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CAE Q 2 > Landing gear > Flashcards

Landing gear Flashcards

1
Q

The air/ground system receives air/ground logic signals from:

a) Radio altimeter 1.
b) The cabin pressure controller.
c) ADIRU 1, ADIRU 2 serves as a back up.
d) Six sensors, two on each landing gear.

A

d) Six sensors, two on each landing gear.

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2
Q

. When during takeoff with RTO selected, the forward thrust levers are moved to idle
before a wheelspeed of 90 kts is reached:
a) The AUTO BRAKE DISARM light doesn’t illuminate and no automatic braking is
applied; the autobrake system remains armed.
b) The AUTO BRAKE DISARM light illuminates and no automatic braking is applied.
c) The AUTO BRAKE DISARM light illuminates and maximum automatic braking is
applied.
d) The AUTO BRAKE DISARM light doesn’t illuminate and maximum automatic braking
is applied.

A

a) The AUTO BRAKE DISARM light doesn’t illuminate and no automatic braking is
applied; the autobrake system remains armed.

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3
Q

Impact fittings located in the opening of each main gear wheel well:
a) Provide automatic braking to the main gear wheels during retraction.
b) Prevent a gear with a spinning damaged tire and loose tread from entering the wheel
well.
c) Allow the landing gear transfer unit to use hydraulic system B pressure to retract the
gear if system A fails.
d) Prevents damage to the wheel well during gear retraction in case the gear strut did
not extend completely after take-off.

A

b) Prevent a gear with a spinning damaged tire and loose tread from entering the wheel
well.

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4
Q

When the manual landing gear extension access door is open:
a) Manual landing gear extension is possible with the landing gear lever in any position.
b) Normal landing gear extension is always possible.
c) Landing gear retraction is possible if hydraulic system A pressure is available.
d) The landing gear lever has to be in the down position for the gear to be extended
manually.

A

a) Manual landing gear extension is possible with the landing gear lever in any position.

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5
Q

When a landing is made with RTO selected:
a) Automatic braking occurs at the RTO level.
b) The AUTO BRAKE DISARM light illuminates one to two seconds after touchdown.
c) The AUTO BRAKE DISARM light illuminates two minutes after touchdown.
d) Automatic braking occurs automatically at auto brake 3 level, one to two seconds
after touchdown.

A

b) The AUTO BRAKE DISARM light illuminates one to two seconds after touchdown.

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6
Q

After braking has started, which of the following pilot actions will disarm the
system immediately and illuminate the AUTO BRAKE DISARM light:
a) Moving the SPEED BRAKE lever to the flight detent position.
b) Advancing the forward thrust lever(s), except during the first 3 seconds after
touchdown for landing.
c) Applying manual brakes.
d) Both b and c are correct.

A

d) Both b and c are correct.

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7
Q

Which system normally provides hydraulic pressure for Nose Wheel Steering?

a) System A.
b) System B.
c) Standby system.
d) Nose wheel steering accumulator.

A

a) System A.

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8
Q

The lockout pin is installed in the steering depressurisation valve. What does this
do?
a) Bypasses system B pressure.
b) Depressurizes both system A & B pressure.
c) Allows airplane pushback or towing without depressurizing the hydraulic systems.
d) Both a and c are correct.

A

c) Allows airplane pushback or towing without depressurizing the hydraulic systems.

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9
Q

The Landing Gear Transfer Unit is used to raise the landing gear at the normal rate
when all of the following conditions exist:
a) Airborne, landing gear lever is positioned to OFF, No.2 engine drops below a limit
value & either main landing gear is not up and locked.
b) Airborne, landing gear lever is positioned UP, either engine drops below a limit value
& either main landing gear is not up and locked.
c) Airborne, landing gear lever is positioned UP, No.1 engine drops below a limit value
& either main landing gear is not up and locked.
d) Airborne, landing gear lever positioned to OFF, No.1 engine drops below a limit value
& either main landing gear is not up and locked.

A

c) Airborne, landing gear lever is positioned UP, No.1 engine drops below a limit value
& either main landing gear is not up and locked.

