DOC AIRBUS | AMM A320FInstallation of the Lateral Left Avionics-Compartment-Door
TASK 52-41-12-400-001-A
Installation of the Lateral Left Avionics-Compartment-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 52-41-12-860-050-A
Subtask 52-41-12-420-050-A ** ON A/C NOT FOR ALL
Subtask 52-41-12-865-052-A
[Rev.10 from 2021]
2026.04.02 06:28:14 UTC
Installation of the Lateral Left Avionics-Compartment-Door
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
CAUTION:
THIS PART IS A REMOVABLE STRUCTURAL COMPONENT (RSC), WHICH CAN BE MOVED BETWEEN AIRCRAFT. THUS IT CAN HAVE DIFFERENT OPERATION CONDITIONS AND A DIFFERENT LIFE RECORD (FLIGHT HOURS/FLIGHT CYCLES/CALENDAR) FROM THE AIRCRAFT IT IS INSTALLED ON OR REMOVED FROM. THE OPERATOR IS RESPONSIBLE FOR THE SPECIFIC TRACKING AND CONTINUED AIRWORTHINESS OF REMOVABLE STRUCTURAL COMPONENTS. INCORRECT MAINTENANCE OF THESE COMPONENTS CAN CAUSE A RISK FOR THE FLIGHT SAFETY.
ZONE: 125
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03GBB1) | Synthetic Oil base Grease-General Purpose Clay Thickened - |
| (Material No.03JAB1) | Silicone base Grease-- Paste - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 125 | LATERAL AVIONIC COMPARTMENT |
| 812 |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 2 | COTTER PINS | AIPC 52-41-01-02-030 |
| 2 | COTTER PINS | AIPC 52-41-81-02-030 |
| 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 52-71-00-710-001-A | Operational Test of the Door Warning System |
Lateral Left Avionics-Compartment-DoorSubtask 52-41-12-860-050-A
A. Aircraft Maintenance Configuration
(1) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position at zone 125.
Subtask 52-41-12-865-051-A (1) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position at zone 125.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
Subtask 52-41-12-916-050-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | EIS/SDAC1 AND 2/DOOR/DET/AVNCS | 46WV | P02 |
C. Preparation for Installation
(1) Clean the area of the aircraft structure where it touches the door seal with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Apply Silicone base Grease-- Paste - (Material No.03JAB1) on the surface of the door seal that touches the aircraft structure.
Subtask 52-41-12-916-050-B ** ON A/C NOT FOR ALL (1) Clean the area of the aircraft structure where it touches the door seal with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Apply Silicone base Grease-- Paste - (Material No.03JAB1) on the surface of the door seal that touches the aircraft structure.
C. Preparation for Installation
(1) Clean the area of the aircraft structure where it touches the door seal with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Apply Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) on the surface of the door seal that touches the aircraft structure.
4. Procedure(1) Clean the area of the aircraft structure where it touches the door seal with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Apply Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) on the surface of the door seal that touches the aircraft structure.
Subtask 52-41-12-420-050-A ** ON A/C NOT FOR ALL
A. Installation of the Lateral Left Avionics-Compartment-Door
(1) Install the bushes (5), (9) and (11).
(2) Put the door (1) in position on the aircraft structure and install the bolts (10), the washers (4) and the nuts (3).
(3) Tighten the nuts (3).
(4) Safety the nuts (3) with the new AIPC 52-41-01-02-030 COTTER PINS (2) or the new AIPC 52-41-81-02-030 COTTER PINS (2).
(5) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(6) Install the bonding leads (6), the washers (7) and the screws (8).
(7) Tighten the screws (8).
(8) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
Subtask 52-41-12-420-050-B ** ON A/C NOT FOR ALL (1) Install the bushes (5), (9) and (11).
(2) Put the door (1) in position on the aircraft structure and install the bolts (10), the washers (4) and the nuts (3).
(3) Tighten the nuts (3).
(4) Safety the nuts (3) with the new AIPC 52-41-01-02-030 COTTER PINS (2) or the new AIPC 52-41-81-02-030 COTTER PINS (2).
(5) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(6) Install the bonding leads (6), the washers (7) and the screws (8).
(7) Tighten the screws (8).
(8) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
A. Installation of the Lateral Left Avionics-Compartment-Door
(1) Install the bushes (6), (10) and (12).
(2) Put the door (1) in position on the aircraft structure and install the bolts (11) and the washers (5).
(3) Install the nuts (3).
(4) If you cannot safety the nuts (3) with the cotter pins (2):
(a) Remove the applicable nut(s) (3).
(b) Install the related washer(s):
1 If necessary, install a set of two washers (4).
2 Make sure that the thickness of the washers (4) is maximum 1.6 mm (0.06 in.).
(c) Install the nut(s) (3).
(5) TORQUE the nuts (3) to between 13.8 and 10.6 m.N (122.12 and 93.81 lbf.in )
.
(6) Safety the nuts (3) with the new AIPC 52-41-81-02-030 COTTER PINS (2).
