DOC AIRBUS | AMM A320FLeak Check on all the Bleed Air Ducts and the Packs Components
TASK 36-22-00-790-802-A
Leak Check on all the Bleed Air Ducts and the Packs Components
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Referenced Information
3. Job Set-up
Subtask 36-22-00-860-053-A ** ON A/C NOT FOR ALL
Subtask 36-22-00-790-054-A ** ON A/C NOT FOR ALL
Subtask 36-22-00-860-054-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 12:37:21 UTC
Leak Check on all the Bleed Air Ducts and the Packs Components
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 AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
WARNING:
DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE AN INJURY.
WARNING:
MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND RELATED DOORS
- COMPONENTS THAT MOVE.
WARNING:
BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
WARNING:
MAKE THE THRUST REVERSER UNSERVICEABLE (INSTALL AND SAFETY THE ICU LOCKOUT PIN) BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF YOU DO NOT INSTALL AND SAFETY THE ICU LOCKOUT PIN, YOU CAN CAUSE ACCIDENTAL OPERATION OF THE THRUST REVERSER AND INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT.
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.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
DO NOT TOUCH THE COMPONENT UNTIL IT IS SUFFICIENTLY
COOL TO PREVENT BURNS.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | FOIL - ALUMINUM |
| No specific | AR | WATER - DISTILLED |
| No specific | AR | WATER - SOAPY SOLUTION |
| 08STHEB | 2 | SURFACE TEMPERATURE INDICATOR |
| 99V36009001000 | 2 | LEAK DETECTOR CAM |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.14QEB1) | Wire-Locking Dia: 0.6 mm CRES Nickel Alloy - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 36-12-00-860-802-A | Pressurization of the Bleed System with the APU |
| TASK 36-12-00-860-803-A | Pressurization of the Bleed System through the HP Ground Connector |
Typical Installation of Indicator Strip-Temp Self AdhesiveSubtask 36-22-00-860-053-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
(1) To do a leak check, you can use two air sources:
Subtask 36-22-00-860-055-A ** ON A/C NOT FOR ALL (1) To do a leak check, you can use two air sources:
- Air source from the APU (Ref. AMM TASK 36-12-00-860-802) or
- Air source from a ground air-supply unit (Ref. AMM TASK 36-12-00-860-803).
NOTE: You must make sure that you only use one source to do the test and its applicable connections.
B. Aircraft Maintenance Configuration
(1) If you do the Leak check of the engine core:
4. Procedure(1) If you do the Leak check of the engine core:
- Pressurize with the Engine 1(2).
Subtask 36-22-00-790-054-A ** ON A/C NOT FOR ALL
A. Leak Check on all the Bleed Air Ducts
(b) Twist the seam of the foil wrap to make it tight.
(c) Make the foil wrap as tight as possible on the tube but do not cause damage to the foil wrap.
14QEB1 Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -
(e) Do a leak check:
(b) Do a check of the indicators strip-temp self-adhesive after the engine or the APU operation with the bleed air system in the operation or after the subsequent flight.
(b) Make sure that there are no leaks.
Subtask 36-22-00-790-055-A ** ON A/C NOT FOR ALL NOTE: There are four procedures to do a leak check at the connections of the bleed air ducts (duct joint, flexible connections).
(1) Soap solution procedure: - Leaks are permitted, if WATER - SOAPY SOLUTION stays on the joint line with a continuous sequence of bubbles. This shows that the leaks are not important.
- Leaks are not permitted, if the air pressure (from the air source) blows the soap solution off the joint line and prevents a continuous sequence of bubbles.
NOTE: Airbus recommends this procedure when you do a leak check with hot air.
(a) Wind an FOIL - ALUMINUM one time on the joint. (b) Twist the seam of the foil wrap to make it tight.
(c) Make the foil wrap as tight as possible on the tube but do not cause damage to the foil 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.
(d) Attach the foil wrap at the two sides of the pneumatic joint with a (e) Do a leak check:
- If there is a leak, the foil installed on the duct breaks or change its color.
NOTE: If you find no leak with the aluminum foil procedure, Airbus recommends this procedure when you do a leak check with hot air.
NOTE: The indicators strip-temp self-adhesive monitors the temperature in a range of approximately 70 DEG.C (158 DEG.F) to 110 DEG.C (230 DEG.F).
