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

TASK 36-11-49-000-827-A
Removal 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	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)

B. 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

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 36-11-41-000-803-A	Removal of the IP Bleed Check-Valve
TASK 36-11-49-000-831-A	Removal of the Indicating Tubes on the Environmental Control System (ECS) Ducts
TASK 36-11-51-000-803-A	Removal of the HP Bleed Valve (HPV)
TASK 36-11-52-000-804-A	Removal 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 71-13-00-010-803-A	Opening of the Fan Cowl Doors
TASK 78-30-00-040-807-A	Deactivation of the Thrust Reverser System for Nacelle Maintenance (ICU)
TASK 78-36-00-010-806-A	Opening 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 36-11-49-861-116-A

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

Subtask 36-11-49-941-135-A

B. Safety Precautions
(1) Make sure that the engine 1(2) shutdown occurred not less than five minutes before you do this procedure.
(2) 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) Put a WARNING NOTICE(S) 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 not less than five minutes before you do this procedure.
(c) Put WARNING NOTICE(S) 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) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
(5) On access door 191DB, on the HP ground connector:
(a) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.

Subtask 36-11-49-865-201-A

C. 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 36-11-49-010-235-A

D. Get Access
(1) Open the fan cowl doors (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 36-11-49-040-159-A

E. 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 36-11-49-010-236-A

F. 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
(3) Put an ACCESS PLATFORM 1M(3 FT) in position.

4. Procedure
Subtask 36-11-49-020-147-A

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

NOTE: If necessary, you can put a protection cap on all the open ports, tubes and hoses.

(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) Use the necessary EXTENSION and ADAPTER - TORQUE, STANDARD to remove the bolts during this procedure.
(4) Remove the ECS duct (8) as follows:
(a) Remove the bolt (1) that attaches the loop clamp (10) and the indicating tube (11) to the support bracket (5).
(b) Remove the bolt (2) that attaches the loop clamp (3) and the tube (4) to the support bracket (5).
(c) Loosen the coupling nut and disconnect the indicating tube (11) from the ECS duct (8).
(d) Loosen the bolt (58) and the loop clamp (57).
(e) Loosen the coupling nut and disconnect the indicating tube (9) from the ECS duct (8).
(f) Remove the V-band clamp (7) that attaches the ECS duct (8) to the lower bleed elbow:
1 It is necessary to record the V-band position to use it during installation.
(g) Remove the ECS duct (8) from the engine.
(h) Remove and discard the E-seal (6) from the lower bleed elbow.
(i) Remove the bolts (56) to remove the bracket (5) from the ECS duct (8).
(j) Remove the Pressure Regulating Valve (PRV) (Ref. AMM TASK 36-11-52-000-804) from the engine.
(5) Remove the ECS duct (14) as follows:
(a) Loosen the coupling nut and disconnect the indicating tube (12) from the ECS duct (14).

PRE SPOL BD-EBU-18003 and PRE SB BD70CR36-036

(b) Loosen the coupling nut and disconnect the indicating tube (13) from the ECS duct (14).
(c) Remove the nut (17) and the bolt (15) that attach the support link (16) to the ECS duct (14). Pull the support link away from the tabs on the ECS duct.
End of PRE SPOL BD-EBU-18003 and PRE SB BD70CR36-036

POST SPOL BD-EBU-18003 and POST SB BD70CR36-036
(d) Remove the indicating tube (13) (Ref. AMM TASK 36-11-49-000-831).

(e) Remove the nut (17), the bracket (65) and the bolt (15) that attach the support link (16) to the ECS duct (14). Pull the support link away from the tabs on the ECS duct.

NOTE: Airbus recommends you to record the position of the bracket (65) for the installation procedure.

End of POST SPOL BD-EBU-18003 and POST SB BD70CR36-036
(f) Remove the High Pressure Valve (HPV) (Ref. AMM TASK 36-11-51-000-803) from the engine.
(g) Remove the Intermediate Pressure (IP) bleed check-valve (Ref. AMM TASK 36-11-41-000-803) from the engine.
(h) Remove the ECS duct (14) from the engine.
(6) Remove the ECS duct (38) as follows:
(a) Loosen the coupling nut and disconnect the tube (44) from the ECS duct (38).
(b) Remove the bolt (39) that attaches the loop clamp (41) and the tube (40) to the tab on the ECS duct (38).
(c) Remove the bolts (42) that attaches the support bracket (43) to the tab on the ECS duct (38).
(d) Remove the nut (35) and the bolt (37) that attaches the support link (36) to the ECS duct (38). Pull the support link away from the tabs on the ECS duct.
(e) Remove the nut (32) and the bolt (33) that attaches the support link (30) to the ECS duct (38). Pull the support link away from the tabs on the ECS ducts.
(f) If necessary, remove the nut (63) and the bolt (64) that attaches the support link (36) to the bracket (62) on the engine side.
(g) Remove the V-band clamp (49) to disconnect the ECS duct (38) from the ECS duct (50):
1 Record the V-band position for the installation procedure.
(h) Remove the bolts (34) that attaches the ECS duct (38) to the engine case.
(i) Remove the ECS duct (38) and discard the seal (45) from the engine.
(j) Remove and discard the E-seal (48) from the ECS duct (38).
(7) Remove the ECS duct (50) as follows:
(a) Remove the nut (53) and the bolt (51) to remove the support link (52) from the tabs on the ECS duct (50).
(b) Remove the bolts (54) that attaches the ECS duct (50) to the engine case.
(c) Remove the ECS duct (50) and discard the seal (55) from the engine.
(8) Remove the ECS duct (21) as follows:
(a) Remove the nut (29) and the bolt (31) that attaches the support link (30) to the ECS duct (21).
(b) Remove the support link (30) from the engine.
(c) Remove the nut (26) and the bolt (28) to remove the support link (27) from the tabs on the ECS duct (21).
(d) If necessary, remove the nut (60) and the bolt (61) that attaches the support link (27) to the bracket (59) on the engine side.
(e) Remove the bolts (22) and (20) that attaches the ECS duct (21) to the engine case.
(f) Remove the ECS duct (21) and discard the seal (23) from the engine.

[Rev.10 from 2021] 2026.04.01 01:11:43 UTC