Perform Leak Check on Bleed Air Ducting in Wing Area between Bleed Air Precooler, Wing Anti Ice Valve and Wing/Fuselage Connection

TASK 36-11-48-790-001-A
Perform Leak Check on Bleed Air Ducting in Wing Area between Bleed Air Precooler, Wing Anti Ice Valve and Wing/Fuselage Connection

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

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

CAUTION: DO NOT USE ENGINE POWER WHEN YOU DO A LEAK TEST OF THE WING ANTI-ICE DUCTS. HOT AIR FROM THE ENGINE CAN CAUSE INJURY.

ZONE: 500
ZONE: 600

1. Reason for the Job
Refer to the MPD TASK: 361148-01
PERFORM LEAK CHECK ON BLEED AIR DUCTING IN WING AREA BETWEEN BLEED AIR PRECOOLER, WING ANTI ICE VALVE AND WING/FUSELAGE CONNECTION
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE
No specific	2	FOIL - ALUMINUM
No specific	AR	GROUND AIR SUPPLY 0 TO 3.5 BAR (50.76 PSI)
No specific	AR	SAFETY BARRIER(S)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	SOLUTION - LEAK DETECTION
No specific	AR	WARNING NOTICE(S)
No specific	AR	WATER - DISTILLED
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
99V36009001000	1	LEAK DETECTOR CAM

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.14QAD1)	Wire-- Stainless Steel Braided -
(Material No.14QEB1)	Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
500	LEFT WING
600	RIGHT WING
191BT, 191DB, 192BT, 521AB, 521BB, 521BT, 521CB, 521EB, 522AB, 621AB, 621BB, 621BT, 621CB, 621EB, 622AB
471AR, 481AL
413DT, 423DT
413DL, 414FR, 423DL, 423FL
413ET, 423ET

D. 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 27-80-00-866-004-A	Extending the Slats on the Ground
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 32-00-00-481-001-A	Installation of the Safety Devices on the Landing Gears
TASK 36-11-48-000-004-A	Removal of the Bleed Air Ducts
TASK 36-11-48-000-802-A	Removal of the Bleed Air Ducts
TASK 36-11-48-400-004-A	Installation of the Bleed Air Ducts
TASK 36-11-48-400-802-A	Installation of the Bleed Air Ducts
TASK 49-00-00-860-005-A	APU Start by External Power
TASK 49-00-00-860-005-A-01	APU Start by Batteries
TASK 49-00-00-860-006-A	APU Shutdown by External Power
TASK 49-00-00-860-006-A-01	APU Shutdown by Batteries
TASK 49-00-00-860-008-A	APU Start by External Power
TASK 49-00-00-860-008-A-01	APU Start by Batteries
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 53-35-11-000-001-A	Removal of the Wing-to-Fuselage Fairings
TASK 53-35-11-400-001-A	Installation of the Wing-to-Fuselage Fairings
TASK 54-52-11-000-805-A	Removal of the Access Skin Panels
TASK 54-52-11-400-805-A	Installation of the Access Skin Panels
TASK 54-53-11-000-804-A	Removal of the Pylon-to-Wing Access Panels and Doors
TASK 54-53-11-400-804-A	Installation of the Pylon-to-Wing Access Panels and Doors
TASK 57-41-37-000-004-A	Removal of the Pressure Relief Panels
TASK 57-41-37-000-005-A	Removal of the NACA Duct Panel
TASK 57-41-37-000-009-A	Removal of the Access Panel
TASK 57-41-37-400-002-A	Installation of the Pressure Relief Panels
TASK 57-41-37-400-005-A	Installation of the NACA Duct Panel
TASK 57-41-37-400-009-A	Installation of the Access Panel
Wing Bleed Air Ducting - Location and Detail ** ON A/C NOT FOR ALL
Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL
Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL
Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL
Wing Bleed Air Ducting - Location and Detail ** ON A/C NOT FOR ALL
Aluminum Procedure ** ON A/C NOT FOR ALL
Leak Detector Camera Procedure ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 36-11-48-941-056-A

A. Safety Precautions
(1) Put the SAFETY BARRIER(S) in position.
(2) Make sure that the ground safety locks are installed on the landing gear (Ref. AMM TASK 32-00-00-481-001).
(3) Put a WARNING NOTICE(S) on the panel 115VU, to tell persons not to start the engine(s).
(4) Put a WARNING NOTICE(S) on the panel 114VU, to tell persons not to operate the flap/slat controls.

Subtask 36-11-48-860-056-A

B. Aircraft Maintenance Configuration

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004).
(2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the slat/flap control lever.

