Installation of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections

TASK 36-11-49-400-827-A
Installation of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections

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: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY.

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)
No specific	AR	ADAPTER - TORQUE, STANDARD
No specific	AR	EXTENSION
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 0.76 and 0.64 m.daN (67.26 and 56.64 lbf.in )
No specific	Torque wrench: range to between 0.79 and 0.68 m.daN (69.91 and 60.18 lbf.in )
No specific	Torque wrench: range to between 1.40 and 1.20 m.daN (123.89 and 106.19 lbf.in )
No specific	Torque wrench: range to between 1.44 and 1.23 m.daN (127.43 and 108.85 lbf.in )
No specific	Torque wrench: range to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )
No specific	Torque wrench: range to between 3.15 and 2.90 m.daN (23.23 and 21.39 lbf.ft )
No specific	Torque wrench: range to between 3.48 and 2.96 m.daN (25.66 and 21.83 lbf.ft )
No specific	Torque wrench: range to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )
No specific	Torque wrench: range to between 7.32 and 6.24 m.daN (53.98 and 46.02 lbf.ft )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CPNCL00062)	LUBRICATING OIL TURBINE ENGINE SYNT BASE
(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, 451AL, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL, 448AR, 461AL, 462AR

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
6	SEAL	AIPC 36-11-49-05-030
45	SEAL	AIPC 36-11-49-05-100
55	SEAL	AIPC 36-11-49-05-100
48	SEAL	AIPC 36-11-49-05-110
23	SEAL	AIPC 36-11-49-05-190

E. 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 24-41-00-862-002-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 36-11-41-400-803-A	Installation of the IP Bleed Check-Valve
TASK 36-11-49-400-831-A	Installation of the Indicating Tubes on the Environmental Control System (ECS) Ducts
TASK 36-11-49-820-802-A	Adjustment of the Environmental Control System (ECS) Support Link
TASK 36-11-51-400-803-A	Installation of the HP Bleed Valve (HPV)
TASK 36-11-52-400-804-A	Installation of the Bleed-Pressure Regulator Valve (PRV)
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
Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections

3. Job Set-up
Subtask 36-11-49-860-126-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 is 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) In the cockpit, 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 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 36-11-49-865-202-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 36-11-49-010-237-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

Subtask 36-11-49-040-160-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).

Subtask 36-11-49-010-238-A

E. Get Access
(1) Make sure that the thrust reverser cowl-doors are open (Ref. AMM TASK 78-36-00-010-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR
(2) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.

4. Procedure

NOTE: When you install the bolts and nuts, it is necessary to tighten them with your hand before you apply the final torque.

Subtask 36-11-49-420-141-A

A. Installation of the Environmental Control System (ECS) Ducts from the Engine Case Ports to Pylon Connections
(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).

NOTE: If installed, you can remove the protection caps installed on all the open ports, tubes and hoses.

NOTE: When you triple torque in this procedure, refer SPM 702400910814.

(4) Use the necessary EXTENSION and ADAPTER - TORQUE, STANDARD to install the bolts during this procedure.
(5) Install the ECS duct (21) as follows:
(a) Make sure that the bolts and the nuts kept after the removal of components are clean and in the correct condition.

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

(b) Lubricate the threads of the bolts that follow with LUBRICATING OIL TURBINE ENGINE SYNT BASE (Material No.CPNCL00062) .

The bolts (20), (22), (28) and (31)
The bolts (54) and (51)
The bolts (34), (37), (39) and (42)
The bolts (1) and (2)
The bolt (15).

(c) Put a new AIPC 36-11-49-05-190 SEAL (23) in position against the flange of the engine case.
(d) Put the ECS duct (21) in position against the gasket (23) and the flange of the engine case.
(e) Install the bolts (22) and (20) to attach the ECS duct (21) to the engine case.
(f) TORQUE the bolts (22) and (20) to between 1.40 and 1.20 m.daN (123.89 and 106.19 lbf.in )

.
(g) If removed or loosened, install the support link (27), as follows:
1 Install the bolt (61) and the nut (60) to attach the support link (27) to the bracket (59) on the engine side.
2 TORQUE the nut (60) to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )

.
(h) Install the bolt (28) and the nut (26) to attach the support link (27) to the tabs on the ECS duct (21).

NOTE: If necessary, you can adjust the support link (27) (Ref. AMM TASK 36-11-49-820-802).

