DOC AIRBUS | AMM A320FDecontamination of the Bleed-Air Ducting System Disconnected at Pressure Regulating Valve (PRV) (4000HA1) with ENGINE 2 Bleed Pressure
TASK 36-11-00-615-807-A-01
Decontamination of the Bleed-Air Ducting System Disconnected at Pressure Regulating Valve (PRV) (4000HA1) with ENGINE 2 Bleed Pressure
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 36-11-00-941-195-A
Subtask 36-11-00-615-061-A
Subtask 36-11-00-210-066-A
[Rev.10 from 2021]
2026.04.01 01:06:12 UTC
Decontamination of the Bleed-Air Ducting System Disconnected at Pressure Regulating Valve (PRV) (4000HA1) with ENGINE 2 Bleed Pressure
WARNING:
MAKE SURE THAT WHEN THE ENGINES OPERATE ON THE GROUND:
- NO PERSONS GO WHERE THE AIRCRAFT CAN CAUSE THEM INJURY OR CAN KILL THEM
- NO OBJECTS STAY WHERE THE ENGINES CAN BLOW THEM AWAY OR WHERE THEY CAN BE PULLED INTO THE ENGINES BY SUCTION.
WARNING:
MAKE SURE THAT THE PNEUMATIC SYSTEM IS DEPRESSURIZED BEFORE YOU START WORK. PRESSURIZED AIR CAN CAUSE INJURY TO PERSONNEL.
WARNING:
ALWAYS USE APPLICABLE GLOVES TO TOUCH HOT PARTS. HOT PARTS CAN CAUSE INJURY TO PERSONS.
WARNING:
BE CAREFUL WHEN THE DUCTS ARE DISCONNECTED THE TEMPERATURE OF THE EXHAUST GASES FROM THE OPEN ENDS OF THE DISCONNECTED DUCTS CAN BE AS HIGH AS 270 DEG.C (518 DEG.F). THE HOT GASES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | BLANKET - HEAT ISOLATION |
| No specific | AR | CAP - BLANKING |
| No specific | AR | COVER - PROTECTION |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | WARNING NOTICE(S) |
| 98F10103500000 | AR | CHOCK-MLG,ENGINE RUN-UP |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 410 | ENG 1 PYLON BOX AND FORWARD FAIRING |
| 420 | ENG 2 PYLON BOX AND FORWARD FAIRING |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 05-24-50-210-801-A | General Visual Inspection of Core Compartment (EWIS) |
| TASK 21-51-00-710-002-A | Operational Test of the Flow Control and Indicating System |
| 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 31-60-00-860-001-A | EIS Start Procedure |
| TASK 31-60-00-860-002-A | EIS Stop Procedure |
| TASK 36-11-00-710-803-A | Operational Test of the Bleed Air System |
| TASK 36-11-49-000-827-A | Removal 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 |
| TASK 36-22-00-790-803-A | Leak Check on all the Bleed Air Ducts and the Pack Components |
| TASK 53-35-13-000-002-A | Removal of the Quick-Release Access Panels from the Belly Fairing Structure |
| TASK 53-35-13-400-002-A | Installation of the Quick-Release Access Panels on the Belly Fairing Structure |
| TASK 71-00-00-860-827-A | Start the Engine (Normal Automatic Start) |
| TASK 71-00-00-860-829-A | Engine Shutdown |
| TASK 71-00-00-869-803-A | Safety Precautions During Engine Ground Operations |
| TASK 78-32-62-210-801-A | General Visual Inspection of Inner Fixed Structure Fire Seals, Thermal Blanket and Thrust Reverser Fire Shields |
Tool InstallationSubtask 36-11-00-941-195-A
A. Safety Precautions
(1) Put the aircraft in the engine run-up condition.
(2) Obey the safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-869-803).
Subtask 36-11-00-865-265-A (1) Put the aircraft in the engine run-up condition.
