DOC AIRBUS | AMM A320FInstallation of the Cockpit Door
TASK 52-51-11-400-001-A
Installation of the Cockpit 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 52-51-11-860-050-A
Subtask 52-51-11-910-050-C
Subtask 52-51-11-410-050-A
[Rev.10 from 2021]
2026.04.01 06:12:50 UTC
Installation of the Cockpit Door
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 220
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.03HBD9) | Synthetic Ester base Grease-General Purpose Low Temp - |
| (Material No.05BAA1) | Threadlocking Adhesive-- Low strength - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 220 | FWD CAB UTILITY AREAS |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 15 | LOCKWASHERS | AIPC 53-14-01-31-080 |
| 14 | LOCKWASHERS | AIPC 53-14-01-31-105 |
| 6 | LOCKWASHERS | AIPC 53-14-81-01-080 |
| 14 | LOCKWASHERS | AIPC 53-14-81-01-100 |
| 12 | LOCKWASHERS | AIPC 53-14-81-01-110 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 25-23-42-000-001-A | Removal of the Ceiling Panels - Forward Utility Area |
| TASK 25-23-42-400-001-A | Installation of the Ceiling Panels - Forward Utility Area |
| TASK 33-21-00-710-001-A | Operational Test of the General Illumination |
| TASK 33-21-12-400-001-A | Installation of the Cabin Entrance Light Dimming Switch |
| TASK 52-51-00-720-001-A | Functional Test of the Door Opening Force |
| TASK 52-51-00-820-001-A | Adjustment of the Cockpit Door, Electrical Release Strikes and Latch Mechanisms |
Cockpit DoorSubtask 52-51-11-860-050-A
A. Aircraft Maintenance Configuration
(1) Make sure that the access to cockpit is available.
(2) Make sure that the ceiling panel 221AC is removed (Ref. AMM TASK 25-23-42-000-001).
Subtask 52-51-11-865-051-A (1) Make sure that the access to cockpit is available.
(2) Make sure that the ceiling panel 221AC is removed (Ref. AMM TASK 25-23-42-000-001).
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 122VU | DOORS/PAX/MONG | 1MQ | T13 |
| ** ON A/C NOT FOR ALL | |||
| 122VU | DOORS CKPT LOCK | 1MQ | T13 |
| 122VU | COCKPIT DOOR LOCK SYSTEM | 1MQ | T13 |
| ** ON A/C ALL | |||
| 2000VU | LIGHT-CABIN-ENTRY | 308LG | J02 |
Subtask 52-51-11-910-050-C
A. 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) Apply Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the lower pivot axle (4).
Subtask 52-51-11-420-050-C ** ON A/C NOT FOR ALL (1) Clean the component interfaces and the adjacent area.
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Apply Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the lower pivot axle (4).
B. Installation of the Cockpit Door
(1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4) and lower the door so that it engages with the pivot axle.
(b) Put the door post (10) in position to the fuselage fitting (15) attach it with the screws (13) and the washers (14).
(2) Install the cockpit wall (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the the screws (7).
(b) Put the cockpit wall (1) in position. Attach it with the screws (7) and the washers (8) to the lavatory sidewall (2).
(c) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to the threads of the screws (11).
(d) Put the cockpit wall (1) in position to the fuselage fitting bracket (16). Attach it with the screws (11) and the washers (12).
(e) Put the wire harness (18) in position on the cockpit panel (1) and attach it with the new TIE WRAP(S) (17).
Subtask 52-51-11-420-050-E ** ON A/C NOT FOR ALL (1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4) and lower the door so that it engages with the pivot axle.
(b) Put the door post (10) in position to the fuselage fitting (15) attach it with the screws (13) and the washers (14).
(2) Install the cockpit wall (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the the screws (7).
(b) Put the cockpit wall (1) in position. Attach it with the screws (7) and the washers (8) to the lavatory sidewall (2).
(c) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to the threads of the screws (11).
(d) Put the cockpit wall (1) in position to the fuselage fitting bracket (16). Attach it with the screws (11) and the washers (12).
(e) Put the wire harness (18) in position on the cockpit panel (1) and attach it with the new TIE WRAP(S) (17).
