Functional Test of the Bleed Regulated Pressure-Transducer with the Bleed Test Set P/N 98L36103002000

TASK 36-11-16-720-001-A-01
Functional Test of the Bleed Regulated Pressure-Transducer with the Bleed Test Set P/N 98L36103002000

FIN: 8HA1 ** ON A/C NOT FOR ALL
FIN: 8HA2 ** ON A/C NOT FOR ALL

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE
No specific	AR	PLUG - BLANKING
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )
98L36103002000	1	TEST SET - ENGINE BLEED

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [8HA1] (XDCR-BLEED REGULATED PRESS, ENG 1)
415AL, 415AR
FOR [8HA2] (XDCR-BLEED REGULATED PRESS, ENG 2)
425AL, 425AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
Functional Test of the Bleed Regulated Pressure-Transducer with the Bleed Test Set P/N 98L36103002000

3. Job Set-up
Subtask 36-11-16-861-054-A ** ON A/C NOT FOR ALL

A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 36-11-16-941-054-A ** ON A/C NOT FOR ALL

B. Safety Precautions
(1) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(2) On the AIR COND panel 30VU:

Make sure that the ENG 1(2) BLEED pushbutton switch is released (OFF legend is on).
Make sure that the APU BLEED pushbutton switch is released (ON legend is off).
Put a WARNING NOTICE(S) in position to tell persons not to operate the pneumatic system.

(3) On the ENG panel 115VU:

Put a WARNING NOTICE(S) in position to tell the persons not to start the engine 1(2).

(4) On the HP ground connector:

Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

(5) On the ENG section of the maintenance panel 50VU:

Make sure that the ON legend of the ENG/FADEC GND PWR 1(2) pushbutton switch is off.
Put a WARNING NOTICE(S) in position to tell persons not to energize the FADEC 1(2).

Subtask 36-11-16-010-054-A ** ON A/C NOT FOR ALL

C. Get Access
(1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position at the pylon access.
(2) Open the access doors:
(a) FOR [8HA1] (XDCR-BLEED REGULATED PRESS, ENG 1)
415AL 415AR
(b) FOR [8HA2] (XDCR-BLEED REGULATED PRESS, ENG 2)
425AL 425AR.

Subtask 36-11-16-860-057-A ** ON A/C NOT FOR ALL

D. Aircraft Maintenance Configuration

CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.

(1) Disconnect the sense line from the bleed regulated pressure-transducer 8HA1(2).
(2) Put the PLUG-BLANKING in each disconnected line end.

Subtask 36-11-16-860-058-A ** ON A/C NOT FOR ALL

E. Aircraft Maintenance Configuration
(1) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).

4. Procedure
Subtask 36-11-16-720-051-A ** ON A/C NOT FOR ALL

A. Functional Test of the Bleed Regulated Pressure-Transducer
(1) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98L36103002000 TEST SET - ENGINE BLEED.

WARNING: MAKE SURE THAT THE PRESSURE SUPPLIED TO BLEED TEST SET 98L36103002000 NEVER EXCEEDS 217 PSI (15 BAR). IF THE PRESSURE SUPPLIED TO THE BLEED TEST SET EXCEEDS THIS VALUE, THERE IS A RISK OF INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT. IF THE AIR CYLINDER DOES NOT HAVE A MANOMETER INSTALLED, YOU MUST INSTALL THE PRIMARY REGULATOR VALVE BETWEEN THE AIR BOTTLE AND BLEED TEST SET 98L36103002000. THE PRIMARY REGULATOR VALVE WILL LIMIT THE PRESSURE IN THE BLEED TEST SET TO 217 PSI (15 BAR).

(2) Connect an air cylinder to the 98L36103002000 TEST SET - ENGINE BLEED.
(3) Connection of the test set:

CAUTION: BE CAREFUL WHEN YOU CONNECT/DISCONNECT THE TEST SET TO/FROM THE EQUIPMENT. THE PRESSURE REGULATING VALVE AND THE PRESSURE GAGE ASSEMBLY OF THE TEST SET ARE HEAVY AND CAN CAUSE DAMAGE TO THE ENGINE.

(a) Connect the 98L36103002000 TEST SET - ENGINE BLEED with the short bend flexible assembly to the union of the bleed regulated pressure-transducer.
(4) Do a reset of the digital pressure gage.
(5) Make sure that the regulator valve of the test set is closed before pressurize the system.
(6) Do the test that follows:

ACTION	RESULT
1.On the ECAM control panel: Push the BLEED key.	On the SD: The BLEED page comes into view and shows the bleed pressure.
2.Pressurize the test set: If there is a manometer on the air cylinder then installation of the primary regulator valve is not necessary. Use the air cylinder shut off valve and the manometer to slowly pressurize the test set to 100 psi (6.8948 bar). If there is no manometer in the air cylinder then installation of primary regulator valve is mandatory. In this case the primary regulator valve will limit the pressure in the test set to 217 psi (14.9616 bar).
3.On the test set: Open the shutoff valve. Use the regulator valve of the test set to slowly pressurize the system from 10 psi (0.6895 bar) to 90 psi (6.2053 bar).	On the test set: The digital pressure gage shows the pressure.
	On the SD: The BLEED page shows the supplied pressure which must agree with the value of the digital pressure gage plus or minus 2 psi (0.14 bar).
4.On the test set: Use the regulator valve of the test set to depressurize the system.	On the test set: The digital pressure gage shows 0 psi (0.0000 bar).

5. Close-up
Subtask 36-11-16-942-052-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Close the shutoff valve of the air cylinder.
(2) Slowly open the purge valve to depressurize the test set.
(3) Disconnection of the test set.

WARNING: BEFORE YOU START TO REMOVE THE TOOLING, MAKE SURE THAT THERE IS NO PRESSURIZED GAS LEFT INSIDE THE DUCTS. IT CAN CAUSE AN INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.

(a) Disconnect the short bend flexible assembly from the union of the bleed regulated pressure-transducer
(4) Connection of the sense line

CAUTION: USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT THE PNEUMATIC LINES ON UNIONS.

(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Connect the sense line to the bleed regulated pressure-transducer 8HA1(2).
(c) TORQUE the nut of the sense line to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )

Subtask 36-11-16-860-059-A ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).

Subtask 36-11-16-410-053-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the access doors:
(a) FOR [8HA1] (XDCR-BLEED REGULATED PRESS, ENG 1)
415AL 415AR
(b) FOR [8HA2] (XDCR-BLEED REGULATED PRESS, ENG 2)
425AL 425AR.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

Subtask 36-11-16-862-054-A ** ON A/C NOT FOR ALL

D. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 01:08:33 UTC