(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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Loss of Automatic Electrical Closure for the Bleed Pressure Regulator Valve on Engine 2
1. Possible Causes
_______________
-VALVE-BLEED PRESS REG (4001HA)
-SOLENOID-BLEED PRESS REG V CTL, ENG 2 (10HA2)
-P/BSW-ENG 2 BLEED (4HA2)
-wiring
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
98D36003000000 1 TEST SET - ENGINE BLEED SYSTEM 98F36003002000 1 TEST SET - ENGINE BLEED SYSTEM
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power AMM 31-60-00-860-001 EIS Start Procedure AMM 31-60-00-860-002 EIS Stop Procedure AMM 36-11-52-000-040 Removal of the Bleed Pressure-Regulator Valve
(4001HA) AMM 36-11-52-400-040 Installation of the Bleed Pressure-Regulator Valve (4001HA) AMM 36-11-55-000-001 Removal of the Bleed-Pressure-Regulator Valve Control-Solenoid (10HA1,10HA2) AMM 36-11-55-400-001 Installation of the Bleed-Pressure-Regulator Valve
Control-Solenoid (10HA1,10HA2) AMM 49-00-00-860-003 APU Start by External Power (GTCP 36-300) AMM 49-00-00-860-004 APU Shutdown by External Power (GTCP 36-300) AMM 49-00-00-860-005 APU Start by External Power (APS 3200) AMM 49-00-00-860-006 APU Shutdown by External Power (APS 3200) AMM 49-00-00-860-008 APU Start by External Power (131-9(A)) AMM 49-00-00-860-009 APU Shutdown by External Power (131-9(A)) ASM 36-11/02
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3. Fault Confirmation
__________________
A. Job Set-up
(1) Aircraft Maintenance Configuration
(a)
Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(b)
Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
B. Test
(1) Do a check of the position of the ENG 2 BLEED pushbutton switch (4HA2).
(a) If the pushbutton switch is pushed:
- on the ECAM control panel 11VU, push the BLEED key (the BLEED page comes into view on the lower ECAM DU)
-approximately 30 minutes after engine 2 shutdown, do a check of the position of the bleed pressure regulator valve (4001HA) on the BLEED page.
NOTE : During the engine shutdown, the bleed pressure regulator
____
valve can close slowly, without closure command. The cause
of this slow closure can be a decreased segmentation play.
1_ If the position is fully closed:
- no more maintenance is necessary.
2_ If the position is not fully closed:
- do the trouble shooting given in Para. 4.A.
(b) If the pushbutton switch is released: 1 Connect the TEST SET - ENGINE BLEED SYSTEM (98D36003000000) or
_ TEST SET - ENGINE BLEED SYSTEM (98F36003002000) to the test port of the bleed pressure regulator valve, and slowly pressurize the system No. 2 to 30 psi (2.0684 bar).
2 On the ECAM control panel 11VU, push the BLEED key (the BLEED
_ page comes into view on the lower ECAM DU).
3 On the AIR COND panel 30VU, make sure that the ENG 2 BLEED
_ pushbutton switch (4HA2) is pushed.
4 On the BLEED page, make sure that the bleed pressure regulator
_ valve is shown open.
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5_ Start the APU:
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