(b)
If the unions are correctly tightened and if the fault continues:
1_ Disconnect the electrical connectors from the bleed
transferred pressure transducer (7HA2) and from the bleed
regulated pressure transducer (8HA2).
2_ Install the TEST SET - ENGINE BLEED SYSTEM (98D36003000000) or
TEST SET - ENGINE BLEED SYSTEM (98F36003002000).
3_ Connect the cable from the test set between the bleed
transferred pressure transducer (7HA2) and the bleed regulated
pressure transducer (8HA2).
4_ Disconnect the sense line from the bleed pressure regulator
valve control solenoid (10HA2) and blank the sense line union.
5_ Disconnect the sense line from the bleed pressure regulator
valve (4001HA) and connect to the test set.
6_ Do this check:
(Ref. Fig. 201/TASK 36-11-00-991-002)
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-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1.
On the test set: The pressure gage of the air cylinder Open the shutoff valve of the air shows the pressure. cylinder.
2.
On the test set: The primary gage shows 35 psig. Use the primary regulator to pressurize the pressure source to 35 psig.
3.
On the test set: Make sure that the same indication is Slowly pressurize the system up shown on the lower ECAM display unit. to 30 psig.
4.
On the test set: Close the shutoff valve.
a If the pressure decreases to 0 psig in less than 20
_
seconds:
-replace the sense line between the upstream of the pressure regulator valve (4001HA) and the bleed transferred pressure transducer (7HA2).
b If the pressure drop is not high or very slow:
_
-replace the SOLENOID-BLEED PRESS REG V CTL, ENG 2 (10HA2) (Ref. AMM TASK 36-11-55-000-001) and (Ref. AMM TASK 36-11-55-400-001).
7 Depressurize the system on the test set.
_
8 Remove the TEST SET - ENGINE BLEED SYSTEM (98D36003000000)
_ TEST SET - ENGINE BLEED SYSTEM (98F36003002000).
B. Test After the subsequent flight, make sure that the fault does not continue.
(1)
If the fault continues:
-Replace the VALVE-BLEED PRESS REG (4001HA) on engine 2 (Ref. AMM TASK 36-11-52-000-040) (Ref. AMM TASK 36-11-52-400-040)
(2)
If the fault continues:
-Replace the VALVE-OVERPRESSURE, ENG 2 (5HA2) (Ref. AMM TASK 36-11-53-000-001) (Ref. AMM TASK 36-11-53-400-001)
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5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1)
Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2)
On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3)
De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
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The Bleed Pressure-Regulator Valve of the Engine 1 is Shown Open Amber on the Lower ECAM DU
1. Possible Causes_______________
-VALVE-BLEED PRESS REG (4001HA)
-SOLENOID-BLEED PRESS REG V CTL, ENG 1 (10HA1)
-XDCR-BLEED TRANSFER PRESS, ENG 1 (7HA1)
-wiring
2. Job Set-up Information______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 36-11-00-740-001 BITE Test of the BMC 1(2)
AMM 36-11-15-000-001 Removal of the Bleed Transferred Pressure Transducer (7HA1,7HA2)
AMM 36-11-15-400-001 Installation of the Bleed Transferred Pressure Transducer (7HA1,7HA2)
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 PNEUMATIC(78)
