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AAL 737 > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

The primary flight controls consist of _____.

a. stabilizer, rudder, and spoilers
b. elevators, yaw damper, and ailerons
c. ailerons, elevators, and spoilers
d. ailerons, elevators, and rudder

A

d. ailerons, elevators, and rudder

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2
Q

The primary flight controls are normally powered by hydraulic system(s) ____.

a. A and Standby
b. A and B
c. B only
d. A only

A

b. A and B

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3
Q

____ can be extended by the Standby Hydraulic System in Alternate mode.

a. Trailing edge flaps
b. Leading edge flaps/slats
c. Elevators
d. Ailerons

A

b. Leading edge flaps/slats

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4
Q

If a FEEL DIFF PRESS light illuminates, ____.

a. depressurize the A or B hydraulic system
b. No crew action is required in flight. Continue normal operations.
c. immediately turn off the associated flight control switch
d. place both Flt Control switches to STBY RUDDER

A

b. No crew action is required in flight. Continue normal operations.

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5
Q

When the Flaps/Slats Electronics Unit (FSEU) detects a trailing edge asymmetry or skew condition, the FSEU closes the TE Flap Bypass Valve, ____.

a. illuminates the amber FLT CONT annunciator light, and displays a needle split on the Flap Position Indicator
b. and displays a needle split on the Flap Position Indicator
c. and freezes the TE Flap needles in place
d. illuminates the green EXT light, and displays a needle split on the flap position indicator

A

b. and displays a needle split on the Flap Position Indicator

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6
Q

On aircraft 3AA - 3LB, load relief for the Trailing edge flaps is only provided for flaps ____.

a. 30 and 40
b. 25, 30 and 40
c. 25 and 30
d. 15

A

a. 30 and 40

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7
Q

During alternate flap operation, the TE flaps are positioned using ____ power.

a. hydraulic
b. manual
c. electrical
d. electrical or hydraulic

A

c. electrical

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8
Q

The SPEED BRAKE lever will automatically move to the down detent, and all spoilers will retract, if ____.

a. the TOGA button is pressed
b. either throttle is advanced after landing
c. wheel spin up drops below 60 knots
d. wheel spin up drops below 50 knots

A

b. either throttle is advanced after landing

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9
Q

In the event hydraulic systems A and B fail, the ailerons and elevators can be operated ____ and the rudder must be operated by the ____ system.

a. mechanically (manually), pneumatic
b. electrically, alternate
c. mechanically (manually), standby
d. automatically, mechanical

A

c. mechanically (manually), standby

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10
Q

If the aileron control system is jammed, the ____ can still fly the aircraft using the ____ after force is applied to the control wheels and they break free.

a. Captain, control tabs
b. Captain, spoilers
c. FO, spoilers
d. FO, ailerons

A

c. FO, spoilers

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11
Q

With the trailing edge flaps at 1, the leading edge slats are ____.

a. in the extend position
b. in the full extend position
c. retracted
d. none of the above

A

a. in the extend position

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12
Q

Hydraulic System A pressure to the Main Rudder PCU is reduced at airspeeds above approximately ______ knots.

a. 120
b. 135
c. 140
d. 150

A

b. 135

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13
Q

The horizontal stabilizer is normally powered _____, but may also be operated _____.

a. manually, electrically
b. automatically, pneumatically
c. electrically, manually
d. none of the above

A

c. electrically, manually

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14
Q

Leading edge devices can be _____ by the Standby Hydraulic System if System B fails.

a. extended and retracted
b. extended
c. retracted
d. none of the above

A

b. extended

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15
Q

On the ground, speed brakes normally use _____ to destroy lift and make braking more effective.

a. ground spoilers only
b. flight spoilers only
c. both flight and ground spoilers
d. compression of the left main landing gear strut to deploy the ground spoilers

A

c. both flight and ground spoilers

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16
Q

In aircraft 3AA-3LB, the LE devices will go to the full extend position when you select _____ or greater with the flap handle.

a. 10
b. 2
c. 5
d. 1

A

a. 10

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17
Q

The _____ of the Stab Trim Indicator corresponds to the allowable range of trim settings for takeoff.

a. green band
b. APL NOSE UP selection settings
c. 3 entire scale
d. 5 to 10 unit range marks

