Functional Test of the Sense Lines Connected to the Bleed Pressure-Regulator Valve with the Bleed Test Set P/N 98L36103002000

TASK 36-11-00-720-007-A-01
Functional Test of the Sense Lines Connected to the Bleed Pressure-Regulator Valve with the Bleed Test Set P/N 98L36103002000

FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL
FIN: 4001HA ** ON A/C NOT FOR ALL

1. Reason for the Job
To make sure that there are no leaks on the sense lines:

Upstream of the bleed pressure-regulator valve,
Connected to the control solenoid (no pressure change).

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

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	AR	PLUG - BLANKING
No specific	AR	WARNING NOTICE(S)
No specific	AR	WRENCH - CROWFOOT
No specific	Torque wrench: range to between 1.76 and 1.44 m.daN (12.98 and 10.62 lbf.ft )
98L36103002000	1	TEST SET - ENGINE BLEED

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL

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 71-13-00-010-010-A	Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-010-040-B	Opening of the Fan Cowl Doors
TASK 71-13-00-410-010-A	Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 71-13-00-410-040-B	Closing of the Fan Cowl Doors
TASK 78-30-00-040-012-A	Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-081-041-A	Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-081-041-B	Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-440-012-A	Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-30-00-481-041-A	Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-30-00-481-041-B	Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-32-00-010-010-A	Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A	Closing of the Thrust Reverser Halves
TASK 78-36-00-010-040-A	Opening of the Thrust Reverser Doors
TASK 78-36-00-010-040-B	Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-A	Closing of the Thrust Reverser Doors
TASK 78-36-00-410-040-B	Closing of the Thrust Reverser Doors
Functional Test of the Sense Lines Connected to the Bleed Pressure-Regulator Valve with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL
Functional Test of the Sense Lines Connected to the Bleed Pressure-Regulator Valve with the Bleed Test Set P/N 98L36103002000 ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 36-11-00-941-097-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the ENG panel 115VU:

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

(2) On the HP ground connector:

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

Subtask 36-11-00-860-073-A ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Make sure that engine 1(2) shutdown occurred for a minimum of 5 minutes before you do this procedure.
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(3) In the cockpit, on the ENG section of maintenance panel 50VU:

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

(4) In the cockpit, on AIR COND panel 30VU:

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

Subtask 36-11-00-010-087-A ** ON A/C NOT FOR ALL

C. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-063-A ** ON A/C NOT FOR ALL

D. Deactivation of the Thrust Reverser

WARNING: MAKE SURE THAT THE THRUST REVERSER IS LOCKED. IF NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE INJURY TO PERSONNEL AND/OR DAMAGE TO THE REVERSER.

(1) Make the thrust reverser unserviceable for maintenance (Ref. AMM TASK 78-30-00-481-041).

Subtask 36-11-00-010-088-A ** ON A/C NOT FOR ALL

E. Open the left thrust reverser door (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL
(2) FOR [1000EM2] (ENGINE-2)
461AL.

Subtask 36-11-00-010-087-B ** ON A/C NOT FOR ALL

F. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-063-C ** ON A/C NOT FOR ALL

G. Deactivation of the Thrust Reverser

WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Do the deactivation of the Hydraulic Control Unit (HCU) of the thrust reverser (Ref. AMM TASK 78-30-00-040-012).

Subtask 36-11-00-010-088-C ** ON A/C NOT FOR ALL

H. Open the left thrust reverser half (Ref. AMM TASK 78-32-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
451AL
(2) FOR [1000EM2] (ENGINE-2)
461AL.

Subtask 36-11-00-010-087-C ** ON A/C NOT FOR ALL

I. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Put an ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position below the engine.

Subtask 36-11-00-040-063-B ** ON A/C NOT FOR ALL

J. Deactivation of the Thrust Reverser

WARNING: MAKE SURE THAT THE THRUST REVERSER IS LOCKED. IF NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE INJURY TO PERSONNEL AND/OR DAMAGE TO THE REVERSER.

(1) Make the thrust reverser unserviceable for maintenance (Ref. AMM TASK 78-30-00-481-041).

Subtask 36-11-00-010-088-B ** ON A/C NOT FOR ALL

K. Open the left thrust reverser door (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL
(2) FOR [1000EM2] (ENGINE-2)
461AL.

4. Procedure
Subtask 36-11-00-720-056-A ** ON A/C NOT FOR ALL

A. Functional Test of the Sense Line (2) Upstream of the Bleed-Pressure Regulator Valve (4001HA)
(1) Use a WRENCH - CROWFOOT to disconnect the sense line (2) from the duct (1).
(2) Put a PLUG - BLANKING in position on the duct (1).
(3) 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).

(4) Connect the air cylinder to the 98L36103002000 TEST SET - ENGINE BLEED.
(5) Connect the 98L36103002000 TEST SET - ENGINE BLEED as follows:

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 to the disconnected sense line (2) with the short bend flexible-assembly.
(6) Do a reset of the digital pressure gage.
(7) Make sure that the pressure regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED is closed before you pressurize the system.
(8) Do the test as follows:

ACTION	RESULT
1.Pressurize the test 98L36103002000 TEST SET - ENGINE BLEED as follows: If there is a manometer in the air cylinder, the installation of the primary regulator valve is not necessary. Use the air-cylinder shut-off valve and the manometer to slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 35 psi (2.4132 bar) If there is no manometer in the air cylinder, the installation of the primary regulator valve is mandatory. In this condition, the primary regulator valve will adjust the pressure in the 98L36103002000 TEST SET - ENGINE BLEED to 217 psi (14.9616 bar).
2.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve Use the regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED to slowly pressurize the system until you get 30 -1 psi or +1 psi (2.0684 -0.0689 bar or +0.0689 bar).	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gauge shows 30 -1 psi or +1 psi (2.0684 -0.0689 bar or +0.0689 bar).
3.On the air cylinder: Close the shutoff valve of the air cylinder.	On the digital pressure gauge: Make sure that the indication shown does not decrease to 0 psi (0.0000 bar) in less than 20 seconds.