(7) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(8) Install the bonding leads (7), the washers (8) and the screws (9).
(9) Tighten the screws (9).
(10) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
Subtask 52-41-12-220-054-A ** ON A/C NOT FOR ALL (1) Install the bushes (6), (10) and (12).
(2) Put the door (1) in position on the aircraft structure and install the bolts (11) and the washers (5).
(3) Install the nuts (3).
(4) If you cannot safety the nuts (3) with the cotter pins (2):
(a) Remove the applicable nut(s) (3).
(b) Install the related washer(s):
1 If necessary, install a set of two washers (4).
2 Make sure that the thickness of the washers (4) is maximum 1.6 mm (0.06 in.).
(c) Install the nut(s) (3).
(5) TORQUE the nuts (3) to between 13.8 and 10.6 m.N (122.12 and 93.81 lbf.in )
.(6) Safety the nuts (3) with the new AIPC 52-41-81-02-030 COTTER PINS (2).
(7) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(8) Install the bonding leads (7), the washers (8) and the screws (9).
(9) Tighten the screws (9).
(10) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802).
B. Check of Clearances
(1) Close the door (1).
(2) Measure clearance J2 between the door stops and the door fittings.
(3) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(4) If clearance J2 is not in the tolerance:
(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1).
(e) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(f) TORQUE the self-locking nuts (4) to between 4.5 and 3.5 m.N (39.82 and 30.97 lbf.in ).
(5) Measure peripheral clearance J3 and out-of-flush dimension J1:
(a) Make sure that out-of-flush dimension J1 between the door (1) and the fuselage is 0 -0.8 mm or +0.8 mm (0 -0.03 in. or +0.03 in.).
(a) Peripheral clearance J3 and out-of-flush dimension J1 are not out of tolerance at the same point.
(b) There are no more than four points with the maximum tolerance of peripheral clearance J3 and out-of-flush dimension J1.
(7) If the condition(s) from step (6) is(are) not obeyed, replace the door (1).
(8) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
Subtask 52-41-12-220-051-A ** ON A/C NOT FOR ALL (1) Close the door (1).
(2) Measure clearance J2 between the door stops and the door fittings.
(3) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(4) If clearance J2 is not in the tolerance:
(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1).
(e) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(f) TORQUE the self-locking nuts (4) to between 4.5 and 3.5 m.N (39.82 and 30.97 lbf.in )
.(5) Measure peripheral clearance J3 and out-of-flush dimension J1:
(a) Make sure that out-of-flush dimension J1 between the door (1) and the fuselage is 0 -0.8 mm or +0.8 mm (0 -0.03 in. or +0.03 in.).
NOTE: A maximum tolerance of 0 -1.2 mm or +0.8 mm (0 -0.05 in. or +0.03 in.) is permitted for out-of-flush dimension J1 at points 1 thru 5.
NOTE: A maximum tolerance of 0 -0.8 mm or +1.2 mm (0 -0.03 in. or +0.05 in.) is permitted for out-of-flush dimension J1 at points 9 thru 12.
NOTE: A maximum tolerance of 0 -1.2 mm or +1.2 mm (0 -0.05 in. or +0.05 in.) is permitted for out-of-flush dimension J1 at points 6, 7, 8, 13 and 14.
(b) Make sure that peripheral clearance J3 between the door (1) and the fuselage is 2 -1 mm or +1 mm (0.08 -0.04 in. or +0.04 in.).NOTE: A maximum tolerance of 2 -1.5 mm or +1.5 mm (0.08 -0.06 in. or +0.06 in.) is permitted for peripheral clearance J3 at points 1 thru 14.
(6) Make sure that:(a) Peripheral clearance J3 and out-of-flush dimension J1 are not out of tolerance at the same point.
(b) There are no more than four points with the maximum tolerance of peripheral clearance J3 and out-of-flush dimension J1.
(7) If the condition(s) from step (6) is(are) not obeyed, replace the door (1).
(8) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
C. Check and Adjustment of the Out-of-flush Dimension and Seal Compression
(1) Close the door (1) and measure clearance J2 between the door stops and the stop fittings.
(2) Make sure that clearance J2 is a minimum of 0.2 mm (0.0079 in.).
(3) Measure out-of-flush dimension J1 between the door (1) and the fuselage at points P1 and P2.
(4) Calculate final out-of-flush dimension J at points P1 and P2 as follows:
J= J1+J2.
(5) Make sure that out-of-flush dimension J is 0 -0.8 mm or +0.8 mm (0.0000 -0.0315 in. or +0.0315 in.).
(6) If out-of-flush dimension J is not in the tolerance:
(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1) and make sure that clearance J2 is a minumum of 0.2 mm (0.0079 in.).
(e) Tighten the self-locking nuts (4).
(f) Close the door (1).
(7) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
Subtask 52-41-12-220-053-A ** ON A/C NOT FOR ALL (1) Close the door (1) and measure clearance J2 between the door stops and the stop fittings.
(2) Make sure that clearance J2 is a minimum of 0.2 mm (0.0079 in.).
