DOC AIRBUS | AMM A320FAdjustment of the Cockpit Door, Electrical Release Strikes and Latch Mechanisms
TASK 52-51-00-820-001-A
Adjustment of the Cockpit Door, Electrical Release Strikes and Latch Mechanisms
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 52-51-00-860-071-A
Subtask 52-51-00-820-050-A ** ON A/C NOT FOR ALL
Subtask 52-51-00-860-072-A
[Rev.10 from 2021]
2026.04.01 12:46:46 UTC
Adjustment of the Cockpit Door, Electrical Release Strikes and Latch Mechanisms
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.05BAA1) | Threadlocking Adhesive-- Low strength - |
| (Material No.05BAE1) | Threadlocking Adhesive-- Medium strength - |
| (Material No.06BQD1) | Silicone Sealant-Non Textile Floor Jointing One part - |
| (Material No.06CMD9) | Silicone Adhesive Sealant-General Purpose One part legacy |
| (Material No.06LCG9) | Non Hardening Jointing Putty-Medium Temp. Area - - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.10ABC1) | Surface Pretreatment-Light Alloys Chemical Conversion Yellow - |
| (Material No.14JAB1) | Sealing Profile-- Silicone Foam - |
| (Material No.14QFB1) | Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - |
| (Material No.14RAD1) | Cord-- Synthetic fiber Dia: 2.5 mm - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 220 | FWD CAB UTILITY AREAS |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 18 | LOCKWASHERS | AIPC 53-14-81-01-080 |
| 6 | LOCKWASHERS | AIPC 53-14-81-01-080 |
| 26 | LOCKWASHERS | AIPC 53-14-81-01-100 |
| 12 | LOCKWASHERS | AIPC 53-14-81-01-110 |
| REFERENCE | DESIGNATION |
|---|---|
| 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 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) |
Subtask 52-51-00-860-071-A
A. Aircraft Maintenance Configuration
(1) Make sure that the cockpit door is closed.
(2) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
Subtask 52-51-00-865-062-A (1) Make sure that the cockpit door is closed.
(2) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
B. Open, safety and tag this(these) circuit breaker(s):
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 |
Subtask 52-51-00-820-050-A ** ON A/C NOT FOR ALL
A. Adjustment of the Cockpit Door
(1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
6 Tighten the locknut (17).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.146 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust them as follows:
1 Remove the adjustment screws (14) from the upper hinge (8) of the cockpit door (3).
2 Apply a layer of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) on the adjustment screws (14).
3 Install the adjustment screws (14) in the upper hinge (8) of the cockpit door (3).
4 Do not tighten them at this time.
5 Prepare the area of the lower hinge (4) as follows:
a Remove the nylon tape together with the old sealant from the area around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
6 Remove the screws (7) from the lower hinge (4).
7 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
8 Install the screws (7) in the lower hinge (4).
9 Do not tighten them at this time.
10 Move the cockpit door (3) until lateral clearances B and C are correct.
11 TORQUE the adjustment screws (14) of the upper hinge (8) to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in )
.
12 Tighten the screws (7) of the lower hinge (4).
13 Prepare the bottom of the lower hinge (4) as follows:
a Put the14RAD1 Cord-- Synthetic fiber Dia: 2.5 mm -
(4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the screws (13) from the structure fitting (15).
2 Put the necessary quantity of the shims (9) between the cockpit door (3) and the upper hinge (8) until the clearance is correct.
4 Install the screws (13) in the structure fitting (15).
5 Tighten the screws (13).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is less than 3.0 mm (0.118 in.).
(b) Make sure that the top of the cockpit door (3) always touches the safety angle (22) during this measurement.
(c) If clearance G is not in the limit, adjust the position of the center electrical release-strike.
(6) If you adjusted clearance F between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) for the cockpit wall panel (1) to be parallel to the structure fitting (15).
(7) If you must make adjustments, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (LN65045-08) (10).The shims (LN65045-08) (10) must be equal to the dimension between the upper hinge (8) and the structure fitting (15).
(d) Install the screws (11), the washers (12) and the shims (LN65045-08) (10).
(e) Do not tighten the screws (11).
(f) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K and L are correct ( 2.00 mm (0.079 in.) minimum), and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Do steps 6 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and adjustment is necessary. If not, go to step 11.
6 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the screws (5).
8 Install the screws (5) and the washers (6).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K and L are correct ( 2.00 mm (0.079 in.) minimum).
13 Tighten the screws (11) and (19), and (5) if necessary.
Subtask 52-51-00-820-050-B ** ON A/C NOT FOR ALL (1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
NOTE: The cockpit door (3) weighs approximately 35.0 kg (77.162 lb).
2 Remove the locknut (17) from the upper hinge (8). 3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
6 Tighten the locknut (17).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.146 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust them as follows:
1 Remove the adjustment screws (14) from the upper hinge (8) of the cockpit door (3).
2 Apply a layer of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) on the adjustment screws (14).
3 Install the adjustment screws (14) in the upper hinge (8) of the cockpit door (3).
4 Do not tighten them at this time.
5 Prepare the area of the lower hinge (4) as follows:
a Remove the nylon tape together with the old sealant from the area around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
6 Remove the screws (7) from the lower hinge (4).
7 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
8 Install the screws (7) in the lower hinge (4).
9 Do not tighten them at this time.
10 Move the cockpit door (3) until lateral clearances B and C are correct.
11 TORQUE the adjustment screws (14) of the upper hinge (8) to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in )
. 12 Tighten the screws (7) of the lower hinge (4).
13 Prepare the bottom of the lower hinge (4) as follows:
a Put the
NOTE: This will make the subsequent removal easier.
b Apply a layer of Silicone Sealant-Non Textile Floor Jointing One part - (Material No.06BQD1) to fill the remaining clearance around the lower hinge (4). (4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the screws (13) from the structure fitting (15).
2 Put the necessary quantity of the shims (9) between the cockpit door (3) and the upper hinge (8) until the clearance is correct.
NOTE: The recommended shims (standard washers P/N LN65045-08) have a thickness of 1.6 mm (0.063 in.) and only a maximum of three shims (max. thickness of 4.8 mm (0.189 in.)) is permitted.
3 Apply a layer of Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) on the screws (13). 4 Install the screws (13) in the structure fitting (15).
5 Tighten the screws (13).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is less than 3.0 mm (0.118 in.).
(b) Make sure that the top of the cockpit door (3) always touches the safety angle (22) during this measurement.
(c) If clearance G is not in the limit, adjust the position of the center electrical release-strike.
(6) If you adjusted clearance F between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) for the cockpit wall panel (1) to be parallel to the structure fitting (15).
(7) If you must make adjustments, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (LN65045-08) (10).The shims (LN65045-08) (10) must be equal to the dimension between the upper hinge (8) and the structure fitting (15).
(d) Install the screws (11), the washers (12) and the shims (LN65045-08) (10).
(e) Do not tighten the screws (11).
(f) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K and L are correct ( 2.00 mm (0.079 in.) minimum), and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Do steps 6 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and adjustment is necessary. If not, go to step 11.
6 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the screws (5).
8 Install the screws (5) and the washers (6).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K and L are correct ( 2.00 mm (0.079 in.) minimum).
13 Tighten the screws (11) and (19), and (5) if necessary.
A. Adjustment of the Cockpit Door
(1) Adjust upper clearance A of the cockpit (3) door as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
(2) Make sure that limit switch 310LG in the cockpit wall (3) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.1457 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust them as follows:
1 Remove the adjustment screws (14) from the upper hinge (8) of the cockpit door (3).
2 Apply a layer of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) on the adjustment screws (14).
3 Install the adjustment screws (14) in the upper hinge (8) of the cockpit door (3).
4 Do not tighten them at this time.
5 Prepare the bottom of the lower hinge (4) as follows:
a Find the end of the nylon tape and remove it with the old sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
6 Remove the screws (7) of the lower hinge (4).
7 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
8 Install the screws (7) in the lower hinge (4).
9 Do not tighten them at this time.
10 Move the cockpit door (3) until lateral clearances B and C are correct.
11 TORQUE the adjustment screws (14) of the upper hinge (8) to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in ).
12 Tighten the screws (7) of the lower hinge (4).
13 Prepare the bottom of the lower hinge (4) as follows:
a Put the14RAD1 Cord-- Synthetic fiber Dia: 2.5 mm -
(4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the screws (13) from the structure fitting (15).