A

a. green band

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18
Q

The autoslat feature is available in flight

a. at all flap settings
b. at landing flap settings
c. with trailing edge flaps selected to 30-40
d. with trailing edge flaps selected to 1, 2, or 5

A

d. with trailing edge flaps selected to 1, 2, or 5

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19
Q

If we move the flap lever from 5 to 10, but the leading edge devices all stay in the extend position, the ____ Light will be illuminated.

a. LE FLAPS TRANSIT
b. LE FLAPS EXT
c. AUTO SLAT FAIL
d. SLATS EXTEND

A

a. LE FLAPS TRANSIT

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20
Q

The maximum altitude for extension of flaps is ____ feet.

a. 11,000
b. 30,000
c. 20,000
d. 15,000

A

c. 20,000

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21
Q

Leading edge devices are normally operated by ____.

a. Hydraulic System A only
b. Hydraulic System B only
c. Standby Hydraulic System
d. Hydraulic Systems A and B

A

b. Hydraulic System B only

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22
Q

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

a. flight spoilers
b. ground spoilers
c. autoslats
d. both A and B above

A

a. flight spoilers

23
Q

With the SPEED BRAKE Lever in the DOWN detent, how can the speedbrakes be deployed on landing?

a. The pilot can raise the lever manually.
b. The speedbrake is not available.
c. The speedbrake lever will automatically move to full up position when the reverse thrust levers are moved to reverse when above 60 knots.
d. Both 1 and 3 are correct

A

d. Both 1 and 3 are correct

24
Q

The LE FLAPS TRANSIT light illuminated indicates _____. Select the most correct answer.

a. leading edge devices are in transit
b. leading edge devices are not in the programmed position with respect to the trailing edge flaps
c. a leading edge device asymmetry
d. any of the above

A

d. any of the above

a. leading edge devices are in transit
b. leading edge devices are not in the programmed position with respect to the trailing edge flaps
c. a leading edge device asymmetry
d. any of the above

25
Q

When using the SPEED BRAKE in flight, the speedbrake lever should _____.

a. be moved to the FLIGHT DETENT only
b. be moved to the UP position
c. be moved to any setting
d. be moved to the DOWN position

A

a. be moved to the FLIGHT DETENT only

26
Q

Speed Brake Load Alleviation System operates in flight under what conditions?

a. Flaps up, gross wt. greater than 155,000 lbs., airspeed greater than 320 kts
b. Flaps up, gross wt. less than 155,000 lbs., at all airspeeds
c. Whenever the airspeed limitations are exceeded for flaps 30 or 40
d. When any flap airspeed limitation is exceeded

A

a. Flaps up, gross wt. greater than 155,000 lbs., airspeed greater than 320 kts

27
Q

If wheel spin-up is not detected by the air/ground sensors, the flight spoilers will deploy when _____.

a. the right main gear strut compresses
b. the left main gear strut compresses
c. any main gear strut compresses
d. thrust reverser extension occurs

A

c. any main gear strut compresses

28
Q

____ can be extended by the Standby Hydraulic System in Alternate mode.

a. Trailing edge flaps
b. Leading edge flaps/slats
c. Ailerons
d. Elevators

A

b. Leading edge flaps/slats

29
Q

During the origination pre-flight, this light illuminates alter the IRS Mode Selectors are to NAV. The “Flight Control Panel…CHECK” is accomplished by ____.

a. Calling Maintenance. The Speed Trim System has failed
b. resetting the Stab Trim to Zero
c. Doing nothing. This is a normal indication while the IRUs are aligning
d. resetting the light with the Press-To-Test Switch

A

c. Doing nothing. This is a normal indication while the IRUs are aligning

30
Q

This light and the Master Caution Lights sell-illuminate during taxi-out. Select the most correct statement.

a. Check the MEL or call Maintenance. There is a dual channel failure of the Speed Trim System.
b. No action is required. The Speed Trim System only works with the autopilot engaged.
c. No action is required. The Speed Trim System will operate 10 seconds after takeoff.
d. Reset the SPEED TRIM FAIL light by pressing either of the Master Caution Lights.

A

a. Check the MEL or call Maintenance. There is a dual channel failure of the Speed Trim System.