(2) Obey the safety precautions during engine ground operations (Ref. AMM TASK 71-00-00-869-803).
B. Make sure that this(these) circuit breaker(s) is(are) closed:
Subtask 36-11-00-865-228-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | AIR BLEED/X FEED/VALVE/BAT | 2HV | D13 |
| 49VU | AIR BLEED/ENG 2/MONG | 3HA2 | D12 |
| 122VU | AIR BLEED/ENG 2/CTL | 2HA2 | Z22 |
C. Open, safety and tag this(these) circuit breaker(s):
Subtask 36-11-00-860-247-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN A/115VAC | 53HH | W22 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN A/28VDC | 55HH | W21 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN B/28VDC | 56HH | Y21 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN B/115VAC | 54HH | Y20 |
D. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits from the external power
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
(3) In the cockpit, on AIR COND panel 30VU:
(a) Make sure that the ENG 2 BLEED pushbutton-switch is released (the OFF legend is on).
(b) Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
(c) Make sure that the PACK 1 and 2 pushbutton switches are released (the OFF legends are on).
(d) Make sure that the PACK FLOW selector-switch is set to LO.
(e) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system on the bleed pushbutton switches.
(4) On the HP ground connector (7300HM):
(a) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.
(5)
Subtask 36-11-00-480-153-A (1) Energize the aircraft electrical circuits from the external power
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
(3) In the cockpit, on AIR COND panel 30VU:
(a) Make sure that the ENG 2 BLEED pushbutton-switch is released (the OFF legend is on).
(b) Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
(c) Make sure that the PACK 1 and 2 pushbutton switches are released (the OFF legends are on).
(d) Make sure that the PACK FLOW selector-switch is set to LO.
(e) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system on the bleed pushbutton switches.
(4) On the HP ground connector (7300HM):
(a) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the pneumatic system.
(5)
E. Preparation for Cleaning of the Bleed Air Ducting System
(1) As the bleed source is engine 2, secure the PACK 2 as follows:
(a) Remove the applicable access panel (Ref. AMM TASK 53-35-13-000-002).
(a) In the cockpit, on AIR COND panel 30VU:
1 Make sure that the ENG 2 BLEED pushbutton-switch is released (the OFF legend is on).
2 Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
3 Make sure that the X BLEED selector-switch is in the CLOSED position:
a Put a WARNING NOTICE(S) in position to tell persons not to operate the X BLEED selector-switch.
(a) On the ECAM control panel, push the BLEED key:
1 On the SD, the BLEED page comes into view.
2 On the BLEED page, do a check of:
1 Remove the bleed air duct from the PRV (4000HA1) of engine 1 (Ref. AMM TASK 36-11-49-000-827).
(4) Point the bleed-air joint duct away from the engine and the electrical cables or equipment.
(6) Put the BLANKET - HEAT ISOLATION on the adjacent electrical cables and components.
4. Procedure(1) As the bleed source is engine 2, secure the PACK 2 as follows:
(a) Remove the applicable access panel (Ref. AMM TASK 53-35-13-000-002).
CAUTION:
MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.
(b) (c) Put the CAP-BLANKING on each disconnected electrical connector and receptacle.WARNING:
MAKE SURE THAT WHEN THE ENGINES OPERATE ON THE GROUND:
(2) Start engine 2 and keep the engine RPM to idle (Ref. AMM TASK 71-00-00-860-827):- NO PERSONS GO WHERE THE AIRCRAFT CAN CAUSE THEM INJURY OR CAN KILL THEM
- NO OBJECTS STAY WHERE THE ENGINES CAN BLOW THEM AWAY OR WHERE THEY CAN BE PULLED INTO THE ENGINES BY SUCTION.
