Boeing 737NG - Flight controls - SmartCockpit - Airline training guides, Aviation, Operations, Safety

The trailing edge flaps devices consist of double slotted flaps inboard outboard of each engine.

True

False

Correct! Wrong!

The ALTERNATE FLAPS Master Switch:

Arms the Alternate Flaps Position Switch, activates the Standby Hydraulic Pump, and closes the Trailing

Fully extends the LE Devices using Standby Hydraulic pressure, and electrically extends the TE Flaps

Closes the Flight Spoiler Shutoff valve

Activates the Standby Hydraulic Pump and pressurizes the STANDBY Rudder Power Control Unit.

Correct! Wrong!

The Power Transfer Unit provides an alternate source of power for the Autoslat System if:

A loss of pressure from the Hydraulic System B engine pump is sensed.

Hydraulic System A engine driven pump is inoperative

A loss of Hydraulic System A pressure is sensed

The Alternate Flaps Position Switch is momentarily held down

Correct! Wrong!

Concerning Mach Trim operation, FCCs use Mach information from the ADC / ADIRU, to compute a Mach trim actuator position whih repositions the elevator feel & centering unit, which adjusts the control column neutral position (column will not move).

False

True

Correct! Wrong!

The column will move

The Autoslat system:

Provides for slat deployment above VMO/MMO

Drives the slats to FULL EXTEND when TE Flaps 1 through 5 are selected and the airplane approaches a stall

Is normally powered by Hydraulic System A

Is normally powered by Transfer Bus No.2

Correct! Wrong!

If the flight crew selects the ALTERNATE FLAPS to the ARM position:

Trailing Edge flap bypass valve closes and standby pump activates.

Standby pump is armed while the Trailing Edge flap bypass valve is energized.

Trailing Edge flap bypass valve closes, standby pump activates and ALTERNATE FLAPS position switch is armed

Standby pump is armed while the Trailing Edge flap bypass valve is de-energized.

Correct! Wrong!

During a normal landing, flight spoilers & ground spoilers will always extend simultaneously.

True

False.

Correct! Wrong!

The FEEL DIFF PRESS light indicates:

A loss of pressure in the elvator feel computer.

An excessive differential pressure in the elevator feel computer.

An excessive temperature in the elevator feel computer

A data loss in the elevator feel computer.

Correct! Wrong!

Excessive differential pressure can be caused by erroneous activation of the Elevator Feel Shift module.

Elevator system feel is provided by the elevator feel computer. This computer receives inputs of:

Only System A hydraulic pressure

Elevator balance tabs position

Altitude & elevator position

Airspeed & stabilzer position.

Correct! Wrong!

The flight spoilers rise on the wing with up aileron and remain faired on the wing with down aileron. When the control wheel is displaced more than approximately ____ degrees, spoiler deflection is initiated.

6,5

Correct! Wrong!

Dual AILERON trim switches, located on the aft electronic panel, must be pushed simultaneously to command trim changes. The trim electrically repositions the aileron feel and centering unit, which causes the control wheel to rotate and redefines the aileron neutral position.

True

False.

Correct! Wrong!

Elevator Feel provides simulated aero forces using airspeed from elevator pitot & stabilizer position.

False

True

Correct! Wrong!

The feel is transmitted to the control columns by the elevator feel & centering unit.

The amber FEEL DIFF PRESS light illuminates when the:

Flaps are not up and a hydraulic pressure imbalance is detected or one of the elevator feel pitot systems fails

Flaps are up and a pressure imbalance between hydraulic systems A & B is detected or if one of the elevator feel pitot systems fails

Flaps are up or down and a hydraulic pressure imbalance is detected or if one of the elevator pitot systems fails. - No correct answer is provided.

Flaps are not up (more than 5) and a hydraulic pressure imbalance is detected or one of the elevator feel pitot systems fails

Correct! Wrong!

To operate the Feel system, the Elevator Feel Computer uses:

Either hydraulics system A or B pressure (whichever is higher)

Either hydraulics system A or B pressure

Hydraulics system B

Hydraulics system A

Correct! Wrong!

