Landing Gear Flashcards
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.
through air/ground sensing.
After retraction, the landing gear are held up by…
- electric locks.
- hydraulic pressure to the up side of the actuator.
- uplocks.
- the gear doors.
uplocks.
After retraction, the EICAS landing gear position indication changes to UP for 10 seconds and then blanks.
- True
- False.
True
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
free fall
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.
Yes, if center hydraulic system is operating.
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.
four electric brake power supply units.
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
True
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.
uses a dedicated DC powered electric hydraulic pump and center hydraulic system fluid to release all door and gear uplocks.
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.
powered by four electric brake power supply units.
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.
two or more brakes are failed or a dragging brake is detected.
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.
center hydraulic system.
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.
each main landing gear beam.
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.
30 knots on both -8 and -9 airplanes.
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.
both thrust levers are retarded to idle and the wheels have spun up.
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.
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.
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.
When invalid brake temperature data or faults are detected, the synoptic displays the average temperature of the remaining brakes.
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.
white on the GEAR synoptic.
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
False
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.
All of the above are correct.
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
center, 70, 8
Antiskid protection is provided on a paired main gear wheel basis.
- True
- False
False
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.
both thrust levers are retarded to idle above 85 knots.
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.
All of the above.
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.
No. The selector normally automatically moves to OFF after takeoff.
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.
the gear position indication changes to UP for 10 seconds and then blanks.
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.
from 0 to 4.9 displayed in white.
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.
Lever lock fails to release.
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.
Failure in the air ground sensing system.
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.
Push the landing gear lever LOCK OVRD switch.
