hydraulics r 01

7/30/2019 Hydraulics R 01

1/69

PT. METRO BATAVIA

Directorate of OperationalSlide 1 of 69

737-300/400

HYDRAULICS

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2/69

PT. METRO BATAVIA


737-300/400 Hydraulic

Schematic

B

system pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank

To reservoir Hydraulic

heat

exchanger

Motor

Electric

pump

To return P

Standby rudder

Groundspoilers

Nose wheelsteering

Alternatebrakes

PAccumulatorisolation valve

Alternate nosewheel steering

Trailingedge flaps

Alternate Brakes Selector Valve

Autobrakecontrol module

Aileron

Rudder

Elevator and Elevator feel

Autopilot B &yaw damper

Leading edge devicesstandby extension

If installed

B

system

reservoirPneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank

To reservoirHydraulic

heat

exchanger

Motor

Electric

pump

P To return

Hydraulic brake

pressure accumulator

Autoslat operation

Leading edgeflaps & slats

A

MotorB

Pump

Power Transfer Unit

(PTU)

Standpipe (quantity 0%).

1 gallon remaining for PTU use only.

Return

Standby

system

reservoir

Motor

To return

PTU control valve

50%

Autopilot A

Normalbrakes

Landing geartransfer unit

Landing gear

No. 1 thrustreverser


Outboard flight spoilers

Inboard flight

spoilers
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3/69

PT. METRO BATAVIA



Schematic

The A system

reservoir is

pressurized with

pneumatic air

from either side of

the pneumatic

manifold, and has

a capacity of 4.8

U.S. gallons.

B

system pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)


4/69

PT. METRO BATAVIA



Schematic

One A system

engine-driven

pump, mounted to

the lower left side

of the No. 1

engine, delivers

approximately 22

gallons per

minute at

3000 psi.

B

system pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)


5/69

PT. METRO BATAVIA



Schematic

One A system

electric motor-

driven pump,

mounted in the

main wheel well,

delivers

approximately six

gallons per

minute at

2700 psi.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)


6/69

PT. METRO BATAVIA



Schematic

There are two

overheat sensors

for the A

system electric

motor-driven

pump; one in the

motor, and one in

the case drain

line. One

hydraulic heat

exchanger,located in the

No. 1 fuel tank,

utilizes fuel to

cool the hydraulic

fluid returning to

the reservoir from

the two pumps.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger


7/69


8/69PT. METRO BATAVIA



Schematic

The Power

Transfer Unit

(PTU) is an

alternate source

of power to the

autoslat system.

Please see the

Flight Controls

presentation for a

detaileddescription

of the PTU.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve





Schematic

The No. 1 thrust

reverser is

powered by A

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve






Schematic

The A system

works in

conjunction with

the B system to

operate the

primary flight

controls.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder






Schematic

Autopilot A is

powered by A

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A





Schematic

The two inboard

flight spoilers are

powered by A

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flight

spoilers





Schematic

The alternate

brakes are

powered by A

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flight

spoilers

Alternatebrakes


Accumulator

isolation valve


14/69

PT. METRO BATAVIA



Schematic

The six ground

spoilers are

powered by A

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

returnGroundspoilers

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flight

spoilers

Alternatebrakes


Accumulator

isolation valve


15/69

PT. METRO BATAVIA



Schematic

Normal extension

and retraction of

the landing gear

is accomplished

via A system

hydraulics.

