DOC AIRBUS | AMM A320FInstallation of the APU Compartment Overpressure Release Door
TASK 52-92-11-400-001-A
Installation of the APU Compartment Overpressure Release Door
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 52-92-11-860-051-A
Subtask 52-92-11-420-050-A
Subtask 52-92-11-410-050-A
[Rev.10 from 2021]
2026.04.02 06:28:39 UTC
Installation of the APU Compartment Overpressure Release Door
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 | SPRING BALANCE 20 DAN (48 LBF) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.12ABE2) | Corrosion Preventive Compound-Water Displacing Oily Film System |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 316AR |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 10 | COTTER PIN | AIPC 52-92-04-01-060 |
| 15 | COTTER PIN | AIPC 52-92-04-01-060 |
| 9 | COTTER PIN | AIPC 52-92-04-01-060 |
| 10 | COTTER PIN | AIPC 52-92-84-01-010 |
| 9 | COTTER PIN | AIPC 52-92-84-01-010 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 51-75-13-916-001-A | Repair to a layer of Moisture-Removing Oil |
| TASK 52-41-00-410-001-A | Close the APU Doors after Access |
APU Compartment Overpressure Release DoorSubtask 52-92-11-860-051-A
A. Aircraft Maintenance Configuration
Subtask 52-92-11-865-051-A B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 52-92-11-910-050-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | APU/APU/CTL | 2KD | L42 |
| 121VU | APU/ECB/SPLY | 1KD | L41 |
C. Preparation for Installation
(1) Clean the component interfaces and the adjacent area.
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Make sure that the parts retained from the removed component are clean and in the correct condition.
(4) Assemble the spring linkage as follows:
(a) Put the connection link (13) into the spring fitting (16) and connect them with the pin (5).
(b) Safety the pin (5) with the washer (14) and the new AIPC 52-92-04-01-060 COTTER PIN (15).
(c) Assemble the springs (6) on the spring fitting (16) and the spring retainer (3).
4. Procedure(1) Clean the component interfaces and the adjacent area.
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Make sure that the parts retained from the removed component are clean and in the correct condition.
(4) Assemble the spring linkage as follows:
(a) Put the connection link (13) into the spring fitting (16) and connect them with the pin (5).
(b) Safety the pin (5) with the washer (14) and the new AIPC 52-92-04-01-060 COTTER PIN (15).
(c) Assemble the springs (6) on the spring fitting (16) and the spring retainer (3).
Subtask 52-92-11-420-050-A
A. Installation of the Overpressure Release Door
(1) Install the overpressure release door (18) on the fuselage as follows:
(a) Put the overpressure release door (18) into the fuselage opening and so that the door bracket (19) touches the fuselage hinge fitting (20).
(b) Make sure that the gap "X" around the overpressure release door (18) and the fuselage opening is within the tolerance.
(c) Connect the fuselage hinge fitting (20) and the door bracket (19) with the screws (22) and the washers (21).
(2) Connect the connection link (13) to the overpressure release door (18) as follows:
(a) Put the connection link (13) in position to the door bracket (12) and install the pin (7).
(b) Safety the pin (7) with the washer (8) and the new AIPC 52-92-04-01-060 COTTER PIN (9) or AIPC 52-92-84-01-010 COTTER PIN (9).
(c) Put the spring fitting (16) into the structure bracket (17) and install the pin (4).
(d) Safety the pin (4) with the washer (11) and the new AIPC 52-92-04-01-060 COTTER PIN (10) or AIPC 52-92-84-01-010 COTTER PIN (10) .
(3) Install the bonding strap (27) with the bolt (26), the washer (24) and the nut (23) on the bonding angle (25) of the door bracket (19) (Ref. AMM TASK 20-28-00-912-802).
(4) Put the spring retainer (3) into the support bracket (23) and install the washer (2) and the nut (1).
Subtask 52-92-11-820-050-A (1) Install the overpressure release door (18) on the fuselage as follows:
(a) Put the overpressure release door (18) into the fuselage opening and so that the door bracket (19) touches the fuselage hinge fitting (20).
(b) Make sure that the gap "X" around the overpressure release door (18) and the fuselage opening is within the tolerance.
(c) Connect the fuselage hinge fitting (20) and the door bracket (19) with the screws (22) and the washers (21).
(2) Connect the connection link (13) to the overpressure release door (18) as follows:
(a) Put the connection link (13) in position to the door bracket (12) and install the pin (7).
(b) Safety the pin (7) with the washer (8) and the new AIPC 52-92-04-01-060 COTTER PIN (9) or AIPC 52-92-84-01-010 COTTER PIN (9).
(c) Put the spring fitting (16) into the structure bracket (17) and install the pin (4).
(d) Safety the pin (4) with the washer (11) and the new AIPC 52-92-04-01-060 COTTER PIN (10) or AIPC 52-92-84-01-010 COTTER PIN (10) .
(3) Install the bonding strap (27) with the bolt (26), the washer (24) and the nut (23) on the bonding angle (25) of the door bracket (19) (Ref. AMM TASK 20-28-00-912-802).
(4) Put the spring retainer (3) into the support bracket (23) and install the washer (2) and the nut (1).
B. Adjustment Procedure
(1) Make sure that the gap "X" around the overpressure release door (18) and the fuselage opening is correct.
(2) If the gap "X" is out of tolerance, loosen the screws (22) and adjust the overpressure release door (18) as required.
(3) Attach a SPRING BALANCE 20 DAN (48 LBF) on the overpressure release door (18) and measure the force necessary to open it.
5. Close-up(1) Make sure that the gap "X" around the overpressure release door (18) and the fuselage opening is correct.
(2) If the gap "X" is out of tolerance, loosen the screws (22) and adjust the overpressure release door (18) as required.
(3) Attach a SPRING BALANCE 20 DAN (48 LBF) on the overpressure release door (18) and measure the force necessary to open it.
NOTE: The operation force must be between 11.2 daN (25.1786 lbf) and 12.2 daN (27.4267 lbf).
(4) If the operation force is out of tolerance, turn the nut (1) as required untill the operation force is correct. Subtask 52-92-11-410-050-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Apply a layer of Corrosion Preventive Compound-Water Displacing Oily Film System (Material No.12ABE2) to the installed components (Ref. AMM TASK 51-75-13-916-001).
(3) Close the APU access doors 316AR and 316AR (Ref. AMM TASK 52-41-00-410-001).
(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).
Subtask 52-92-11-865-052-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Apply a layer of Corrosion Preventive Compound-Water Displacing Oily Film System (Material No.12ABE2) to the installed components (Ref. AMM TASK 51-75-13-916-001).
(3) Close the APU access doors 316AR and 316AR (Ref. AMM TASK 52-41-00-410-001).
(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).