DOC AIRBUS | AMM A320FInstallation of the Aft Cargo-Compartment Door
TASK 52-32-11-400-001-A
Installation of the Aft Cargo-Compartment Door
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 52-32-11-860-060-A
Subtask 52-32-11-910-050-B ** ON A/C NOT FOR ALL
Subtask 52-32-11-910-051-A
[Rev.10 from 2021]
2026.04.01 01:41:58 UTC
Installation of the Aft Cargo-Compartment Door
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
THIS PART IS A REMOVABLE STRUCTURAL COMPONENT (RSC), WHICH CAN BE MOVED BETWEEN AIRCRAFT. THUS IT CAN HAVE DIFFERENT OPERATION CONDITIONS AND A DIFFERENT LIFE RECORD (FLIGHT HOURS/FLIGHT CYCLES/CALENDAR) FROM THE AIRCRAFT IT IS INSTALLED ON OR REMOVED FROM. THE OPERATOR IS RESPONSIBLE FOR THE SPECIFIC TRACKING AND CONTINUED AIRWORTHINESS OF REMOVABLE STRUCTURAL COMPONENTS. INCORRECT MAINTENANCE OF THESE COMPONENTS CAN CAUSE A RISK FOR THE FLIGHT SAFETY.
ZONE: 826
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE |
| No specific | 1 | CRANE 200KG (440 LB) |
| No specific | Torque wrench: range to between 1.35 and 1.0 m.daN (119.47 and 88.50 lbf.in )  | |
| 98A52008509000 | 1 | SLING-UNIVERSAL,DOORS |
| 98D52307523000 | 1 | EXTRACTOR-HINGE PINS,CARGO DOOR |
| 98D52307524000 | 2 | STRUT-SUPPORT,CARGO DOORS |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03JCA9) | Silicone base Grease-Mechanisms and Seals - - |
| (Material No.06AAB1) | Polysulfide Sealant-General Purpose Fillet - |
| (Material No.06AAC1) | Polysulfide Sealant-General Purpose Interfay - |
| (Material No.12ABE2) | Corrosion Preventive Compound-Water Displacing Oily Film System |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 826 | AFT CARGO COMPARTMENT DOOR |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 17 | COTTER PIN | AIPC 52-36-04-08-080 |
| 17 | COTTER PIN | AIPC 52-36-84-40-080 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 11-00-00-400-022-A | Installation of the Hoisting-Point Cover Patches |
| TASK 12-22-52-640-017-A | Lubrication of the Forward or Aft Cargo-Compartment Door-Seal |
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 29-00-00-864-001-A | Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action |
| TASK 29-10-00-863-002-A | Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart |
| TASK 52-30-00-080-001-A | Removal of the Safety Support Equipment |
| TASK 52-30-00-480-001-A | Installation of the Safety Support Equipment |
| TASK 52-30-00-860-001-A | Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
| TASK 52-30-00-860-002-A | Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
| TASK 52-32-11-820-001-A | Adjustment of the AFT Cargo Compartment Door |
| TASK 52-32-11-820-004-A | Adjustment of the Door Opening Angle |
| TASK 52-32-24-400-001-A | Installation of the Wiring Harness |
| TASK 52-71-00-820-003-A | Adjustment of the Proximity Switches of the Cargo-Compartment Door Threshold |
| SRM 534611 | |
Subtask 52-32-11-860-060-A
A. Aircraft Maintenance Configuration
Installation of the Cargo Door Sling ** ON A/C NOT FOR ALL
Installation of the Cargo Door Sling ** ON A/C NOT FOR ALL
(1) Make sure that the ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the opened cargo door.
(2) Put a CRANE 200KG (440 LB) in position at the cargo door.
(3) Attach the hoisting sling to the replacement cargo door as follows:
(b) Attach the ring of the turnbuckles (7) to the hooks of the three-leg sling (8).
(c) Remove the self-adhesive disks(1) from the hoisting points (3).
(d) Remove the plastic cap (2) from the hoisting point (1).
(e) Install the ring bolts (5) with the rubber washers (4) in the hoisting points (3). Tighten the ring bolts (5) only with your hand.
(f) Attach the ropes (6) to the ring of the ring bolts (5).
