Installation of the IP Bleed Check-Valve

TASK 36-11-41-400-803-A
Installation of the IP Bleed Check-Valve

WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 454
ZONE: 464

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

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE
No specific	AR	FOIL - ALUMINUM
No specific	1	MALLET - PLASTIC
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 1.40 and 1.30 m.daN (123.89 and 115.04 lbf.in )
No specific	Torque wrench: range to between 3.16 and 2.90 m.daN (23.30 and 21.39 lbf.ft )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CPNCL02658)	ARDROX 9D4A
(Material No.CPNCL02659)	Wire - LOCKWIRE NICKEL ALLOY
(Material No.08CKB9)	Cleaner-Hydraulic Spillage Absorbent powder -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
454	HOT SECTION
464	HOT SECTION
191DB
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR, 462AR

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
3	SEAL	AIPC 36-11-41-05-030
1	SEAL	AIPC 36-11-41-05-040

E. Referenced Information

REFERENCE	DESIGNATION
TASK 20-23-22-910-001-A	Marking of the Unions after Application of Standard or Specific Tightening Torque
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 24-41-00-862-002-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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-11-49-400-827-A	Installation of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections
TASK 49-00-00-860-009-A	APU Shutdown by External Power (131-9(A))
TASK 49-00-00-860-009-A-01	APU Shutdown by Batteries (131-9(A))
TASK 71-00-00-860-827-A	Start the Engine (Normal Automatic Start)
TASK 71-00-00-860-828-A	Start the Engine (Normal Manual Start)
TASK 71-00-00-860-829-A	Engine Shutdown
TASK 71-13-00-010-803-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-803-A	Closing of the Fan Cowl Doors
TASK 78-30-00-040-807-A	Deactivation of the Thrust Reverser System for Nacelle Maintenance (ICU)
TASK 78-30-00-440-807-A	Reactivation of the Thrust Reverser System after Nacelle Maintenance (ICU)
TASK 78-36-00-010-806-A	Opening of the Thrust Reverser Cowl Doors
TASK 78-36-00-410-806-A	Closing of the Thrust Reverser Cowl Doors
IP Bleed Check-Valve

3. Job Set-up
Subtask 36-11-41-860-068-A

A. Aircraft Maintenance Configuration
(1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002) or (Ref. AMM TASK 24-41-00-861-002).
(2) In the cockpit, on AIR COND panel 30VU:
(a) Make sure that the ENG 1(2) BLEED pushbutton-switch is released (OFF legend on).
(b) Make sure that the APU BLEED pushbutton-switch is released (ON legend off).
(c) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the pneumatic system.
(3) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position for a minimum of five minutes before you do this procedure.
(c) Make sure that the WARNING NOTICE(S) are in position to tell persons not to operate:

The ENG/MODE selector switch, and
The ENG/MASTER 1(2) control switch.

(4) On the ENG section of maintenance panel 50VU:
(a) Make sure that the ON legend of the FADEC GND PWR/1(2) pushbutton-switch is off.
(b) Make sure that the WARNING NOTICE(S) is in position to tell persons not to energize FADEC 1(2).
(5) On the access door 191DB, on the HP ground connector:
(a) Make sure that the WARNING NOTICE(S) is in position to tell persons not to pressurize the pneumatic system.

Subtask 36-11-41-865-064-A

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-41-010-077-A

C. Get Access
(1) Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR
(2) Make sure that the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE is in position below the fan cowl doors.
(3) Make sure that the right thrust-reverser cowl-door is open (Ref. AMM TASK 78-36-00-010-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
462AR

Subtask 36-11-41-040-065-A

D. Deactivation of the Thrust Reverser System for Maintenance

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Make sure that you did the deactivation of the thrust reverser system for nacelle maintenance (Ref. AMM TASK 78-30-00-040-807).

4. Procedure
Subtask 36-11-41-420-055-A

A. Installation of the IP Bleed Check-Valve
(1) If you use the APU to energize the electrical circuits, stop the APU:

For GTCP 36-300 APU (Ref. AMM D/O 49-00-00-86)
For APS 3200 APU (Ref. AMM D/O 49-00-00-86)
For 131-9(A) APU (Ref. AMM TASK 49-00-00-860-009).

(2) In the cockpit, on the SD bleed page:
(a) Make sure that the pressure and the temperature of the bleed-air duct system are in ambient conditions.

WARNING: MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.

WARNING: DO NOT TOUCH THE UNIT UNTIL IT IS SUFFICIENTLY COOL TO PREVENT BURNS WHEN YOU DO THE MAINTENANCE TASK(S).

(3) Remove the CAP - PROTECTION installed on all the open ports, the tubes and the hoses.
(4) Make sure that the parts retained from the removed component are clean and in the correct condition.
(5) Install the IP bleed check-valve (2) as follows:
(a) Put the new AIPC 36-11-41-05-040 SEAL (1) and the new AIPC 36-11-41-05-030 SEAL (3) in the position.
(b) Put the IP bleed check-valve (2) in position on the engine.
(c) If the High Pressure (HP)/Low Pressure (LP) core Environmental Control System (ECS) duct (6) is removed, install it (Ref. AMM TASK 36-11-49-400-827).

