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737 SV Study Guide/Memory/Flows > Hydraulics/Landing Gear/Brakes > Flashcards

Hydraulics/Landing Gear/Brakes Flashcards

1
Q

The operation of the standby hydraulic system is _______ by a leak in hydraulic system B.

A

Not affected

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2
Q

What is the purpose of the PTU?

A

To supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when system B engine-driven pump volume is lost

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3
Q

What is the purpose of the landing gear transfer unit?

A

To raise the landing gear at the normal rate when system A engine-driven pump volume is lost

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4
Q

The landing gear transfer unit operates when airborne, ______________, and the No. 1 engine RPM drops below a limit value.

A

the landing gear is positioned up and either main landing gear is not up and locked

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5
Q

The standby system uses a single electric motor-driven pump and ____________________ .

A

can be activated manually or automatically

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6
Q

The standby hydraulic system powers the thrust reversers, __________, and rudder.

A

leading edge flaps and slats (extend only) and the standby yaw damper

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7
Q

Automatic operation of the standby hydraulic pump is initiated when _______ and loss of hydraulic system A or B

A

flaps are extended; and airborne, or wheel speed greater than 60 knots

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8
Q

Positioning either FLT CONTROL switch to STBY RUD, __________, closes the related flight control shutoff valve; deactivates the related flight control LOW PRESSURE light; allows the standby system to power the rudder and thrust reversers.

A

All answers are correct

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9
Q

Positioning the ALTERNATE FLAPS master switch to ARM: __________, operates the trailing edge flap bypass valve, allows the standby system to power the leading edge flaps and slats and thrust reversers, and arms the ALTERNATE FLAPS position switch.

A

Activates the standby electric motor-driven pump

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10
Q

On the B737-800, ___________ when there is a leak in the standby hydraulic system.

A

The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72%

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11
Q

What is indicated by an amber illuminated Electric Hydraulic Pump OVERHEAT light?

A
  • the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated
  • the pump itself has overheated
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12
Q

The respective engine-driven hydraulic pump LOW PRESSURE light is ________ when pulling the Engine 1 fire warning switch.

A

Deactivated

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13
Q

An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to which flight controls?

A
  • ailerons & elevator

- rudder

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14
Q

An illuminated amber standby hydraulic LOW QUANTITY light is ___________ and indicates low quantity in the standby hydraulic reservoir.

A

Always armed

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15
Q

An illuminated amber standby hydraulic LOW PRESSURE light is __________ and indicates low output pressure.

A

armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated

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16
Q

When Positioning the ENG 1 hydraulic pump switch to OFF, the pump_____ to rotate and fluid flow is isolated from the system component.

A

Continues

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17
Q

After an engine fire warning switch is pulled, the hydraulic fluid flow to the related engine-driven pump is shut off and ______________.

A

Its LOW PRESSURE light is deactivated

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18
Q

_____ is the minimum fuel for ground operation of electric hydraulic pumps in the related main tank.

A

1675 lbs

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19
Q

What happens if a leak develops in the A system hydraulic engine-driven pump or its related lines?

A

a standpipe in the reservoir prevents a total system fluid loss

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20
Q

What happens if a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines?

A

the quantity in the reservoir steadily decreases to zero and all system pressure is lost

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21
Q

What happens if a leak develops in either pump, line or component of system B?

A

the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational

22
Q

The operation of the standby hydraulic system _______ by a leak in hydraulic system B.

A

Is not affected

23
Q

Which system can power all flight controls with no decrease in aircraft controllability?

A

Either A or B hydraulic system

24
Q

What is the maximum tire ground speed?

A

195 knots

25
Q

The brake wear indicators should extend beyond the brake flange with the parking brake in what position?

A

Set

26
Q

Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic system?

A

Hydraulic system A

27
Q

The alternate brake system is powered by _________ and the normal brakes system is powered by _______.

A

Hydraulic system A; Hydraulic system B

28
Q

Antiskid protection is provided which brake system(s)?

A

on both brake system (normal and alternate)

29
Q

The ____________ stop rotation of the main gear wheels during landing gear retraction.

A

Brakes automatically

30
Q

The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________ during landing gear retraction.

A

Snubbers

31
Q

What happens Moving the LANDING GEAR lever to the OFF position?

A

hydraulic pressure from the landing gear system is removed

32
Q

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

A

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

33
Q

What does an extinguished green landing gear indicator light indicate?

A

Landing gear is not down and locked

34
Q

When the LANDING GEAR lever is moved to DN, hydraulic system pressure is used to release the uplocks. How is the landing gear extended?

A

hydraulic pressure, gravity, and air loads

35
Q

If _________ green landing gear indicator light(s) (center panel and/or overhead panel) for each gear is/are illuminated, the landing gear is down and locked

A

At least one

36
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, ___________, and either main landing gear is not up and locked.

A

No. 1 engine RPM drops below a limit value

37
Q

What effect on landing gear retraction does opening the Manual Extension Access Door have?

A

Disables it

38
Q

With the landing gear lever ____________, manual landing gear extension is possible.

A

In any position

39
Q

The 737 manual gear releases on the flight deck are used to_________ that allow the gear to_________ to the down and locked position.

A

Release uplocks; free-fall

40
Q

Nose wheel steering will be available ____________

A

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

41
Q

Pushing the rudder pedal down allows for nose wheel turning up to ______in both directions.

A

7 degrees

42
Q

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

A

A lockout pin

43
Q

Switching the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering

A

Hydraulic system B

44
Q

If the normal and alternate brake system pressure is lost, trapped hydraulic pressure in the brake accumulator can still provide ____________ or a parking brake application.

A

Several braking applications

45
Q

Skid, locked wheel, touchdown, and hydroplane protection will be available ____________.

A

With the normal and alternate braking system

46
Q

The 737 parking brake can be set with _________.

A

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

47
Q

What is the normal hydraulic brake pressure as indicated on the brake accumulator _________?

A

3000 psi

48
Q

Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects the desired ________for touchdown.

A

Deceleration rate

49
Q

With the AUTO BRAKE Select Switch in the RTO position, maximum brake pressure is automatically applied when the thrust levers are retarded to idle at or above ____ knots.

A

90 knots

50
Q

On a dry runway, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking.

A

Less than

51
Q

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

A
  • moving speed brake lever to full forward or applying manual brakes
  • advancing the forward thrust lever(s), except during the first 3 seconds after touchdown

737 SV Study Guide/Memory/Flows (17 decks)

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