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SWA-737 > 2016 PC Guide - Hydraulics - Main5 > Flashcards

2016 PC Guide - Hydraulics - Main5 Flashcards

1
Q

What is normal system A pressure

A

3000 psi

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2
Q

What would hydraulic system A quantity indicate with a leak in the engine driven pump or its associated lines?

A

20%

due to standpipe

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3
Q

What would hydraulic system A quantity indicate with a leak in the electric pump or its associated lines?

A

0%

would lose all hydraulic fluid

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4
Q

With a loss of system A, what does the “A” Flight Control LOW PRESSURE light indicate?

A

Hydraulic pressure to the primary flight controls (Aileron, Elevator, and Rudder) is low due to the complete loss of system A.

comes on if pressure is less than 1300 psi

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5
Q

With loss of system A, what does the FEEL DIFF PRESS light indicate?

A

Indicates an excessive differential hydraulic pressure sensed in the elevator feel computer between hydraulic systems A & B.

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6
Q

What happens when you move the associated Flight Control switch to STBY RUD, as directed by the QRH?

A

The associated hydraulic NO LONGER powers the flight controls.

The Standby Rudder pump and PCU will power the rudder.

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7
Q

What caused the standby Hydraulic system to automatically activate?

A

1) Low pressure in hydraulic systems A and/or B with
- flaps extended, and..
- in flight or on the ground with wheel speed greater than 60 KIAS

NOTE: auto operation doe son deactivate the flight control low pressure light

NOTE: When airborne and the flaps are retracted, the standby pump shuts off and the valve closes (Standby Rudder ON light extinguishes)

2) Force Fight Monitor triggered
3) (CL) The rudder pressure reducer failed to change system A pressure (to the rudder PCU) to normal at 700’ RA on landing

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8
Q

What does the Force Fight Monitor System do?

A

Detects opposing pressure between main rudder PCU A and B actuators. If opposing force is detected, the Force Fight Monitor automatically turns on the Standby Hydraulic Pump and power the standby rudder PCU to provide the pilot with adequate rudder control.

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9
Q

What does the Rudder Pressure Reducer do and why?

A

Reduces system A pressure to the rudder PCU above 1000 ft RA to give the pilot more time to react to large rudder deflections. Pressure should be returned to normal at 700 ft RA on approach to landing.

NOTE: The NGs have a Rudder Pressure Limiter that performs a similar function by reducing both A & B pressure by 25% to limit full rudder authority in flight. This occurs at speeds above approx. 135 KIAS.

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10
Q

With a loss of the A system, what MAJOR aircraft systems will be affected, and what additional procedure will you eventually have to accomplish?

A

Landing Gear - Manual Gear Extension

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11
Q

With the loss of System A hydraulics, will the following systems be available upon landing?

  • Braking
  • Thrust Reverse
  • Nose Wheel Steering
  • Ground Spoilers
  • Flight Spoilers
A

Braking - YES via normal brakes bowered by system B

Thrust Reverse - YES, at a slower rated due to being powered by Standby System

Nose Wheel Steering - YES via alternate steering powered by System B

Ground Spoilers - NO

Flight Spoilers - YES, 2 (NG) / 1 (CL) on each wing via the System B hydraulics.

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12
Q

Is the Alternate Nose Wheel Steering automatic.

A

NO

Alternate Nose Wheel Steering must be selected.

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13
Q

Is the selection of Alternate Nose Wheel Steering directed by the QRH?

A

YES

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14
Q

Where is the Alternate Nose Wheel Steering switch located?

A

The switch is located on the CAs forward instrument panel.

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15
Q

If the Alternate Nose Wheel Steering switch is set to ALT, can you tow the aircraft?

A

NO

The switch must be returned to NORM prior to the aircraft being towed.

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16
Q

Where can you find the maximum speed for the landing gear extension?

A

placard o the forward panel near the gear handle.

17
Q

What is the normal B system pressure?

