W DOC AIRBUS | AMM A320F

Adjustment of the Cockpit Door - Electrical Release Strikes

TASK 52-51-00-820-808-A
Adjustment of the Cockpit Door - Electrical Release Strikes

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 220
1. Reason for the Job
NOTE: Two persons are necessary to do this procedure.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
FLASHLIGHT
No specific
1
GAGE - SET, FEELER
No specific
1
RULER - STEEL
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
No specific
1
SCRAPER - NON METALLIC
No specific
1
TIE WRAP(S)
No specific
Torque wrench: range to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ) T
No specific
Torque wrench: range to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in ) T
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.05BAA1)
Threadlocking Adhesive-- Low strength -
(Material No.05BAE1)
Threadlocking Adhesive-- Medium strength -
(Material No.06CMD9)
Silicone Adhesive Sealant-General Purpose One part legacy
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
220
FWD CAB UTILITY AREAS
221AC
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
33
WASHER
AIPC 53-14-81-01-080
30
WASHER
AIPC 53-14-81-01-110
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 23-72-51-000-001-A
Removal of the Anti-Hijack-System Cameras
TASK 23-72-51-400-001-A
Installation of the Anti-Hijack-System Cameras
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)
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 33-21-12-000-001-A
Removal of the Cabin Entrance Light Dimming Switch
TASK 33-21-12-400-001-A
Installation of the Cabin Entrance Light Dimming Switch
TASK 52-51-00-710-002-A
Operational Test of the Cockpit-Door Locking System (CDLS)
TASK 52-51-00-820-001-A
Adjustment of the Cockpit Door, Electrical Release Strikes and Latch Mechanisms
TASK 52-51-00-820-810-A
Adjustment of the Cockpit Door - Clearance A between the Cockpit Door and Wall Panel (Pelmet)
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
F Cockpit Door - Adjustment of the Electrical Release Strikes
3. Job Set-up
Subtask 52-51-00-860-134-A
A. Aircraft Maintenance Configuration
   (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 52-51-00-865-152-A
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUDOORS/PAX/MONG1MQT13
** ON A/C NOT FOR ALL
122VUDOORS CKPT LOCK1MQT13
122VUCOCKPIT DOOR LOCK SYSTEM1MQT13
Subtask 52-51-00-010-061-A ** ON A/C NOT FOR ALL
C. Get Access
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
   (1) Remove anti-hijack camera [12RA] (Ref. AMM TASK 23-72-51-000-001).
   (2) Remove ceiling panel 221AC (Ref. AMM TASK 25-23-42-000-001).
   (3) Remove the limit switch 310LG (16) from the cockpit wall panel (1) (Ref. AMM TASK 33-21-12-000-001).
   (4) Remove the cockpit wall panel (1) as follows:
     (a) Remove the screw (20), the washer (21) and the cover (22) from the upper hinge (25).
     (b) Cut and discard the tie-wrap (28).
     (c) Remove the wire harness (29) from the cockpit wall panel (1).
     (d) Hold the cockpit wall panel (1) and remove the screws (17) and the washers (18) from the bracket (19).
NOTE: The bracket (19) is installed on the lavatory sidewall (2).
     (e) Disconnect the cockpit wall panel (1) from the lavatory sidewall (2).
     (f) Hold the cockpit wall panel (1) and remove the screws (23) and the washers (24) from the bracket (26). If the shims (27) are installed, remove them.
       1 Do not discard the shims (27). Record the positions of the shims (27).
NOTE: The bracket (26) is part of the upper hinge (25).
     (g) Remove the cockpit wall panel (1).
Subtask 52-51-00-010-061-B ** ON A/C NOT FOR ALL
C. Get Access
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
   (1) Remove anti-hijack camera [12RA] (Ref. AMM TASK 23-72-51-000-001).
   (2) Remove ceiling panel 221AC (Ref. AMM TASK 25-23-42-000-001).
   (3) Remove the limit switch 310LG (16) from the cockpit wall panel (1) (Ref. AMM TASK 33-21-12-000-001).
   (4) Remove the cockpit wall panel (1) as follows:
     (a) Remove the screw (20), the washer (21) and the cover (22) from the upper hinge (25).
     (b) Cut and discard the tie-wrap (28).
     (c) Remove the wire harness (29) from the cockpit wall panel (1).
     (d) Release the lockwashers (33) from the screws (32).
     (e) Hold the cockpit wall panel (1) and remove the screws (32), the lockwashers (33) and the plates (34) from the bracket (19).
NOTE: The bracket (19) is installed on the lavatory sidewall (2).
     (f) Discard the lockwashers (33).
     (g) Disconnect the cockpit wall panel (1) from the lavatory sidewall (2).
     (h) Release the lockwashers (30) from the screws (23).