The system operates normally even with only one hydraulics system remaining

If wheel spinup is not detected on landing with the speed brake armed the flight spoilers will deploy automatically :

When the ground spoilers deploy

Flight spoilers do not deploy on landing, only ground spoilers deploy.

Only when the RIGHT main landing gear strut compresses

When the air/ground system senses the ground mode (any strut compresses)

Correct! Wrong!

At what flap setting(s) should the leading edge slats be in the FULL EXTEND position?

1 to 5

5 to 40.

Greater than 5

Correct! Wrong!

What is number of ground spoilers on each wing?

Correct! Wrong!

Speed Trim Failure (SPEED TRIM FAIL) Light - If illuminated (amber) this indicates a:

Failure of the speed trim system but also indicates failure of the elevator system if the MASTER WARNING cannot be reset.

Failure of the speed trim system but also indicates a failure of a single FCC channel when MASTER CAUTION light recall is activated and light extinguishes when Master Caution System is reset.

Failure of the speed trim system

Partial failure of the speed trim system if the MASTER CAUTION can be reset.

Correct! Wrong!

During the ALTERNATE FLAPS OPERATION procedure, the flight crew should plan a Flaps 15 landing. After arming the ALTERNATE FLAPS MASTER SWITCH (230 kt max), the flight crew set the flaps to desired flap position and extend flaps on maneuvering speed schedule. The LE FLAPS TRANSIT light will remain illuminates until the flaps approach the:

Flaps 15 position.

Flaps 10 position

Flaps 1 position

Flaps 5 position

Correct! Wrong!

Leading Edge devices are normally operated by ______

Hydraulic Systems A & B

Hydraulic System B

Hydraulic System A

Standby Hydraulic system.

Correct! Wrong!

The elevator transfer mechanism allows:

Forces from either control column to be transferred to the stabilizer.

The elevator feel and centering unit to transfer the source of power for elevator actuators to hydraulic systems A or B, depending upon which is producing higher pressure.

The elevator feel & centering unit to transfer proper aerodynamic forces to the control columns

The control column to be physically separated in the event of an elevator jam.

Correct! Wrong!

Mach Trim system corrects for Mach tuck by moving stabilizer up.

True.

False.

Correct! Wrong!

It moves elevators up (not the stabilizer)

? With a loss of both system A & B, the elevator FEEL DIFF PRESS light will illuminate:

False

True

Correct! Wrong!

The trailing edge flaps are at 15 units. The correct indication on the aft overhead panel for the leading edge devices is:

All LE devices FULL EXT lights illuminated

All LE devices EXT lights illuminated

All amber TRANSIT lights illuminated

LE slats EXT lights and LE flaps FULL EXT lights illuminated.

Correct! Wrong!

In the event of hydraulic Systems A & B fail, ailerons, elevators, and rudder can be operated with the Standby system.

False

True

Correct! Wrong!

If the spoilers become jammed:

The first officer’s control wheel operates the spoilers and ailerons

The ALT spoiler system is selected

The first officer’s control wheel operates the ailerons

The captain’s control wheel operates the ailerons

Correct! Wrong!

If the flight crew activates the FLT CONTROL switch Overhead panel to STBY RUD, it activates the:

Standby hydraulic system pump and opens the standby rudder shutoff valve to pressurize standby rudder power control unit.

Standby hydraulic systemp pump.

Standby hydraulic system pump and closes flight control shutoff valve, isolating ailerons and elevators.

Standby hydraulic system pump and closes the standby rudder shutoff valve

Correct! Wrong!

Loss of Hydraulic System B pressure does not cause illumination of the amber YAW DAMPER light or yaw damper disengagement.

False.

True.

Correct! Wrong!

During flight with both hydraulic systems A & B inoperative:

Trim is available for the stabilizer and rudder only. Aileron trim is inoperative with the autopilots disengaged.

The standby hydraulic system operates the trailing edge flaps normally

The standby hydraulic system operates the flaps flaps system normally

The autoslat system is still functional through the operation of the PTU

Correct! Wrong!