Please see the

Landing Gear

presentation for a

detaileddescription of the

landing gear

transfer unit.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

returnLanding geartransfer unit

Landing gear

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flight

spoilers

Alternatebrakes


Groundspoilers

Accumulator

isolation valve


16/69


17/69

PT. METRO BATAVIA



Schematic

The B system

reservoir is

pressurized with

pneumatic air

from either side of

the pneumatic

manifold, and has

a capacity of 7.2

U.S. gallons.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flight

spoilers

Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



3 300/400 H d li


18/69

PT. METRO BATAVIA



Schematic

One B system

engine-driven

pump, mounted to

the lower left side

of the No. 2

engine, delivers

approximately 22

gallons per

minute at

3000 psi.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Engine

driven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A

Inboard flightspoilers

Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



737 300/400 H d li


19/69

PT. METRO BATAVIA



Schematic

One B system

electric motor-

driven pump,

mounted in the

main wheel well,

delivers

approximately six

gallons per

minute at

2700 psi.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Engine

driven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Engine

driven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



737 300/400 H d li


20/69

PT. METRO BATAVIA



Schematic

There are two

overheat sensors

for the B

system electric

motor-driven

pump; one in the

motor, and one in

the case drain

line. One

hydraulic heat

exchanger,located in the

No. 2 fuel tank,

utilizes fuel to

cool the hydraulic

fluid returning to

the reservoir from

the two pumps.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger

737 300/400 H d li


21/69

PT. METRO BATAVIA



Schematic

There is one low

pressure light for

each B system

hydraulic pump.

The low pressure

sensors are

located upstream

of their respective

check valve.

Total B system

pressure is readdownstream of

both check

valves.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger

P To return

737 300/400 H d li


22/69

PT. METRO BATAVIA



Schematic

Normal autoslat

and leading edge

flaps & slats

operation is from

B system

hydraulics.

Recall that the

Power Transfer

Unit (PTU) is an

alternate sourceof power to the

autoslat system.

Please see the

Flight Controls

presentation for a

detailed

description

of the PTU.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger

P To returnAutoslat operation


737 300/400 H d li


23/69

PT. METRO BATAVIA



Schematic

The No. 2 thrust

reverser is

powered by B

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger




737 300/400 Hydraulic


24/69

PT. METRO BATAVIA



Schematic

The B system

works in

conjunction with

the A system to

operate the

primary flight

controls.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger






25/69

PT. METRO BATAVIA



Schematic

Autopilot B is

powered by B

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger




Autopilot B& yaw damper



26/69

PT. METRO BATAVIA



Schematic

The two outboard

flight spoilers are

powered by B

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger








27/69

PT. METRO BATAVIA



Schematic

Both normal and

accumulator

brakes are

powered by B

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger






P

Hydraulic brake

pressure accumulatorNormalbrakes



28/69

PT. METRO BATAVIA



Schematic

Autobrakes are

powered by B

system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return


Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger






P

Hydraulic brake




29/69

PT. METRO BATAVIA



Schematic

The trailing edgeflaps are powered

by B system

hydraulics.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return


Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger






P

Hydraulic brake


Trailingedge flaps



30/69

PT. METRO BATAVIA



Schematic

Under certainconditions, the

B system will

retract the landing

gear via the

landing gear

transfer unit.

Please see the

Landing Gear

presentation for adetailed

description of the

landing gear

transfer unit.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return


Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


heat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


heat

exchanger






P

Hydraulic brake


Trailingedge flaps



31/69

PT. METRO BATAVIA



Schematic

As an alternatesource of power,

the B system

will operate the

nose wheel

steering, if an

alternate nose

wheel steering

switch is

installed.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank

To reservoir Hydraulicheat

exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank

To reservoirHydraulicheat

exchanger






P

Hydraulic brake


Trailingedge flaps



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Schematic

The standbyreservoir is

mounted on the

keel beam in the

main gear wheel

well and has a

capacity of 2.8

U.S. gallons. A

balance line

connects the

standby reservoirto the B system

reservoir.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


exchanger






P

Hydraulic brake


Trailingedge flaps

Return

Standby

system

reservoir

50%



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Schematic

The standbysystem electric

motor-driven

pump is mounted

aft of the standby

reservoir on the

keel beam. The

pump delivers

approximately

three gallons per

minute at3000 psi. Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


exchanger






P

Hydraulic brake


Trailingedge flaps

Standby

system

reservoir

Return

50%

To return

Motor



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Schematic


the standby

system can

extend, but not

retract, the

leading edge

devices.

Please see the

Flight Controlspresentation for

additional

information on

the alternate

method of

extending the

leading edge

devices.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


exchanger






P

Hydraulic brake


Trailingedge flaps

Standby

system

reservoir

Return

50%

To return

Motor




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Schematic


the standby

system can

operate the

rudder when

certain conditions

exist.

