Flight Controls Flashcards
At radio altitudes less than _________do not deploy the speed brakes in flight.
- 1,000 feet
At radio altitudes less than _________do not deploy the speed brakes in flight.
- 1,000 feet
Full power control to the ailerons is provided by _____________ hydraulic system.
- Either
If you have a total hydraulic power failure, rotation of the controls wheels _________ positions the ailerons.
- mechanically
If you have a jammed spoiler system, force applied to the _____ control wheel provides roll control from the
ailerons.
- Captain’s
If you have a jammed aileron system, force applied to the _____ control wheel provides roll control from the
spoilers.
- 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.
- 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.
- 10 degrees
On the 737, __________ Aileron Trim Switch(es) repositions the aileron neutral control position.
- Movement of both
Looking at the pitch control surfaces, these consist of _______ powered elevators and an _______ powered
stabilizer.
- hydraulically; electrically
If you have a control column jam, an override mechanism allows ___________.
- the control columns to be physically separated
If the FEEL DIFF PRESS light Illuminates, this indicates _______.
- excessive differential hydraulic pressure is sensed in the elevator feel computer
On the 737, engagement and disengagement of the Mach Trim System is accomplished _____________.
- 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
The Elevator Feel Shift module increases hydraulic system A pressure to the elevator feel and centering unit
during a stall. This increases the _________ force to approximately double the normal feel pressure.
- forward control column
There are two modes on the main electric and autopilot stabilizer trim: high speed with flaps _________ and
low speed with flaps _________.
- extended; retracted
Actuating either pair of stabilizer trim switches ______________, if the autopilot is engaged.
- automatically disengages the autopilot
With the stabilizer trim outside the takeoff trim range ___________ if takeoff is attempted.
- 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.
- 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 ____________________.
- disconnected from the single stabilizer trim moto
When control column movement opposes the trim direction, what will occur?
- 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 ____________.
- electric trim can be used regardless of control column position
Switching the STAB TRIM override switch to OVERRIDE ____________.
- 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.
- is not
___________ operates the rudder system.
- Either hydraulic system
B737-800, the yaw damper uses the _____________.
- 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 _____________,.
- in flight after takeoff and before landing
The rudder pedals permit limited nose gear steering up to ______ degrees each side of center for steering.
- 7
Which hydraulic system powers the ground spoilers?
- A
When the SPEED BRAKE lever is actuated all of the spoilers will__________.
- 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 ___________.
- 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 __________.
- both thrust levers are at IDLE
An illuminated SPEED BRAKE DO NOT ARM light indicates ___________.
- 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 speedbrake lever _______ 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.
- FLIGHT DETENT; UP
In the event of a total hydraulic system B failure, the trailing edge flaps ___________.
- can be operated electrically
____________ is provided through the electrical alternate flap drive system.
- 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
preventing further travel.
- 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
trailing edge flaps will _______ if airspeed exceeds a predetermined limit.
- retract to 30
Why are there mechanical Flap Gates positioned at the flaps 1 and flaps 15 detent?
- for single engine and normal go-around
Where would a TE flaps asymmetry error or skew indication issue be seen?
- The Flap Position Indicator
The 737 Leading edge devices are normally extended and retracted by ___________.
- hydraulic power from system B
The 737 Leading edge devices _______ be retracted by the standby hydraulic system.
- cannot
At flaps 1, the Auto Slat system _____________ as the aircraft approaches a stall condition.
- automatically drives the slats to FULL EXTEND
At flaps 1, the Auto Slat system _____________ as the aircraft approaches a stall condition.
- automatically drives the slats to FULL EXTEND