2 Put the necessary quantity of the shims (9) between the cockpit door (3) and the upper hinge (8) until the clearance is correct.
4 Install the screws (13) in the structure fitting (15).
5 Tighten the screws (13).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not in the limit, adjust the position of the center electrical release-strike.
(6) If you adjusted clearance F, between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) so that the cockpit wall panel (1) and the structure fitting (15) are parallel.
(7) If you must make adjustments, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (LN65045-08) (10) that are the same as the dimension between the upper hinge (8) and the structure fitting (15).
(d) Install the screws (11), the washers (12) and the shims (LN65045-08) (10).
(e) Do not tighten the screws (11).
(f) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are correct and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Do steps 6 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and adjustment is necessary. If not, go to step 11.
6 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (5).
8 Install the screws (5) and the washers (6).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are correct.
13 Tighten the screws (11) and (19), and if necessary (5).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
Subtask 52-51-00-820-050-C ** ON A/C NOT FOR ALL (1) Adjust upper clearance A of the cockpit (3) door as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
NOTE: The cockpit door (3) weighs approximately 35.0 kg (77.162 lb).
2 Remove the locknut (17) from the upper hinge (8). 3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
(2) Make sure that limit switch 310LG in the cockpit wall (3) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.1457 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust them as follows:
1 Remove the adjustment screws (14) from the upper hinge (8) of the cockpit door (3).
2 Apply a layer of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) on the adjustment screws (14).
3 Install the adjustment screws (14) in the upper hinge (8) of the cockpit door (3).
4 Do not tighten them at this time.
5 Prepare the bottom of the lower hinge (4) as follows:
a Find the end of the nylon tape and remove it with the old sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
6 Remove the screws (7) of the lower hinge (4).
7 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
8 Install the screws (7) in the lower hinge (4).
9 Do not tighten them at this time.
10 Move the cockpit door (3) until lateral clearances B and C are correct.
11 TORQUE the adjustment screws (14) of the upper hinge (8) to between 1.1 and 0.9 m.daN (97.35 and 79.65 lbf.in )
. 12 Tighten the screws (7) of the lower hinge (4).
13 Prepare the bottom of the lower hinge (4) as follows:
a Put the
NOTE: This will make the subsequent removal easier.
b Apply a layer of Silicone Sealant-Non Textile Floor Jointing One part - (Material No.06BQD1) to fill the remaining clearance around the lower hinge (4). (4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the screws (13) from the structure fitting (15).
2 Put the necessary quantity of the shims (9) between the cockpit door (3) and the upper hinge (8) until the clearance is correct.
NOTE: The recommended shims (standard washers P/N LN65045-08) have a thickness of 1.6 mm (0.063 in.) and only a maximum of three shims (max. thickness of 4.8 mm (0.189 in.)) is permitted.
3 Apply a layer of Silicone Adhesive Sealant-General Purpose One part legacy (Material No.06CMD9) on the screws (13). 4 Install the screws (13) in the structure fitting (15).
5 Tighten the screws (13).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not in the limit, adjust the position of the center electrical release-strike.
(6) If you adjusted clearance F, between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) so that the cockpit wall panel (1) and the structure fitting (15) are parallel.
(7) If you must make adjustments, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (LN65045-08) (10) that are the same as the dimension between the upper hinge (8) and the structure fitting (15).
(d) Install the screws (11), the washers (12) and the shims (LN65045-08) (10).
(e) Do not tighten the screws (11).
(f) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are correct and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Do steps 6 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and adjustment is necessary. If not, go to step 11.
6 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (5).
8 Install the screws (5) and the washers (6).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are correct.
13 Tighten the screws (11) and (19), and if necessary (5).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
A. Adjustment of the Cockpit Door
(1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than this limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C for the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21).
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust as follows:
1 Loosen the adjustment screws (14) and (27) of the upper hinge (8).
a Find the end of the nylon tape and remove it together with the old sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
3 Remove the screws (7) from the lower hinge (4).
4 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
5 Install the screws (7) in the lower hinge (4).
6 Do not tighten them.
7 Move the cockpit door (3) until lateral clearances B and C are correct.
8 TORQUE the adjustment screw (14) of the upper hinge (8) to between 2.2 and 1.8 m.daN (16.22 and 13.27 lbf.ft ).
9 TORQUE the adjustment screw (27) of the upper hinge (8) to between 1.65 and 1.35 m.daN (146.02 and 119.47 lbf.in ).
10 Tighten the screws (7) of the lower hinge (4).
11 Prepare the bottom of the lower hinge (4) as follows:
a Put the14RAD1 Cord-- Synthetic fiber Dia: 2.5 mm -
(4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the bolts (5) and the washers (6).
2 Release the lockwashers (26) from the bolts (13).
3 Remove the bolts (13).
4 Remove and discard the lockwashers (26).
5 Remove the bolts (11) and washers (12).
6 Remove the cockpit wall panel (1).
7 Remove the shims (9).
8 Put the necessary quantity of the shims (24) in position.
9 Do not remove the base plate (25) from the adjacent structure fitting (15).
13 Install the shims (24) that are not used for adjustment adjacent to the base plate (25).
14 Install the bolts (13) and the new lockwashers (26).
15 Tighten the bolts (13).
16 Safety the bolts with the lockwashers (26).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not correct, adjust the position of the center electrical release-strike (refer to Para. 4.B.).
(6) If you adjusted clearance F between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) to make the cockpit wall panel (1) and the structure fitting (15) parallel (forward and rearward).
(7) If the adjustment of clearance F is necessary, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (9) that are the same as the dimension between the upper hinge (8) and the structure fitting bracket (10).
(f) Do not tighten the screws (11).
(g) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 If necessary, apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
6 Do steps 5 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and the adjustment is necessary. If not, go to step 11.
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to the threads of the screws (5).
8 Install the washers (6) and the screws (5).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in an up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct.
13 Tighten the screws (19) and (11), and if necessary (5).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
Subtask 52-51-00-820-050-D ** ON A/C NOT FOR ALL (1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is less than this limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
NOTE: The cockpit door (3) weighs approximately 35.0 kg (77.162 lb).
2 Remove the locknut (17) from the upper hinge (8). 3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C for the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21).
NOTE: The safety angle (21) is installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.146 in.) minimum.(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.354 in.) and 10 mm (0.394 in.).
(e) If clearances B and C are not in the limits, adjust as follows:
1 Loosen the adjustment screws (14) and (27) of the upper hinge (8).
NOTE: This will let the notch of the upper hinge body move to the groove of the upper hinge clamp-plate.
2 Prepare the base around the lower hinge (4) as follows: a Find the end of the nylon tape and remove it together with the old sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) and Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
3 Remove the screws (7) from the lower hinge (4).
4 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
5 Install the screws (7) in the lower hinge (4).
6 Do not tighten them.
7 Move the cockpit door (3) until lateral clearances B and C are correct.
8 TORQUE the adjustment screw (14) of the upper hinge (8) to between 2.2 and 1.8 m.daN (16.22 and 13.27 lbf.ft )
. 9 TORQUE the adjustment screw (27) of the upper hinge (8) to between 1.65 and 1.35 m.daN (146.02 and 119.47 lbf.in )
. 10 Tighten the screws (7) of the lower hinge (4).
