# Boeing 737: Flight Controls Quiz!

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The Boeing 737 is a narrow-body aircraft manufactured by Boeing at the Renton Factory in Washington. A Power Control Unit powers the primary flight controls. Either system A or system B can operate direct flight controls. In this quiz, you will be asked how many flight spoilers are located on each wing's upper surface and what the transform mechanism allows. You can do it.

• 1.

### How many flight spoilers are located on the upper surface of each wing?

• A.

Two

• B.

Three

• C.

Four

• D.

Six

C. Four
Explanation
The correct answer is four because flight spoilers are located on the upper surface of each wing.

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• 2.

### In the event of an elevator jam, a transfer mechanism allows:

• A.

For lighter than normal forces to be used on the control column for takeoff or landing.

• B.

The control columns to be physically separated.

• C.

Applying force against the jam will breakout only the Captain's control column.

• D.

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

B. The control columns to be physically separated.
Explanation
The transfer mechanism in the event of an elevator jam allows the control columns to be physically separated. This means that if one control column becomes jammed or unresponsive, the other control column can still be used to control the elevator. This separation ensures that the pilots can maintain control of the aircraft even in the event of an elevator malfunction.

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• 3.

### Autopilot trim and stabilizer trim use separate motors.

• A.

True

• B.

False

B. False
Explanation
The statement is false because autopilot trim and stabilizer trim do not use separate motors. In fact, they both use the same motor to adjust the trim settings of an aircraft. The autopilot trim system is responsible for automatically adjusting the aircraft's trim based on inputs from the autopilot system, while the stabilizer trim system allows the pilot to manually adjust the trim settings. Both systems work together to ensure the aircraft maintains its desired pitch and stability during flight.

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• 4.

### Conditions for speed trim operation include:

• A.

5 seconds after takeoff.

• B.

Ten seconds after release of trim switches.

• C.

100 KIAS - Mach 0.68

• D.

N1 above 50%.

C. 100 KIAS - Mach 0.68
Explanation
The speed trim operation is activated when the aircraft reaches a speed of 100 knots indicated airspeed (KIAS) or Mach 0.68. This means that once the aircraft reaches this speed, the speed trim system will automatically adjust the aircraft's trim settings to maintain stability and control. The other conditions mentioned, such as the time after takeoff and release of trim switches, as well as N1 above 50%, may be relevant for other aircraft systems or procedures, but they are not directly related to the speed trim operation.

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• 5.

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

• A.

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

• B.

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

• C.

Main and standby yaw damper functions are inoperative.

• D.

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.

C. Main and standby yaw damper functions are inoperative.
Explanation
With the loss of hydraulic system B, both the main and standby yaw damper functions become inoperative. The main yaw damper functions require hydraulic system A to provide normal pressure and the yaw damper switch to be ON. Similarly, the standby yaw damper functions also require hydraulic system A to provide normal pressure and the yaw damper switch to be ON. However, if the FLT CONTROL B switch is placed to STBY RUD and the YAW DAMPER switch is reset to ON, the standby yaw damper functions can be made available. But in this given scenario, there is no mention of any action being taken to activate the standby yaw damper functions, so the correct answer is that both main and standby yaw damper functions are inoperative.

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• 6.

### When the standby yaw damper is active, rudder movements are indicated on the yaw damper indicator.

• A.

True

• B.

False

B. False
Explanation
When the standby yaw damper is active, rudder movements are not indicated on the yaw damper indicator. The standby yaw damper is designed to provide stability and control to the aircraft, particularly during yawing motions. It operates independently from the rudder and does not directly indicate rudder movements. Therefore, the statement is false.

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• 7.

### Yaw damper inputs (main or standby) can be overridden:

• A.

Only when the yaw damper switch is OFF.

• B.

By trim inputs but not rudder pedal inputs

• C.

By rudder pedal inputs but not trim inputs.

• D.

By either trim or rudder pedal inputs.

D. By either trim or rudder pedal inputs.
Explanation
Yaw damper inputs can be overridden by either trim or rudder pedal inputs. This means that if the yaw damper switch is ON, the inputs from either the trim or the rudder pedals will have the ability to override the yaw damper system. This allows the pilot to have control over the aircraft's yaw movement, either through adjustments to the trim or by using the rudder pedals to directly input commands.

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• 8.

### The number of ground spoilers on each wing is:

• A.

Two.

• B.

Three.

• C.

Four.

• D.

Six.

A. Two.
Explanation
The correct answer is two because ground spoilers are aerodynamic devices that are deployed on the wings of an aircraft during landing to increase drag and reduce lift. They help in slowing down the aircraft by disrupting the smooth airflow over the wings. Typically, there are two ground spoilers on each wing, making a total of four on the aircraft.

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• 9.

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

• A.

Only when the right main landing gear strut is compressed.

• B.

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

• C.

When the ground spoilers deploy.

• D.