What is the maximum flap extension altitude?

17 000 feet

10 000 feet

23 000 feet

20 000 feet

Correct! Wrong!

What is the correct flap setting for a jammed stabilizer landing?

30 or 40

Correct! Wrong!

The Flap/Slat Electronics Unit (FSEU) provides:

Uncommanded motion protection for LE devices and TE flaps.

LE skew detection for slats 2 through 7 except during autoslat operation

TE asymetry protection by removing hydraulic pressure to the TE flaps if an asymetry is detected

All statements are correct.

Correct! Wrong!

The amber LE FLAPS TRANSIT light:

Indicates LE Slats are fully extended

Provides TE Flaps asymetry protection.

Indicates all LE Devices are fully extended

Is inhibited during Autoslat operation inflight

Correct! Wrong!

During an ALL FLAPS UP LANDING, the speed to be maintained is:

VREF40 + 30

VREF40 + 55

VREF40 + 60

VREF40 + 15

Correct! Wrong!

A Mach Trim system provides speed stability at the higher Mach numbers.Mach trim is automatically accomplished above:

Mach 0.615

Mach 0.50

Mach 0.655

Mach 0.70

Correct! Wrong!

With the loss of hydraulic system B, (system A operating normally):

Main yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON.

Main & standby yaw damper functions are lost

Standby yaw damper functions are available if the FLT CONTROL B switch is placed to STBY RUD and the YAW DAMPER switch is reset to ON

Standby yaw damper functions are available as long as hydraulic system A is providing normal pressure and the yaw damper switch is ON

Correct! Wrong!

Yaw damper inputs (main or standby) can be overriden:

By rudder pedal inputs but not trim inputs

By trim inputs but not rudder pedal inputs

By either trim or rudder pedal inputs.

Only when the yaw damper switch is off

Correct! Wrong!

The primary flight controls consist of rudder, ailerons and ______

Spoilers

Elevators

Speedbrakes

Flaps

Correct! Wrong!

The Speed Trim System (STS) is a speed stability augmentation system designed to improve flight characteristics during operation with a low gross weight, aft center of gravity and high thrust when the autopilot is not engaged.

False

True

Correct! Wrong!

The STS monitors inputs of stabilizer position, thrust lever position, airspeed and vertical speed and then trims the stabilizer using the autopilot stabilizer trim.Remember that the SPEED TRIM FAIL amber light is often illuminated when you arrive at the aircraft. It is only due to the Inertial Vertical Speed Indicator which is not powered by the ADIRUs (IRS selectors OFF): the STS receives invalid inputs.

The flap load relief system is operational at:

Flaps 30 & 40

Flaps 40 only.

Flaps 15, 30 & 40

All flap settings

Correct! Wrong!

The number of slats located on each wing are:

Correct! Wrong!

During descent from altitude you need to decrease your aispeed by using your speed brakes. What is the correct position of the SPEED BRAKE LEVER.

ARMED

FLIGHT DETENT

Any intermediate position.

Correct! Wrong!

The speedbrake lever will move forward and all spoilers will retract if either thrust lever is advanced after landing.

True

False.

Correct! Wrong!

If the SPEEDBRAKES EXTENDED light is illuminated in flight. It indicates:

The speed brake lever is beyond the ARMED position with either the TE flaps extended more than Flaps 5 or the Radio altitude is less than 500 ft

The speed brake lever is beyond the ARMED position with either the TE flaps extended more than Flaps 15 or the Radio altitude is less than 2500 ft

The speed brake lever is beyond the ARMED position with either the TE flaps extended more than Flaps 10 or the Radio altitude is less than 800 ft

The speed brake lever is beyond the ARMED position with either the TE flaps extended more than Flaps 1 or the Radio altitude is less than 800 ft

Correct! Wrong!

Main electric trim has 2 speed modes : high & low speed.

True.

Correct! Wrong!

