W DOC AIRBUS | AMM A320F

Leak Check of Wing Bleed Air on the Pylon to Wing Ducting Flexible Seals and the Wing to Fuselage 'S' Duct

TASK 36-11-48-790-002-A
Leak Check of Wing Bleed Air on the Pylon to Wing Ducting Flexible Seals and the Wing to Fuselage 'S' Duct

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.
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: 190
ZONE: 520
ZONE: 620
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 5M (16 FT)- ADJUSTABLE
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
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.14QAD1)
Wire-- Stainless Steel Braided -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
190
BELLY FAIR, AIR CONDITIONING & HYD COMPT
520
LEFT WING FIXED LEADING EDGE
620
RIGHT WING FIXED LEADING EDGE
191BT, 191DB, 192BT, 521AB, 521BT, 621AB, 621BT
 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 36-11-48-400-004-A
Installation of the Bleed Air Ducts
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
F Wing Bleed Air Ducting - Access Panel Location
F Wing Bleed Air Ducting, Flexible Connections - Location and Detail
3. Job Set-up
Subtask 36-11-48-941-057-A ** ON A/C NOT FOR ALL
A. Safety Precautions
   (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
   (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 36-11-48-860-058-A ** ON A/C NOT FOR ALL
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 installed on the slat/flap control lever.
WARNING: OPEN CIRCUIT BREAKERS 1JH, 2JH1, 2JH2, 3JH1 AND 3JH2 (ENGINE 1 AND 2 IGNITION SYSTEMS). THEN OPEN CIRCUIT BREAKERS 2KS1 AND 2KS2 (FADEC A AND EIU 1 AND 2) AND 4KS1 (FADEC B AND EIU 1). IF YOU DO NOT OBEY THIS SEQUENCE, THE ENGINE AUTOMATIC IGNITION- SYSTEM WILL OPERATE. THIS CAN CAUSE INJURY TO MAINTENANCE PERSONNEL.
   (3) Open circuit breakers:
Subtask 36-11-48-865-068-A ** ON A/C NOT FOR ALL
C. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
Subtask 36-11-48-010-059-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) Put an ACCESS PLATFORM 5M (16 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):
     (a) For the LH wing:
     (b) For the RH wing:
   (3) Remove and discard the braided wire from the insulation muffs on the flexible connectors (1) thru (5).
   (4) Remove the insulation muffs.
4. Procedure
Subtask 36-11-48-790-058-A ** ON A/C NOT FOR ALL
A. Leak Check of the Bleed Air Flexible Connections (Air supplied by the GAPC)
NOTE: APU type APS3200 and Allied Signal 131-9(A) can be used as an alternative to the GAPC. Aircraft with APU GTCP 36-300 installed must use the GAPC for this procedure.
   (1) For access to the HP-Ground Connection 7300HM:
  • open the access door 191DB.
   (2) Connect a GROUND AIR SUPPLY 0 TO 3.5 BAR (50.76 PSI) to the HP-Ground Connection.
   (3) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
   (4) On the AIR COND panel 30VU:
  • put the X BLEED switch to the OPEN position.
   (5) 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.
   (6) 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).
   (7) Use SOLUTION - LEAK DETECTION to do a leak check on:
     (a) The flexible connectors (1) and (2) on the wing leading edge ducting between rib 7 and rib 8.
     (b) The flexible connectors (3), (4) and (5) on the wing to fuselage 'S' duct.
NOTE: Leakage is permitted when a series of bubbles are continuous on the joint line, and as one bubble breaks another one forms. Leakage is not permitted when air pressure blows detection solution from the joint line and prevents a continuous series of bubbles.
   (8) Stop the GAPC.
   (9) On the AIR COND panel 30VU:
  • put the X BLEED switch to the AUTO position.
   (10) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
   (11) Disconnect the GAPC from the HP-Ground Connection.
   (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 36-11-48-790-057-B ** ON A/C NOT FOR ALL
B. Leak Check of the Bleed Air Flexible Connections (Air supplied by the APU 131-9(A))
   (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 the ECAM control panel 11VU:
  • push (in) the BLEED P/BSW
  • make sure that the BLEED page is shown on the lower ECAM DU.
   (4) 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.
   (5) Start the 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 the AIR COND panel 30VU:
  • push (in) the APU BLEED P/BSW
  • make sure that the APU BLEED P/BSW ON light comes on (blue)
  • make sure that 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 P/BSW
  • 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 SOLUTION - LEAK DETECTION to do a leak check on:
     (a) The flexible connectors (1) and (2) on the wing leading edge ducting between rib 7 and rib 8.
     (b) The flexible connectors (3), (4) and (5) on the wing to fuselage 'S' duct.
NOTE: Leakage is permitted when a series of bubbles are continuous on the joint line, and as one bubble breaks another one forms. This indicates that the detection solution is stable on the joint line. Leakage is not permitted, when air pressure blows detection solution from the joint line and prevents a continuous series of bubbles.
   (10) On the AIR COND panel 30VU, release (out) the APU BLEED P/BSW:
  • make sure that the APU BLEED P/BSW light goes off.
   (11) Stop the 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).
5. Close-up
Subtask 36-11-48-410-059-B ** ON A/C NOT FOR ALL
A. Close Access
   (1) Use WATER - DISTILLED to remove remaining any leak detection solution from the ducting and dry with a Textile-Lint free Cotton - (Material No.14SBA1) .
   (2) Install the insulation muffs on the flexible connectors (1) thru (5).
   (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):
     (a) For the LH wing:
     (b) For the RH wing:
   (6) If the GAPC was used:
  • close the access door 191DB.
Subtask 36-11-48-860-059-A ** ON A/C NOT FOR ALL
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) 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 36-11-48-865-069-A ** ON A/C NOT FOR ALL
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
Subtask 36-11-48-942-055-A ** ON A/C NOT FOR ALL
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 01:09:52 UTC
"Aviabrain" 2025