A

300 psi

18
Q

What would Hydraulic B system quantity indicate with a leak in the engine driven pump or its associated lines?

A

0%

Has a standpipe, but remaining fluid is only sufficient for PTU

19
Q

What would Hydraulic B system quantity indicate with a leak in the electric pump or its associated lines?

A

0%

Has a standpipe, but remaining fluid is only sufficient for PTU.

20
Q

Is any residual fluid retained when the B quantity indicates zero?

If so, why?

A

Yes, for operation of the PTU.

In the event of a loss of the B hydraulic system, a small amount of fluid is retained (standpipe) for operation of the auto slats via the PTU.

NOTE: Hydraulic system A powers a pump that uses B fluid to move the auto slats to the full extend position if required.

21
Q

With loss of system B, what does the B Flight Control LOW PRESSURE light indicate?

A

Hydraulic pressure to the primary flight controls (Aileron, Elevator, and Rudder) is low due to the complete loss of system B.

occurs at approx 1300 psi

22
Q

With the loss of system B, what does the FEEL DIFF PRESS light indicate?

A

Indicates an excessive differential hydraulic pressure is sensed in the elevator feel computer between hydraulic systems A and B.

23
Q

With loss of system B, dies the YAW DAMPER light illuminate?

A

NO, but the YD is inop.

Even though the yaw damper is inoperative, the Yaw Damper light will not illuminate until the B FLIGHT CONTROL switch is placed to OFF or STBY RUD.

24
Q

With loss of system B, can the Yaw Damper be cycled OFF then ON to regain the system?

A

No, the Standby Yaw Damper con only be engaged if both Flight Control switches are placed to STBY RUDDER and the Yaw Damper switch is then placed to ON (NG)

25
Q

With a loss of the B system, what major aircraft system will be affected, and what additional procedure will you eventually have to accomplish?

A

The trailing edge flaps will be affected.

Will have to extend electrically via the Alternate Flap Extension Procedure.

26
Q

What happens when you position the Alternate Flaps Master Switch to ARM?

A

Allows the flaps to be controlled electrically by:

  • Activating the standby hydraulic pump
  • Closing the Trailing Edge Flap bypass valve
  • Arming the Alternate Flap Position Switch
27
Q

What happens when you move the Alternate Flaps Position Switch to Down?

A

The Leading Edge Devices are immediately driven to the full extend position via the standby hydraulic system.

The Trailing Edge Flaps are electrically extended as long as the switch is held down.

28
Q

Once extended, by the Alternate Flaps Position Switch, can the trailing edge flaps be raised?

A

Yes

Let cool for 15 seconds before reversing direction.

29
Q

Is there asymmetry protection while extending/retracting the trailing edge flaps electrically.

A

NO

30
Q

Once manually extended, can the leading edge devices be raised?

A

NO

31
Q

Is there a limitation regarding electrically moving the trailing edge flaps?

A

YES

The alternate flap duty cycle is one complete cycle then 5 minutes OFF.

A complete cycle is 0-15 and back to 0.

The alternate flap position switch must be in the OFF position for 15 seconds before reversing direction of movement.

32
Q

With the loss of System B hydraulics, will the following systems be available?

  • Braking
  • Thrust Reverse
  • Nose Wheel Steering
  • Ground Spoilers
  • Flight Spoilers
A

Braking - YES via alternate brakes powered by the A system

Thrust Reverse - YES, at a slower rate due to being power by the Standby system

Nose Wheel Steering - YES, via normal steering powered by System A

Ground Spoilers - YES, via the A system

Flight Spoilers - YES, 2 (NG) / 1 (CL) on each wing via the System A hydraulics

33
Q

With loss of system B, are any additional OPC selections required prior to landing?

A

YES -

Loss of System B
Flaps 15

34
Q

Where would you find the maximum speed that an Alternate Flap Extension can be initiated?

A

Placarded on forwarded instrument panel.

NG - 230 KIAS
CL - 230 KIAS

SWA-737 (21 decks)

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