B. Installation of the Cockpit Door
(1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4) and lower the door so that it engages with the pivot axle (4).
(b) Put the door post (8) in position to the fuselage fitting (15).
(c) Insert the base plate (9) and the shims (10) in the positions recorded during the removal.
(d) Attach the door post (8) to the fuselage fitting (15) with the screws (13) and the new AIPC 53-14-01-31-105 LOCKWASHERS (14).
(2) Install the cockpit wall (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the screws (5).
(b) Put the cockpit wall (1) in position. Attach it with the screws (5) and the washers (6) through the brackets (7) to the lavatory sidewall (2).
(c) Put the cockpit wall (1) in position to the fuselage fitting bracket (16).
(d) Insert the shims (17) in the positions recorded on removal.
(e) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the the screws (11).
(f) Attach the cockpit wall (1) with the screws (11) and the washers (12).
(g) Put the wire harness (19) in position on the cockpit panel (1) and attach it with the new TIE WRAP(S) (18).
Subtask 52-51-11-420-050-F ** ON A/C NOT FOR ALL (1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4) and lower the door so that it engages with the pivot axle (4).
(b) Put the door post (8) in position to the fuselage fitting (15).
(c) Insert the base plate (9) and the shims (10) in the positions recorded during the removal.
(d) Attach the door post (8) to the fuselage fitting (15) with the screws (13) and the new AIPC 53-14-01-31-105 LOCKWASHERS (14).
(2) Install the cockpit wall (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the screws (5).
(b) Put the cockpit wall (1) in position. Attach it with the screws (5) and the washers (6) through the brackets (7) to the lavatory sidewall (2).
(c) Put the cockpit wall (1) in position to the fuselage fitting bracket (16).
(d) Insert the shims (17) in the positions recorded on removal.
(e) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to threads of the the screws (11).
(f) Attach the cockpit wall (1) with the screws (11) and the washers (12).
(g) Put the wire harness (19) in position on the cockpit panel (1) and attach it with the new TIE WRAP(S) (18).
B. Installation of the Cockpit Door
(1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4).
(b) Lower the cockpit door (3) until it engages in the lower pivot axle (4).
(c) Put the upper hinge (8) in position on the fuselage fitting (15).
(d) Put the shims (10) and the base plate (9) in the positions recorded during the removal procedure.
(e) Attach the upper hinge (8) to the fuselage fitting (15) with the new AIPC 53-14-81-01-100 LOCKWASHERS (14) and the screws (13).
(f) TORQUE the screws (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in )
.
(g) Safety the screws (13) with the lockwashers (14).
(2) Install the cockpit wall panel (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Put the cockpit wall panel (1) in position.
(b) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (7), the shims (20) and (21), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5).
(c) TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ).
(d) Safety the screws (5) with the lockwashers (6).
(e) Put the cockpit wall panel (1) in position on the fuselage fitting bracket (16).
(f) Put the shims (17) in the positions recorded during the removal procedure.
(g) Attach the cockpit wall panel (1) with the shim (28), the new AIPC 53-14-81-01-110 LOCKWASHERS (12) and the screws (11).
(h) TORQUE the screws (11) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ).
(i) Safety the screws (11) with the lockwashers (12).
(j) Put the wire harness (19) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (18).
Subtask 52-51-11-420-050-G ** ON A/C NOT FOR ALL (1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4).
(b) Lower the cockpit door (3) until it engages in the lower pivot axle (4).
(c) Put the upper hinge (8) in position on the fuselage fitting (15).
(d) Put the shims (10) and the base plate (9) in the positions recorded during the removal procedure.
(e) Attach the upper hinge (8) to the fuselage fitting (15) with the new AIPC 53-14-81-01-100 LOCKWASHERS (14) and the screws (13).
(f) TORQUE the screws (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in )
. (g) Safety the screws (13) with the lockwashers (14).
(2) Install the cockpit wall panel (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Put the cockpit wall panel (1) in position.
(b) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (7), the shims (20) and (21), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5).
(c) TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. (d) Safety the screws (5) with the lockwashers (6).
(e) Put the cockpit wall panel (1) in position on the fuselage fitting bracket (16).