Subtask 36-11-48-865-066-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	AIR BLEED/ENG 1/CTL	3HA1	D12
49VU	AIR BLEED/ENG 1/MONG	2HA1	D11
** ON A/C ALL
49VU	AIR BLEED/X FEED/VALVE/BAT	2HV	D13
** ON A/C NOT FOR ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
** ON A/C NOT FOR ALL
122VU	AIR BLEED/ENG 2/CTL	3HA2	Z23
122VU	AIR BLEED/ENG 2/MONG	2HA2	Z22
** ON A/C ALL
122VU	AIR BLEED/X FEED VALVE/NORM	1HV	Z20
** ON A/C NOT FOR ALL
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-48-010-058-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the wing leading edge panels, zone 510(610).
(2) Remove the applicable access panels (Ref. AMM TASK 53-35-11-000-001), (Ref. AMM TASK 57-41-37-000-004), (Ref. AMM TASK 57-41-37-000-005), (Ref. AMM TASK 57-41-37-000-009):

Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL

(a) For the LH wing:

remove the access panels 191BT 521AB 521BB 521CB 521EB 521BT 522AB.

(b) For the RH wing:

remove the access panels 192BT 621AB 621BB 621CB 621EB 621BT 622AB.

remove the access panels 413DL 414FR.

(d) For the RH engine pylon:

remove the access panels 423DL 423FL.

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.

(3) On the bleed air ducting between the wing/fuselage connection, anti-ice valve and the precooler:

remove and discard the braided wire from the insulation muffs.

(4) Remove the insulation muffs.

Subtask 36-11-48-010-058-C ** ON A/C NOT FOR ALL

remove the access panels 191BT 521AB 521BB 521CB 521EB 521BT 522AB.

(b) For the RH wing:

remove the access panels 192BT 621AB 621BB 621CB 621EB 621BT 622AB.

remove the access panels 413DT 471AR.

(d) For the RH engine pylon:

remove the access panels 423DT 481AL.

(3) On the bleed air ducting between the wing/fuselage connection, anti-ice valve and the precooler:

remove and discard the braided wire from the insulation muffs.

(4) Remove the insulation muffs.

Subtask 36-11-48-010-058-D ** ON A/C NOT FOR ALL

D. Get Access
(1) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the wing leading-edge panels.
(2) Remove the applicable access panels (Ref. AMM TASK 53-35-11-000-001), (Ref. AMM TASK 57-41-37-000-004), (Ref. AMM TASK 57-41-37-000-005) and (Ref. AMM TASK 57-41-37-000-009):
(a) For the LH wing:

Remove access panels 191BT 521AB 521BB 521CB 521EB 521BT and 522AB.

(b) For the RH wing:

Remove access panels 192BT 621AB 621BB 621CB 621EB 621BT and 622AB.

Remove access panels 413DT and 413ET (Ref. AMM TASK 54-52-11-000-805) and (Ref. AMM TASK 54-53-11-000-804).

(d) For the RH engine pylon:

Remove access panels 423DT and 423ET (Ref. AMM TASK 54-52-11-000-805) and (Ref. AMM TASK 54-53-11-000-804).

(3) Remove the braided wire from the bleed air ducting between the wing/fuselage connection, anti-ice valve and the precooler:

Remove and discard the braided wire from the insulation muffs.
Remove the insulation muffs.

4. Procedure
Subtask 36-11-48-790-055-B ** ON A/C NOT FOR ALL

A. Leak Check of the Bleed Air Ducting (Air supplied by the APU)

NOTE: Two leak check procedures are given. One procedure uses air supplied by the APU and the other uses air supplied by the Ground Air Power Cart (GAPC).
You can use one of the two procedures to do the leak check of the applicable connections.

(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001).
(3) On ECAM control panel 11VU:

Push (in) the BLEED pushbutton switch.
Make sure that the BLEED page is shown on the lower ECAM DU.

(4) On panel 25VU:

Make sure that the ANTI-ICE/WING pushbutton switch is released (out)
Make sure that the ANTI-ICE/WING pushbutton switch ON light is off.

(5) Start the APU:

For APS 3200 APU (Ref. AMM TASK 49-00-00-860-005)
For 131-9(A) APU (Ref. AMM TASK 49-00-00-860-008).

NOTE: After the APU starts, Airbus recommends you to wait for a minimum of 3 minutes for the warm-up period, before you select the APU BLEED.

(6) On AIR COND panel 30VU:

Push (in) the APU BLEED pushbutton-switch
Make sure that the APU BLEED pushbutton-switch ON light comes on (blue) and the bleed air system is pressurized.