(a) In the cockpit, on AIR COND panel 30VU:
1 Make sure that the ENG 2 BLEED pushbutton-switch is released (the OFF legend is on).
2 Make sure that the APU BLEED pushbutton-switch is released (the ON legend is off).
3 Make sure that the X BLEED selector-switch is in the CLOSED position:
a Put a WARNING NOTICE(S) in position to tell persons not to operate the X BLEED selector-switch.
WARNING:
BE CAREFUL WHEN THE DUCTS ARE DISCONNECTED THE TEMPERATURE OF THE EXHAUST GASES FROM THE OPEN ENDS OF THE DISCONNECTED DUCTS CAN BE AS HIGH AS 270 DEG.C (518 DEG.F). THE HOT GASES CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(3) Remove the engine bleed-air duct as follows:(a) On the ECAM control panel, push the BLEED key:
1 On the SD, the BLEED page comes into view.
2 On the BLEED page, do a check of:
- The pressure value in the duct that reads the bleed pressure sensor
- The temperature value in the duct that reads the bleed temperature sensor.
1 Remove the bleed air duct from the PRV (4000HA1) of engine 1 (Ref. AMM TASK 36-11-49-000-827).
(4) Point the bleed-air joint duct away from the engine and the electrical cables or equipment.
NOTE: The open end of the bleed-air joint duct points in the direction where the hot bleed air is open freely to the atmosphere.
(5) Put a COVER - PROTECTION on the open end of the PRV (4000HA1).(6) Put the BLANKET - HEAT ISOLATION on the adjacent electrical cables and components.
Subtask 36-11-00-615-061-A
A. Cleaning of the Odor Smell in the Bleed-Air Ducting System
(1) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the pushed position (the OFF legend is off).
(b) Set the ENG 2 BLEED pushbutton-switch to the pushed position (the OFF legend is off).
(c) Set the X BLEED selector-switch to the OPEN position.
(2) On the ECAM control panel, push the BLEED key:
(a) On the SD, the BLEED page comes into view.
(b) The BLEED page shows that the X BLEED valve is OPEN.
(3) On the ECAM display, make sure that the engine bleed temperature is 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F):
(a) If necessary, slowly push the ENGINE-2 thrust lever to make the engine bleed temperature to 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F). Not reach more than 40% of N1.
(4) Wait for a minimum of 15 minutes.
(5) The ECAM control panel can show abnormal BLEED and pack fault messages.
(7) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the released position (the OFF legend is on).
(b) Set the ENG 2 BLEED pushbutton-switch to the released position (the OFF legend is on).
(c) Set the X BLEED selector-switch to the AUTO position.
(8) Stop engine 2 (Ref. AMM TASK 71-00-00-860-829).
5. Close-up(1) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the pushed position (the OFF legend is off).
(b) Set the ENG 2 BLEED pushbutton-switch to the pushed position (the OFF legend is off).
(c) Set the X BLEED selector-switch to the OPEN position.
(2) On the ECAM control panel, push the BLEED key:
(a) On the SD, the BLEED page comes into view.
(b) The BLEED page shows that the X BLEED valve is OPEN.
(3) On the ECAM display, make sure that the engine bleed temperature is 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F):
(a) If necessary, slowly push the ENGINE-2 thrust lever to make the engine bleed temperature to 200 -10 DEG.C or +10 DEG.C (392 -18 DEG.F or +18 DEG.F). Not reach more than 40% of N1.
(4) Wait for a minimum of 15 minutes.
(5) The ECAM control panel can show abnormal BLEED and pack fault messages.
NOTE: The system operates correctly and it is not necessary to do the related troubleshooting procedure at this step.
(6) Slowly pull ENGINE-2 thrust lever to the idle position. (7) In the cockpit, on AIR COND panel 30VU:
(a) Set the PACK 2 pushbutton-switch to the released position (the OFF legend is on).
(b) Set the ENG 2 BLEED pushbutton-switch to the released position (the OFF legend is on).
(c) Set the X BLEED selector-switch to the AUTO position.
