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 upstream of the pressure regulator valve (4001HA) and the bleed transferred pressure transducer (7HA1).
 b  If the pressure drop-is not high or very slow:
_
 -replace the SOLENOID-BLEED PRESS REG V CTL, ENG 1 (10HA1) (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) or
_ 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 1 (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 1 (5HA1) (Ref. AMM TASK 36-11-53-000-001) (Ref. AMM TASK 36-11-53-400-001)
 1
 -EFF : ALL

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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).

 1
 -EFF : ALL

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 High Variation of the Bleed Pressure Indication for the Engine 2
 1. Possible Causes
_______________
 -SOLENOID-BLEED PRESS REG V CTL, ENG 2 (10HA2)
 -VALVE-BLEED PRESS REG (4001HA)
 -VALVE-OVERPRESSURE, ENG 2 (5HA2)
 -sense line between the upstream of the pressure regulator valve (4001HA) and the bleed transferred pressure transducer (7HA2)
 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 36-11-00-740-001 BITE Test of the BMC 1(2) 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 36-11-53-000-001 Removal of the Overpressure Valve (5HA1,5HA2) AMM 36-11-53-400-001 Installation of the Overpressure Valve (5HA1,5HA2) 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) 36-11-00-991-002 Fig. 201
 1
 -EFF : ALL

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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). - on the ECAM control panel, push the BLEED key (on the lower

 ECAM display unit, the BLEED page comes into view).
 B. Test
 (1) Do the operational test of the BMC2 (with the CFDS) (Ref. AMM TASK 36-11-00-740-001).
 4. Fault Isolation
_______________
 A. If the test gives a maintenance message, you can find the related trouble shooting procedure in the applicable Page Block 101.
　
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