The Speed Trim System (STS) operates most frequently during takeoffs & go-arounds. Conditions for speed trim operation are:

Airspeed between 100 KIAS and Mach 0.68, 10 seconds after takeoff, 5 seconds following release of trim switches, N1 above 60%, autopilot not engaged, sensing of trim requirement

Airspeed between 100 KIAS and Mach 0.68, 10 seconds after takeoff, 5 seconds following release of trim switches, N1 above 40%, sensing of trim requirement

Airspeed between 100 KIAS and Mach 0.68, 10 seconds after takeoff, 5 seconds following release of trim switches, N1 above 40%, autopilot not engaged, sensing of trim requirement

Airspeed between 100 KIAS and Mach 0.68, 15 seconds after takeoff, 5 seconds following release of trim switches, N1 above 60%, sensing of trim requirement

Correct! Wrong!

In addition to Hydraulic System A & B, the rudder can also be powered by the Standby Hydraulic System through the:

System B Standby Rudder Power Control Unit

System A Standby Rudder Power Control Unit

Main Rudder Power Control Unit

Standby Rudder Power Control Unit

Correct! Wrong!

Why are mechanical gates installed on the flap selector unit.

To prevent inadvertent flap lever movement beyond F1 and F15 during G/A

To hinder flap movement beyond F15 until gear down is selected.

Prevent flap movement to UP position

Prevent flap movement to UP position when speed is too low.

Correct! Wrong!

Landing flap 40 selected and in position. An IAS of 178kts is flown due to a highwind gust. Would you expect:

Flaps to retract to 25.

Flaps to retract to 30.

Flaps to retract to 15.

Flaps to remain in the current configuration.

Correct! Wrong!

! When the flaps are set at 40, the TE flaps:- retract to 30 if airspeed exceeds 163 knots- re-extend when airspeed is reduced below 158 knots.When the flaps are set at 30, the TE flaps:- retract to 25 if the airspeed exceeds 176 knots- re-extend when airspeed is reduced below 171 knots.

Roll control is provided by the ailerons, assisted by the _____

Flight spoilers

Flight spoilers & ground spoilers

Ground spoilers

Flight spoilers or ground spoilers (depending on speed)

Correct! Wrong!

The airspeed range for trim operation is:

100-300 KIAS

100 KIAS - Mach 0.50

100 KIAS - Mach 0.615

158-300 KIAS

Correct! Wrong!

What is the number of flight spoilers located on each wing?

Correct! Wrong!

The flight control computers use Mach Information from the _____ to compute a Mach trim actuator position.

Mach/Airspeed Indicator and thrust levers position

Airspeed Indicator and any thrust lever position.

ADIRU

Airspeed Indicator

Correct! Wrong!

The SPEED BRAKE DO NOT ARM light indicates that the speedbrake is not usable.

True

False

Correct! Wrong!

During a steady right-handed turn on the ground, correct indications of the Yaw Damper indicator would be?

Steady full scale right deflection

Steady in the center position.

Steady full scale left deflection.

Correct! Wrong!

What do the MACH TRIM FAIL, SPEED TRIM FAIL & AUTO SLAT FAIL lights have in common? + All of the above.

Will illuminate during Master Caution Recall if only one computer has failed.

All statements are correct.

Also illuminates the Master Caution & FLT CONT annunciator lights.

Will illuminate if both system computers fail.

Correct! Wrong!

Extending the flaps to flaps 15 using ALTERNATE FLAPS takes approximately _______

2 minutes

30 seconds

4 minutes.

1 minute

Correct! Wrong!

Boeing 737NG – Flight controls

The trailing edge flaps devices consist of double slotted flaps inboard outboard of each engine.

The ALTERNATE FLAPS Master Switch:

The Power Transfer Unit provides an alternate source of power for the Autoslat System if:

Concerning Mach Trim operation, FCCs use Mach information from the ADC / ADIRU, to compute a Mach trim actuator position whih repositions the elevator feel & centering unit, which adjusts the control column neutral position (column will not move).

The Autoslat system:

If the flight crew selects the ALTERNATE FLAPS to the ARM position:

During a normal landing, flight spoilers & ground spoilers will always extend simultaneously.

