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United 737 SV study > United 737 Hydraulics > Flashcards

United 737 Hydraulics 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 a 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

____ 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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10
Q

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

A
  1. The hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated.
  2. The pump itself has overheated.
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11
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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12
Q

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

A

Aileron and elevator

Rudder

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13
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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14
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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15
Q

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

A

continues

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16
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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17
Q

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

A

1675

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18
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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19
Q

What happens if a leak develops 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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20
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 approx. zero and system B pressure is lost however the power transfer unit is still operational.

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21
Q

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

A

is not affected

22
Q

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

A

Either A or B hydraulic system

23
Q

What is the max tire ground speed?

A

195 Knots

24
Q

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

A

Hydraulic System A

25
Q

The alternate brake system is powered by ______ and the normal brakes system is powered by_____

A

Hydraulic system A

Hydraulic system B

26
Q

Antiskid protection is provided by which brake system?

A

on both brake system (normal and alternate)

27
Q

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

A

brakes automatically

28
Q

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

A

snubbers

29
Q

What happens when moving the LANDING GEAR lever to the OFF position?

A

Hydraulic pressure from the landing gear system is removed

30
Q

An illuminated red landing gear indicator light indicates the ____ or the related landing gear is in disagreement with LANDING GEAR lever position ( in transit or unsafe)

A

Landing gear not down and locked (with either or both forward thrust levers retarded to idle and below 800’ agl. )

31
Q

What does an extinguished green landing gear indicator light indicate?

A

The gear is not down and locked

32
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
Air Loads

33
Q

If ___ green landing gear indicator lights (center panel and or overhead panel) for each gear is/are illuminated, the landing gear is down and locked.

A

AT LEAST one

34
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

35
Q

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

A

disables it

36
Q

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

A

in any position

37
Q

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

A

Release uplocks

Free-Fall

38
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

39
Q

Pushing the rudder pedals down allows for nose wheel turning up to ____ degrees in both directions

A

7 degrees

40
Q

____ allows the aircraft to push back or be towed without depressing hydraulic system A.

A

A lockout pin

41
Q

Switching the Nose Wheel Steering switch to ALT, allows ____ to provide power for nosewheel steering.

A

Hydraulic system B

42
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

43
Q

Skid, locked wheel, touchdown and hydroplane protection will be available ____

A

with the normal and alternate braking system

44
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

45
Q

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

A

3000 PSI - that’s the green part

46
Q

Placing the AUTO BRAKE select switch to 1,2,3 or MAX selects the desired ____ for touchdown

A

Deceleration rate

47
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

48
Q

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

A

less than

49
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 Full Forward
Applying Manual Brakes
Advancing the forward thrust levers- except during the first 3 seconds after touchdown

50
Q

The aircraft has ___ hydraulic systems!

A

3

51
Q

Normal operating pressure for each hydraulic system is _____ psi

A

3000

52
Q

On the ground with both engines shutdown, a REFILL indciation illuminated white RF next to the hydraulic quantity indicates ____

A

hydraulic quantity below 76%

United 737 SV study (14 decks)

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