DOC AIRBUS | AMM A320FInstallation of the Avionics-Ventilation Skin Air-Inlet-Valve
TASK 21-26-52-400-001-A
Installation of the Avionics-Ventilation Skin Air-Inlet-Valve
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 21-26-52-860-050-A Subtask 21-26-52-865-051-A
Subtask 21-26-52-420-051-A
Subtask 21-26-52-010-052-A
[Rev.10 from 2021]
2026.04.02 06:11:07 UTC
Installation of the Avionics-Ventilation Skin Air-Inlet-Valve
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.06AEB2) | Polysulfide Sealant-Low Adhesion Fillet Structure |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 127 | REAR AVIONIC COMPARTMENT |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 5 | O-RING | AIPC 21-26-01-11-020 |
| 5 | O-RING | AIPC 21-26-81-11-030 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 20-28-00-912-803-A | Bonding Surface Preparation |
| TASK 21-26-00-710-001-A | Operational Check of the Avionics Equipment Ventilation-System via MCDU |
| TASK 21-26-00-710-001-A-01 | Operational Check of the Avionics Equipment Ventilation (without the CFDS) |
| 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) |
Skin Air-Inlet ValveSubtask 21-26-52-860-050-A Subtask 21-26-52-865-051-A
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 21-26-52-010-051-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | AIR COND/AVNCS VENT/CTL | 6HQ | D06 |
| 49VU | AIR COND/AVNCS VENT/CTL | 5HQ | D05 |
| 122VU | AIR COND/AVNCS/VENT/MONG | 3HQ | Y17 |
C. Get Access
(1) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position on the left side of the aircraft below the valve.
4. Procedure(1) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position on the left side of the aircraft below the valve.
Subtask 21-26-52-420-051-A
A. Installation of the Avionics-Ventilation Skin Air-Inlet-Valve
(1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Clean the component interfaces and the adjacent area.
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(5) Make sure that the deactivation switch of the valve (4) is in the ON position.
(6) Remove the blanking plug from the air inlet.
(7) Apply Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) to the mating surfaces of the structure (1) and the valve (4):
(a) Make sure that you also apply Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) on the peripheral clearance between the edge of the valve (4) and the aircraft structure:
1 It is necessary to fully fill the space around the valve between the aircraft structure and the valve. To do this, you must apply a sufficient quantity of sealant before you install the valve.
(9) Remove the CAP-BLANKING from each electrical connector and receptacle.
(11) Install the valve (4) in position on the structure (1).
(12) Install the six screws (2) and the four screws (3) and tighten them.
(13) Use a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to remove the unwanted Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) and make the surface smooth.
(14) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
Subtask 21-26-52-865-052-A (1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Clean the component interfaces and the adjacent area.
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(5) Make sure that the deactivation switch of the valve (4) is in the ON position.
(6) Remove the blanking plug from the air inlet.
(7) Apply Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) to the mating surfaces of the structure (1) and the valve (4):
(a) Make sure that you also apply Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) on the peripheral clearance between the edge of the valve (4) and the aircraft structure:
1 It is necessary to fully fill the space around the valve between the aircraft structure and the valve. To do this, you must apply a sufficient quantity of sealant before you install the valve.
NOTE: Airbus recommends you to apply a new sealant. It is not necessary to wait for the sealant to cure before you install the skin air-inlet valve.
NOTE: Airbus recommends that the sealant is not tacky at the aircraft dispatch. The technical data sheet of the sealant gives the instructions about the time you can wait until the sealant is no more tacky.
(8) Install a new AIPC 21-26-01-11-020 O-RING (5) or AIPC 21-26-81-11-030 O-RING (5) in the groove of the valve (4). (9) 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.
(10) Connect the electrical connector (6). (11) Install the valve (4) in position on the structure (1).
(12) Install the six screws (2) and the four screws (3) and tighten them.
(13) Use a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to remove the unwanted Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) and make the surface smooth.
(14) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 21-26-52-710-050-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | AIR COND/AVNCS VENT/CTL | 6HQ | D06 |
| 49VU | AIR COND/AVNCS VENT/CTL | 5HQ | D05 |
| 122VU | AIR COND/AVNCS/VENT/MONG | 3HQ | Y17 |
C. Do an operational test of the ventilation system of the avionics equipment. (Ref. AMM TASK 21-26-00-710-001)
5. Close-upNOTE: As an alternative procedure, you can do this operational test without the CFDS.
Subtask 21-26-52-010-052-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the access platform(s).
Subtask 21-26-52-862-051-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the access platform(s).