31
Q

If instead, this light illuminates once you are in flight, the autopilot _____.

a. has lost the ability to trim the aircraft
b. is still fully operational
c. can only be engaged in CWS P Mode
d. if engaged, has now disengaged and cannot be re-engaged

A

b. is still fully operational

32
Q

You observe these lights on the system B hydraulic panel. The QRH directs you to use the Alt Flaps procedure. After arming the All Flaps master switch, you extend the trailing edge flaps electrically. The leading edge flaps are extended ______.

a. by Hydraulic System A and the PTU
b. by the hydraulic fluid in the standby system
c. electrically by the alternate flaps toggle switch
d. automatically when you arm the alternate flaps master switch

A

b. by the hydraulic fluid in the standby system

33
Q

While extending the flaps electrically through the 5 degree flap position, if you still observe these
lights, ____.
a. there is a disagreement between the flap handle and the LED’s
b. the LEDs are still in transit
c. the flap gage is indicating an erroneous position
d. the flaps have not approached the flaps 10 degree position or beyond

A

d. the flaps have not approached the flaps 10 degree position or beyond

34
Q

When the flaps have been lowered to 15 degrees with the ALT system and a missed approach has been executed, the _____.

a. TE flaps can be retracted with the ALT system but not the LE devices
b. TE flaps can be retracted with the ALT system while the LE devices will retract with the PTU
c. TE and LE flaps will retract with the ALT system
d. flaps cannot be retracted

A

a. TE flaps can be retracted with the ALT system but not the LE devices

35
Q

When positioning the flaps for takeoff from UP to 1, the crew noticed this condition. What could have caused this malfunction?

a. Jammed T.E. Flaps
b. Jammed L.E. Devices
c. Skewed T.E. Flap
d. Jammed Rudder

A

c. Skewed T.E. Flap

36
Q

The __ protects the flaps in this condition.

a. FCC
b. DEU
c. EEC
d. FSEU

A

d. FSEU

37
Q

The FSEU protects the flaps during ____ operation.

a. Alternate Flap
b. Normal Flap
c. both Normal and Alternate Flap
d. The FSEU does not provide any flap protection.

A

b. Normal Flap

38
Q

As you advance the thrust lever for takeoff, would you get an intermittent horn with the LEDs
positioned as indicated?
a. NO. The LED’s are not part of the takeoff warning system.
b. NO. The TE Flaps are set at 5 Degrees.
c. Yes. The LED’s are not in the proper position.
d. No. If the parking brake is released

A

c. Yes. The LED’s are not in the proper position.

39
Q

The previous condition has now been corrected. The takeoff warning sounds again. What else could cause this? (picture from previous scenario)

a. Stab trim in green band and auto throttle switch not armed.
b. Parking brake released and RTO not selected.
c. Stab Trim not in green band or parking brake lever set.
d. Stab Trim in green band and Stab Trim Cutout Switches in normal

A

c. Stab Trim not in green band or parking brake lever set.

40
Q

With the TE Flap/Leading Edge Devices set, Stab Trim in the green band, parking break off, and speed brake handle stowed you still have a takeoff Warning Horn. What else could be causing this?

a. You must press TO/GA to silence the horn.
b. An over wing Exit Door did not lock properly.
c. Spoiler(s) are not fully down.
d. Trailing Edge Flaps are at a 15 degree setting

A

c. Spoiler(s) are not fully down.

41
Q

During normal operations with these two FLT CONTROL switches in the ON position. They control pressure to the respective _____.

a. rudder only
b. elevator only
c. aileron only
d. rudder, aileron, and elevator

A

d. rudder, aileron, and elevator

42
Q

After loss of system A. the QRH directs you to move the A FLT CONTROL switch to STBY RUD. This action will pressurize the ______.

a. aileron, elevator, and rudder systems
b. landing gear transfer unit
c. Standby Rudder and the #1 thrust reverser
d. A system PCU

A

c. Standby Rudder and the #1 thrust reverser

43
Q

With this switch in STBY RUD position how would you know if the standby rudder valve is open?

a. The low pressure light under the B FLT CONTROL Switch extinguishes.
b. The Standby HYD Low Quantity light illuminates.
c. The Low pressure light under the A FL T CONTROL Switch extinguishes.
d. Elevator Feel Diff light extinguishes