     (i) Hold the cockpit wall panel (1) and remove the screws (23), the lockwashers (30), the plate (31) and the shims (27) from the bracket (26).
       1 Do not discard the shims (27). Record the positions of the shims (27).
NOTE: The bracket (26) is part of the upper hinge (25).
     (j) Discard the lockwashers (30).
     (k) Remove the cockpit wall panel (1).
4. Procedure
Subtask 52-51-00-820-061-A
A. Adjustment of the Cockpit Door - Electrical Release Strikes
   (1) If necessary, use the FLASHLIGHT to do the adjustment of clearances G and H.
   (2) Get access to the upper, center and lower electrical release-strikes (10) as follows:
     (a) Open the cockpit door (3).
     (b) Remove the screws (5) and the safety angle (4) from the lavatory wall (2).
     (c) Remove the screws (7) and the access covers (6) from the housings (8).
     (d) Temporarily install the safety angle (4) with the screws (5) on the lavatory wall (2).
     (e) Close the cockpit door (3).
   (3) Make sure that the latch tenon (11) touches the catch (9) of the center electrical release-strike (10).
   (4) Adjust clearance G between the cockpit door (3) and the safety angle (4) as follows:
     (a) Use the RULER - STEEL and measure clearance G between the cockpit door (3) and the safety angle (4).
     (b) Make sure that clearance G is between 0.5 mm (0.0197 in.) and 3 mm (0.1181 in.).
     (c) If clearance G is more than the limits, adjust the center electrical release-strike (10) as follows (movement in the rear direction):
       1 Open the cockpit door (3).
       2 If necessary, remove the sealant from the lower part of the applicable long aluminum shim (12) with the SCRAPER - NON METALLIC.
       3 Remove one of the long aluminum shims (12).
       4 Add a short aluminum shim (15) with a thickness of 1 mm (0.0394 in.) between the spring pack (13) and the center electrical release-strike (10).
       5 Make sure that clearance G is correct.
       6 Fill the gap with Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) at the lower part of the long aluminum shim (12).
     (d) If the latch tenon (11) does not engage in the catch (9), adjust the center electrical release-strike (10) as follows (movement in the flight direction):
       1 Open the cockpit door (3).
       2 Replace the short aluminum shim (14) with a thickness of 2 mm (0.0787 in.) with a short aluminum shim (15) with a thickness of 1 mm (0.0394 in.).
       3 If necessary, remove the sealant from the lower part of the applicable long aluminum shim (12) with the SCRAPER - NON METALLIC.
       4 Add a long aluminum shim (12) with a thickness of 1 mm (0.0394 in.).
       5 Make sure that the latch tenon (11) engages correctly in the catch (9).
       6 If the latch tenon (11) does not engage correctly in the catch (9):
  • Remove the short aluminum shim (15), and
  • Add a second long aluminum shim (12) with a thickness of 1 mm (0.0394 in.).
       7 Make sure that the latch tenon (11) engages correctly in the catch (9).
       8 Fill the gap with Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) at the lower part of the long aluminum shim (12).
   (5) Adjust clearance H between the catch (9) of the upper and lower electrical release-strikes (10) and the latch tenons (11) as follows:
     (a) Use the GAGE - SET, FEELER and measure clearance H between the catch (9) of the upper and lower electrical release-strikes (10) and the latch tenons (11).
     (b) Make sure that clearance H is between 0.5 mm (0.0197 in.) and 1.5 mm (0.0591 in.).
     (c) If clearance H is not in the limits, adjust the upper and lower electrical release-strikes (10) as follows (movement in the rear direction):
       1 Open the cockpit door (3).
       2 If necessary, remove the sealant from the lower part of the applicable long aluminum shim (12) with the SCRAPER - NON METALLIC.
       3 Remove one of the long aluminum shims (12).
       4 Add a short aluminum shim (15) with a thickness of 1 mm (0.0394 in.) between the spring pack (13) and the center electrical release-strike (10).
       5 Make sure that clearance H is correct.
       6 Fill the gap with Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) at the lower part of the long aluminum shim (12).
     (d) If the latch tenon (11) does not engage in the catch (9), adjust the upper and lower electrical release-strikes (10) as follows (movement in the flight direction):
       1 Open the cockpit door (3).
       2 Replace the short aluminum shim (14) with a thickness of 2 mm (0.0787 in.) with a short aluminum shim (15) with a thickness of 1 mm (0.0394 in.).
       3 If necessary, remove the sealant from the lower part of the applicable long aluminum shim (12) with the SCRAPER - NON METALLIC.
       4 Add a long aluminum shim (12) with a thickness of 1 mm (0.0394 in.).
       5 Make sure that clearance H is correct.
       6 If clearance H is not correct:
  • Remove the short aluminum shim (15), and
  • Add a second long aluminum shim (12) with a thickness of 1 mm (0.0394 in.).