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

B. When the air/ground system senses the ground mode (any strut compresses).
Explanation
When the air/ground system senses the ground mode (any strut compresses), the flight spoilers will deploy automatically. This means that as soon as any of the landing gear struts are compressed upon landing, the flight spoilers will be activated. The activation of the flight spoilers helps to increase drag and reduce lift, aiding in the deceleration of the aircraft during landing. Therefore, the correct answer is when the air/ground system senses the ground mode (any strut compresses).

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• 10.

### The number of slats located on each wing is:

• A.

2

• B.

3

• C.

4

• D.

6

C. 4
Explanation
The correct answer is 4 because the question asks for the number of slats located on each wing. Among the given options, 4 is the only number that represents the number of slats on each wing.

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• 11.

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

• A.

True

• B.

False

A. True
Explanation
The statement is true because the trailing edge devices on an aircraft typically include double-slotted flaps located both inboard and outboard of each engine. These flaps are used to increase the lift and drag of the aircraft during takeoff and landing, allowing for better control and maneuverability.

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• 12.

### The flap load relief system is operational at:

• A.

All flap settings.

• B.

Flaps 15, 30, and 40.

• C.

Flaps 30 and 40.

• D.

Flaps 40 only.

C. Flaps 30 and 40.
Explanation
The flap load relief system is operational at Flaps 30 and 40. This means that when the flaps are set to either 30 or 40, the system will activate to relieve excessive loads on the flaps. It is not operational at all flap settings or at Flaps 15 only. Therefore, the correct answer is Flaps 30 and 40.

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• 13.

### The flap/ slat electronics unit (FSEU) provides:

• A.

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

• B.

TE asymmetry protection.

• C.

Uncommanded motion protection for LE devices or TE flaps.

• D.

All of the above are correct.

D. All of the above are correct.
Explanation
The flap/slat electronics unit (FSEU) provides LE skew detection for slats 2 through 7 except during autoslat operation. This means that it can detect any misalignment or skewing of the leading edge slats. It also provides TE asymmetry protection, which means it can detect any asymmetrical movement of the trailing edge flaps. Additionally, it provides uncommanded motion protection for both the leading edge devices and the trailing edge flaps. Therefore, all of the given statements are correct.

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• 14.

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

• A.

All amber TRANSIT lights illuminated.

• B.

All LE devices FULL EXT lights illuminated.

• C.

All LE devices EXT lights illuminated.

• D.

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

B. All LE devices FULL EXT lights illuminated.
Explanation
The correct indication on the aft overhead panel for the leading edge devices is "All LE devices FULL EXT lights illuminated." This means that all the leading edge devices, including both the LE slats and LE flaps, are fully extended. The other options do not accurately represent the correct indication for the leading edge devices.

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• 15.

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

• A.

ARMED

• B.

FLIGHT DETENT.

• C.

UP.

• D.

Any intermediate position.

B. FLIGHT DETENT.
Explanation
During the descent from altitude, the correct position of the SPEED BRAKE LEVER is in the FLIGHT DETENT. This position allows the speed brakes to be deployed and helps in decreasing the airspeed effectively. The FLIGHT DETENT position ensures that the speed brakes are armed and ready for use, providing the necessary aerodynamic drag to slow down the aircraft during descent.

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• 16.

### What is the maximum flap extension altitude?

• A.

10,000 feet

• B.

17,000 feet.

• C.

20,000 feet.

• D.

23,000 feet.

C. 20,000 feet.
Explanation
The maximum flap extension altitude refers to the highest altitude at which the flaps on an aircraft can be extended. Flaps are used to increase lift during takeoff and landing, and they are typically retracted once the aircraft reaches a certain altitude. In this case, the correct answer is 20,000 feet, which means that the flaps can be extended up to this altitude before they need to be retracted.

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• 17.

### The ALTERNATE FLAPS master switch:

• A.

Fully extends the LE devices using standby hydraulic pressure, and electrically extends the TE flaps.

• B.

Closes the Flight Spoiler Shutoff valve.

• C.

Activates the standby hydraulic pump and pressurizes the standby rudder Power Control Unit.

• D.

Arms the ALTERNATE FLAPS position switch, activates the standby hydraulic pump, and closes the Trailing Edge Flaps Bypass valve.

D. Arms the ALTERNATE FLAPS position switch, activates the standby hydraulic pump, and closes the Trailing Edge Flaps Bypass valve.
Explanation
The ALTERNATE FLAPS master switch performs multiple functions. It arms the ALTERNATE FLAPS position switch, which allows the flaps to be controlled manually. It also activates the standby hydraulic pump, which provides hydraulic pressure to extend the flaps. Additionally, it closes the Trailing Edge Flaps Bypass valve, ensuring that the hydraulic pressure is directed to the flaps and not bypassed.

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• 18.

### An alternate retraction system is provided for the LE devices.

• A.

True

• B.

False

B. False
Explanation
An alternate retraction system is not provided for the LE devices.

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• 19.

### The amber LE FLAPS TRANSIT light:

• A.

Indicates all LE devices are fully extended.

• B.

Indicates LE slats are fully extended.

• C.

Is inhibited during autoslat operation in flight.

• D.

Provides TE flaps asymmetry protection.

