曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
push-button selects the pressurized or depressurized
mode.
The Engine Driven Pump cooling and lubricating flow
passes through the case drain filter installed in the
return circuit.
Pump outlet pressure is 3000 psi (206 bar) at zero
flow.
The Engine Driven Pump includes a blocking valve which
isolates the pump from the hydraulic system when the
pump operates in the depressurized mode.
Case drain filter clogging indication: DP = 87 ± 8.7 psi
(6 ± 0.6 bar).
GROUND COUPLINGS
The ground service panel consists of two connectors
used to pressurize the green hydraulic system from a
ground cart, a selector valve, two connectors and a
hand pump used for hydraulic reservoir refilling.
TMUHYDB03-T01 LEVEL 3
EFFECTIVITY 29-11-00 Page 2
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 38
ALL
GREEN HYDRAULIC SYSTEM D/O
TMUHYDB03-P01 LEVEL 3
EFFECTIVITY 29-11-00 Page 3
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 39
ALL
GREEN HYDRAULIC SYSTEM D/O
PRESSURE SWITCH
The pressure switch monitors the Engine Driven Pump
outlet pressure for ECAM indications.
The threshold of pressure switch is 1740 psi (120 bar).
NOTE: A check valve downstream of the pump stops the
fluid flow to the pump if the system is
pressurized by the Power Transfer Unit (PTU).
POWER TRANSFER UNIT
The Power Transfer Unit will run automatically when
the differential pressure between the green and yellow
circuits is greater than 500 psi (34.5 bar).
The PTU is inhibited during the first engine start and
cargo door operation.
HIGH PRESSURE MANIFOLD
PRESSURE SWITCHES
The signals from both pressure switches are sent to
the Flight Control Computers, to the Braking Steering
Control Unit, to the ECAM and to the Flight
Augmentation Computer.
The threshold of the pressure switches is 1450 psi
(99.5 bar).
PRESSURE TRANSDUCER
The pressure transducer provides data for pressure
indication on the ECAM and sends information to ELAC
1 and 2.
LEAK MEASUREMENT VALVE
The leak Measurement valve isolates the flight controls
when the guarded LEAK MEASUREMENT VALVES pushbutton
on the maintenance panel is set to OFF.
HP FILTER
The high pressure filter is equipped with a clogging
indicator.
The clogging indicator operates when the differential
pressure is higher than 87 ± 8.7 psi (6 ± 0.6 bar).
ACCUMULATOR
The accumulator acts as a damper for small changes.
It also makes a supply of fluid available in case of
any demand.
The accumulator is precharged with nitrogen to 1885
psi (130 bar) at 20°C. It holds 1.1l (0.29 USgal) of
total volume of fluid when it is full.
SAMPLING VALVE
A sampling valve is provided on the HP manifold.
PRESSURE RELIEF VALVE
The system relief valve connects the high pressure
circuit to the return circuit in case of overpressure.
The relief valve opens at 3436 psi (237 bar) and closes
at 3190 psi (220 bar).
TMUHYDB03-T02 LEVEL 3
EFFECTIVITY 29-11-00 Page 4
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 40
ALL
GREEN HYDRAULIC SYSTEM D/O
TMUHYDB03-P02 LEVEL 3
EFFECTIVITY 29-11-00 Page 5
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 41
ALL
GREEN HYDRAULIC SYSTEM D/O
LEAK MEASUREMENT MANIFOLD
The leak measurement valve block supplies the flight
controls of the right hand wing, left hand wing and
tail section via three outputs.
Operating a spool valve allows the associated section
to be supplied for leak measurement test.
POWER TRANSFER MANIFOLD
NORMAL BRAKING SELECTOR VALVE
The normal braking selector valve cuts-off the
hydraulic supply to the normal brakes.
SOLENOID VALVE
The solenoid valve installed in the Power Transfer
Unit supply line stops the Power Transfer Unit
operation.
PRIORITY VALVE
The priority valve makes sure that all available
hydraulic pressure is sent to the primary flight
controls if pressure in the system is reduced.
RETURN MANIFOLD
The return manifold comprises:
- one return filter equipped with a clogging
indicator.
- one temperature transmitter which consists of
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
ATA 29 HYDRAULIC POWER(6)