A

c. The Low pressure light under the A FL T CONTROL Switch extinguishes

44
Q

With the loss of B Hydraulic System, the yaw damper will ____.

a. remain operating from the A hydraulic System
b. be inoperative causing the Yaw Damper Light to illuminate
c. be inoperative, but the Yaw Damper Light will not be illuminated until the Flt control B switch is moved to STBY RUD
d. cause the Yaw Damper Switch to trip off

A

c. be inoperative, but the Yaw Damper Light will not be illuminated until the Flt control B switch is moved to STBY RUD

45
Q

Placing the B FLT CONTROL switch to STBY RUD will cause the YAW DAMPER switch to ______.

a. pressurize the A Hydraulic system making it fully operational
b. operate the standby FSEU
c. trip OFF and illuminate the Yaw Damper Light
d. allow you to reconnect the Yaw Damper by selecting the Yaw Damper switch on

A

c. trip OFF and illuminate the Yaw Damper Light

46
Q

Subsequently, the A Hydraulic System also fails. How would you gain control of the Standby Yaw Damper?

a. Turn the Yaw Damper Switch ON.
b. Ensure both A and B Flight Control Switches are in the Standby Rudder Position and then place the Yaw Damper Switch ON.
c. Check that the B System Low Pressure light is illuminated.
d. You cannot recover the Standby Yaw Damper with a Feel Diff Light illuminated.

A

b. Ensure both A and B Flight Control Switches are in the Standby Rudder Position and then place the Yaw Damper Switch ON.

47
Q

With the STAB TRIM positioned as indicated, what would happen when the throttles are advanced for TO with all other systems set properly?

a. An intermittent horn would sound.
b. A steady horn would sound.
c. There would be no alert since this is the proper setting for TO.
d. The trim would automatically go to the proper setting.

A

c. There would be no alert since this is the proper setting for TO

48
Q

If the trim was set to 10 units nose up and then the throttles are advanced for takeoff. What kind of alert would you get, if any?

a. A flashing red light
b. A steady horn
c. A Stab out of Trim Light
d. An intermittent warning horn

A

d. An intermittent warning horn

49
Q

While applying nose down trim, the electric trim stops. How can you continue to trim if you need more nose down trim?

a. Speed trim system will fix the problem.
b. Have the other pilot push the elevator forward.
c. Trim manually.
d. Engage autopilot and trim again.

A

c. Trim manually

50
Q

(MAX 8) Fly-by-wire Spoiler system provides the following new features.

a. Maneuver Load Alleviation (MLA), Landing Attitude Modifier (LAM) and Coordinated Flare Cue landing assistance.
b. Emergency Descent Spoilers (EDS).
c. Elevator Jam Landing Assist System.
d. Both b and c above

A

d. Both b and c above.

51
Q

(MAX 8) Emergency Descent Speed Brakes system (EDS):

a. Generates additional drag to allow the Max to capture and maintain a glidepath similar to the NG.
b. Armed when the airplane is above 30,000 feet and the cabin altitude warning is active.
c. Fully automatic with operation transparent to the crew.
d. Both b and c above.

A

b. Armed when the airplane is above 30,000 feet and the cabin altitude warning is active.

52
Q

(MAX 8) The Spoiler Control Electronics Unit (SCE):

a. One sensor is applied to the Captains yoke and provides input for Coordination with the HUD Flare Cue during landing.
b. Translates signals from the speedbrake lever position sensor, the First Officer’s control wheel and other airplane data inputs.
c. Must be selected on during initial FMC setup.
d. Both a and b are correct

A

b. Translates signals from the speedbrake lever position sensor, the First Officer’s control wheel and other airplane data inputs.

53
Q

(MAX 8) The Spoiler light indicates:

a. One or more spoiler pairs are inoperative.
b. The spoilers are deployed.
c. The spoilers are not in the commanded position.
d. There is a fault in the fly-by-wire system.

A

a. One or more spoiler pairs are inoperative.

54
Q

(MAX 8) The Elevator Jam Landing Assist Switch is located on:

a. Aft Overhead Panel
b. First Class Seating Area
c. Fwd Attendant Panel
d. E/E Compartment

A

a. Aft Overhead Panel

AAL 737 (32 decks)

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