11 Prepare the bottom of the lower hinge (4) as follows:
a Put the
NOTE: This will make the subsequent removal easier.
b Apply a layer of Silicone Sealant-Non Textile Floor Jointing One part - (Material No.06BQD1) to fill the remaining clearance around the lower hinge (4). (4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows:
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.020 in.) and 2.5 mm (0.098 in.).
(c) If clearance F is not correct, adjust it as follows:
1 Remove the bolts (5) and the washers (6).
2 Release the lockwashers (26) from the bolts (13).
3 Remove the bolts (13).
4 Remove and discard the lockwashers (26).
5 Remove the bolts (11) and washers (12).
6 Remove the cockpit wall panel (1).
7 Remove the shims (9).
8 Put the necessary quantity of the shims (24) in position.
9 Do not remove the base plate (25) from the adjacent structure fitting (15).
NOTE: The base plate (25) is painted yellow for identification.
10 Install the shims (24) between the upper hinge (8) and the structure fitting (15) until the clearance is correct. NOTE: The shims (24) that are not used are installed between the structure fitting (15) and the lockwashers (26).
11 Do not discard the shims (24). NOTE: The bolt (13) length is calculated to use all the shims (24).
12 Install the shims (24) that are used for adjustment between the structure fitting (15) and the upper hinge (8). 13 Install the shims (24) that are not used for adjustment adjacent to the base plate (25).
14 Install the bolts (13) and the new lockwashers (26).
15 Tighten the bolts (13).
16 Safety the bolts with the lockwashers (26).
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not correct, adjust the position of the center electrical release-strike (refer to Para. 4.B.).
(6) If you adjusted clearance F between the cockpit door (3) and the safety angle (21) to get the correct dimension:
(a) Use the same quantity of the shims (9) to make the cockpit wall panel (1) and the structure fitting (15) parallel (forward and rearward).
(7) If the adjustment of clearance F is necessary, do the steps that follow:
(a) Hold the cockpit wall panel (1) and remove the screws (11) and the washers (12).
(b) Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (11).
(c) Use the correct quantity of the shims (9) that are the same as the dimension between the upper hinge (8) and the structure fitting bracket (10).
NOTE: The shims (9) that are not used are installed between the structure fitting bracket (10) and the washers (12).
(d) Do not discard the shims (9). NOTE: The screw (11) length is calculated to use all the shims (9).
(e) Install the screws (11), the spare and adjustment shims (9) and the washers (12). (f) Do not tighten the screws (11).
(g) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(8) If distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct and the cockpit wall panel (1) is parallel to the cockpit door (3) (up/down), fully tighten the screws (11).
(a) If distances K and L are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
1 Hold the cockpit wall panel (1) and remove the screws (19) and the washers (18).
2 If necessary, apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) on the threads of the screws (19).
3 Install the screws (19) and the washers (18).
4 Do not tighten the screws (19).
5 Hold the cockpit wall panel (1) and remove the screws (5) and the washers (6).
6 Do steps 5 thru 10 only if the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down) and the adjustment is necessary. If not, go to step 11.
7 Apply a layer of Threadlocking Adhesive-- Low strength - (Material No.05BAA1) to the threads of the screws (5).
8 Install the washers (6) and the screws (5).
9 Do not tighten the screws (5).
10 Move the cockpit wall panel (1) in an up or down direction until it is parallel to the cockpit door (3).
11 Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
12 Move the cockpit wall panel (1) in a lateral direction until distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct.
13 Tighten the screws (19) and (11), and if necessary (5).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
A. Adjustment of the Cockpit Door
(1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is not in the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
6 Tighten the locknut (17).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.146 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.3543 in.) and 10 mm (0.3937 in.).
(e) If clearances B and C are not in the limits, adjust as follows:
1 Loosen the adjustment screws (14) and (27) of the upper hinge (8).
a Find the end of the cord and remove it together with the sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
3 Remove the screws (7) from the lower hinge (4).
4 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
5 Install the screws (7) in the lower hinge (4). Do not tighten the screws (7) at this time.
6 Move the cockpit door (3) until lateral clearances B and C are correct.
7 TORQUE the adjustment screw (14) of the upper hinge (8) to between 22 and 18 m.N (16.22 and 13.27 lbf.ft ).
8 TORQUE the adjustment screw (27) of the upper hinge (8) to between 16.5 and 13.5 m.N (146.02 and 119.47 lbf.in ).
9 Tighten the screws (7) of the lower hinge (4).
10 Prepare the base around the lower hinge (4) as follows:
a Put the14RAD1 Cord-- Synthetic fiber Dia: 2.5 mm -
b Make sure that approximately 100 mm (3.9370 in.) of the cord goes out of the two ends.
c Apply a layer of Silicone Sealant-Non Textile Floor Jointing One part - (Material No.06BQD1) to fill the remaining clearance around the lower hinge (4).
d Make a loop at each end of the cord. Carefully push the cord ends in the sealant.
(a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.0197 in.) and 2.5 mm (0.0984 in.).
(c) If clearance F is not correct, adjust it as follows:
2 Release the lockwashers (6) from the screws (5).
3 Hold the cockpit wall panel (1) and remove the screws (5), the lockwashers (6) and the plates (29).
a Keep the screws (5) and the plates (29).
b Discard the lockwashers (6).
4 Release the lockwashers (26) from the screws (13).
5 Remove the screws (13) and the lockwashers (26).
a Keep the screws (13).
b Discard the lockwashers (26).
6 Release the lockwashers (12) from the screws (11).
7 Hold the cockpit wall panel (1) in position and remove the screws (11), the lockwashers (12), the plate (28) and the shims (9).
a Keep the screws (11) and the plate (28).
b Record the positions of the shims (9).
c Discard the lockwashers (12).
8 Adjust the position of the shims (24) between the upper hinge (8) and the structure fitting (15) until clearance F is correct. Make sure that you:
a Do not discard the shims (24).
d Install the shims (24) that are not used for the adjustment of clearance F adjacent on the base plate (25).
9 Put the upper hinge (8) in position on the fuselage fitting (15).
10 Make sure that the correct number of shims (24) and the base plate (25) are installed in the correct position.
11 Attach the upper hinge (8) to the fuselage fitting (15) with the new AIPC 53-14-81-01-100 LOCKWASHERS (26) and the screws (13).
12 TORQUE the screws (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in ).
13 Safety the screws (13) with the lockwashers (26).
14 Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (31), the plates (29), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5).
15 TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ). Do not safety the screws (5) with the lockwashers (6) at this time.
16 Put the cockpit wall panel (1) in position on the fuselage fitting bracket (10).
17 Put the shims (9) in the positions recorded during the removal procedure.
18 Attach the cockpit wall panel (1) with the new AIPC 53-14-81-01-110 LOCKWASHERS (12) and the screws (11).
19 TORQUE the screws (11) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ). Do not safety the screws (11) with the lockwashers (12) at this time.
(5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not correct, adjust the position of the center electrical release-strike (refer to Para. 4.B.).
(6) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(7) If distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
(a) Release the lockwashers (18) from the screws (19).
(b) Hold the cockpit wall panel (1) and remove the screws (19), the lockwashers (18) and the plates (30).
(c) Discard the lockwashers (18).
(d) Install the plates (30), the new AIPC 53-14-81-01-080 LOCKWASHERS (18) and the screws (19). Do not tighten the screws (19) at this time.
(e) If the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down), do the steps that follow:
1 If you did not install new lockwashers (6) in step (4)(c), do the steps that follow:
a Release the lockwashers (6) from the screws (5).
b Hold the cockpit wall panel (1) and remove the screws (5), the lockwashers (6) and the plates (29).
c Discard the lockwashers (6).
d Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (31), the plates (29), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5). Do not tighten the screws (5) at this time.
2 If you installed new lockwashers (6) in step (4)(c), do the step that follows:
a Hold the cockpit wall panel (1) and loosen the screws (5).
3 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3). Make sure that dimension A is correct and between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(f) If distances K and L are not correct, do the step that follows:
1 Move the cockpit wall panel (1) in a lateral direction until distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct.