(7) On the ECAM lower DU, make sure that the BLEED page shows:

The X BLEED valve is open (green in-line)
The APU BLEED valve is open (green in-line).

(8) On the ECAM control panel:

Push (in) the APU pushbutton switch
Make sure that the APU page comes into view on the lower ECAM DU
Make sure that the APU BLEED pressure is shown.

(9) Use a SOLUTION - LEAK DETECTION to do a leak check of the wing bleed-air-duct connections. Do the leak check from the wing/fuselage connection to the wing anti-ice valve and the precooler on:

All air ducts
Each duct joint
All flexible connections.

NOTE: Leakage is permitted when a series of bubbles are continuously maintained on the joint line. This shows that the detection solution can stay on the joint line. Leakage is not permitted when the air pressure blows detection solution from the joint line to prevent a continuous series of bubbles.

(10) On AIR COND panel 30VU:

Release (out) the APU BLEED pushbutton-switch
Make sure that the APU BLEED pushbutton-switch ON light goes off.

(11) Stop the APU:

For APS 3200 APU (Ref. AMM TASK 49-00-00-860-006)
For 131-9(A) APU (Ref. AMM TASK 49-00-00-860-009).

(12) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(13) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(14) Replace and/or reseal ducts that leak (Ref. AMM TASK 36-11-48-000-004) and (Ref. AMM TASK 36-11-48-400-004).

Subtask 36-11-48-790-056-B ** ON A/C NOT FOR ALL

B. Leak Check of the Bleed Air Ducting (Air supplied by the GAPC)
(1) Put a WARNING NOTICE(S) on the panel 30VU, to tell persons not to operate the pneumatic system.
(2) For access to the HP-Ground Connection 7300HM:

open access door 191DB.

(3) Connect a GROUND AIR SUPPLY 0 TO 3.5 BAR (50.76 PSI) to the HP-Ground Connection.
(4) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(5) On the AIR COND panel 30VU:

put the X BLEED switch to the OPEN position.

(6) On the panel 25VU:

make sure that the ANTI-ICE/WING P/BSW is released (out)
make sure that the ANTI-ICE/WING P/BSW ON light is off.

(7) Start the Ground Air Power Cart (GAPC) and adjust the air pressure slowly until it becomes stable at 44 psi (3.0337 bar) +/- 4 psi (0.2758 bar).
(8) Use SOLUTION - LEAK DETECTION to do a leak check of the wing bleed air ducting connections. Do the leak check from the wing/fuselage connection, to the wing anti-ice valve and the precooler on:

all the air ducts, each duct joint and all flexible connections.

NOTE: Leakage is permitted when a series of bubbles are continuously maintained on the joint line, and as one bubble breaks another forms. This indicates that the detection solution can maintain itself on the joint line. Leakage is not permitted, when air pressure blows detection solution from the joint line to prevent a continuous series of bubbles.

(9) Stop the Ground Air Power Cart (GAPC).
(10) On the AIR COND panel 30VU:

put the X BLEED switch to the AUTO position.

(11) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(12) Replace and/or reseal ducts that leak (Ref. AMM TASK 36-11-48-000-004) and (Ref. AMM TASK 36-11-48-400-004).

Subtask 36-11-48-790-055-G ** ON A/C NOT FOR ALL

C. Leak Check of the Bleed Air Ducting (Air Supplied from the APU)

NOTE: Two leak check procedures are given. One procedure uses air supplied from the APU and the other uses air supplied from the High Pressure Ground Cart (HPGC).
You can use one of these two procedures to do the leak check of the applicable connections.

(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001).
(3) On ECAM control panel 11VU:
(a) Push the BLEED pushbutton switch.
(b) Make sure that the BLEED page is shown on the lower ECAM DU.
(4) On panel 25VU:

Make sure that the ANTI-ICE/WING pushbutton-switch is released (the ON legend is off).

(5) Start the APU:

For APS 3200 APU (Ref. AMM D/O 49-00-00-86)
For 131-9(A) APU (Ref. AMM TASK 49-00-00-860-008).

NOTE: After the APU starts, Airbus recommends you to wait for a minimum of 3 minutes of warm-up period before you select the APU BLEED.

(6) On AIR COND panel 30VU:
(a) Push the APU BLEED pushbutton-switch.
(b) Make sure that the APU BLEED pushbutton-light comes on (blue) and the bleed air system is pressurized.
(7) On the ECAM lower DU, make sure that the BLEED page shows:
(a) The X BLEED valve is open (green in-line).
(b) The APU BLEED valve is open (green in-line).
(8) On the ECAM control panel:
(a) Push the APU pushbutton switch.
(b) Make sure that the APU page comes into view on the lower ECAM DU.
(c) Make sure that the APU BLEED pressure is shown.
(9) Do a leak check of all the bleed air ducts as follows:

NOTE: There are two procedures to do a leak check at the connections of the bleed air ducts (the duct joint and the flexible connections).