       7 Fill the gap with Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) at the lower part of the long aluminum shim (12).
   (6) Install the access covers (6) as follows:
     (a) Remove the screws (5) and the safety angle (4) from the lavatory wall (2).
     (b) Install the access covers (6) with the screws (7) on the housings (8).
     (c) Tighten the screws (7).
     (d) Install the safety angle (4) on the lavatory wall (2) as follows:
       1 Apply a small quantity of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) on the threads of the screws (5).
       2 Install the safety angle (4) with the screws (5).
       3 TORQUE the screws (5) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in ) T.
Subtask 52-51-00-865-159-A
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUDOORS/PAX/MONG1MQT13
** ON A/C NOT FOR ALL
122VUDOORS CKPT LOCK1MQT13
122VUCOCKPIT DOOR LOCK SYSTEM1MQT13
Subtask 52-51-00-710-072-A
C. Operational Test of the Cockpit Door and the Latch Mechanism
   (1) Do an operational test of the cockpit door (3) and the latch mechanism (Ref. AMM TASK 52-51-00-710-002).
   (2) If the results of the test are unsatisfactory or you cannot adjust the electrical release strike as in step 4.A:
     (a) Do the adjustment procedure of the cockpit door (3), the electrical release strikes and the latch mechanisms (Ref. AMM TASK 52-51-00-820-001).
5. Close-up
Subtask 52-51-00-410-057-A ** ON A/C NOT FOR ALL
A. Close Access
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the cockpit wall panel (1) as follows:
     (a) Put the cockpit wall panel (1) in position.
     (b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (23).
     (c) Attach the cockpit wall panel (1) to the upper hinge (25) with the bracket (26) and the shims (27) in the order that they were removed.
NOTE: The bracket (26) is part of the upper hinge (25).
     (d) Install the washers (24) and the screws (23). Do not tighten the screws (23) at this time.
     (e) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (17).
     (f) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (19), the washers (18) and the screws (17). Do not tighten the screws (17) at this time.
     (g) Make sure that clearance A is between 4 mm (0.1575 in.) and 5.5 mm (0.2165 in.) (Ref. AMM TASK 52-51-00-820-810).
     (h) Tighten the screws (17) and (23).
     (i) Put the wire harness (29) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (28).
     (j) Put the cover (22), the washer (21) and the screw (20) in position on the upper hinge (25).
     (k) Tighten the screw (20).
   (3) Install the limit switch 310LG (16) on the cockpit wall panel (1) (Ref. AMM TASK 33-21-12-400-001).
   (4) Install ceiling panel 221AC (Ref. AMM TASK 25-23-42-400-001).
   (5) Install anti-hijack camera [12RA] (Ref. AMM TASK 23-72-51-400-001).
Subtask 52-51-00-410-057-B ** ON A/C NOT FOR ALL
A. Close Access
F Cockpit Door - Removal of the Cockpit Wall Panel ** ON A/C NOT FOR ALL
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the cockpit wall panel (1) as follows:
     (a) Put the cockpit wall panel (1) in position.
     (b) Attach the cockpit wall panel (1) to the upper hinge (25) with the bracket (26) and the shims (27) in the order that they were removed.
NOTE: The bracket (26) is part of the upper hinge (25).
     (c) Install the plate (31), the new lockwashers AIPC 53-14-81-01-110 WASHER (30) and the screws (23). Do not tighten the screws (23) at this time.
NOTE: The plate (31) is part in the primer color. The plate (31) is installed on top of the bracket (26) and directly under the lockwashers (30).
     (d) Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (19), the plates (34), the new lockwashers AIPC 53-14-81-01-080 WASHER (33) and the screws (32). Do not tighten the screws (32) at this time.
     (e) Make sure that clearance A is between 4 mm (0.1575 in.) and 5.5 mm (0.2165 in.) (Ref. AMM TASK 52-51-00-820-810).
     (f) TORQUE the screws (23) and the screws (32) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ) T.
     (g) Safety the screws (23) with the lockwashers (30).
     (h) Safety the screws (32) with the lockwashers (33).
     (i) Put the wire harness (29) in position on the cockpit wall panel (1) and safety it with the new TIE WRAP(S) (28).
     (j) Put the cover (22), the washer (21) and the screw (20) in position on the upper hinge (25).
     (k) Tighten the screw (20).
   (3) Install the limit switch 310LG (16) on the cockpit wall panel (1) (Ref. AMM TASK 33-21-12-400-001).
   (4) Install ceiling panel 221AC (Ref. AMM TASK 25-23-42-400-001).
   (5) Install anti-hijack camera [12RA] (Ref. AMM TASK 23-72-51-400-001).
Subtask 52-51-00-860-135-A
B. Put the aircraft back to the serviceable condition.
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.02 06:28:24 UTC
"WTRUIB" 2025