(a) Wind a 08STHEB SURFACE TEMPERATURE INDICATOR around the overheat sensing element in the applicable area. (b) Do a check of the indicators strip-temp self-adhesive after the engine or the APU operation with the bleed air system in the operation or after the subsequent flight.
- There is a leak in the area if the temperature is more than 110 DEG.C (230 DEG.F).
NOTE: Airbus recommends this procedure when you do a leak check of the air ducts, pressurized with the hot compressed air.
(a) Use a 99V36009001000 LEAK DETECTOR CAM to examine for leaks while the bleed air duct is pressurized.(b) Make sure that there are no leaks.
B. Leak Check on the Pack Components
(1) Do a visual inspection of the pack components and the related ducts for leaks.
(2) Soap solution procedure:
(a) Leaks are permitted, if the WATER - SOAPY SOLUTION stays on the joint line with the continuous sequence of bubbles. This shows that the leaks are not important.
(b) Leaks are not permitted, if the air pressure (from the air source) blows the soap solution off the joint line and prevents the continuous sequence of bubbles.
(3) Aluminum foil procedure:
(b) Twist the seam of the foil wrap to make it tight.
(c) Make the foil wrap as tight as possible on the tube but do not cause damage to the foil wrap.
(d) Install the lockwire:
14QEB1 Wire-Locking Dia: 0.6 mm CRES Nickel Alloy -
(e) Do a leak check:
1 If there is a leak, the foil installed on the duct breaks or its color changes.
(4) Indicator-strip-temp self-adhesive procedure:
(b) Do a check of the indicators strip-temp self-adhesive after the engine or the APU operation with the bleed air system in the operation or after the subsequent flight.
(b) Make sure that there are no leaks.
5. Close-up(1) Do a visual inspection of the pack components and the related ducts for leaks.
(2) Soap solution procedure:
(a) Leaks are permitted, if the WATER - SOAPY SOLUTION stays on the joint line with the continuous sequence of bubbles. This shows that the leaks are not important.
(b) Leaks are not permitted, if the air pressure (from the air source) blows the soap solution off the joint line and prevents the continuous sequence of bubbles.
(3) Aluminum foil procedure:
NOTE: Airbus recommends this procedure when you do a leak check with hot air.
(a) Wind the FOIL - ALUMINUM one time on the joint. (b) Twist the seam of the foil wrap to make it tight.
(c) Make the foil wrap as tight as possible on the tube but do not cause damage to the foil wrap.
(d) Install the lockwire:
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.
1 Attach the foil wrap at the two sides of the pneumatic joint with the (e) Do a leak check:
1 If there is a leak, the foil installed on the duct breaks or its color changes.
(4) Indicator-strip-temp self-adhesive procedure:
NOTE: If you find no leak with the aluminum foil procedure, Airbus recommends this procedure when you do a leak check with hot air.
NOTE: The indicators strip-temp self-adhesive monitors the temperature in a range of approximately 70 DEG.C (158 DEG.F) to 110 DEG.C (230 DEG.F).
(a) Wind a 08STHEB SURFACE TEMPERATURE INDICATOR around the overheat sensing element in the applicable area. (b) Do a check of the indicators strip-temp self-adhesive after the engine or the APU operation with the bleed air system in the operation or after the subsequent flight.
- There is a leak in the area if the temperature is more than 110 DEG.C (230 DEG.F).
NOTE: Airbus recommends this procedure when you do a leak check of the air ducts, pressurized with the hot compressed air.
(a) Use the 99V36009001000 LEAK DETECTOR CAM to examine for leaks while the bleed air duct is pressurized.(b) Make sure that there are no leaks.
Subtask 36-22-00-860-054-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
(1) Put the aircraft back to its initial configuration.
(2) If you used WATER - SOAPY SOLUTION, use WATER - DISTILLED to remove all the soap solution from the ducts, and dry with Textile-Lint free Cotton - (Material No.14SBA1) or remove materials used to do the leak test.
(1) Put the aircraft back to its initial configuration.
(2) If you used WATER - SOAPY SOLUTION, use WATER - DISTILLED to remove all the soap solution from the ducts, and dry with Textile-Lint free Cotton - (Material No.14SBA1) or remove materials used to do the leak test.