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UAL B737 Study (2.27.2024) > Landing Gear system > Flashcards

Landing Gear system Flashcards

1
Q

The maximum tire ground speed is _____.
() 195 knots
() 185 knots
() 175 knots

A

() 195 knots

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2
Q

Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by _______________.
() standby system
() hydraulic system A
() hydraulic system B

A

() hydraulic system A

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3
Q

During retraction, the nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________.

() brakes automatically
() snubbers
() parking brake should be momentarily set to

A

() snubbers

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4
Q

After retraction, the main gear are held in place by ______and the nose gear is held in place by ______________.
() hydraulic pressure; mechanical uplock
() mechanical uplocks; an overcenter lock
() rubber seals; hydraulic pressure

A

() mechanical uplocks; an overcenter lock

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5
Q

An illuminated red landing gear indicator light indicates the related landing gear is in disagreement with LANDING GEAR lever position (in transits or unsafe), or ____________________.

() landing gear is up
() the landing gear manual extension must be used
() landing gear is not down and locked (with either or both forward thrust levers retarded to idle and below 800 feet AGL)

A

() landing gear is not down and locked (with either or both forward thrust levers retarded to idle and below 800 feet AGL)

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6
Q

An extinguished green landing gear indicator light indicates _______________.
() landing gear is down and locked
() the landing gear manual extension must be used
() landing gear is not down and locked

A

() landing gear is not down and locked

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7
Q

When the LANDING GEAR lever is moved to UP, _______________.
() the landing gear retracts
() the landing gear extends
() hydraulic pressure is removed from the landing gear

A

() the landing gear retracts

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8
Q

When the LANDING GEAR lever is moved to DN, hydraulic system ___ pressure is used to release the uplocks. The landing gear extends by _______________.
() A; hydraulic pressure, gravity, and air loads
() B; gravity, and air loads
() STBY, hydraulic pressure, gravity, and air loads

A

() A; hydraulic pressure, gravity, and air loads

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9
Q

The landing gear is down and locked _________ green landing gear indicator light(s) (center panel and/or overhead panel) for each gear is/are illuminated.
() as long as one
() with both

A

() as long as one

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10
Q

Manual landing gear extension is possible with the landing gear lever ____________.
() in any position
() UP or DOWN
() DOWN or OFF

A

() in any position

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11
Q

Nose wheel steering is available _____________________.
() when the nose gear is in the down position and compressed by the weight of the airplane
() when the nose gear is in the down position
() at all times

A

() when the nose gear is in the down position and compressed by the weight of the airplane

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12
Q

Pushing the rudder pedal allows for nose wheel turning up to ______in either direction.
() 7 degrees
() 25 degrees
() 78 degrees

A

() 7 degrees

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13
Q

If hydraulic system B is low or fails, _____________automatically supplies pressure to the alternate brake system.
() standby system pressure
() electric friction
() hydraulic system A

A

() hydraulic system A

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14
Q

Normal hydraulic brake pressure as indicated on the brake accumulator _________.
() 3000 psi
() 2500 psi
() 1676 psi

A

() 3000 psi

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15
Q

An amber illuminated AUTO BRAKE DISARM light indicates _______________.
() the auto brakes are set to MAX
() a malfunction exists in automatic braking system () the AUTO BRAKE select switch is set to OFF

A

() a malfunction exists in automatic braking system

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16
Q

An amber illuminated ANTISKID INOP light indicates _______________.
() a system fault is detected
() the anti-skid system need to be reset
() the auto brakes need to be armed

A

() a system fault is detected

17
Q

The auto brake system uses ______________ to provide maximum deceleration for rejected takeoff.
() hydraulic system A pressure
() hydraulic system B pressure
() hydraulic system A or B pressure

A

() hydraulic system B pressure

18
Q

After the autobraking has started, any of the following pilot actions disarm the system immediately and illuminate the AUTO BRAKE DISARM light:

() Advancing the forward thrust levers(s), except during the first 3 seconds after touchdown
() Moving speed brake lever to full forward or applying manual brakes
() All Answers are Correct

A

() All Answers are Correct

19
Q

On dry runways, the maximum autobrake deceleration rate in the landing mode is _____ that produced by full pedal braking.

() More than
() Less than
() Equal to

A

() Less than

20
Q

With the AUTO BRAKE select switch in RTO, maximum brake pressure is automatically applied when the thrust levers are retarded to idle at or above ___ Knots.

() 120
() 90
() 60

A

() 90

21
Q

Placing the AUTO BRAKE select switch to 1, 2, 3, or MAX, selects desired _____ for landing.

() Deceleration Rate
() Brake Pressure

A

() Deceleration Rate

22
Q

Anti-skid protection is provided in the _______.

() Normal and alternate brake systems
() normal braking system only
() alternate braking system only

A

() Normal and alternate brake systems

23
Q

The parking brake can be set with _____.

() hydraulic system A
() A or B hydraulic system, or the accumulator if A and B are not pressurized
() hydraulic system B

A

() A or B hydraulic system, or the accumulator if A and B are not pressurized

24
Q

Skid, locked wheel, touchdown and hydroplane protection is available_________.

() only with the normal braking system
() with normal and alternate braking system
() only with the alternate braking system

A

() with normal and alternate braking system

25
Q

_____ allows the aircraft to push back or be towed without depressurizing system A.

() a bypass switch on the forward panel
() pulling nose wheel circuit breaker
() a lockout pin

A

() a lockout pin

26
Q

The nose wheel steering wheel ______ rudder pedal steering.

() works in the opposite direction of the
() overrides
() is secondary to the

A

() overrides

27
Q

The landing gear transfer unit allows hydraulic system B to supply the volume of hydraulic fluid required to raise the landing gear at the normal rate when airborne, LANDING GEAR lever is positioned UP, either main landing gear is not up and locked and ____.

() No. 2 engine RPM drops below a limit value
() the A electric hydraulic pump is inoperative
() No. 1 engine RPM drops below a limit value

A

() No. 1 engine RPM drops below a limit value

UAL B737 Study (2.27.2024) (22 decks)

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