DOC AIRBUS | AMM A320FInstallation of the Outflow Valve (From Inside)
TASK 21-31-51-400-001-A
Installation of the Outflow Valve (From Inside)
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Expendable Parts
D. Referenced Information
3. Job Set-up
Subtask 21-31-51-860-055-A
Subtask 21-31-51-420-050-D ** ON A/C NOT FOR ALL
Subtask 21-31-51-410-055-A
[Rev.10 from 2021]
2026.04.02 06:11:15 UTC
Installation of the Outflow Valve (From Inside)
WARNING:
MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE.
HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
FIN: 10HL
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 2M (6 FT) |
| No specific | AR | GAGE - FEELER |
| No specific | Torque wrench: range to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in )  |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 162CW, 826 |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 6 | GASKET | AIPC 21-31-04-08-020 |
| 6 | GASKET | AIPC 21-31-84-01-210 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 21-31-00-710-002-A | Operational Test of the Pressure Control and Monitoring |
| TASK 21-31-00-710-003-A | Operational Test of Manual Mode Selection and Manual Mode Pressure Control and Functional Test of Manual Mode Cabin Altitude/Outflow Valve Position Indication |
| 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 25-55-12-000-003-A | Removal of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65 |
| TASK 25-55-12-400-003-A | Installation of the Sidewall Panels in the Aft Cargo Compartment - FR59/FR65 |
| TASK 52-30-00-860-001-A | Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
| TASK 52-30-00-860-002-A | Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
Outflow Valve 10HLSubtask 21-31-51-860-055-A
A. Aircraft Maintenance Configuration
(1) Make sure that:
(a) The aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
(b) The ACCESS PLATFORM 2M (6 FT) is in position below the outflow valve area in zone 172.
(c) The AFT cargo-compartment door 826 is open (Ref. AMM TASK 52-30-00-860-001).
(d) The ACCESS PLATFORM 2M (6 FT) is in position at the AFT cargo-compartment door 826.
(e) The access panel 162CW is removed (Ref. AMM TASK 25-55-12-000-003).
Subtask 21-31-51-865-079-A (1) Make sure that:
(a) The aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
(b) The ACCESS PLATFORM 2M (6 FT) is in position below the outflow valve area in zone 172.
(c) The AFT cargo-compartment door 826 is open (Ref. AMM TASK 52-30-00-860-001).
(d) The ACCESS PLATFORM 2M (6 FT) is in position at the AFT cargo-compartment door 826.
(e) The access panel 162CW is removed (Ref. AMM TASK 25-55-12-000-003).
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | AIR COND/CAB/PRESS/CTL1 | 1HL | D09 |
| ** ON A/C NOT FOR ALL | |||
| 122VU | AIR COND/AFT CARGO VENT/FAN | 30HN | S22 |
| ** ON A/C ALL | |||
| 122VU | AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/SPLY | 6HU | U19 |
| 122VU | AIR COND/CAB PRESS/CTL/MAN | 3HL | Y23 |
| 122VU | AIR COND/CAB PRESS/CTL/2 | 2HL | Y22 |
Subtask 21-31-51-420-050-D ** ON A/C NOT FOR ALL
A. Installation of the Outflow Valve
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Put the gasket (6) in position on the outflow valve (5).
(a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(7) Carefully put the outflow valve (5) and the gasket (6) in position.
(8) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(9) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in ).
(10) Use a GAGE - FEELER and measure the gap between the support brackets (25) and the attachment-lugs of the gearbox assembly.
(11) Use as necessary a mixture of washer(s) (24) to close the gap.
(13) Tighten the bolts (22) (Ref. AMM TASK 20-28-00-912-802).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
(16) Make sure that all the electrical connections are clean and in the correct condition.
(17) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(18) Make sure that the work area is clean and clear of tools and other items.
Subtask 21-31-51-420-050-H ** ON A/C NOT FOR ALL WARNING:
SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
(1) Make sure that there is no blanking plug installed in the static port of the outflow valve electronic boxes. (2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Put the gasket (6) in position on the outflow valve (5).
(a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(7) Carefully put the outflow valve (5) and the gasket (6) in position.
NOTE: The outflow valve weighs approx. 12.5 kg (27.5578 lb).
The actuator side of the outflow valve must point to the bottom of the aircraft.
