DOC AIRBUS | AMM A320FInstallation of the Avionics-Ventilation Skin Air-Inlet-Valve (Alternative Procedure)
TASK 21-26-52-400-001-A-01
Installation of the Avionics-Ventilation Skin Air-Inlet-Valve (Alternative Procedure)
This task is alternative and temporary and it must be used when the cure time is not sufficient before the aircraft dispatch.
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 21-26-52-860-052-A
Subtask 21-26-52-420-053-A
Subtask 21-26-52-010-057-A
[Rev.10 from 2021]
2026.04.02 06:11:08 UTC
Installation of the Avionics-Ventilation Skin Air-Inlet-Valve (Alternative Procedure)
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
1. Reason for the JobThis task is alternative and temporary and it must be used when the cure time is not sufficient before the aircraft dispatch.
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.05RAB9) | Adhesive Film Tape-- Aluminium Foil - |
| (Material No.06AEB2) | Polysulfide Sealant-Low Adhesion Fillet Structure |
| (Material No.14DAB1) | Release Agent-- Water Base - |
| 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 21-26-52-000-001-A | Removal of the Avionics-Ventilation Skin Air-Inlet-Valve |
| TASK 21-26-52-400-001-A | Installation of the Avionics-Ventilation Skin Air-Inlet-Valve |
| TASK 21-26-52-400-001-A-01 | Installation of the Avionics-Ventilation Skin Air-Inlet-Valve (Alternative Procedure) |
| 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 21-26-52-860-052-A
A. Aircraft Maintenance Configuration
(1) Make sure that the aircraft electrical circuits are energized
(Ref. AMM TASK 24-41-00-861-002).
Subtask 21-26-52-865-056-A (1) Make sure that the aircraft electrical circuits are energized
(Ref. AMM TASK 24-41-00-861-002).
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 21-26-52-010-056-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 21-26-52-420-053-A
A. Installation of the Avionics-Ventilation Skin Air-Inlet-Valve (Alternative Procedure)
(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).
(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) 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:
(a) 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.
(14) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(15) Apply the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to prevent damage to the sealant:
1 Apply Release Agent-- Water Base - (Material No.14DAB1) on the sealant. This helps to remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) after the sealant cure time.
2 Put an applicable length strip of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) along the edge of the valve (4) and the aircraft structure.
3 Put the overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the valve (4) to make sure that the surface is smooth. The minimum overlap length of the applied Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is 25 mm (1 in.).
4 Make sure that there is no Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) on:
(16) Do a visual inspection of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight:
(a) If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
1 Make sure that the sealant is in the correct condition (no damage and no missing part):
a If the sealant is damaged, remove the skin air-inlet valve (Ref. AMM TASK 21-26-52-000-001) and install it again (Ref. AMM TASK 21-26-52-400-001) or (Ref. AMM TASK 21-26-52-400-001).
b If the sealant is not damaged, replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (refer to step (15)).
(17) Do the visual inspection of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight until you can keep the aircraft on the ground to obey the material manufacturer's instructions. These instructions are necessary for the sealant to fully cure:
(a) Remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
(b) Let the sealant cure as given in the manufacturer's instructions.
Subtask 21-26-52-865-057-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).
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.
NOTE: During the flight, temperature is less than 10 DEG.C (50 DEG.F) because of this the sealants do not dry. The sealant cure time given in the technical data sheet does not include flight hours.
(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) 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:
(a) 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.
(14) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
(15) Apply the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to prevent damage to the sealant:
CAUTION:
BEFORE YOU APPLY THE TAPE, MAKE SURE THAT THE SEALANT IS NOT TACKY. IF IT IS TACKY, THE TAPE CAN CAUSE DAMAGE TO THE SEALANT.
(a) Apply the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to the space between the valve (4) and the aircraft structure. If the sealant is no more tacky, do the steps that follow:1 Apply Release Agent-- Water Base - (Material No.14DAB1) on the sealant. This helps to remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) after the sealant cure time.
2 Put an applicable length strip of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) along the edge of the valve (4) and the aircraft structure.
3 Put the overlap strips of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) around the valve (4) to make sure that the surface is smooth. The minimum overlap length of the applied Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is 25 mm (1 in.).
4 Make sure that there is no Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) on:
- The valve section of the assembly
- The fillet seal around the valve section.
(16) Do a visual inspection of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight:
(a) If the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) is damaged, then:
1 Make sure that the sealant is in the correct condition (no damage and no missing part):
a If the sealant is damaged, remove the skin air-inlet valve (Ref. AMM TASK 21-26-52-000-001) and install it again (Ref. AMM TASK 21-26-52-400-001) or (Ref. AMM TASK 21-26-52-400-001).
b If the sealant is not damaged, replace the damaged Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) (refer to step (15)).
(17) Do the visual inspection of the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) before each flight until you can keep the aircraft on the ground to obey the material manufacturer's instructions. These instructions are necessary for the sealant to fully cure:
(a) Remove the Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) .
(b) Let the sealant cure as given in the manufacturer's instructions.
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 21-26-52-710-052-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 Centralized Fault Display System (CFDS).
Subtask 21-26-52-010-057-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 21-26-52-862-053-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the access platform(s).