(g) If necessary, TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ).
(h) TORQUE the screws (19) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in ).
(8) Safety the screws (5), (11) and (19):
(a) Safety the screws (5) with the lockwashers (6).
(b) Safety the screws (11) with the lockwashers (12).
(c) Safety the screws (19) with the lockwashers (18).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
Subtask 52-51-00-820-051-A ** ON A/C NOT FOR ALL (1) Adjust upper clearance A of the cockpit door (3) as follows:
(a) Measure clearance A between the top of the closed cockpit door (3) and the cockpit wall panel (1).
(b) Make sure that clearance A is between 4.0 mm (0.157 in.) and 5.5 mm (0.217 in.).
(c) If clearance A is not in the limit, adjust it as follows:
1 Open the cockpit door (3) and carefully lift it until there is no load on the adjustment nut (16).
NOTE: The cockpit door (3) weighs approximately 35.0 kg (77.162 lb).
2 Remove the locknut (17) from the upper hinge (8). 3 Turn the adjustment nut (16) until clearance A is correctly adjusted.
4 Lower the cockpit door (3) and make sure that clearance A is correct.
5 Install the locknut (17) on the upper hinge (8).
6 Tighten the locknut (17).
(2) Make sure that limit switch 310LG in the cockpit wall panel (1) is correctly adjusted (Ref. AMM TASK 33-21-12-400-001).
(3) Adjust lateral clearances B and C of the cockpit door (3) as follows:
(a) Measure clearance B between the cockpit door (3) and the inboard edge of the safety angle (21) installed on the galley wall (20).
(b) Make sure that clearance B is 3.7 mm (0.146 in.) minimum.
(c) Measure clearance C between the cockpit door (3) and the lavatory wall (2).
(d) Make sure that clearance C is between 9 mm (0.3543 in.) and 10 mm (0.3937 in.).
(e) If clearances B and C are not in the limits, adjust as follows:
1 Loosen the adjustment screws (14) and (27) of the upper hinge (8).
NOTE: This will let the notch of the upper hinge body move to the groove of the upper hinge clamp-plate.
2 Prepare the base around the lower hinge (4) as follows: a Find the end of the cord and remove it together with the sealant from the base around the lower hinge (4).
b Use the Textile-Lint free Cotton - (Material No.14SBA1) with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the lower hinge (4) and the adjacent area.
3 Remove the screws (7) from the lower hinge (4).
4 Apply a layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the screws (7).
5 Install the screws (7) in the lower hinge (4). Do not tighten the screws (7) at this time.
6 Move the cockpit door (3) until lateral clearances B and C are correct.
7 TORQUE the adjustment screw (14) of the upper hinge (8) to between 22 and 18 m.N (16.22 and 13.27 lbf.ft )
. 8 TORQUE the adjustment screw (27) of the upper hinge (8) to between 16.5 and 13.5 m.N (146.02 and 119.47 lbf.in )
. 9 Tighten the screws (7) of the lower hinge (4).
10 Prepare the base around the lower hinge (4) as follows:
a Put the
b Make sure that approximately 100 mm (3.9370 in.) of the cord goes out of the two ends.
c Apply a layer of Silicone Sealant-Non Textile Floor Jointing One part - (Material No.06BQD1) to fill the remaining clearance around the lower hinge (4).
d Make a loop at each end of the cord. Carefully push the cord ends in the sealant.
NOTE: This will make the subsequent removal easier.
(4) Adjust clearance F between the cockpit door (3) and the safety angle (21) as follows: (a) Measure clearance F between the cockpit door (3) and the safety angle (21).
(b) Make sure that clearance F is between 0.5 mm (0.0197 in.) and 2.5 mm (0.0984 in.).
(c) If clearance F is not correct, adjust it as follows:
NOTE: Two persons are necessary for the adjustment of clearance F.
1 Hold the cockpit door (3) and the cockpit wall panel (1) in position.2 Release the lockwashers (6) from the screws (5).
3 Hold the cockpit wall panel (1) and remove the screws (5), the lockwashers (6) and the plates (29).
a Keep the screws (5) and the plates (29).
b Discard the lockwashers (6).
4 Release the lockwashers (26) from the screws (13).
5 Remove the screws (13) and the lockwashers (26).
a Keep the screws (13).
b Discard the lockwashers (26).
6 Release the lockwashers (12) from the screws (11).
7 Hold the cockpit wall panel (1) in position and remove the screws (11), the lockwashers (12), the plate (28) and the shims (9).
a Keep the screws (11) and the plate (28).
b Record the positions of the shims (9).
c Discard the lockwashers (12).
8 Adjust the position of the shims (24) between the upper hinge (8) and the structure fitting (15) until clearance F is correct. Make sure that you:
a Do not discard the shims (24).
NOTE: The lengths of the screws (13) are calculated to use all the shims (24).
NOTE: The shims (24), that are not used for the adjustment of clearance F, are installed between the structure fitting (15) and the lockwasher (26).
b Do not remove the base plate (25) from the adjacent structure fitting (15). NOTE: The base plate (25) is painted yellow for identification.
c Install the shims (24) that are used for the adjustment of clearance F between the structure fitting (15) and the upper hinge (8). d Install the shims (24) that are not used for the adjustment of clearance F adjacent on the base plate (25).
9 Put the upper hinge (8) in position on the fuselage fitting (15).
10 Make sure that the correct number of shims (24) and the base plate (25) are installed in the correct position.
11 Attach the upper hinge (8) to the fuselage fitting (15) with the new AIPC 53-14-81-01-100 LOCKWASHERS (26) and the screws (13).
12 TORQUE the screws (13) to between 13.2 and 10.8 m.N (116.81 and 95.58 lbf.in )
. 13 Safety the screws (13) with the lockwashers (26).
14 Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (31), the plates (29), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5).
15 TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. Do not safety the screws (5) with the lockwashers (6) at this time. 16 Put the cockpit wall panel (1) in position on the fuselage fitting bracket (10).
17 Put the shims (9) in the positions recorded during the removal procedure.
18 Attach the cockpit wall panel (1) with the new AIPC 53-14-81-01-110 LOCKWASHERS (12) and the screws (11).
19 TORQUE the screws (11) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. Do not safety the screws (11) with the lockwashers (12) at this time. (5) Measure clearance G between the cockpit door (3) and the safety angle (22).
(a) Make sure that clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(b) Make sure that the tenon of the center latch mechanism always touches the catch of the center electrical release-strike during this measurement.
(c) If clearance G is not correct, adjust the position of the center electrical release-strike (refer to Para. 4.B.).
(6) Measure distances K and L between the cockpit wall panel (1) and the safety angles (21) and (22).
(7) If distances K (13.00 mm (0.5118 in.) maximum) and L (9.00 mm (0.3543 in.) maximum) are not correct or the cockpit wall panel (1) is not parallel to the cockpit door (3) (up/down), do the steps that follow:
(a) Release the lockwashers (18) from the screws (19).
(b) Hold the cockpit wall panel (1) and remove the screws (19), the lockwashers (18) and the plates (30).
(c) Discard the lockwashers (18).
(d) Install the plates (30), the new AIPC 53-14-81-01-080 LOCKWASHERS (18) and the screws (19). Do not tighten the screws (19) at this time.
(e) If the cockpit wall panel (1) and the cockpit door (3) are not parallel (up/down), do the steps that follow:
1 If you did not install new lockwashers (6) in step (4)(c), do the steps that follow:
a Release the lockwashers (6) from the screws (5).
b Hold the cockpit wall panel (1) and remove the screws (5), the lockwashers (6) and the plates (29).
c Discard the lockwashers (6).
d Attach the cockpit wall panel (1) to the lavatory sidewall (2) with the bracket (31), the plates (29), the new AIPC 53-14-81-01-080 LOCKWASHERS (6) and the screws (5). Do not tighten the screws (5) at this time.
2 If you installed new lockwashers (6) in step (4)(c), do the step that follows:
a Hold the cockpit wall panel (1) and loosen the screws (5).