(a) Make sure that the location pins (8) are in the correct position in the outflow valve support-structure. The actuator side of the outflow valve must point to the bottom of the aircraft.
(8) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(9) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in )
. (10) Use a GAGE - FEELER and measure the gap between the support brackets (25) and the attachment-lugs of the gearbox assembly.
(11) Use as necessary a mixture of washer(s) (24) to close the gap.
NOTE: The maximum gap limit is 0.00 +0.35 mm or -0.35 mm (0.0000 +0.0138 in. or -0.0138 in.).
(12) Install the bolts (22) and the washers (21) in the support brackets (25). (13) Tighten the bolts (22) (Ref. AMM TASK 20-28-00-912-802).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
NOTE: This step is only applicable for outflow valves P/N 9023-15703-81 and previous.
(b) Put the bonding strap (4) in position on the outflow valve (5). Install the washer (28) and the bolt (27) (Ref. AMM TASK 20-28-00-912-802). NOTE: This step is only applicable for outflow valve P/N 20790-01AA and subsequent.
(15) Remove the blanking caps from the disconnected electrical connectors. (16) Make sure that all the electrical connections are clean and in the correct condition.
(17) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(18) Make sure that the work area is clean and clear of tools and other items.
A. Installation of the Outflow Valve
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6) or AIPC 21-31-84-01-210 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Loosen the nuts (20).
(a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(8) Carefully put the outflow valve (5) and the gasket (6) in position.
(9) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(10) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in ).
(11) Install the bolts (22) and the washers (21) in the support brackets (25).
(12) Tighten the bolts (22).
(13) Tighten the nuts (20).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
(16) Put the grill (9) in position in the retaining clips (10) and install the quick release fasteners (12).
(17) Remove the bolt (30) and the washer (31).
(18) Put the bonding straps (4) and (11) in position and install the washer (31) and the bolt (30) (Ref. AMM TASK 20-28-00-912-802).
(19) Remove the blanking caps from the disconnected electrical connectors.
(20) Make sure that all the electrical connections are clean and in the correct condition.
(21) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(22) Make sure that the work area is clean and clear of tools and other items.
Subtask 21-31-51-420-050-I ** ON A/C NOT FOR ALL WARNING:
SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
(1) Make sure that there is no blanking plug installed in the static port of the outflow valve electronic boxes. (2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6) or AIPC 21-31-84-01-210 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Loosen the nuts (20).
NOTE: Only loosen the nuts sufficiently to allow the support brackets (25) to move up or down.
(7) Put the gasket (6) in position on the outflow valve (5). (a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(8) Carefully put the outflow valve (5) and the gasket (6) in position.
NOTE: The outflow valve weighs approx. 12.5 kg (27.5578 lb).
The actuator side of the outflow valve must point to the bottom of the aircraft.
(a) Make sure that the location pins (8) are in the correct position in the outflow valve support-structure. The actuator side of the outflow valve must point to the bottom of the aircraft.
(9) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(10) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in )
. (11) Install the bolts (22) and the washers (21) in the support brackets (25).
(12) Tighten the bolts (22).
(13) Tighten the nuts (20).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
NOTE: This step is only applicable for outflow valves P/N 9023-15703-81 and previous.
(b) Put the bonding strap (4) in position on the outflow valve (5). Install the washer (28) and the bolt (27) (Ref. AMM TASK 20-28-00-912-802). NOTE: This step is only applicable for outflow valve P/N 20790-01AA and subsequent.
(15) Put the bonding strap (4) in position and temporarily install the washer (31) and the bolt (30). (16) Put the grill (9) in position in the retaining clips (10) and install the quick release fasteners (12).
(17) Remove the bolt (30) and the washer (31).
(18) Put the bonding straps (4) and (11) in position and install the washer (31) and the bolt (30) (Ref. AMM TASK 20-28-00-912-802).
(19) Remove the blanking caps from the disconnected electrical connectors.
(20) Make sure that all the electrical connections are clean and in the correct condition.
(21) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(22) Make sure that the work area is clean and clear of tools and other items.
A. Installation of the Outflow Valve
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Loosen the nuts (20).
(a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(8) Carefully put the outflow valve (5) and the gasket (6) in position.
(9) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(10) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in ).
(11) Install the bolts (22) and the washers (21) in the support brackets (25).
(12) Tighten the bolts (22).
(13) Tighten the nuts (20).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
(16) Make sure that all the electrical connections are clean and in the correct condition.