(9) Monitor and record the pressure indications.
(10) Slowly open the purge valve to release the pressure from the 98L36103002000 TEST SET - ENGINE BLEED.
(11) Disconnect the 98L36103002000 TEST SET - ENGINE BLEED as follows:

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 sense line (2).
(12) Remove the PLUG - BLANKING from the duct (1).

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

(13) Connect the sense line (2) as follows:
(a) Make sure that there is no grease or oil on the pneumatic and sense line unions.
(b) Connect the sense line (2) to the union of the duct (1).

NOTE: To prevent the damage to the fitting end of the sense line, Airbus recommends you to turn the union with your hand and not with a spanner.

Subtask 36-11-00-720-057-A ** ON A/C NOT FOR ALL

B. Functional Test of the Sense Line (3) Connected to the Control Solenoid (10HA1, 10HA2)
(1) Use a WRENCH - CROWFOOT to disconnect the sense line (3) from the bleed-pressure regulator valve (4).
(2) Put a PLUG - BLANKING in position on the bleed-pressure regulator valve (4).
(3) Close the shutoff valve, the purge valve and the pressure regulator valve on the 98L36103002000 TEST SET - ENGINE BLEED.

(4) Connect the air cylinder to the 98L36103002000 TEST SET - ENGINE BLEED.
(5) Connect the 98L36103002000 TEST SET - ENGINE BLEED as follows:

(a) Connect the 98L36103002000 TEST SET - ENGINE BLEED with the short bend flexible-assembly to the disconnected sense line (3).
(6) Do a reset of the digital pressure gage.
(7) Make sure that the pressure regulator valve of the 98L36103002000 TEST SET - ENGINE BLEED is closed before you pressurize the system.
(8) Do the test that follows:

ACTION	RESULT
1.Pressurize the 98L36103002000 TEST SET - ENGINE BLEED as follows: If there is a manometer on the air cylinder, the installation of the primary regulator valve is not necessary. Use the air-cylinder shut-off valve and the manometer to slowly pressurize the 98L36103002000 TEST SET - ENGINE BLEED to 35 psi (2.4132 bar) If there is no manometer in the air cylinder, the installation of the primary regulator valve is mandatory. In this condition, the primary regulator valve will adjust the pressure in the 98L36103002000 TEST SET - ENGINE BLEED to 217 psi (14.9616 bar).
2.On the 98L36103002000 TEST SET - ENGINE BLEED: Open the shutoff valve Use the pressure regulator valve to slowly pressurize the system until you get 30 -1 psi or +1 psi (2.0684 -0.0689 bar or +0.0689 bar).	On the 98L36103002000 TEST SET - ENGINE BLEED: The digital pressure gage shows 30 -1 psi or +1 psi (2.0684 -0.0689 bar or +0.0689 bar).
3.On the air cylinder: Close the shutoff valve of the air cylinder.	On the digital pressure gage: Make sure that the indication shown does not decrease to 0 psi (0.0000 bar) in less than 20 seconds.

(9) Monitor and record the pressure indications.
(10) Slowly open the purge valve to depressurize the 98L36103002000 TEST SET - ENGINE BLEED.
(11) Disconnect the 98L36103002000 TEST SET - ENGINE BLEED as follows:

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 sense line (3).
(12) Remove the PLUG - BLANKING from the bleed-pressure regulator valve (4).

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

(13) Connect the sense line (3) as follows:
(a) Make sure that there is no grease or oil on the pneumatic and sense line unions.
(b) Connect the sense line (3) to the bleed-pressure regulator valve (4).

NOTE: To prevent the damage to the fitting end of the sense line, Airbus recommends you to turn the union with your hand and not with a spanner.

5. Close-up
Subtask 36-11-00-860-074-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) In the cockpit, on AIR COND panel 30VU:

Release the ENG 1(2) BLEED pushbutton-switch (the OFF legend is on).

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

Subtask 36-11-00-410-086-A ** ON A/C NOT FOR ALL

B. Close Access
(1) Close the left thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL
(b) FOR [1000EM2] (ENGINE-2)
461AL.

Subtask 36-11-00-440-064-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).

Subtask 36-11-00-410-087-A ** ON A/C NOT FOR ALL

D. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

Subtask 36-11-00-410-086-B ** ON A/C NOT FOR ALL

E. Close Access
(1) Close the left thrust-reverser halves (Ref. AMM TASK 78-32-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL.
(b) FOR [1000EM2] (ENGINE-2)
461AL.

Subtask 36-11-00-440-064-C ** ON A/C NOT FOR ALL

F. Do the activation of the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012)

Subtask 36-11-00-410-087-C ** ON A/C NOT FOR ALL

G. Close Access
(1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

Subtask 36-11-00-410-086-C ** ON A/C NOT FOR ALL

H. Close Access
(1) Close the left thrust-reverser doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL
(b) FOR [1000EM2] (ENGINE-2)
461AL.

Subtask 36-11-00-440-064-B ** ON A/C NOT FOR ALL

I. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).

Subtask 36-11-00-410-087-B ** ON A/C NOT FOR ALL

J. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 01:06:53 UTC