(a) Soap solution procedure:

NOTE: Duct joint leakage is permitted if the detection solution stays on the joint line with a continuous series of bubbles. This shows that the detection solution can stay on the joint line.
Duct joint leakage is not permitted when the air pressure blows the detection solution from the joint line to prevent a continuous series of bubbles.

(b) Aluminum foil procedure:

Aluminum Procedure ** ON A/C NOT FOR ALL

NOTE: This procedure is recommended when you do a leak check with hot air.

1 Wind the FOIL - ALUMINUM one time on the joint.
2 Twist and tighten the seam of the foil wrap.
3 Make the foil wrap as tight as possible on the tube but do not cause damage to the wrap.
4 Install the lockwire as follows:

a Attach the foil wrap to the two sides of the pneumatic joint with 14QEB1Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -.
5 Do a check for leaks:
a If there is a leak:

The foil installed on the duct breaks or changes its color.

(10) On AIR COND panel 30VU:

Make sure that the APU BLEED pushbutton-switch is released (the ON light goes off).

(11) Stop the APU:

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).

(12) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(13) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(14) Replace and/or seal the ducts again where you found the leakage (Ref. AMM TASK 36-11-48-000-802), (Ref. AMM D/O 36-11-48-00), (Ref. AMM TASK 36-11-48-400-802) and (Ref. AMM D/O 36-11-48-40).

Subtask 36-11-48-790-056-D ** ON A/C NOT FOR ALL

D. Leak Check of the Bleed Air Ducting (Air Supplied from the HPGC)
(1) Put a WARNING NOTICE(S) in position on panel 30VU to tell persons not to operate the pneumatic system.
(2) For access to HPGC 7300HM:

Open access door 191DB.

(3) Connect a GROUND AIR SUPPLY 0 TO 3.5 BAR (50.76 PSI) to the HPGC.
(4) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(5) On AIR COND panel 30VU:

Put the X BLEED switch to the OPEN position.

(6) On panel 25VU:

Make sure that the ANTI-ICE/WING pushbutton switch is released (the ON light is off).

(7) Start the HPGC and adjust the air pressure slowly until it becomes stable at 44 +4 psi or -4 psi (3.0337 +0.2758 bar or -0.2758 bar).
(8) Do the leak check of all the bleed air ducts:

NOTE: There are three procedures to do a leak check at the connections of the bleed air ducts (the duct joint and the flexible connections).

(a) Soap solution procedure:

NOTE: Duct joint leakage is permitted, if the detection solution stays on the joint line with a continuous sequence of bubbles. This shows that the detection solution can hold itself on the joint line.
Duct joint leakage is not permitted, when the air pressure blows the detection solution off the joint line to prevent a continuous sequence of bubbles.

(b) Aluminum foil procedure:

NOTE: Airbus recommends this procedure when you do a leak check with hot air.

1 Wind an FOIL - ALUMINUM one time on the joint.
2 Twist and tighten the seam of the foil wrap.
3 Make the foil wrap as tight as possible on the tube but do not cause damage to the foil wrap.

4 Attach the foil wrap to the two sides of the pneumatic joint with a 14QEB1Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -.
5 Do a leak check.
(c) Leak-detector camera procedure:

Leak Detector Camera Procedure ** ON A/C NOT FOR ALL

NOTE: Airbus recommends this procedure when you do a leak check of the air ducts, pressurized with the hot compressed air.

1 Use a 99V36009001000 LEAK DETECTOR CAM to examine for leaks while the bleed air duct is pressurized.

NOTE: Leaks are shown on the leak-detector camera display in conspicuous colors.

2 Make sure that there are no leaks.
3 If there is a leak, do the applicable procedure to stop the leakage.
(9) Stop the HPGC.
(10) On AIR COND panel 30VU:

Put the X BLEED switch to the AUTO position.

(11) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(12) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(13) Replace and/or seal the ducts again, where you find the leakage (Ref. AMM TASK 36-11-48-000-802), (Ref. AMM D/O 36-11-48-00), (Ref. AMM TASK 36-11-48-400-802) and (Ref. AMM D/O 36-11-48-40).