3 Move the cockpit wall panel (1) in the up or down direction until it is parallel to the cockpit door (3). Make sure that dimension A is correct and between 4 mm (0.157 in.) and 5.5 mm (0.217 in.).
(f) If distances K and L are not correct, do the step that follows:
1 Move the cockpit wall panel (1) in a lateral direction until distances K ( 13.00 mm (0.5118 in.) maximum) and L ( 9.00 mm (0.3543 in.) maximum) are correct.
(g) If necessary, TORQUE the screws (5) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. (h) TORQUE the screws (19) to between 3.08 and 2.52 m.N (27.26 and 22.30 lbf.in )
. (8) Safety the screws (5), (11) and (19):
(a) Safety the screws (5) with the lockwashers (6).
(b) Safety the screws (11) with the lockwashers (12).
(c) Safety the screws (19) with the lockwashers (18).
(9) Make sure that the self-adhesive foam tape (23) is in the correct condition.
(10) If the self-adhesive foam tape (23) is not in the correct condition, do the steps that follow:
(a) Remove the defective self-adhesive foam tape (23).
(b) Clean the contact surface with Non Aqueous Cleaner-General - - (Material No.08BAA9) and the Textile-Lint free Cotton - (Material No.14SBA1) .
(c) Install the new self-adhesive foam tape (23) Sealing Profile-- Silicone Foam - (Material No.14JAB1) in position with the correct width and thickness.
B. Adjustment of the Electrical Release Strikes
(2) Get access to the upper, center and lower electrical release-strikes as follows:
(a) Open the cockpit door (2).
(b) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(c) Remove the screws (18) and the covers (17) from the housings (16).
(d) Temporarily install the safety angle (14) with the screws (19) on the lavatory wall (15).
(3) Close the cockpit door (2) and make sure that it touches the safety angle (14).
(4) Adjust the clearance J between the latch tenon (22) and the catch (23) of the center electrical release strike (21) as follows:
(a) Measure the clearance J between the latch tenon (22) and the catch (23) of the center electrical release strike (21).
(b) Make sure that the clearance J is between 0.5 mm (0.020 in.) and 1.0 mm (0.039 in.).
(c) If the clearance J is not in the limits, adjust the center electrical release strike (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (24).
3 Add a short aluminum shim (25) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release strike (21).
4 Make sure that the clearance J between the cockpit door (2) and the safety angle (14) is correct.
5 If not, remove the long aluminum shim (24) and add a second short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
6 Make sure that the clearance J is correct.
(5) Adjust the clearance H between the latch tenon (22) and the catch (23) of the upper and lower electrical release-strikes (21) as follows:
(a) Measure the clearance H between the latch tenon (22) and the catch (23) of the upper and lower electrical release-strikes (21).
(b) Make sure that the clearance H is between 1.0 mm (0.039 in.) and 1.5 mm (0.059 in.).
(c) If the clearance H is not in the limits, adjust the upper and lower electrical release-strikes (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove the long aluminum shim (24) with a thickness of 1.0 mm (0.039 in.) and add a short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
3 Make sure that the clearance H is correct.
4 If not, remove the long aluminum shim (24) and add a second short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
5 Make sure that the clearance H is correct.
(6) Install the access covers (17) as follows:
(a) Remove the screws (19) and the safety angle (14) from lavatory wall (15).
(b) Install the access covers (17) with the screws (18) on the housings (16).
(c) Install the safety angle (14) on the lavatory wall (15) as follows:
1 Apply a small amount of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) to the threads of the screws (19).
2 Install the safety angle (14) with the screws (19).
Subtask 52-51-00-820-051-B ** ON A/C NOT FOR ALL NOTE: The subsequent adjustment is only possible, when the nose of the electrical release-strike housing has been reworked.
(1) If it is necessary to rework the nose of the housing (16), refer to Figure 502. Then apply a layer of Surface Pretreatment-Light Alloys Chemical Conversion Yellow - (Material No.10ABC1) to the reworked surface. (2) Get access to the upper, center and lower electrical release-strikes as follows:
(a) Open the cockpit door (2).
(b) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(c) Remove the screws (18) and the covers (17) from the housings (16).
(d) Temporarily install the safety angle (14) with the screws (19) on the lavatory wall (15).
(3) Close the cockpit door (2) and make sure that it touches the safety angle (14).
(4) Adjust the clearance J between the latch tenon (22) and the catch (23) of the center electrical release strike (21) as follows:
(a) Measure the clearance J between the latch tenon (22) and the catch (23) of the center electrical release strike (21).
(b) Make sure that the clearance J is between 0.5 mm (0.020 in.) and 1.0 mm (0.039 in.).
(c) If the clearance J is not in the limits, adjust the center electrical release strike (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (24).
3 Add a short aluminum shim (25) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release strike (21).
4 Make sure that the clearance J between the cockpit door (2) and the safety angle (14) is correct.
5 If not, remove the long aluminum shim (24) and add a second short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
6 Make sure that the clearance J is correct.
(5) Adjust the clearance H between the latch tenon (22) and the catch (23) of the upper and lower electrical release-strikes (21) as follows:
(a) Measure the clearance H between the latch tenon (22) and the catch (23) of the upper and lower electrical release-strikes (21).
(b) Make sure that the clearance H is between 1.0 mm (0.039 in.) and 1.5 mm (0.059 in.).
(c) If the clearance H is not in the limits, adjust the upper and lower electrical release-strikes (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove the long aluminum shim (24) with a thickness of 1.0 mm (0.039 in.) and add a short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
3 Make sure that the clearance H is correct.
4 If not, remove the long aluminum shim (24) and add a second short aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
5 Make sure that the clearance H is correct.
(6) Install the access covers (17) as follows:
(a) Remove the screws (19) and the safety angle (14) from lavatory wall (15).
(b) Install the access covers (17) with the screws (18) on the housings (16).
(c) Install the safety angle (14) on the lavatory wall (15) as follows:
1 Apply a small amount of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) to the threads of the screws (19).
2 Install the safety angle (14) with the screws (19).
B. Adjustment of the Electrical Release Strikes
Cockpit Door - Adjustment ** ON A/C NOT FOR ALL
Cockpit Door - Adjustment ** ON A/C NOT FOR ALL
Cockpit Door - Adjustment ** ON A/C NOT FOR ALL
Electrical Release Strikes - Access ** ON A/C NOT FOR ALL
Electrical Release Strikes - Access ** ON A/C NOT FOR ALL
Electrical Release Strikes - Adjustment ** ON A/C NOT FOR ALL
Electrical Release Strikes - Adjustment ** ON A/C NOT FOR ALL
(1) Get access to the upper, center and lower electrical release-strikes (21) as follows:
(a) Open the cockpit door (2).
(b) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(c) Remove the screws (18) and the covers (17) from the housings (16).
(d) Temporarily install the safety angle (14) with the screws (19) on the lavatory wall (15).
(e) Close the cockpit door (2).
(2) Make sure that the latch tenon (22) touches the catch (23) of the center electrical release-strike (21).
(3) Adjust the clearance G between the cockpit door (2) and the safety angle (14) as follows:
(a) Measure the clearance G between the cockpit door (2) and the safety angle (14).
(b) Make sure that the clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(c) If the clearance G is more than the limits, adjust the center electrical release-strike (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (25).
3 Add a short aluminum shim (28) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release-strike (21).
4 Make sure that the clearance G between the cockpit door (2) and the safety angle (14) is correct.
(d) If the latch tenon (22) does not engage with the catch (23), adjust the center electrical release-strike (21) as follows (movement in the forward direction):
1 Open the cockpit door.
2 Replace the short aluminum shim (27) with a thickness of 2.0 mm (0.079 in.) with a short aluminum shim (28) with a thickness of 1.0 mm (0.039 in.).