In addition to this

presentation,please see the

Flight Controls

presentation for

more information

on when the

standby system

will act as an

alternate power

source to the

rudder.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


exchanger






P

Hydraulic brake


Trailingedge flaps

Standby

system

reservoir

Return

50%

To return

Motor


Standby rudder



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Schematic


the standby

system can

operate the thrust

reversers if

normal hydraulic

pressure is lost.

Please see the

Engines/APUpresentation for a

detailed

description

of the thrust

reverser system.

Bsystem pressure

A

system pressure

Supply

Standby

system pressure

Case drain

return

If installed



Motor

Electric

pump

Enginedriven

pump

Hydraulic shutoff

Nose wheelsteering


Landing gear

Electric

pump

Motor

Hydraulic shutoff

Enginedriven

pump

A

system

reservoir

Pneumatic air

Return

Standpipe

(quantity 25%)

No. 1

fuel

tank


exchanger

To return P AMotor

B

Pump

Power Transfer Unit

(PTU)

PTU control valve


Aileron

Rudder


Autopilot A


Alternatebrakes


Groundspoilers

Accumulator

isolation valve

B

system


Return

Standpipe

(quantity 50%)



No. 2

fuel

tank


exchanger






P

Hydraulic brake


Trailingedge flaps

Standby

system

reservoir

Return

50%

To return

Motor


Standby rudder

This concludes the review of the Hydraulic Schematic. The next section

will discuss the Hydraulic Panels and Indicators. Click Next to continue.
http://localhost/var/www/apps/conversion/tmp/Cactus%20Aviation%20Services%20LLC%20Contact%20Information.ppshttp://localhost/var/www/apps/conversion/tmp/Cactus%20Aviation%20Services%20LLC%20Contact%20Information.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Pictures%20for%20Presentations/Pictures.ppshttp://localhost/var/www/apps/conversion/tmp/Cactus%20Aviation%20Services%20LLC%20Contact%20Information.pps


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Hydraulic Panel


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Hydraulic Panel

Associated lights and

switches for the A

hydraulic system

Associated lights and

switches for the B

hydraulic system


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Hydraulic Panel

Engine Hydraulic Pump (HYD PUMPS) Switches:

ON

De-energizes the pump depressurizing solenoid,

which results in repositioning of a blocking valve

to allow pump pressure to enter system.

OFF

Energizes the pump depressurizing solenoid,

which results in repositioning of a blocking valve

to block pump output.

Note: It is recommended that the engine

hydraulic pump switches remain ON at shutdown

to prolong the service life of the depressurizing

solenoid.


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Hydraulic Panel

Electric Hydraulic Pump (HYD PUMPS) Switches:

ON

Provides electrical power to the associated

electric motor-driven pump.

OFF

Electrical power removed from the pump.

Note: The power source for the A hydraulic

system electric pump is generator bus 2. The

power source for the B hydraulic system

electric pump is generator bus 1.


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Hydraulic Panel

Electric Hydraulic Pump OVERHEAT Lights:

Illuminated

Associated electric motor-driven pump has

overheated. From case drain return 225 265

degree F and From Pump or Case drain 235275 degree F


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Hydraulic Panel

Hydraulic Pump LOW PRESSURE Lights:

Illuminated

Output pressure of associated pump is low < 1300

PSI

Note: When an engine fire warning switch is

pulled-up, the associated engine-driven pump

LOW PRESSURE light is deactivated. For

example, pulling up on the No. 1 engine fire

warning switch will result in a loss of hydraulic

fluid flow to the A system engine-driven pump

and more importantly, an engine shutdown.

Therefore, in order to eliminate a nuisance light,

the LOW PRESSURE light for the A system

engine-driven pump is deactivated.

Please see the Fire Protection presentation for a

list of items that occur when an engine fire

warning switch is pulled-up.


43/69


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Standby HydraulicsLights and Associated Switches are Located on the top-half of the

Flight Control Panel

STANDBY HYD LOW QUANTITY Light:

Illuminated

Indicates low quantity in standby hydraulic

reservoir (approximately 50%) or 1,4 USG

Note: This light is always armed.