(3) Measure out-of-flush dimension J1 between the door (1) and the fuselage at points P1 and P2.
(4) Calculate final out-of-flush dimension J at points P1 and P2 as follows:
J= J1+J2.
(5) Make sure that out-of-flush dimension J is 0 -0.8 mm or +0.8 mm (0.0000 -0.0315 in. or +0.0315 in.).
(6) If out-of-flush dimension J is not in the tolerance:
(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1) and make sure that clearance J2 is a minumum of 0.2 mm (0.0079 in.).
(e) Tighten the self-locking nuts (4).
(f) Close the door (1).
(7) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
D. Check of the Peripheral Clearance
(1) Make sure that peripheral clearance J3 between the door (1) and the fuselage is 2 +1 mm or -1 mm (0.0787 +0.0394 in. or -0.0394 in.).
Subtask 52-41-12-220-051-B ** ON A/C NOT FOR ALL (1) Make sure that peripheral clearance J3 between the door (1) and the fuselage is 2 +1 mm or -1 mm (0.0787 +0.0394 in. or -0.0394 in.).
E. Check and Adjustment of the Out-of-flush Dimension and Seal Compression
(1) Close the door (1) and measure clearance J2 between the door stops and the stop fittings.
(2) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(3) Measure out-of-flush dimension J1 between the door (1) and the fuselage at points P1 and P2.
(4) Calculate final out-of-flush dimension J at points P1 and P2 as follows:
J= J1+J2.
(5) Make sure that out-of-flush dimension J is 0 -0.8 mm or +0.8 mm (0.00 -0.03 in. or +0.03 in.).
(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1) and make sure that clearance J2 is a minumum of 0.2 mm (0.0079 in.).
(e) TORQUE the self-locking nuts (4) to between 4.5 and 3.5 m.N (39.82 and 30.97 lbf.in ).
(f) Close the door (1).
(7) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
Subtask 52-41-12-220-053-B ** ON A/C NOT FOR ALL (1) Close the door (1) and measure clearance J2 between the door stops and the stop fittings.
(2) Make sure that clearance J2 is a minimum of 0.2 mm (0.01 in.).
(3) Measure out-of-flush dimension J1 between the door (1) and the fuselage at points P1 and P2.
(4) Calculate final out-of-flush dimension J at points P1 and P2 as follows:
J= J1+J2.
(5) Make sure that out-of-flush dimension J is 0 -0.8 mm or +0.8 mm (0.00 -0.03 in. or +0.03 in.).
NOTE: A maximum tolerance of 0 -1.2 mm or +1.2 mm (0.00 -0.05 in. or +0.05 in.) is permitted for out-of-flush dimension J at points P1 and P2 if the peripheral clearance J3, at points P1 and P2, is not in the maximum tolerance.
(6) If the out-of-flush dimension J is not in the tolerance:(a) Open the door (1).
(b) Remove the self-locking nuts (4), the screws (2) and the washers (3).
(c) Install a new set of washers (3), the screws (2) and the self-locking nuts (4).
(d) Close the door (1) and make sure that clearance J2 is a minumum of 0.2 mm (0.0079 in.).
(e) TORQUE the self-locking nuts (4) to between 4.5 and 3.5 m.N (39.82 and 30.97 lbf.in )
.(f) Close the door (1).
(7) Make sure that the door seal is correctly compressed on all its length and that seal compression J4 is 3 -1.5 mm or +1.5 mm (0.12 -0.06 in. or +0.06 in.).
F. Check of the Peripheral Clearance
(1) Make sure that peripheral clearance J3 between the door (1) and the fuselage is 2 +1 mm or -1 mm (0.08 +0.04 in. or -0.04 in.).
Subtask 52-41-12-220-052-A (1) Make sure that peripheral clearance J3 between the door (1) and the fuselage is 2 +1 mm or -1 mm (0.08 +0.04 in. or -0.04 in.).
NOTE: A maximum tolerance of 2 -1.5 mm or +1.5 mm (0.08 -0.06 in. or +0.06 in.) is permitted for peripheral clearance J3, if out-of flush dimension J, at points P1 and P2, is not in the maximum tolerance.
G. Check of the Load on the Locking Handle
(1) Close door 812.
(2) Measure the load on the door handle with the DYNAMOMETER 20 DAN (45 LBF) - PULL and make sure that it is between 8 daN (17.98 lbf) and 16 daN (35.97 lbf).
Subtask 52-41-12-710-050-A 5. Close-up(1) Close door 812.
(2) Measure the load on the door handle with the DYNAMOMETER 20 DAN (45 LBF) - PULL and make sure that it is between 8 daN (17.98 lbf) and 16 daN (35.97 lbf).
Subtask 52-41-12-865-052-A
A. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 52-41-12-410-050-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | EIS/SDAC1 AND 2/DOOR/DET/AVNCS | 46WV | P02 |
B. Close Access
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Close door 812.
(3) Remove the access platform(s).
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Close door 812.
(3) Remove the access platform(s).