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AA787 > Landing Gear > Flashcards

Landing Gear Flashcards

1
Q

On the ground, the landing gear lever is held in the DN position by an automatic lever lock. In flight, the lever lock is automatically released…
- by a landing gear mechanical lock release.
- when altitude is greater than 25 feet RA.
- through air/ground sensing.
- when groundspeed is greater than 100 knots.

A

through air/ground sensing.

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2
Q

After retraction, the landing gear are held up by…
- electric locks.
- hydraulic pressure to the up side of the actuator.
- uplocks.
- the gear doors.

A

uplocks.

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3
Q

After retraction, the EICAS landing gear position indication changes to UP for 10 seconds and then blanks.
- True
- False.

A

True

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4
Q

The alternate landing gear extension system uses a dedicated DC powered electric hydraulic pump and center hydraulic system fluid to release all gear and door uplocks. The landing gear then _________________ to the down and locked position.
- are hydraulically powered
- free fall
- are electrically driven
- are electrically and hydraulically powered

A

free fall

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5
Q

Following an alternate extension, can the landing gear be retracted?
- No, it is not possible to retract landing gear that has been extended using alternate extension.
- Yes, if right and left system hydraulic fluid is available.
- Yes, if center hydraulic system is operating.
- Yes, if normal electrical power is available.

A

Yes, if center hydraulic system is operating.

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6
Q

The braking system is powered by…
- the center hydraulic system.
- the left and right hydraulic system.
- center system hydraulic accumulators.
- four electric brake power supply units.

A

four electric brake power supply units.

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7
Q

There are three marks on the tiller assembly. The center mark identifies the neutral position of the tiller, while the other two identify the maximum left and right displacements.
- True
- False

A

True

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8
Q

Selecting DOWN on the ALTERNATE GEAR switch…
- uses electric motors to mechanically release the doors and gear uplocks.
- uses a dedicated DC powered electric hydraulic pump and center hydraulic system fluid to release all door and gear uplocks.
- uses the C1 electric motor-driven demand pumps (EMP) to release.
- uses the C2 Electric motor-driven (EMP) demand pump to release the doors and gear uplocks.

A

uses a dedicated DC powered electric hydraulic pump and center hydraulic system fluid to release all door and gear uplocks.

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9
Q

The brake system is…
- alternatively powered by the left hydraulic system.
- automatically selected to alternate if the normal system pressure is low.
- powered by the right hydraulic system.
- powered by four electric brake power supply units.

A

powered by four electric brake power supply units.

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10
Q

BRAKES advisory message on EICAS indicates…
- an antiskid system fault has occurred.
- two or more brakes are failed or a dragging brake is detected.
- the autobrake system is disarmed.
- the parking brake is set.

A

two or more brakes are failed or a dragging brake is detected.

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11
Q

Hydraulic power for gear retraction, extension and steering is supplied by the…
- left and right hydraulic system.
- center hydraulic system.
- left hydraulic system.
- right hydraulic system.

A

center hydraulic system.

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12
Q

Air/ground logic signals come from sensors located on…
- the right main landing gear beam.
- the nosewheel strut.
- the left main landing gear beam.
- each main landing gear beam.

A

each main landing gear beam.

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13
Q

During each manual brake applications, the brake control system applies one-half of the brakes on each main landing gear if wheel speeds are less than…
- 70 knots, (-8).
- 30 knots, (-9).
- 30 knots on both -8 and -9 airplanes.
- Both 1 and 2 are correct.

A

30 knots on both -8 and -9 airplanes.

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14
Q

After landing, autobrake application begins when…
- the nosewheel strut is compressed and main wheels have spun up.
- the nosewheel strut is compressed and both thrust levers are at idle.
- both thrust levers are retarded to idle and the wheels have spun up.
- either thrust lever is retarded to idle and the main gear strut are compressed.

A

both thrust levers are retarded to idle and the wheels have spun up.

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15
Q

The parking brake system electric actuators are clamped in position during parking brake application. As brakes cool,
- the aircraft is required to remain powered to maintain clamping force.
- the parking brake system has a “park and adjust” feature which monitors the condition of the brakes after application and adjusts the clamping force as needed.
- the brakes will remain set for 12 hours after application.
- the parking brake needs to be reset after the initial application.

A

the parking brake system has a “park and adjust” feature which monitors the condition of the brakes after application and adjusts the clamping force as needed.