The FEEL DIFF PRESS light indicates:

Elevator system feel is provided by the elevator feel computer. This computer receives inputs of:

The flight spoilers rise on the wing with up aileron and remain faired on the wing with down aileron. When the control wheel is displaced more than approximately ____ degrees, spoiler deflection is initiated.

Dual AILERON trim switches, located on the aft electronic panel, must be pushed simultaneously to command trim changes. The trim electrically repositions the aileron feel and centering unit, which causes the control wheel to rotate and redefines the aileron neutral position.

Elevator Feel provides simulated aero forces using airspeed from elevator pitot & stabilizer position.

The amber FEEL DIFF PRESS light illuminates when the:

To operate the Feel system, the Elevator Feel Computer uses:

If wheel spinup is not detected on landing with the speed brake armed the flight spoilers will deploy automatically :

At what flap setting(s) should the leading edge slats be in the FULL EXTEND position?

What is number of ground spoilers on each wing?

Speed Trim Failure (SPEED TRIM FAIL) Light - If illuminated (amber) this indicates a:

Leading Edge devices are normally operated by ______

The elevator transfer mechanism allows:

Mach Trim system corrects for Mach tuck by moving stabilizer up.

? With a loss of both system A & B, the elevator FEEL DIFF PRESS light will illuminate:

The trailing edge flaps are at 15 units. The correct indication on the aft overhead panel for the leading edge devices is:

In the event of hydraulic Systems A & B fail, ailerons, elevators, and rudder can be operated with the Standby system.

If the spoilers become jammed:

If the flight crew activates the FLT CONTROL switch Overhead panel to STBY RUD, it activates the:

Loss of Hydraulic System B pressure does not cause illumination of the amber YAW DAMPER light or yaw damper disengagement.

During flight with both hydraulic systems A & B inoperative:

What is the maximum flap extension altitude?

What is the correct flap setting for a jammed stabilizer landing?

The Flap/Slat Electronics Unit (FSEU) provides:

The amber LE FLAPS TRANSIT light:

During an ALL FLAPS UP LANDING, the speed to be maintained is:

A Mach Trim system provides speed stability at the higher Mach numbers.Mach trim is automatically accomplished above:

With the loss of hydraulic system B, (system A operating normally):

Yaw damper inputs (main or standby) can be overriden:

The primary flight controls consist of rudder, ailerons and ______

The Speed Trim System (STS) is a speed stability augmentation system designed to improve flight characteristics during operation with a low gross weight, aft center of gravity and high thrust when the autopilot is not engaged.

The flap load relief system is operational at:

The number of slats located on each wing are:

During descent from altitude you need to decrease your aispeed by using your speed brakes. What is the correct position of the SPEED BRAKE LEVER.

The speedbrake lever will move forward and all spoilers will retract if either thrust lever is advanced after landing.

If the SPEEDBRAKES EXTENDED light is illuminated in flight. It indicates:

Main electric trim has 2 speed modes : high & low speed.

The Speed Trim System (STS) operates most frequently during takeoffs & go-arounds. Conditions for speed trim operation are:

In addition to Hydraulic System A & B, the rudder can also be powered by the Standby Hydraulic System through the:

Why are mechanical gates installed on the flap selector unit.

Landing flap 40 selected and in position. An IAS of 178kts is flown due to a highwind gust. Would you expect:

Roll control is provided by the ailerons, assisted by the _____

The airspeed range for trim operation is:

What is the number of flight spoilers located on each wing?

The flight control computers use Mach Information from the _____ to compute a Mach trim actuator position.

The SPEED BRAKE DO NOT ARM light indicates that the speedbrake is not usable.

During a steady right-handed turn on the ground, correct indications of the Yaw Damper indicator would be?

What do the MACH TRIM FAIL, SPEED TRIM FAIL & AUTO SLAT FAIL lights have in common? + All of the above.

Extending the flaps to flaps 15 using ALTERNATE FLAPS takes approximately _______