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737 > Hydraulics > Flashcards

Hydraulics Flashcards

1
Q

What is the power source for the system B ELEC 1 hydraulic pump

A

AC 1

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2
Q

Which statement is true regarding the standby hydraulic system connection to other reservoirs

A

Connected to system B reservoir

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3
Q

A leak in the number two engine driven hydraulic pump will drain the B system reservoir to empty

A

False

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4
Q

What would be the first indication of a leak in the Standby Hydraulic System

A

System B quantity decreases

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5
Q

During cruise at FL 310, the pilots notice that the brake pressure reads 0 psi. System B pressure is 3000 psi and system B quantity is full. What is the problem

A

The brake accumulator precharge has leaked out

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6
Q

How is hydraulic fluid cooled

A

Heat exchangers in the respective main fuel tank

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7
Q

What occurs when a fire switch is pulled

A

Shuts off hydraulic fluid supply to respective engine driven pump

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8
Q

What would extinguish (disarm) a number one engine driven hydraulic pump LOW PRESSURE light

A

Pulling the respective fire switch

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9
Q

Which of the following are operated by the A hydraulic system

A

Alternate brakes for all main wheels

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10
Q

Which of the following is/are operated by the B hydraulic system

A

Normal brakes for all main wheels

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11
Q

What does an illuminated single hydraulic pump LOW PRESSURE light indicate

A

The pump output pressure is below acceptable limits

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12
Q

What does an illuminated hydraulic OVERHEAT light indicate

A

Electric pump overheat

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13
Q

When is the STANDBY HYD LOW QUANTITY light armed

A

Whenever the aircraft electrical buses are powered

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14
Q

When is the STANDBY HYD LOW PRESSURE light armed

A

When electric power is supplied to the standby pump

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15
Q

When performing the Standby Rudder Check (crew option) , what occurs when the B FLT CONTRoL switch is placed to OFF

A

The B system flight control valve closes and B system pressure is isolated from the primary flight controls

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16
Q

What occurs when the B FLT CONTROL switch is placed from OFF to STBY RUD position

A

All answers are correct

17
Q

After placing a FLT CONTROL switch to STBY RUDDER, how is the open position of the standby rudder shutoff valve indicated

A

The respective FLT CONTROL LOW PRESSURE light extinguishes

18
Q

When does the standby pump activate automatically

A

Loss of A or B system pressure with flaps extended with flaps extended while airborne, or on the ground with wheel speed greater than 60 knots

19
Q

Which action turns on the STANDBY HYD pump

A

ALTERNATE FLAP master switch placed to ARM position

20
Q

The Power Transfer Unit provides a backup source of hydraulic pressure (power) to operate

A

Leading edge flaps and slats

21
Q

The electric hydraulic pumps of system A and B are equipped with thermal switches. What is the cockpit indication when a pump thermal switch activates

A

The respective OVERHEAT light illuminates

22
Q

The Auto Slat system

A

Is normally powered by System B

23
Q

Puling the #2 Fire Switch

A

Shuts off fluid to the engine driven hydraulic pump in System B

24
Q

A standby system hydraulic leak is first indicated by

A

A decrease in B quantity indication

25
Q

System A electric hydraulic pump is powered by which electrical power source(500)

A

Gen Bus #2

26
Q

The Standby Hydraulic System provides hydraulic power to the

A

Rudder, thrust reversers, and leading edge devices

27
Q

The normal brake system is powered by

A

Hydraulic system B

28
Q

What is the minimum fuel quantity in each wing tank for operation of the electric hydraulic pumps on the ground

A

1676 pounds

29
Q

The Standby System hydraulic pump is driven by

A

An electric motor

30
Q

The Power Transfer Unit is driven by

A

Hydraulic pressure from system A

31
Q

Which hydraulic system pumps must be turned OFF during pushback if the nosewheel steering bypass pin is not installed

A

System A

737 (17 decks)

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