(i) TORQUE the nut (26) to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )

.
(j) Install the bolt (31) and the nut (29) to attach the support link (30) to the tabs on the ECS duct (21).
(k) TORQUE the nut (29) to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )

.
(6) Install the ECS duct (50) as follows:
(a) Put a new AIPC 36-11-49-05-100 SEAL (55) in position against the flange of the engine case.
(b) Put the ECS duct (50) in position against the gasket (55) and the flange of the engine case.
(c) Install the bolts (54) to attach the ECS duct (50) on the engine case.
(d) TORQUE the bolts (54) to between 1.44 and 1.23 m.daN (127.43 and 108.85 lbf.in )

.
(e) Install the bolt (51) and the nut (53) to attach the support link (52) to the tabs on the ECS duct (50).
(f) TORQUE the nut (53) to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )

.
(7) Install the ECS duct (38) as follows:
(a) Put a new AIPC 36-11-49-05-100 SEAL (45) in position against the flange of the engine case.
(b) Install a new AIPC 36-11-49-05-110 SEAL (48) in the aft opening of the ECS duct (38).
(c) Put the ECS duct (38) in position against the gasket (45) and the flange of the engine case.
(d) Install the bolts (34) to attach the ECS duct (38) to the engine case.
(e) TORQUE the bolts (34) to between 1.44 and 1.23 m.daN (127.43 and 108.85 lbf.in )

.
(f) Install the V-band clamp (49) to connect the ECS duct (38) to the ECS duct (50) as follows:

NOTE: You can use the recorded V-band position made during the removal procedure.

1 Loosely assemble the V-band clamp (49) around the flanges of the ECS duct (38) and (50).
2 TORQUE the nut on the V-band clamp (49) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

.
3 Lightly tap around the outer diameter of the V-band clamp (49) with a MALLET - PLASTIC. Do not hit the latch mechanism on the V-band clamp (49).
4 TORQUE the nut on the V-band clamp (49) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

a second time.
(g) Install the bolts (42) to attach the tab on the ECS duct (38) to the support bracket (43).
(h) TORQUE the bolts (42) to between 0.76 and 0.64 m.daN (67.26 and 56.64 lbf.in )

.
(i) Install the bolt (39) to attach the loop clamp (41) and the tube (40) to the tab on the ECS duct (38).
(j) TORQUE the bolt (39) to between 0.76 and 0.64 m.daN (67.26 and 56.64 lbf.in )

.
(k) Put the tube (44) in position on the ECS duct (38), then connect the coupling nut on the tube (44) to the ECS duct (38).
(l) TORQUE the coupling nut that connects the tube (44) to the ECS duct (38) to between 3.48 and 2.96 m.daN (25.66 and 21.83 lbf.ft )

.
(8) Install the ECS duct (14) as follows:
(a) Put the ECS duct (14) in a position adjacent to the ECS duct (21).
(b) Install the Intermediate Pressure (IP) bleed check-valve (Ref. AMM TASK 36-11-41-400-803).
(c) Install the High Pressure Valve (HPV) (Ref. AMM TASK 36-11-51-400-803).

PRE SPOL BD-EBU-18003 and PRE SB BD70CR36-036
(d) Put the indicating tube (13) in position on the ECS duct (14), then connect the coupling nut on the indicating tube (13) to the ECS duct (14).
(e) TRIPLE TORQUE the coupling nut that connects the indicating tube (13) to the ECS duct (14) to between 3.15 and 2.90 m.daN (23.23 and 21.39 lbf.ft )

.
(f) Put the support link (16) in position between the tabs on the ECS duct (14).
(g) Install the bolt (15) and the nut (17) to attach the support link (16) to the ECS duct (14).

NOTE: You can install the bolt (15) from one of the two sides.

(h) TORQUE the nut (17) to between 7.32 and 6.24 m.daN (53.98 and 46.02 lbf.ft )

.
End of PRE SPOL BD-EBU-18003 and PRE SB BD70CR36-036

POST SPOL BD-EBU-18003 and POST SB BD70CR36-036
(i) Put the support link (16) in position between the tabs on the ECS duct (14).
(j) Install the bolt (15), the bracket (65) and the nut (17) to attach the support link (16) to the ECS duct (14).

NOTE: You can install the bolt (15) from one of the two sides.

NOTE: Airbus recommends you to put the bracket (65) in the position that you recorded during the removal procedure.

(k) Install the indicating tube (13) (Ref. AMM TASK 36-11-49-400-831).
(l) TORQUE the nut (17) to between 7.32 and 6.24 m.daN (53.98 and 46.02 lbf.ft )

.
End of POST SPOL BD-EBU-18003 and POST SB BD70CR36-036
(m) Put the indicating tube (12) in position on the ECS duct (14), then connect the coupling nut on the indicating tube (12) to the ECS duct (14).
(n) TRIPLE TORQUE the coupling nut that connects the indicating tube (12) to the ECS duct (14) to between 3.15 and 2.90 m.daN (23.23 and 21.39 lbf.ft )

.
(9) Install the ECS duct (8) as follows:
(a) Put the bracket (5) in position on the ECS duct (8).
(b) Install the bolts (56) to attach the bracket (5) to the ECS duct (8).
(c) TORQUE the bolts (56) to between 1.40 and 1.20 m.daN (123.89 and 106.19 lbf.in )

.
(d) Install a new AIPC 36-11-49-05-030 SEAL (6) in the opening of the lower bleed elbow.
(e) Put the ECS duct (8) in position adjacent to the lower bleed elbow.
(f) Install the V-band clamp (7) to connect the ECS duct (8) to the lower bleed elbow as follows:

NOTE: You can use the recorded V-band position made during the removal procedure.

