曝光台 注意防骗
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(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.
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.
PRESSURE RELIEF VALVE
The pressure relief valve connects the high pressure
circuit to the return circuit in case of over pressure.
The relief valve opens at 3436 psi (237 bar) and closes
at 3190 psi (220 bar).
SAMPLING VALVE
A sampling valve is provided on the HP Manifold.
TMUHYDC03-T02 LEVEL 3
EFFECTIVITY 29-12-00 Page 4
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 48
ALL
BLUE HYDRAULIC SYSTEM D/O
TMUHYDC03-P02 LEVEL 3
EFFECTIVITY 29-12-00 Page 5
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 49
ALL
BLUE 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
of the flight controls to be supplied for leak
measurement test.
RETURN MANIFOLD
The return manifold comprises:
- one return filter equipped with a clogging
indicator.
- one temperature transmitter which consists of
one temperature switch and two temperature
transducers.
The bypass operates when the differential pressure
across the filter is more than 29 ± 2.35 psi (2 ± 0.16
bar).
Temperature switch and probes send data to the ECAM
for indication and warnings.
GROUND COUPLINGS
On ground it is possible to pressurize the blue
hydraulic system from a ground power unit.
TMUHYDC03-T03 LEVEL 3
EFFECTIVITY 29-12-00 Page 6
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 50
ALL
BLUE HYDRAULIC SYSTEM D/O
TMUHYDC03-P03 LEVEL 3
EFFECTIVITY 29-12-00 Page 7
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 51
ALL
SELF EXAMINATION
When does the electric pump pressurize the blue
system?
A - When the aircraft is on the ground, ELEC
PUMP push-button is set to AUTO and OVRD
(override) push-button is set to ON.
B - When the green and yellow systems are
detected in low pressure configuration.
C - As soon as one engine is running and
OVRD pushbutton is set to ON.
When does the RAT deploy automatically?
A - In flight, if blue hydraulic power is
lost.
B - As soon as two hydraulic power systems
are lost.
C - At speeds greater than 100Kts, if all
electrical power sources are lost.
TMUHYDC03 LEVEL 3
EFFECTIVITY 29-12-00 Page 8
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 52
ALL
29 - HYDRAULIC POWER
29-13-00 YELLOW HYDRAULIC SYSTEM D/O
CONTENTS:
Reservoir
Reservoir Pressurization
Fire Valve
Engine Driven Pump
Ground Couplings
Pressure Switch
Power Transfer Unit
Electric Pump
Hand Pump
High Pressure Manifold
Leak Measurement Manifold
Power Transfer Unit Manifold
Return Manifold
Self Examination
TMUHYDD04 LEVEL 3
EFFECTIVITY 29-13-00 Page 1
Jul 31/00
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 29 HYDRAULIC POWER
UF94200
EFFECTIVITY Page 53
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