damper is not engaged
With the YAW DAMPER Switch ON, the yaw damper is engaged to the main rudder power control unit if ___________________.
() the B FLT CONTROL switch is in the ON position
() the B FLT CONTROL switch is in the OFF position
() the A, B and Standby hydraulic systems are inoperative
() the B FLT CONTROL switch is in the ON position
Momentarily pressing the ALTERNATE FLAPS position switch to DOWN ________________.
() partially extends LE devices using residual A system pressure
() partially extends LE devices using residual B system pressure
() fully extends LE devices using standby hydraulic pressure
() fully extends LE devices using standby hydraulic pressure
An illuminated amber Speed Trim Failure (SPEED TRIM FAIL) Light indicates ________________.
() a failure of the speed trim system
() a failure of the mach trim system
() a failure of the autopilot
() a failure of the speed trim system
An illuminated amber Automatic Slat Failure (AUTO SLAT FAIL) Light during MASTER CAUTION recall indicates ________________.
() a failure of a single Stall Management / Yaw Damper computer
() a failure of both Stall Management / Yaw Damper computers
() a failure of the autopilot
() a failure of a single Stall Management / Yaw Damper computer
An illuminated amber STBY RUD ON Light indicates ________________.
() the standby rudder system is commanded on to pressurize the standby rudder power control unit
() the standby rudder has failed
() the standby hydraulic system has failed
() the standby rudder system is commanded on to pressurize the standby rudder power control unit
Do not deploy the speed brakes in flight at radio altitudes less than ___.
() 2,000 ft
() 1,000 ft
() 1,500 ft
() 1,000 ft
If the manual trim is used to position the stabilizer beyond the electrical trim limits, ____ may be used to return the stabilizer to electrical trim units.
() only manual trim
() only Mach trim
() the stabilizer trim switches
() the stabilizer trim switches
The ground spoilers are powered by hydraulic system ___.
() B
() A
() A and B
() A
