High Variation of the Bleed Pressure Indication for the Engine 1

TASK 36-11-00-810-900-A
High Variation of the Bleed Pressure Indication for the Engine 1

1. Possible Causes

sense line between upstream of the pressure regulator valve (4001HA) and the bleed transferred-pressure transducer (7HA1)
SOLENOID-BLEED PRESS REG V CTL, ENG 1 [10HA1]

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	Torque wrench: range to between 1.76 and 1.44 m.daN (12.98 and 10.62 lbf.ft )

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 36-11-00-720-007	Functional Test of the Sense Lines Connected to the Bleed Pressure-Regulator Valve with the Bleed Test Set P/N 98D36003000000
AMM 36-11-00-740-001	BITE Test of the BMC 1(2)
AMM 36-11-49-000-029	Removal of the Pneumatic Sense Lines in the Pylon
AMM 36-11-49-000-820	Removal of the Pneumatic Sense Lines in the Pylon
AMM 36-11-49-400-029	Installation of the Pneumatic Sense Lines in the Pylon
AMM 36-11-49-400-820	Installation of the Pneumatic Sense Lines in the Pylon
AMM 36-11-55-000-001	Removal of the Bleed-Pressure-Regulator Valve Control-Solenoid
AMM 36-11-55-400-001	Installation of the Bleed-Pressure-Regulator Valve Control-Solenoid

3. Fault Confirmation
Subtask 36-11-00-860-050-A ** ON A/C NOT FOR ALL

A. Job Set-Up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001
(c) On the ECAM control panel, push the BLEED key (on the lower ECAM display unit, the BLEED page comes into view).

Subtask 36-11-00-710-246-A ** ON A/C NOT FOR ALL

B. Test
(1) Do the operational test of the BMC1 (with the CFDS) AMM 36-11-00-740-001.

4. Fault Isolation

NOTE: For the test of the engine bleed-air system, Airbus recommends to use bleed test set P/N 98L36103002000 for more accuracy.

Subtask 36-11-00-810-150-B ** ON A/C NOT FOR ALL

A. If the test gives a maintenance message:

do the trouble shooting procedure related to the maintenance message.

CAUTION: USE TWO WRENCHES DURING DISCONNECTION OF THE SENSE LINE, ONE TO MAINTAIN THE FIXED NUT AND THE SECOND ONE TO LOOSEN/TIGHTEN THE SENSE LINE COUPLING.

CAUTION: BE CAREFUL WITH THE SEMI-FLEXIBLE SENSE LINE. DEFORMATION OF THE RIGID PART OR LARGE DEFORMATION OF THE FLEXIBLE PART CAN QUICKLY CAUSE LEAKAGE.

(1) If there is no message:

do a check of the sense line unions upstream of the bleed transferred pressure transducer (7HA1).

(a) If the unions are loose, TORQUE these unions to between 1.76 and 1.44 m.daN (12.98 and 10.62 lbf.ft )

and stop trouble shooting.
(b) If the unions are correctly tightened and if the fault continues:
1 Do the functional test of the sense line upstream of the bleed-pressure regulator valve (4001HA) AMM 36-11-00-720-007.
a If the pressure decreases to 0 psi (0 bar) in less than 20 seconds:

replace the sense line between upstream of the pressure regulator valve (4001HA) and the bleed transferred-pressure transducer (7HA1) AMM 36-11-49-000-029 and AMM 36-11-49-400-029.

b If the pressure drop-is not high or very slow:

replace the SOLENOID-BLEED PRESS REG V CTL, ENG 1 [10HA1] AMM 36-11-55-000-001 and AMM 36-11-55-400-001.

Subtask 36-11-00-810-150-C ** ON A/C NOT FOR ALL

A. If the test gives a maintenance message:

Do the trouble shooting procedure related to the maintenance message.

CAUTION: USE TWO WRENCHES DURING DISCONNECTION OF THE SENSE LINE, ONE TO MAINTAIN THE FIXED NUT AND THE SECOND ONE TO LOOSEN/TIGHTEN THE SENSE LINE COUPLING.

CAUTION: BE CAREFUL WITH THE SEMI-FLEXIBLE SENSE LINE. DEFORMATION OF THE RIGID PART OR LARGE DEFORMATION OF THE FLEXIBLE PART CAN QUICKLY CAUSE LEAKAGE.

(1) If there is no message:

Do a check of the sense line unions upstream of the bleed transferred-pressure transducer (7HA1).

(a) If the unions are loose, TORQUE these unions to between 1.76 and 1.44 m.daN (12.98 and 10.62 lbf.ft )

Replace the sense line between upstream of the pressure regulator valve (4001HA) and the bleed transferred-pressure transducer (7HA1) AMM 36-11-49-000-820 and AMM 36-11-49-400-820.

b If the pressure decreases slowly:

Replace the SOLENOID-BLEED PRESS REG V CTL, ENG 1 [10HA1] AMM 36-11-55-000-001 and AMM 36-11-55-400-001.

Subtask 36-11-00-710-247-A ** ON A/C NOT FOR ALL

B. Test
(1) After the subsequent flight, make sure that the fault does not continue.

5. Close-up
Subtask 36-11-00-860-051-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
AMM 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
AMM 24-41-00-862-002.

[Rev.8 from Aug 2018] 2026.04.04 04:33:48 UTC