1 Loosely assemble the V-band clamp (7) around the flange of the ECS duct (8) and the lower bleed elbow.
2 TORQUE the nut on the V-band clamp (7) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

.
3 Lightly tap around the outer diameter of the V-band clamp (7) with a MALLET - PLASTIC. Do not hit the latch mechanism on the V-band clamp (7).
4 TORQUE the nut on the V-band clamp (7) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

a second time.
(g) Install the Pressure Regulating Valve (PRV) (Ref. AMM TASK 36-11-52-400-804).
(h) Put the indicating tube (9) in position on the ECS duct (8), then connect the coupling nut on the indicating tube (9) to the ECS duct (8).
(i) TRIPLE TORQUE the coupling nut that connects the indicating tube (9) to the ECS duct (8) to between 3.15 and 2.90 m.daN (23.23 and 21.39 lbf.ft )

.
(j) Tighten the bolt (58) on the loop clamp (57).
(k) TORQUE the bolt (58) to between 0.79 and 0.68 m.daN (69.91 and 60.18 lbf.in )

.
(l) Put the indicating tube (11) in position on the ECS duct (8), then connect the coupling nut on the indicating tube (11) to the ECS duct (8).
(m) TRIPLE TORQUE the coupling nut that connects the indicating tube (11) to the ECS duct (8) to between 3.15 and 2.90 m.daN (23.23 and 21.39 lbf.ft )

.
(n) Install the bolt (2) to attach the loop clamp (3) and the tube (4) to the support bracket (5).
(o) TORQUE the bolt (2) to between 0.79 and 0.68 m.daN (69.91 and 60.18 lbf.in )

.
(p) Install the bolt (1) to attach the loop clamp (10) and the indicating tube (11) to the support bracket (5).
(q) TORQUE the bolt (1) to between 0.79 and 0.68 m.daN (69.91 and 60.18 lbf.in )

.
(10) Install the support links as follows:
(a) If removed or loosened, install the support link (36), as follows:
1 Install the bolt (64) and the nut (63) to attach the support link (36) to the bracket (62) on the engine side.
2 TORQUE the nut (63) to between 1.40 and 1.20 m.daN (123.89 and 106.19 lbf.in )

.
(b) Put the support link (36) in position between the tabs on the ECS duct (38).
(c) Install the bolt (37) and the nut (35) to attach the support link (36) to the ECS duct (38).

NOTE: If necessary, you can adjust the support link (36) (Ref. AMM TASK 36-11-49-820-802).

(d) TORQUE the nut (35) to between 1.40 and 1.20 m.daN (123.89 and 106.19 lbf.in )

.
(e) Put the support link (30) in position between the tabs on the ECS duct (38).
(f) Install the bolt (33) and the nut (32) to attach the support link (30) to the ECS duct (38).

NOTE: If necessary, you can adjust the support link (30) (Ref. AMM TASK 36-11-49-820-802).

(g) TORQUE the nut (32) to between 4.88 and 4.16 m.daN (35.99 and 30.68 lbf.ft )

Subtask 36-11-49-480-083-A

B. Prepare 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 the dry developer on all the pneumatic components.

(b) Install an FOIL - ALUMINUM around the locations of the pneumatic joint as follows:
1 Wind the foil wrap around the joint one time.
2 Twist the seam of the foil wrap 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 Wire - LOCKWIRE NICKEL ALLOY (Material No.CPNCL02659) on the two sides of the pneumatic joint.

Subtask 36-11-49-410-192-A

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-410-806)
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR

Subtask 36-11-49-440-116-A

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

Subtask 36-11-49-865-203-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 36-11-49-860-128-A

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

Subtask 36-11-49-720-100-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 36-11-49-865-208-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 36-11-49-040-162-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 36-11-49-010-243-A

J. Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-806):
(1) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR
(2) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR

Subtask 36-11-49-080-062-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 36-11-49-860-129-A

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

Subtask 36-11-49-865-207-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 36-11-49-410-188-A

Subtask 36-11-49-440-115-A

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

Subtask 36-11-49-410-189-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 WARNING NOTICE(S).
(3) Remove the access platform(s).

Subtask 36-11-49-862-113-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 01:11:44 UTC