CAUTION: MAKE SURE THAT THE KEY ENGAGES WITH THE SLOT. IF THE KEY DOES NOT ENGAGE WITH THE SLOT, THE VALVE WILL NOT BE IN THE CORRECT POSITION. THIS WILL CAUSE LEAKAGE AT THE CONNECTION.

(d) Align the key in the HP/LP core ECS duct (6) flange with the mating slot in the IP bleed check-valve (2) flange.
(e) Loosely assemble the V-retainer couplings (4) and (7) around the flanges of the IP bleed check-valve (2).
(6) Torque the V-retainer couplings (4) and (7) as follows:
(a) TORQUE the V-retainer couplings (4) and (7) to between 1.40 and 1.30 m.daN (123.89 and 115.04 lbf.in )

.
(b) Lightly tap around the outer diameter of the V-retainer couplings (4) and (7) with a MALLET - PLASTIC. Do not hit the latch mechanism on the V-retainer couplings.
(c) TORQUE again the V-retainer couplings (4) and (7) to between 1.40 and 1.30 m.daN (123.89 and 115.04 lbf.in )

.
(7) TORQUE the sense lines (8) and (9) at the HP/LP core ECS duct (6) to between 3.16 and 2.90 m.daN (23.30 and 21.39 lbf.ft )

.
(8) Put a mark on the connections (Ref. AMM TASK 20-23-22-910-001).
(9) Make sure that the work area is clean and clear of tools and other items.

Subtask 36-11-41-480-053-A

B. Preparation for the Leak Test
(1) Find the location of a pneumatic joint air-leak with one of the two procedures that follow:
(a) Apply Cleaner-Hydraulic Spillage Absorbent powder - (Material No.08CKB9) or ARDROX 9D4A (Material No.CPNCL02658) around the pneumatic joints, only on the connections of the removed pneumatic components.

NOTE: Airbus recommends that you do not apply dry developer on all the pneumatic components.

(b) Install an FOIL - ALUMINUM around the pneumatic joint locations:
1 Wind the foil wrap around the joint one time.
2 Twist the seam of the foil wrap to make it tight.
3 Make the foil wrap as tight as possible on the tube but do not cause damage to the wrap.

WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.

4 Attach the foil wrap with a Wire - LOCKWIRE NICKEL ALLOY (Material No.CPNCL02659) on the two sides of the pneumatic joint.

Subtask 36-11-41-410-073-A

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the right thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-410-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
462AR

Subtask 36-11-41-440-059-A

D. Do the reactivation of the thrust reverser system after nacelle maintenance (Ref. AMM TASK 78-30-00-440-807).

Subtask 36-11-41-865-065-A

E. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-41-860-069-A

F. Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).

Subtask 36-11-41-720-055-A

G. Do this Test
(1) On ECAM control-panel 11VU, push the BLEED key (on the lower ECAM DU, the BLEED page comes into view).
(2) On the lower ECAM DU, on the BLEED page:

Make sure that the related HP bleed valve is shown closed.

(3) Start the related engine with the normal automatic start procedure (Ref. AMM TASK 71-00-00-860-827) or normal manual start procedure (Ref. AMM TASK 71-00-00-860-828) and keep it at idle.
(4) On the AIR COND panel 30VU:

Push the ENG 1(2) BLEED pushbutton switch (the OFF legend goes off).

(5) After five minutes, on the lower ECAM DU, on the BLEED page:

Make sure that the related HP bleed valve is shown open.

(6) Stop the engine (Ref. AMM TASK 71-00-00-860-829).

Subtask 36-11-41-865-066-A

H. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-41-040-066-A

I. Deactivation of the Thrust Reverser System for Maintenance

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Do the deactivation of the thrust reverser system for nacelle maintenance (Ref. AMM TASK 78-30-00-040-807).

Subtask 36-11-41-010-078-A

J. Open the right thrust-reverser cowl-door (Ref. AMM TASK 78-36-00-010-806):
(1) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
452AR
(2) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
462AR

Subtask 36-11-41-080-053-A

K. Make sure that there are no leaks at the junction of the removed pneumatic components on the related engine.

NOTE: There is a leak when the foil installed on the duct breaks or when it is too hot.
There is a leak when the leak air removes the dry developer from the junction.

(1) Remove the materials that you used to do the leak test.

5. Close-up
Subtask 36-11-41-860-070-A

A. Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).

Subtask 36-11-41-865-067-A

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-41-410-071-A

Subtask 36-11-41-440-058-A

D. Do the reactivation of the thrust reverser system after maintenance (Ref. AMM TASK 78-30-00-440-807).

Subtask 36-11-41-410-072-A

E. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

Subtask 36-11-41-862-056-A

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

[Rev.10 from 2021] 2026.04.01 12:38:12 UTC