STANDBY HYD LOW PRESSURE Light:

Illuminated

Indicates output pressure of standby pump is

low < 1300 PSI

Note: This light is armed only when

standby pump operation has been

selected or automatic standby function

is activated.


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FLT CONTROL Switches:

STBY RUD

Activates standby pump and opens standby

rudder shutoff valve to pressurize standby rudder

power control unit.

OFF

Closes flight control shutoff valve isolating

ailerons, elevators, and rudder from associated

hydraulic system pressure.

ON (guarded position)

Normal operating position.


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FLT CONTROL LOW PRESSURE Lights:

Illuminated

Indicates low hydraulic system ("A" or B)

pressure to ailerons, elevator, and rudder.

Deactivated when associated FLIGHT CONTROLswitch is positioned to STBY RUD and standby

rudder shutoff valve is fully open.

On airplanes with the rudder pressure reducer

installed, the A system light indicates A

system pressure is low when normal system

pressure is commanded.

Light GOES OFF after FLT CONTROL switch

selected to STBY RUD


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ALTERNATE FLAPS Master Switch:

OFF (guarded position)


ARM Activates standby pump.

Closes trailing edge flap bypass valve (to prevent

hydraulic lock of flap drive unit).

Arms the standby hydraulic LOW PRESSURE

light.

Arms the ALTERNATE FLAPS position switch.

Arms the leading edge standby drive extension

shutoff valve.


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ALTERNATE FLAPS Position Switch:

Functions only when the ALTERNATE FLAPS

master switch is in the ARM position.

UP Electrically retracts trailing edge flaps.

Leading edge devices remain extended and

cannot be retracted by the alternate flaps system.

OFF


DOWN (spring loaded to OFF) (Momentary) Opens the leading edge standby

drive extension shutoff valve and fully extends

leading edge devices using standby hydraulic

pressure.

(Hold) Electrically extends trailing edge flaps

(no asymmetry protection is provided).


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PT. METRO BATAVIA


Hydraulic Indicators

A and B Hydraulic

System Pressure Gauge

A Hydraulic SystemQuantity Gauge

B Hydraulic System

Quantity Gauge


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A and B Hydraulic System Pressure Gauge

Indicates total system pressure for the A and

B hydraulic system.

Normal pressure (green): 3000 psi.

Maximum pressure (red): 3500 psi.Two needles, A and B.

Note: When both pumps for a system are OFF,

respective pointer reads zero.


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A Hydraulic System Quantity Gauge

Indicates quantity of hydraulic fluid in the

A system reservoir.

If needle points to RFL (refill), reservoir needs

more fluid. Small blue dot is a calibration point used by

maintenance.

FULL (F) = 4.8 U.S. gallons

REFILL (RFL) = 4.2 U.S. gallons

For EIS Secondary display

FULL (F) = 100% = 4,8 USG

REFILL (RFL) = 88% = 4,2 USG


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B Hydraulic System Quantity Gauge

Indicates quantity of hydraulic fluid in the

B system reservoir.

If needle points to RFL (refill), reservoir needs

more fluid. Small blue dot is a calibration point used by

maintenance.

FULL (F) = 7.2 U.S. gallons or 100% on EIS

REFILL (RFL) = 6.4 U.S. gallons or 88% on EIS

This concludes the review of the Hydraulic Panels and Indicators. The remainder

of the presentation will discuss the hydraulic system in greater detail.

Click Next to continue.

System Description
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B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

System Description

There are three hydraulics systems: A, B, and Standby. Each hydraulic system has a fluid reservoir

located in the main gear wheel well. System A and B reservoirs are pressurized by bleed air. A

balance line connects the standby system reservoir to the B system reservoir for pressurization and

servicing. Pressurization of all reservoirs ensures positive fluid flow from the reservoirs to the pumps and

maintains normal return pressure to the hydraulic system.