(f) Put the shims (17) in the positions recorded during the removal procedure.
(g) Attach the cockpit wall panel (1) with the shim (28), the new AIPC 53-14-81-01-110 LOCKWASHERS (12) and the screws (11).
(h) TORQUE the screws (11) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. (i) Safety the screws (11) with the lockwashers (12).
(j) Put the wire harness (19) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (18).
B. Installation of the Cockpit Door
(1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4).
(b) Lower the cockpit door (3) until it engages with the lower pivot axle (4).
(c) Put the upper hinge (11) in position on the fuselage fitting (7).
(d) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the bolts (13).
(e) Attach the upper hinge (11) to the fuselage fitting (7) with the washers (12) and the bolts (13).
(f) TORQUE the bolts (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in ).
(2) Install the cockpit wall panel (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Put the cockpit wall panel (1) in position.
(b) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (17), the shims (16) and (18), the new AIPC 53-14-01-31-080 LOCKWASHERS (15) and the screws (14).
(c) TORQUE the screws (14) to between 0.31 and 0.25 m.daN (27.43 and 22.12 lbf.in ).
(d) Safety the screws (14) with the lockwashers (15).
(e) Put the cockpit wall panel (1) in position on the fuselage fitting bracket (8).
(f) Attach the cockpit wall panel (1) with the washers (6) and the screws (5).
(g) Tighten the screws (5).
(h) Put the wire harness (10) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (9).
Subtask 52-51-11-820-050-B Subtask 52-51-11-865-052-A (1) Install the cockpit door (3) as follows:
(a) Put the cockpit door (3) in position on the lower pivot axle (4).
(b) Lower the cockpit door (3) until it engages with the lower pivot axle (4).
(c) Put the upper hinge (11) in position on the fuselage fitting (7).
(d) Apply Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the bolts (13).
(e) Attach the upper hinge (11) to the fuselage fitting (7) with the washers (12) and the bolts (13).
(f) TORQUE the bolts (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in )
.(2) Install the cockpit wall panel (1) between the galley wall and the lavatory sidewall (2) as follows:
(a) Put the cockpit wall panel (1) in position.
(b) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (17), the shims (16) and (18), the new AIPC 53-14-01-31-080 LOCKWASHERS (15) and the screws (14).
(c) TORQUE the screws (14) to between 0.31 and 0.25 m.daN (27.43 and 22.12 lbf.in )
.(d) Safety the screws (14) with the lockwashers (15).
(e) Put the cockpit wall panel (1) in position on the fuselage fitting bracket (8).
(f) Attach the cockpit wall panel (1) with the washers (6) and the screws (5).
(g) Tighten the screws (5).
(h) Put the wire harness (10) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (9).
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 52-51-11-710-050-C | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 122VU | DOORS/PAX/MONG | 1MQ | T13 |
| ** ON A/C NOT FOR ALL | |||
| 122VU | DOORS CKPT LOCK | 1MQ | T13 |
| 122VU | COCKPIT DOOR LOCK SYSTEM | 1MQ | T13 |
| ** ON A/C ALL | |||
| 2000VU | LIGHT-CABIN-ENTRY | 308LG | J02 |
E. Operational Test
(1) Install the limit switch 310LG in the cockpit wall (1) (Ref. AMM TASK 33-21-12-400-001).
(2) Do the functional test of the door opening force (Ref. AMM TASK 52-51-00-720-001).
(3) Do the operational test of the entrance light dimming (Ref. AMM TASK 33-21-00-710-001).
5. Close-up(1) Install the limit switch 310LG in the cockpit wall (1) (Ref. AMM TASK 33-21-12-400-001).
(2) Do the functional test of the door opening force (Ref. AMM TASK 52-51-00-720-001).
(3) Do the operational test of the entrance light dimming (Ref. AMM TASK 33-21-00-710-001).
Subtask 52-51-11-410-050-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Make sure that the cockpit door is open.
(3) Install ceiling panel 221AC between the galley and the lavatory (Ref. AMM TASK 25-23-42-400-001).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Make sure that the cockpit door is open.
(3) Install ceiling panel 221AC between the galley and the lavatory (Ref. AMM TASK 25-23-42-400-001).