5. Close-up
Subtask 36-11-48-865-067-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	AIR BLEED/ENG 1/CTL	3HA1	D12
49VU	AIR BLEED/ENG 1/MONG	2HA1	D11
** ON A/C ALL
49VU	AIR BLEED/X FEED/VALVE/BAT	2HV	D13
** ON A/C NOT FOR ALL
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
** ON A/C NOT FOR ALL
122VU	AIR BLEED/ENG 2/CTL	3HA2	Z23
122VU	AIR BLEED/ENG 2/MONG	2HA2	Z22
** ON A/C ALL
122VU	AIR BLEED/X FEED VALVE/NORM	1HV	Z20
** ON A/C NOT FOR ALL
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22

Subtask 36-11-48-410-058-B ** ON A/C NOT FOR ALL

B. Close Access
(1) Use WATER - DISTILLED to remove any leak detecting solution from the ducting and dry with a Textile-Lint free Cotton - (Material No.14SBA1) .
(2) Install the insulation muffs that have been removed.
(3) Use Wire-- Stainless Steel Braided - (Material No.14QAD1) to safety the insulation muffs.
(4) Make sure that the work area is clean and clear of tools and other items.
(5) Install the applicable access panels (Ref. AMM TASK 53-35-11-400-001), (Ref. AMM TASK 57-41-37-400-002), (Ref. AMM TASK 57-41-37-400-005), (Ref. AMM TASK 57-41-37-400-009):

Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL

(a) For the LH wing:

install the access panels 191BT 521AB 521BB 521CB 521EB 521BT 522AB.

(b) For the RH wing:

install the access panels 192BT 621AB 621BB 621CB 621EB 621BT 622AB.

install the access panels 413DL 414FR.

(d) For the RH engine pylon:

install the access panels 423DL 423FL.

(6) If the GAPC was used:

close the access door 191DB.

Subtask 36-11-48-410-058-E ** ON A/C NOT FOR ALL

B. Close Access
(1) Use WATER - DISTILLED to remove SOLUTION - LEAK DETECTION from the ducting and dry it with a Textile-Lint free Cotton - (Material No.14SBA1) .
(2) Install the insulation muffs that you removed.
(3) Install the braided wire:

(a) Use Wire-- Stainless Steel Braided - (Material No.14QAD1) to safety the insulation muffs.
(4) Make sure that the work area is clean and clear of tools and other items.
(5) Install the applicable access panels (Ref. AMM TASK 53-35-11-400-001) (Ref. AMM TASK 57-41-37-400-002) (Ref. AMM TASK 57-41-37-400-005) and (Ref. AMM TASK 57-41-37-400-009):
(a) For the LH wing:

Install access panels 191BT 521AB 521BB 521CB 521EB 521BT and 522AB.

(b) For the RH wing:

Install access panels 192BT 621AB 621BB 621CB 621EB 621BT and 622AB.

Install access panels 413DT and 413ET (Ref. AMM TASK 54-52-11-400-805) and (Ref. AMM TASK 54-53-11-400-804).

(d) For the RH engine pylon:

Install access panels 423DT and 423ET (Ref. AMM TASK 54-52-11-400-805) and (Ref. AMM TASK 54-53-11-400-804).

(6) Close access door 191DB.

Subtask 36-11-48-410-058-I ** ON A/C NOT FOR ALL

B. Close Access
(1) Use WATER - DISTILLED to remove leak detecting solution from the ducting and dry with a Textile-Lint free Cotton - (Material No.14SBA1) .
(2) Install the insulation muffs that have been removed.
(3) Use Wire-- Stainless Steel Braided - (Material No.14QAD1) to safety the insulation muffs.
(4) Make sure that the work area is clean and clear of tools and other items.
(5) Install the applicable access panels (Ref. AMM TASK 53-35-11-400-001), (Ref. AMM TASK 57-41-37-400-002), (Ref. AMM TASK 57-41-37-400-005), (Ref. AMM TASK 57-41-37-400-009):

Wing Bleed Air Ducting - Access Panel Location ** ON A/C NOT FOR ALL

(a) For the LH wing:

install the access panels 191BT 521AB 521BB 521CB 521EB 521BT 522AB.

(b) For the RH wing:

install the access panels 192BT 621AB 621BB 621CB 621EB 621BT 622AB.

install the access panels 413DT 471AR.

(d) For the RH engine pylon:

install the access panels 423DT 481AL.

(6) If the GAPC was used:

Close the access door 191DB.

Subtask 36-11-48-860-057-A

C. Aircraft Maintenance Configuration

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever on panel 114VU.
(2) Fully retract the slats (Ref. AMM TASK 27-80-00-866-005).

Subtask 36-11-48-942-054-A

D. Removal of Equipment
(1) Remove the safety barriers.
(2) Remove the WARNING NOTICE(S).
(3) Remove the access platform(s).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.10 from 2021] 2026.04.01 12:38:29 UTC