3 Add a long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
4 Make sure that the latch tenon (22) engages correctly with the catch (23).
5 If the latch tenon (22) does not engage correctly with the catch (23):
(4) Adjust the clearance H between the catch (23) of the upper and lower electrical release-strikes (21) and the latch tenons (22) as follows:
(a) Measure the clearance H between the catch (23) of the upper and lower electrical release-strikes (21) and the latch tenons (22).
(b) Make sure that the clearance H is between 0.5 mm (0.020 in.) and 1.5 mm (0.059 in.).
(c) If the clearance H is not in the limits, adjust the upper and lower electrical release-strikes (21) as follows (movement in the rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (25).
3 Add a short aluminum shim (28) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release-strike (21).
4 Make sure that the clearance H is correct.
(d) If the latch tenon (22) does not engage with the catch (23), adjust the upper and lower electrical release-strikes (21) as follows (movement in the forward direction):
1 Open the cockpit door.
2 Replace the short aluminum shim (27) with a thickness of 2.0 mm (0.079 in.) with a short aluminum shim (28) with a thickness of 1.0 mm (0.039 in.).
3 Add a long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
4 Make sure that the clearance H is correct.
5 If the clearance H is not correct:
(a) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(b) Install the access covers (17) with the screws (18) on the housings (16).
(c) Install the safety angle (14) on the lavatory wall (15) as follows:
1 Apply a small amount of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) to the threads of the screws (19).
2 Install the safety angle (14) with the screws (19).
Subtask 52-51-00-820-052-A ** ON A/C NOT FOR ALL Cockpit Door - Adjustment ** ON A/C NOT FOR ALL Cockpit Door - Adjustment ** ON A/C NOT FOR ALL Cockpit Door - Adjustment ** ON A/C NOT FOR ALL Electrical Release Strikes - Access ** ON A/C NOT FOR ALL Electrical Release Strikes - Access ** ON A/C NOT FOR ALL Electrical Release Strikes - Adjustment ** ON A/C NOT FOR ALL Electrical Release Strikes - Adjustment ** ON A/C NOT FOR ALL (a) Open the cockpit door (2).
(b) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(c) Remove the screws (18) and the covers (17) from the housings (16).
(d) Temporarily install the safety angle (14) with the screws (19) on the lavatory wall (15).
(e) Close the cockpit door (2).
(2) Make sure that the latch tenon (22) touches the catch (23) of the center electrical release-strike (21).
(3) Adjust the clearance G between the cockpit door (2) and the safety angle (14) as follows:
(a) Measure the clearance G between the cockpit door (2) and the safety angle (14).
(b) Make sure that the clearance G is between 0.5 mm (0.020 in.) and 3.0 mm (0.118 in.).
(c) If the clearance G is more than the limits, adjust the center electrical release-strike (21) as follows (movement in rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (25).
3 Add a short aluminum shim (28) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release-strike (21).
4 Make sure that the clearance G between the cockpit door (2) and the safety angle (14) is correct.
(d) If the latch tenon (22) does not engage with the catch (23), adjust the center electrical release-strike (21) as follows (movement in the forward direction):
1 Open the cockpit door.
2 Replace the short aluminum shim (27) with a thickness of 2.0 mm (0.079 in.) with a short aluminum shim (28) with a thickness of 1.0 mm (0.039 in.).
3 Add a long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
4 Make sure that the latch tenon (22) engages correctly with the catch (23).
5 If the latch tenon (22) does not engage correctly with the catch (23):
- remove the short aluminum shim (28) and add a second long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
(4) Adjust the clearance H between the catch (23) of the upper and lower electrical release-strikes (21) and the latch tenons (22) as follows:
(a) Measure the clearance H between the catch (23) of the upper and lower electrical release-strikes (21) and the latch tenons (22).
(b) Make sure that the clearance H is between 0.5 mm (0.020 in.) and 1.5 mm (0.059 in.).
(c) If the clearance H is not in the limits, adjust the upper and lower electrical release-strikes (21) as follows (movement in the rear direction):
1 Open the cockpit door.
2 Remove one of the long aluminum shims (25).
3 Add a short aluminum shim (28) with a thickness of 1 mm (0.039 in.) between the spring pack (26) and the center electrical release-strike (21).
4 Make sure that the clearance H is correct.
(d) If the latch tenon (22) does not engage with the catch (23), adjust the upper and lower electrical release-strikes (21) as follows (movement in the forward direction):
1 Open the cockpit door.
2 Replace the short aluminum shim (27) with a thickness of 2.0 mm (0.079 in.) with a short aluminum shim (28) with a thickness of 1.0 mm (0.039 in.).
3 Add a long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
4 Make sure that the clearance H is correct.
5 If the clearance H is not correct:
- remove the short aluminum shim (28) and add a second long aluminum shim (25) with a thickness of 1.0 mm (0.039 in.).
(a) Remove the screws (19) and the safety angle (14) from the lavatory wall (15).
(b) Install the access covers (17) with the screws (18) on the housings (16).
(c) Install the safety angle (14) on the lavatory wall (15) as follows:
1 Apply a small amount of Threadlocking Adhesive-- Medium strength - (Material No.05BAE1) to the threads of the screws (19).
2 Install the safety angle (14) with the screws (19).
C. Adjustment of the Latch Mechanisms
(1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (37) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.0 mm (0.118 in.) and 4.00 mm (0.1575 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position.
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the plugs (44) from the screws (43).
2 Loosen the screws (43) and move the center latch mechanism (37) until dimension Q is correct.
3 Tighten the screws (43).
4 Install the plugs (44).
(5) Adjust dimension Q of the upper and lower latch mechanisms (38) as follows:
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (35) and (36) as follows:
a Remove the plug fasteners (34) from the rod covers (35) and (36).
b Remove the plugs (31) from the screws (32).
c Remove the screws (32) and the washers (33) from the rod covers (35) and (36).
d Remove the rod covers (35) and (36) from the cockpit door (2).
3 Loosen the locknuts (41) at each end of the connection rods (42).
4 Turn the connection rods (42) to adjust the latch tenons (22) correctly.
6 Safety the locknuts (41) with the14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
7 Install the rod covers (35) and (36) as follows:
a Put the rod covers (35) and (36) in position and attach them with the screws (32), the washers (33) and the plug fasteners (34).
b Install the plugs (31) on the screws (32).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
Subtask 52-51-00-820-052-B ** ON A/C NOT FOR ALL (1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (37) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.0 mm (0.118 in.) and 4.00 mm (0.1575 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position.
NOTE: This makes sure that the latch tenon (22) does not touch the access cover (17) during the flight.
(4) Adjust dimension Q of the center latch mechanism (37) as follows: NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the center electrical release-strike (21).
(a) Measure dimension Q of the center latch mechanism (37). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the plugs (44) from the screws (43).
2 Loosen the screws (43) and move the center latch mechanism (37) until dimension Q is correct.
3 Tighten the screws (43).
4 Install the plugs (44).
(5) Adjust dimension Q of the upper and lower latch mechanisms (38) as follows:
NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the upper and lower electrical release-strike (21).
(a) Measure dimension Q of the upper and lower latch mechanisms (38). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (35) and (36) as follows:
a Remove the plug fasteners (34) from the rod covers (35) and (36).
b Remove the plugs (31) from the screws (32).
c Remove the screws (32) and the washers (33) from the rod covers (35) and (36).
d Remove the rod covers (35) and (36) from the cockpit door (2).
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
2 Cut and remove the lockwire from the locknuts (41) and the safety device (40).3 Loosen the locknuts (41) at each end of the connection rods (42).
4 Turn the connection rods (42) to adjust the latch tenons (22) correctly.
NOTE: The connection rods (42) have a right thread at one end and a left thread at the other end for their adjustment.
5 Tighten the locknuts (41).6 Safety the locknuts (41) with the
7 Install the rod covers (35) and (36) as follows:
a Put the rod covers (35) and (36) in position and attach them with the screws (32), the washers (33) and the plug fasteners (34).
b Install the plugs (31) on the screws (32).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
NOTE: The rear face of each latch tenon has three arrow marks. If you can see only the last (inboard) arrow mark with the cockpit door closed, then their adjustment is correct.