(8) Stop engine 2 (Ref. AMM TASK 71-00-00-860-829).
Subtask 36-11-00-210-066-A
A. General Visual Inspection (GVI)
(1) Do a GVI of the core compartment (Ref. AMM TASK 05-24-50-210-801):
(a) Specially, examine the area/components near the exhaust plumes of the ECS interface duct.
(2) Do a GVI of the thrust reverser thermal-blanket (Ref. AMM TASK 78-32-62-210-801):
(a) Specially, examine the thermal blankets near the exhaust plumes of the ECS interface ducts.
Subtask 36-11-00-080-130-A (1) Do a GVI of the core compartment (Ref. AMM TASK 05-24-50-210-801):
(a) Specially, examine the area/components near the exhaust plumes of the ECS interface duct.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
(b) If you see contamination, use the manufacturer's instructions to clean them.(2) Do a GVI of the thrust reverser thermal-blanket (Ref. AMM TASK 78-32-62-210-801):
(a) Specially, examine the thermal blankets near the exhaust plumes of the ECS interface ducts.
B. Put the aircraft back to its initial configuration.
(2) Remove the COVER - PROTECTION from the open end of the PRV (4000HA1).
(3) Install the bleed air duct in the PRV (4000HA1) of engine 1 (Ref. AMM TASK 36-11-49-400-827).
(4) Connect the electrical connectors to the FCV as follows:
(a) Remove the CAP-BLANKING from each electrical connector and receptacle.
(5) Make sure that the work area is clean and clear of tools and other items.
Subtask 36-11-00-865-229-A WARNING:
ALWAYS USE APPLICABLE GLOVES TO TOUCH HOT PARTS. HOT PARTS CAN CAUSE INJURY TO PERSONS.
(1) Remove the BLANKET - HEAT ISOLATION from the adjacent electrical cables and components.(2) Remove the COVER - PROTECTION from the open end of the PRV (4000HA1).
(3) Install the bleed air duct in the PRV (4000HA1) of engine 1 (Ref. AMM TASK 36-11-49-400-827).
(4) Connect the electrical connectors to the FCV as follows:
(a) Remove the CAP-BLANKING from each electrical connector and receptacle.
CAUTION:
MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.
(b) (c) Install the removed access panel (Ref. AMM TASK 53-35-13-400-002).(5) Make sure that the work area is clean and clear of tools and other items.
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 36-11-00-790-079-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN A/115VAC | 53HH | W22 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN A/28VDC | 55HH | W21 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN B/28VDC | 56HH | Y21 |
| 122VU | AIR COND/TEMP CTL SYS 2/CHAN B/115VAC | 54HH | Y20 |
D. Leak Test
(1) Do a leak test of the bleed-air ducting system (Ref. AMM TASK 36-22-00-790-803):
(a) Make sure that there are no leaks.
Subtask 36-11-00-710-073-A (1) Do a leak test of the bleed-air ducting system (Ref. AMM TASK 36-22-00-790-803):
(a) Make sure that there are no leaks.
E. Operational Test
(1) Do an operational test of the bleed-air ducting system (Ref. AMM TASK 36-11-00-710-803).
(2) Do an operational test of the flow control and indicating system (Ref. AMM TASK 21-51-00-710-002).
Subtask 36-11-00-860-248-A (1) Do an operational test of the bleed-air ducting system (Ref. AMM TASK 36-11-00-710-803).
(2) Do an operational test of the flow control and indicating system (Ref. AMM TASK 21-51-00-710-002).
F. Aircraft Maintenance Configuration
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits supplied from the external power
(Ref. AMM TASK 24-41-00-862-002).
(4) Remove the WARNING NOTICE(S).
(5) Remove the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits supplied from the external power
(Ref. AMM TASK 24-41-00-862-002).
(4) Remove the WARNING NOTICE(S).
(5) Remove the 98F10103500000 CHOCK-MLG,ENGINE RUN-UP.