(17) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(18) Make sure that the work area is clean and clear of tools and other items.
Subtask 21-31-51-865-100-A WARNING:
SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
(1) Make sure that there is no blanking plug installed in the static port of the outflow valve electronic boxes. (2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Clean the component interfaces and the adjacent area.
(4) Make sure that the gasket (6) is in a good condition. If necessary, replace the AIPC 21-31-04-08-020 GASKET (6).
(5) Make sure that the joining faces of the outflow valve (5) and the aircraft structure are free from grease and sealants.
(6) Loosen the nuts (20).
NOTE: Only loosen the nuts sufficiently to allow the support brackets (25) to move up or down.
(7) Put the gasket (6) in position on the outflow valve (5). (a) Make sure that the gasket location tab is on the forward, actuator side of the outflow valve.
(8) Carefully put the outflow valve (5) and the gasket (6) in position.
NOTE: The outflow valve weighs approx. 12.5 kg (27.5578 lb).
The actuator side of the outflow valve must point to the bottom of the aircraft.
(a) Make sure that the location pins (8) are in the correct position in the outflow valve support-structure. The actuator side of the outflow valve must point to the bottom of the aircraft.
(9) Install the outflow valve attach-screws (7) from the outside of the aircraft as identified in the removal procedure.
(10) TORQUE in sequence (refer to sequence chart) the screws (7) to between 0.55 and 0.45 m.daN (48.67 and 39.82 lbf.in )
. (11) Install the bolts (22) and the washers (21) in the support brackets (25).
(12) Tighten the bolts (22).
(13) Tighten the nuts (20).
(14) Bonding strap installation:
(a) Put the bonding strap (4) in position on the outflow valve (5). Install the washers (28), the bolt (27) and the nut (29) (Ref. AMM TASK 20-28-00-912-802).
NOTE: This step is only applicable for outflow valves P/N 9023-15703-81 and previous.
(b) Put the bonding strap (4) in position on the outflow valve (5). Install the washer (28) and the bolt (27) (Ref. AMM TASK 20-28-00-912-802). NOTE: This step is only applicable for outflow valve P/N 20790-01AA and subsequent.
(15) Remove the blanking caps from the disconnected electrical connectors. (16) Make sure that all the electrical connections are clean and in the correct condition.
(17) Connect the electrical connectors (1) 10HL-B, (3) 10HL-A, (23) 10HL-E, (26) 10HL-D and (2) 10HL-C in that order.
(18) Make sure that the work area is clean and clear of tools and other items.
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 21-31-51-865-116-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | AIR COND/CAB/PRESS/CTL1 | 1HL | D09 |
| ** ON A/C NOT FOR ALL | |||
| 122VU | AIR COND/AFT CARGO VENT/FAN | 30HN | S22 |
| ** ON A/C ALL | |||
| 122VU | AIR COND/LAV/GALLEY VENT CTL/EXTRACT FAN/SPLY | 6HU | U19 |
| 122VU | AIR COND/CAB PRESS/CTL/MAN | 3HL | Y23 |
| 122VU | AIR COND/CAB PRESS/CTL/2 | 2HL | Y22 |
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 21-31-51-710-050-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 122VU | RPCU | 4HL | X23 |
D. Test the Pressure Control and Monitoring System
(2) Do the operational test of the manual pressure control and monitoring system (Ref. AMM TASK 21-31-00-710-003).
5. Close-upNOTE: The Operational Test of the Pressure Control and Monitoring System must be performed on both system channels. Ensure that TEST OK or a failure message is displayed. If the test is interrupted it must be restarted until TEST OK or failure message is displayed.
(1) Do the operational test of the pressure control and monitoring system (Ref. AMM TASK 21-31-00-710-002). (2) Do the operational test of the manual pressure control and monitoring system (Ref. AMM TASK 21-31-00-710-003).
Subtask 21-31-51-410-055-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the access panel 162CW (Ref. AMM TASK 25-55-12-400-003).
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).
(5) Close the AFT cargo-compartment door 826 (Ref. AMM TASK 52-30-00-860-002).
Subtask 21-31-51-862-051-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the access panel 162CW (Ref. AMM TASK 25-55-12-400-003).
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).
(5) Close the AFT cargo-compartment door 826 (Ref. AMM TASK 52-30-00-860-002).