C. Adjustment of the Latch Mechanisms
(1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (50) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in their fully closed positions before the center latch tenon engages.
(3) Adjust the clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure the clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that the clearance P is between 5.5 mm (0.217 in.) and 7.5 mm (0.295 in.).
(c) If the clearance P is not in the limits, adjust the upper clearance A of the cockpit door again (refer to para. A.)
(d) Make sure that the cockpit door is in its highest possible position and the clearance P in its given limits. This makes sure that the latch tenon (22) does not touch the access cover (17) during the flight.
(4) Adjust the dimension Q of the center latch mechanism (50) as follows:
(b) Make sure that the dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If the dimension Q of center latch mechanism (50) is not correct, adjust it as follows:
1 Remove the plugs (47) from the screws (49).
2 Loosen the screws (49) and move the center latch mechanism (50) until the dimension Q is correct.
3 Tighten the screws (49) and install the plugs (47).
(5) Adjust the dimensions Q of the top and lower latch mechanisms (47) as follows.
(b) Make sure that the dimensions Q are between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If the dimensions Q are not correct, adjust them as follows:
a Remove the caps (31), (35) and (39) from the screws (32), (36) and (40).
b Remove the screws (32), (36) and (40) with the washers (33), (37) and (41) from the rod covers (34) and (38).
c Disconnect the rod covers (34) and (38) from the cockpit door (2).
2 Cut and remove the lockwire from the jam nuts (46) and the safety device (45).
3 Loosen the jam nuts (46) at each end of the connection rods (44).
4 Turn the connection rods (44) to adjust the latch tenons (22) correctly.
.
6 Safety the jam nuts (46) with the14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
7 Install the covers (34) and (38) as follows:
a Put the rod covers (34) and (38) in their installation position on the cockpit door (2).
b Make sure that the mounting holes of the rod covers (34) and (38) align with the attachment holes of the mounting block (42).
c Attach the rod covers (34) and (38) with the screws (32), (36) and (40) and the washers (33), (37) and (41).
d Install the caps (31), (35) and (39) on the screws (32), (36) and (40).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
Subtask 52-51-00-820-052-C ** ON A/C NOT FOR ALL (1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (50) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in their fully closed positions before the center latch tenon engages.
(3) Adjust the clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure the clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that the clearance P is between 5.5 mm (0.217 in.) and 7.5 mm (0.295 in.).
(c) If the clearance P is not in the limits, adjust the upper clearance A of the cockpit door again (refer to para. A.)
(d) Make sure that the cockpit door is in its highest possible position and the clearance P in its given limits. This makes sure that the latch tenon (22) does not touch the access cover (17) during the flight.
(4) Adjust the dimension Q of the center latch mechanism (50) as follows:
NOTE: The dimension Q is used to make sure that the latch tenon (22) engages correctly with the catch (23) of the center electrical release-strike (21).
(a) Measure the dimension Q of the center latch mechanism (50). (b) Make sure that the dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If the dimension Q of center latch mechanism (50) is not correct, adjust it as follows:
1 Remove the plugs (47) from the screws (49).
2 Loosen the screws (49) and move the center latch mechanism (50) until the dimension Q is correct.
3 Tighten the screws (49) and install the plugs (47).
(5) Adjust the dimensions Q of the top and lower latch mechanisms (47) as follows.
NOTE: The dimension Q is used to make sure that the latch tenon (22) engages correctly with the catch (23) of the upper and lower electrical release-strike (21).
(a) Measure the dimensions Q of the top and lower latch mechanisms (47). (b) Make sure that the dimensions Q are between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If the dimensions Q are not correct, adjust them as follows:
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
CAUTION:
USE THE DOUBLE WRENCHING PROCEDURE TO TORQUE THE JAM NUTS. USE ONE WRENCH ON THE JAM NUT AND A SECOND WRENCH ON THE ROD. ALSO MAKE SURE THAT YOU DO NOT APPLY TOO MUCH TORQUE TO THE JAM NUTS. IF YOU DO NOT USE THIS PROCEDURE, THE APPLIED TORQUE CAN TWIST THE BELL CRANK. IF YOU APPLY TOO MUCH TORQUE, THE BELL CRANK WILL BREAK.
1 Remove the two rod covers (34) and (38) as follows: a Remove the caps (31), (35) and (39) from the screws (32), (36) and (40).
b Remove the screws (32), (36) and (40) with the washers (33), (37) and (41) from the rod covers (34) and (38).
c Disconnect the rod covers (34) and (38) from the cockpit door (2).
2 Cut and remove the lockwire from the jam nuts (46) and the safety device (45).
3 Loosen the jam nuts (46) at each end of the connection rods (44).
4 Turn the connection rods (44) to adjust the latch tenons (22) correctly.
NOTE: The connection rods (44) have a right-hand thread at one end and a left-hand thread at the other end. Therefore you can adjust their length if you turn the rod body.
5 Torque the jam nuts (46) against the rod body to between 0.374 and 0.306 m.daN (33.10 and 27.08 lbf.in ) . 6 Safety the jam nuts (46) with the
7 Install the covers (34) and (38) as follows:
a Put the rod covers (34) and (38) in their installation position on the cockpit door (2).
b Make sure that the mounting holes of the rod covers (34) and (38) align with the attachment holes of the mounting block (42).
c Attach the rod covers (34) and (38) with the screws (32), (36) and (40) and the washers (33), (37) and (41).
d Install the caps (31), (35) and (39) on the screws (32), (36) and (40).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
NOTE: The rear face of each latch tenon has three arrow marks. If you can see only the last (inboard) arrow mark with the cockpit door closed, then their adjustment is correct.
C. Adjustment of the Latch Mechanisms
(1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (50) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.00 mm (0.1181 in.) and 4.00 mm (0.1575 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position and clearance P in its given limits.
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q of the center latch mechanism (50) is not correct, adjust it as follows:
1 Remove the plugs (48) from the screws (49).
2 Loosen the screws (49) and move the center latch mechanism (50) until dimension Q is correct.
3 Tighten the screws (49).
4 Install the plugs (48).
(5) Adjust dimensions Q of the top and lower latch mechanisms (47) as follows.
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (34) and (38) as follows:
a Remove the caps (31), (35) and (39) from the screws (32), (36) and (40).
b Remove the screws (32), (36) and (40) and the washers (33), (37) and (41) from the rod covers (34) and (38).
c Disconnect the rod covers (34) and (38) from the cockpit door (2).
3 Loosen the jam nuts (45) at each end of the connection rods (44).
4 Turn the connection rods (44) to adjust the latch tenons (22) correctly.
.
6 Safety the jam nuts (46) with the14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
7 Install the rod covers (34) and (38) as follows:
a Put the rod covers (34) and (38) in their installation position on the cockpit door (2).
b Make sure that the mounting holes of the rod covers (34) and (38) align with the attachment holes of the mounting block (42).
c Install the washers (33), (37) and (41) and the screws (32), (36) and (40) on the rod covers (34) and (38).
d Install the caps (31), (35) and (39) on the screws (32), (36) and (40).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
Subtask 52-51-00-820-052-D ** ON A/C NOT FOR ALL (1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (50) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.00 mm (0.1181 in.) and 4.00 mm (0.1575 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position and clearance P in its given limits.
NOTE: This makes sure that the latch tenon (22) does not touch the access cover (17) during the flight.
(4) Adjust dimension Q of the center latch mechanism (50) as follows: NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the center electrical release-strike (21).
(a) Measure dimension Q of the center latch mechanism (37). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q of the center latch mechanism (50) is not correct, adjust it as follows:
1 Remove the plugs (48) from the screws (49).
2 Loosen the screws (49) and move the center latch mechanism (50) until dimension Q is correct.
3 Tighten the screws (49).
4 Install the plugs (48).
(5) Adjust dimensions Q of the top and lower latch mechanisms (47) as follows.
NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the upper and lower electrical release-strike (21).
(a) Measure dimension Q of the top and lower latch mechanisms (47). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (34) and (38) as follows:
a Remove the caps (31), (35) and (39) from the screws (32), (36) and (40).
b Remove the screws (32), (36) and (40) and the washers (33), (37) and (41) from the rod covers (34) and (38).
c Disconnect the rod covers (34) and (38) from the cockpit door (2).
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
2 Cut and remove the lockwire from the jam nuts (46) and the safety device (45).3 Loosen the jam nuts (45) at each end of the connection rods (44).
4 Turn the connection rods (44) to adjust the latch tenons (22) correctly.
NOTE: The connection rods (44) have a right thread at one end and a left thread at the other end for their adjustment.
CAUTION:
USE THE DOUBLE WRENCHING PROCEDURE TO TORQUE THE JAM NUTS. USE ONE WRENCH ON THE JAM NUT AND A SECOND WRENCH ON THE ROD. ALSO MAKE SURE THAT YOU DO NOT APPLY TOO MUCH TORQUE TO THE JAM NUTS. IF YOU DO NOT USE THIS PROCEDURE, THE APPLIED TORQUE CAN TWIST THE BELL CRANK. IF YOU APPLY TOO MUCH TORQUE, THE BELL CRANK WILL BREAK.
5 Torque the jam nuts (46) against the rod body to between 0.374 and 0.306 m.daN (33.10 and 27.08 lbf.in ) . 6 Safety the jam nuts (46) with the
7 Install the rod covers (34) and (38) as follows:
a Put the rod covers (34) and (38) in their installation position on the cockpit door (2).
b Make sure that the mounting holes of the rod covers (34) and (38) align with the attachment holes of the mounting block (42).
c Install the washers (33), (37) and (41) and the screws (32), (36) and (40) on the rod covers (34) and (38).
d Install the caps (31), (35) and (39) on the screws (32), (36) and (40).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
NOTE: The rear face of each latch tenon has three arrow marks. If you can see only the last (inboard) arrow mark with the cockpit door closed, then their adjustment is correct.
C. Adjustment of the Latch Mechanisms
(1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (37) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.00 mm (0.1181 in.) and 4.0 mm (0.157 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position.
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the plugs (44) from the screws (43).
2 Loosen the screws (43) and move the center latch mechanism (37) until dimension Q is correct.
3 Tighten the screws (43).
4 Install the plugs (44).
(5) Adjust dimension Q of the upper and lower latch mechanisms (38) as follows:
(b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (35) and (36) as follows:
a Remove the plug fasteners (34) from the rod covers (35) and (36).
b Remove the plugs (31) from the screws (32).
c Remove the screws (32) and the washers (33) from the rod covers (35) and (36).
d Remove the rod covers (35) and (36) from the cockpit door (2).
3 Loosen the locknuts (41) at each end of the connection rods (42).
4 Turn the connection rods (42) to adjust the latch tenons (22) correctly.
6 Safety the locknuts (41) with the14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
7 Install the rod covers (35) and (36) as follows:
a Put the rod covers (35) and (36) in position and attach them with the screws (32), the washers (33) and the plug fasteners (34).
b Install the plugs (31) on the screws (32).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
Subtask 52-51-00-720-054-A (1) Make sure that the cockpit door (2) is correctly closed and the D-ring of the center latch mechanism (37) stays in its recess.
(2) Make sure that the top and bottom latch tenons are in the fully closed position before the center latch tenon engages.
(3) Adjust clearance P between the latch tenon (22) and the slot of the access cover (17) as follows:
(a) Measure clearance P between the latch tenon (22) and the slot of the access cover (17).
(b) Make sure that clearance P is between 3.00 mm (0.1181 in.) and 4.0 mm (0.157 in.).
(c) If clearance P is not in the limits, adjust upper clearance A of the cockpit door again (refer to para. A.).
(d) Make sure that the cockpit door is in its highest possible position.
NOTE: This makes sure that the latch tenon (22) does not touch the access cover (17) during the flight.
(4) Adjust dimension Q of the center latch mechanism (37) as follows: NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the center electrical release-strike (21).
(a) Measure dimension Q of the center latch mechanism (37). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the plugs (44) from the screws (43).
2 Loosen the screws (43) and move the center latch mechanism (37) until dimension Q is correct.
3 Tighten the screws (43).
4 Install the plugs (44).
(5) Adjust dimension Q of the upper and lower latch mechanisms (38) as follows:
NOTE: Dimension Q is used to make sure that the latch tenon (22) engages correctly in the catch (23) of the upper and lower electrical release-strike (21).
(a) Measure dimension Q of the upper and lower latch mechanisms (38). (b) Make sure that dimension Q is between 7.0 mm (0.276 in.) and 9.0 mm (0.354 in.).
(c) If dimension Q is not correct, adjust it as follows:
1 Remove the rod covers (35) and (36) as follows:
a Remove the plug fasteners (34) from the rod covers (35) and (36).
b Remove the plugs (31) from the screws (32).
c Remove the screws (32) and the washers (33) from the rod covers (35) and (36).
d Remove the rod covers (35) and (36) from the cockpit door (2).
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
2 Cut and remove the lockwire from the locknuts (41) and the safety device (40).3 Loosen the locknuts (41) at each end of the connection rods (42).
4 Turn the connection rods (42) to adjust the latch tenons (22) correctly.
NOTE: The connection rods (42) have a right thread at one end and a left thread at the other end for their adjustment.
5 Tighten the locknuts (41).6 Safety the locknuts (41) with the
7 Install the rod covers (35) and (36) as follows:
a Put the rod covers (35) and (36) in position and attach them with the screws (32), the washers (33) and the plug fasteners (34).
b Install the plugs (31) on the screws (32).
(6) Do a visual check for the correct adjustment of the three latch tenons (22).
NOTE: The rear face of each latch tenon has three arrow marks. If you can see only the last (inboard) arrow mark with the cockpit door closed, then their adjustment is correct.
D. Adjustment Check
(1) Make sure that there is no remaining load on the electrical release strikes when they are de-energized:
(a) In the cockpit, on the COCKPIT DOOR section of panel 119VU, set toggle switch 26MQ to the UNLOCK position.
(b) Make sure that the cockpit door is open.
(c) Turn each catch of the three electrical release strikes.
(3) Open the cockpit door again.
(a) Make sure that none of the catches of the three electrical release strikes automatically moves when the electrical release strikes are de-energized.
(b) If a minimum of one catch of the three electrical release strikes automatically moves, do the adjustment of the cockpit door again.
(4) In the cockpit, on the COCKPIT DOOR section of panel 119VU, set toggle switch 26MQ to the NORM position.
Subtask 52-51-00-865-063-A (1) Make sure that there is no remaining load on the electrical release strikes when they are de-energized:
(a) In the cockpit, on the COCKPIT DOOR section of panel 119VU, set toggle switch 26MQ to the UNLOCK position.
(b) Make sure that the cockpit door is open.
(c) Turn each catch of the three electrical release strikes.
NOTE: If you can turn the catches easily, then the electrical release strikes have no load.
(2) Close the cockpit door.(3) Open the cockpit door again.
(a) Make sure that none of the catches of the three electrical release strikes automatically moves when the electrical release strikes are de-energized.
(b) If a minimum of one catch of the three electrical release strikes automatically moves, do the adjustment of the cockpit door again.
(4) In the cockpit, on the COCKPIT DOOR section of panel 119VU, set toggle switch 26MQ to the NORM position.
E. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 52-51-00-710-053-A 5. Close-up| 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 |
Subtask 52-51-00-860-072-A
A. Put the aircraft back to the serviceable condition.
(1) Make sure that the cockpit door is open.
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
(1) Make sure that the cockpit door is open.
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).