See picture of

A system reservoir

See picture of

standby system

reservoir and pump

See picture of

B system reservoir

System Description
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PT. METRO BATAVIA


B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

System Description

Both A and B hydraulic system have a total of two pumps each; one engine-driven pump, and one

electric motor-driven pump. The A system engine-driven pump is operated by the No. 1 engine, and the

B system engine-driven pump is operated by the No. 2 engine. The engine-driven pumps deliver

approximately 22 gallons/min. The ENG 1 or ENG 2 pump ON/OFF switch controls the engine-driven

pump output pressure. Positioning the switch to OFF isolates fluid flow from the system components by

energizing a depressurization solenoid. However, the pump will continue to rotate as long as the engine

is operating. It is recommended that the engine hydraulic pump switches remain ON at shutdown toprolong the service life of the depressurizing solenoid.

System Description


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PT. METRO BATAVIA


B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

System Description

The ELEC 2 (A system) or ELEC 1 (B system) pump ON/OFF switch controls the respective electric

motor-driven pump. The electric motor-driven pumps deliver approximately six gallons/min. If an overheat

condition is detected in the pump or in the case drain line, the respective OVERHEAT light illuminates.

Note the labeling of the electric motor-driven pumps on the panel: ELEC 2 for A system and ELEC 1 for

B system. This serves as a reminder that the A system electric motor-driven pump receives its

electrical power from generator bus 2, and the B system electric motor-driven pump receives its power

from generator bus 1. This ensures that at least one hydraulic pump will be available for each system(A and B) in the case of an engine failure.

System Description


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B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

System Description

As the A and B system pumps operate, hydraulic fluid is used to cool and lubricate the pumps. After

cooling and lubrication, the fluid travels through a case drain which leads to a heat exchanger. The heat

exchanger for the A system is located in the No. 1 fuel tank, and the heat exchanger for the B system

is located in the No. 2 fuel tank. The heat exchangers are composed of coils of fine aluminum tubing

which use fuel as a coolant. A minimum of 250 gallons (1676 lbs.) of main tank fuel is required to provide

hydraulic fluid cooling. The hydraulic fluid returns to its respective reservoir after being cooled. The

standby system does not have an associated heat exchanger.

System Description


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B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

System Description

One standpipe is located in the A system reservoir, and is associated with the engine-driven pump. The

purpose of a standpipe is to prevent total fluid loss in the system.

If a fluid leak develops in the engine-driven pump or its related lines, the standpipe prevents complete

fluid loss. Approximately 25% of the fluid will remain, therefore is indicated on the A system

quantity gauge. System A hydraulic pressure is now maintained by the electric motor-driven pump.

Consequently, the system components will operate at a slower rate due to the lower volume output of thispump (six gallons/min.).

If a fluid leak develops in the electric motor-driven pump or its related lines, or components common to

both the engine and electric motor-driven pumps, the quantity in the reservoir will steadily decrease to

zero and all A system pressure will be lost.

System Description


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Two standpipes are located in the B system reservoir; one standpipe for each pump.

If a fluid leak develops in the engine-driven pump or its related lines, the standpipe prevents complete

fluid loss. Approximately 50% of the fluid will remain, therefore is indicated on the B system

quantity gauge. System B hydraulic pressure is now maintained by the electric motor-driven pump.

Consequently, the system components will operate at a slower rate due to the lower volume output of thispump (six gallons/min.).

If a fluid leak develops in the electric motor-driven pump or its related lines, or components common to

both the engine and electric motor-driven pumps, the quantity in the reservoir will steadily decrease to

zero and all B system pressure will be lost. However, approximately one gallon remains in the reservoir

for Power Transfer Unit operation only. Please see the Flight Control presentation for a detailed

description of the Power Transfer Unit.

B

system

reservoir

A

system

reservoir

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 25%)

Hydraulic shutoff

No. 1

fuel

tank


heat

exchanger

Motor

Electric

pump

Pneumatic air

Return

Engine

driven

pump

Standpipe

(quantity 50%)

Hydraulic shutoff

No. 2

fuel

tank


heat

exchanger

Motor

Electric

pump



Return

Standby

system

reservoir

Motor

50%

PTU control valve Autoslat operation


AMotor

BPump

Power Transfer Unit

(PTU)

System Description

System Description


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The standby hydraulic system is provided as a backup to the A and/or B hydraulic system. It is

available when pressure is lost from the A and/or B hydraulic system. The standby system provides

hydraulic

hydraulics r 01

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