C. Is inhibited during autoslat operation in flight.
Explanation
The amber LE FLAPS TRANSIT light is inhibited during autoslat operation in flight. Autoslat is a system that automatically extends the leading edge slats on an aircraft to improve lift and control at low speeds. When the autoslat system is active, the LE FLAPS TRANSIT light is turned off to indicate that the slats are not in transit but rather in their extended position. This helps pilots to know the status of the slats during autoslat operation.

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• 20.

### The auto slat system:

• A.

Provides for slat deployment above Vmo/ Mmo.

• B.

Drives the slats to the full extended position when the TE Flaps 1 through 5 are selected and the airplane approaches a stall.

• C.

• D.

B. Drives the slats to the full extended position when the TE Flaps 1 through 5 are selected and the airplane approaches a stall.
Explanation
The auto slat system is designed to automatically extend the slats to their full position when the airplane approaches a stall and the trailing edge flaps are set to positions 1 through 5. This helps to increase the lift generated by the wings and improve the aircraft's overall performance and handling characteristics during critical flight conditions.

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• 21.

### The Power Transfer Unit (PTU) provides an alternate source of power for the auto slat system if:

• A.

A loss of hydraulic system A pressure is sensed.

• B.

The hydraulic system A engine driven pump is inoperative.

• C.

The Alternate Flaps position switch is momentarily held down.

• D.

Pressure from the hydraulic system B engine driven pump drops below limits.

D. Pressure from the hydraulic system B engine driven pump drops below limits.
Explanation
The Power Transfer Unit (PTU) is designed to provide an alternate source of power for the auto slat system in certain situations. One of these situations is when the pressure from the hydraulic system B engine driven pump drops below limits. This means that if the hydraulic system B pump is not providing enough pressure, the PTU will kick in and supply power to the auto slat system. This ensures that the slats can still function properly even if there is a problem with the hydraulic system B pump.

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• 22.

### In addition to hydraulic system A and B, the rudder can also be powered by the standby hydraulic system through the:

• A.

System A standby rudder Power Control Unit.

• B.

System B standby rudder Power Control Unit.

• C.

Standby rudder Power Control Unit.

• D.

Main rudder Power Control Unit.

C. Standby rudder Power Control Unit.
Explanation
The standby rudder Power Control Unit is capable of powering the rudder in addition to hydraulic system A and B. This unit serves as a backup system, ensuring that the rudder can still be operated even if one or both of the hydraulic systems fail.

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• 23.

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

• A.

Altitude and elevator position.

• B.

Elevator balance tabs position.

• C.

Only system A hydraulic pressure.

• D.

Airspeed and stabilizer position.

D. Airspeed and stabilizer position.
Explanation
The elevator feel computer is responsible for providing the feel of the elevator system. It takes inputs such as airspeed and stabilizer position to determine the appropriate elevator position. These inputs are crucial in ensuring that the elevator responds correctly to changes in airspeed and stabilizer position, allowing for a smooth and controlled flight. The other inputs mentioned, such as altitude, elevator position, elevator balance tabs position, and system A hydraulic pressure, may be important for other aspects of the elevator system but are not directly related to the feel of the system.

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• 24.

### The amber FEEL DIFF PRESS light illuminates when the:

• A.

Excessive differential pressure exists in the elevator feel computer.

• B.

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

• C.

Flaps are up or down and a hydraulic pressure imbalance is detected or if one of the elevator pitot systems fails.

• D.

A. Excessive differential pressure exists in the elevator feel computer.
Explanation
The correct answer is "Excessive differential pressure exists in the elevator feel computer." This means that when there is a significant difference in pressure within the elevator feel computer, the amber FEEL DIFF PRESS light will illuminate. This could indicate a potential issue or malfunction within the system, which requires attention and investigation.

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• 25.

### Select the correct statement.

• A.

The primary flight controls are powered by hydraulic systems A and B, with backup from the standby hydraulic system for the rudder and manual reversion for the ailerons and elevator.

• B.

Flight spoilers are used both for roll control, descent and deceleration.

• C.

The trailing edge flaps can be both extended and retracted using the alternate flap drive system.

• D.

All statements are correct.

D. All statements are correct.
Explanation
All three statements provided in the question are correct. The primary flight controls are indeed powered by hydraulic systems A and B, with the standby hydraulic system serving as a backup for the rudder and manual reversion being available for the ailerons and elevator. Flight spoilers are used for roll control, descent, and deceleration. Additionally, the trailing edge flaps can be extended and retracted using the alternate flap drive system. Therefore, the answer "All statements are correct" is accurate.

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• 26.

### Loss of hydraulic system B pressure does not disengage the yaw damper switch.

• A.

True

• B.

False

A. True
Explanation
When the hydraulic system B pressure is lost, it does not affect the yaw damper switch. The yaw damper switch is a separate system that helps stabilize the aircraft during flight. Even if there is a loss of hydraulic system B pressure, the yaw damper switch will still remain engaged and continue to function properly. Therefore, the statement is true.

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• Mar 22, 2023
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