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10
Q 
Statements:
1) The alternate brake system anti-skid protection is applied to main wheel pairs, in
stead of individual wheels.
2) Both normal and alternate brake systems provide skid, locked wheel,
touchdown and hydroplane protection.
a) Only statement 1 is correct.
b) Only statement 2 is correct.
c) Both statements are correct.
d) No statement is correct.
A

c) Both statements are correct.

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11
Q

Which pressure does the Hydraulic Brake Pressure indicator indicate?

a) Normal pressure of 3500 psi.
b) Maximum pressure of 3500 psi.
c) Normal pre-charge of 2800 psi.
d) Normal pre-charge in the brake accumulator of 1200 psi.

A

b) Maximum pressure of 3500 psi.

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12
Q

During alternate brake system operation, the following protection is provided:

a) Skid, locked wheel, touchdown and hydroplane.
b) Skid and hydroplane only.
c) Skid, locked wheel, and hydroplane only.
d) None of the above

A

a) Skid, locked wheel, touchdown and hydroplane.

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13
Q

Landing autobrake settings may be selected after touchdown:
a) However, the AUTOBRAKE DISARM light will illuminate and auto brake application
will not occur.
b) However, auto brake action will occur only when both thrust levers are retarded to
reverse thrust range.
c) Prior to deceleration through 30 kts groundspeed.
d) After deceleration through 30 kts groundspeed.

A

c) Prior to deceleration through 30 kts groundspeed.

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14
Q

The air/ground system receives air/ground logic signals from:

a) The altimeter.
b) The cabin pressure controller.
c) Six sensors, two on each landing gear.
d) The FMC position updating from the GPS.

A

c) Six sensors, two on each landing gear.

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15
Q

Which of the following is not part of the braking system?

a) Antiskid protection.
b) Parking brake.
c) Brake accumulator.
d) Nose wheel brakes

A

d) Nose wheel brakes

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16
Q

Which of the following conditions must exist to arm the RTO mode prior to takeoff?

a) AUTO BRAKE select switch positioned to ON.
b) Wheel speed greater than 60 kts.
c) Forward thrust lever positioned to IDLE.
d) Position ANTISKID switch to RTO.

A

c) Forward thrust lever positioned to IDLE.

17
Q

What could cause the amber ANTISKID INOP light to illuminate?

a) AUTO BRAKE select switch positioned to OFF.
b) The antiskid monitoring system has detected a system fault.
c) Brake accumulator pressure in the red band.
d) System B pressure is low.

A

b) The antiskid monitoring system has detected a system fault.

18
Q

Which airspeed value must be considered in a wheel well fire situation?

a) Observe extend limit speed (280K/.72M)
b) Retract landing gear speed of 245 kts maximum.
c) Maintain 235 kts maximum for 20 minutes.
d) Observe extend limit speed (270K/.82M)

A

d) Observe extend limit speed (270K/.82M)

19
Q

.Rejecting a takeoff with RTO selected, after a wheel speed of 90 kts is reached:

a) Maximum braking is applied when thrust levers are retarded to IDLE.
b) Automatic braking is applied when reverse thrust is selected.
c) Automatic speed brake deployment when thrust levers are retarded to idle.
d) The AUTO BRAKE DISARM light will illuminate.

A

a) Maximum braking is applied when thrust levers are retarded to IDLE.

20
Q

Hydraulic pressure from system B will be used to raise the landing gear:
a) When system A pressure is low and the landing gear lever is positioned UP.
b) When the ALTERNATE NOSE WHEEL switch is positioned ON.
c) When the #1 engine RPM drops below a limit value (i.e. engine #1 fails), with either
main landing gear not up and locked and the landing gear lever is positioned UP.
d) After a failure of the #1 engine hydraulic pump with the landing gear still down and
the landing gear lever is positioned up.

A

c) When the #1 engine RPM drops below a limit value (i.e. engine #1 fails), with either
main landing gear not up and locked and the landing gear lever is positioned UP.

CAE Q 2 (15 decks)

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