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16
Q

Brake temperature values range from 0.0 to 9.9 in 0.1 increments. Which of the following is NOT correct?
- For values of 3.0 to 4.9, the brake symbol for the hottest brake on each main gear truck becomes solid white.
- Normal range values of 0 to 4.9 are white.
- BRAKE TEMP advisory EICAS message displays when any brake registers 5.0 or higher on the gear synoptic display.
- When invalid brake temperature data or faults are detected, the synoptic displays the average temperature of the remaining brakes.

A

When invalid brake temperature data or faults are detected, the synoptic displays the average temperature of the remaining brakes.

17
Q

Normal tire pressure values are displayed in…
- white on the GEAR synoptic.
- green on the EICAS.
- amber on the GEAR synoptic.
- cyan on the STAT synoptic.

A

white on the GEAR synoptic.

18
Q

If a rejected takeoff is initiated at or below 85 knots, the RTO autobrake function still operates when either engine thrust reverser is raised to the reverse idle detent.
- True
- False

A

False

19
Q

The rudder pedal steering disconnect switch…
- temporarily disables the rudder pedal inputs to nose wheel steering.
- is used during a flight controls freedom of motion check.
- must be held down to function and is spring loaded to the out position.
- All of the above are correct.

A

All of the above are correct.

20
Q

Nosewheel steering is powered by the _______ hydraulic system. Primary steering control up to ___ degrees in either direction is provided by a nosewheel steering tiller for each pilot. Limited steering is available through the rudder pedal inputs up to __ degrees in either direction.
- center, 90, 5
- right, 90, 5
- left 70, 8
- center, 70, 8

A

center, 70, 8

21
Q

Antiskid protection is provided on a paired main gear wheel basis.
- True
- False

A

False

22
Q

You experience an engine failure at 90 knots during the takeoff roll with autobrakes selected to RTO. A rejected takeoff is initiated. RTO will automatically apply maximum brake pressure when…
- the groundspeed is below 85 knots.
- the indicated airspeed is below 65 knots.
- the first thrust lever is at idle.
- both thrust levers are retarded to idle above 85 knots.

A

both thrust levers are retarded to idle above 85 knots.

23
Q

Which of the following will cause the autobrake to disarm during a rejected takeoff?
- Pedal braking applied.
- Autobrake fault.
- Loss of inertial data from the IRUs.
- All of the above.

A

All of the above.

24
Q

During the After Takeoff checklist, you notice that the AUTOBRAKE selector remained in the RTO position. Is this normal after takeoff?
- Yes. The selector must be manually moved to OFF.
- Yes. The selector stays in the RTO position until a new setting is selected.
- No. The selector normally automatically moves to OFF after takeoff.
- No. After takeoff, the selector normally automatically defaults to AUTOBRAKES 2 in preparation for landing.

A

No. The selector normally automatically moves to OFF after takeoff.

25
Q

On the 787-8, when the landing gear lever is placed in the UP position, the gear retraction sequence is started. After retraction, the landing gear position will be indicated on the EICAS by…
- an expanded gear position indication indicating UP in white in all three landing gear positions.
- an expanded gear position indicating UP in green in all three landing gear positions.
- a gear position indication with a single UP displayed in white, indicating all landing gear are up and locked, until gear is extended.
- the gear position indication changes to UP for 10 seconds and then blanks.

A

the gear position indication changes to UP for 10 seconds and then blanks.

26
Q

The normal brake temperature range is…
- from 0 to 4.9 displayed in white.
- from 3.0 to 4.0 displayed in cyan.
- from 5.0 to 9.9 displayed in amber.
- from 0.0 to 3.0 displayed in magenta.

A

from 0 to 4.9 displayed in white.

27
Q

After takeoff, the landing gear handle will not raise as it normally should. What would prevent the gear handle from being raised?
- Gear can never be raised until 100 feet AGL.
- Flaps are still in the takeoff range.
- Lever lock fails to release.
- Landing gear has tilted.

A

Lever lock fails to release.

28
Q

What would prevent the lever lock from releasing the gear handle?
- Parking brake is set.
- Center system hydraulic system failure.
- Right main gear side brace is locked.
- Failure in the air ground sensing system.

A

Failure in the air ground sensing system.

29
Q

How can the landing gear be retracted in the event the gear handle will not move on the first attempt after takeoff?
- It can not be retracted.
- Verify the C1 and C2 EMPs switches are both in the ON position.
- Select the UP spoition on the ALTN GEAR switch.
- Push the landing gear lever LOCK OVRD switch.

A

Push the landing gear lever LOCK OVRD switch.

AA787 (20 decks)

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