|_____________ hydraulic system is capable of providing full power control to the ailerons. Only the A Only the B Either.
In the event of total hydraulic power failure, rotation of the pilots’ controls wheels _________ positions the ailerons. mechanically electrically pneumatically.
If the spoiler system is jammed, force applied to the _____ control wheel provides roll control from the ailerons. Captain’s First Officer’s.
If the aileron system is jammed, force applied to the _____ control wheel provides roll control from the spoilers. Captain’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.
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.
Where is the aileron trim indicator located? on top of the control wheel on the aft overhead panel on the center pedal stool.
__________ Aileron Trim Switch(es) repositions the aileron neutral control position. Movement of either Movement of both Movement of the required (Left or Right).
The pitch control surfaces consist of _______ powered elevators and an _______ powered stabilizer. hydraulically; electrically electrically; hydraulically hydraulically; hydraulically.
In the event of a control column jam, an override mechanism allows ___________. the control columns to be physically separated the captains control column to override the first officer’s control column for pneumatic separation of the control column.
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.
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.
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.
The Elevator Feel Shift module increases hydraulic system A pressure to the elevator feel and centering unit during a stall. This increases _________ force to approximately four times normal feel pressure. aft control column aileron control column forward control column.
The main electric and autopilot stabilizer trim have two modes: high speed with flaps _________ and low speed with flaps _________. extended; retracted retracted; extended.
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.
___________ 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.
If 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 the stabilizer trim switches only Mach Trim.
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.
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.
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.
The speed trim system (STS) is a speed stability augmentation system designed to improve flight characteristics during operations with a low gross weight, aft center of gravity, and high thrust when the autopilot _______ engaged. is not is.
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.
___________ operates the rudder. Only the A hydraulic system Only the B 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.
__________ 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.
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.
Above approximately 135 knots, both hydraulic system A and B pressure are each reduced. This function limits full rudder authority _____________,. on the ground in flight after takeoff and before landing only before landing.
The rudder pedals permit limited nose gear steering up to ______ degrees each side of center. 7 10 15.
The Rudder Trim OFF Flag indicates the rudder trim __________. is inoperative is operative indicator is inoperative.
Rotating the rudder trim control knob, __________. electrically trims the rudder hydraulically trims the rudder pneumatically trims the rudder.
The ground spoilers are powered by hydraulic system _____. A B A and B.
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.
Using the flight spoilers during a turn will ___________. greatly decrease the roll rate decrease rate of descent 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.
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.
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.
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.
____________ is provided through the alternate (electrical) flap drive system. Asymmetry and skew protection Asymmetry protection No asymmetry or skew protection.
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.
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.
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.
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.
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.
Where would a TE flaps asymmetry or skew indication be seen? The Flap Position Indicator The Aft Overhead Panel all answers are correct.
Leading edge devices are normally extended and retracted by ___________. electric power hydraulic power from system A hydraulic power from system B.
Leading edge devices _______ be retracted by the standby hydraulic system. can 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.
At flaps 1, the Auto Slat system _____________ as the aircraft approaches the stall condition. automatically drives the slats to FULL EXTEND automatically drives the slats to EXTEND automatically retracts the slats from EXTEND to UP.
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.
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.
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.
The Flight SPOILER switches are in the OFF position for normal operating procedures are used for maintenance purposes only all answers are correct.
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.
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.
Placing the ALTERNATE FLAPS Master Switch to ARM, closes the TE flap bypass valve, ________________ and arms the ALTERNATE FLAPS position switch
closes the standby hydraulic valve activates the standby pump extends the leading edge devices.
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.
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.
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.
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 hydraulic system is capable of supplying backup pressure to which of the following primary flight controls? Rudder Aileros Flaps Elevator.
The Power Transfer Unit (PTU) will activate only after failure of the…. No. 1 engine-driven hydraulic system No.2 engine-driven hydraulic system No.1 electric hydraulic pump No. 2 electric hydraulic pump.
At radio altitudes less than _________do not deploy the speed brakes in flight. 1,000 feet 2,000 feet 1,500 feet.