(g) Attach the ends of the ropes (6) to the hooks of the turnbuckles (7).
(h) If necessary, adjust the length of the leg with the turnbuckle (7) until the three legs have the same length.
(i) Carefully operate the crane until the leg of the hoisting sling is under load.
(4) Make sure that the Yellow hydraulic system is depressurized and put it in the maintenance configuration.
(Ref. AMM TASK 29-00-00-864-001)
Subtask 52-32-11-865-063-A Installation of the Cargo Door Sling ** ON A/C NOT FOR ALL Installation of the Cargo Door Sling ** ON A/C NOT FOR ALL (2) Put a CRANE 200KG (440 LB) in position at the cargo door.
(3) Attach the hoisting sling to the replacement cargo door as follows:
NOTE: The hoisting sling of the cargo doors (PN 98A52008509040) is part of the 98A52008509000 SLING-UNIVERSAL,DOORS. The hoisting sling includes the three-leg sling (PN 98A52008509104), the turnbuckle (PN 98A52008509100), the rope (PN 98A52008509504) and the ring bolt (PN 98A52008509102).
(a) Attach the ring of the three-leg sling (8) to the crane. (b) Attach the ring of the turnbuckles (7) to the hooks of the three-leg sling (8).
(c) Remove the self-adhesive disks(1) from the hoisting points (3).
(d) Remove the plastic cap (2) from the hoisting point (1).
(e) Install the ring bolts (5) with the rubber washers (4) in the hoisting points (3). Tighten the ring bolts (5) only with your hand.
(f) Attach the ropes (6) to the ring of the ring bolts (5).
(g) Attach the ends of the ropes (6) to the hooks of the turnbuckles (7).
(h) If necessary, adjust the length of the leg with the turnbuckle (7) until the three legs have the same length.
(i) Carefully operate the crane until the leg of the hoisting sling is under load.
(4) Make sure that the Yellow hydraulic system is depressurized and put it in the maintenance configuration.
(Ref. AMM TASK 29-00-00-864-001)
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N30 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N31 |
| ** ON A/C ALL | |||
| 122VU | DOORS/CARGO | 1MJ | T12 |
| 123VU | Y HYD/ELEC/PUMP | 3802GX | AB06 |
| 123VU | Y HYD/ELEC/ELEC PUMP/NORM | 3801GX | AB03 |
Subtask 52-32-11-910-050-B ** ON A/C NOT FOR ALL
A. Preparation for Installation
(1) Clean the component interfaces and the adjacent area.
(2) Examine the door frame of the fuselage for the correct condition.
(3) Examine the bushes in the piano hinges of the fuselage for possible damage. If a repair is not possible, replace the applicable piano hinges halves.
(4) Make sure that the hinge pins (24) are clean and in the correct condition.
(5) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bushes of all piano hinges and to the hinge pins (24).
(6) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the countersink of the screws (31).
(7) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bolt (14).
Subtask 52-32-11-420-050-I ** ON A/C NOT FOR ALL (1) Clean the component interfaces and the adjacent area.
(2) Examine the door frame of the fuselage for the correct condition.
(3) Examine the bushes in the piano hinges of the fuselage for possible damage. If a repair is not possible, replace the applicable piano hinges halves.
(4) Make sure that the hinge pins (24) are clean and in the correct condition.
(5) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bushes of all piano hinges and to the hinge pins (24).
(6) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the countersink of the screws (31).
(7) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bolt (14).
B. Installation of the Cargo Door
(1) Put the replacement cargo door in its correct installation position. Make sure that you align the piano hinge halves of the cargo door with the piano hinge halves of the fuselage.
(2) Install the hinge pins (24) with 98D52307523000 EXTRACTOR-HINGE PINS,CARGO DOOR to connect the two parts of the piano hinge halves.
(3) Adjust the lateral clearances between the cargo door and the fuselage as follows:
(a) Make sure that the door locking handle is in the UNLOCKED position.
(b) Close the cargo door carefully with the CRANE 200KG (440 LB) and put the door locking handle in the LOCKED position.
(c) Make sure that the lateral clearances A thru F are correct.
(d) Measure the clearances K between the heads of the shouldered bushings in the piano hinge halves of the cargo door and the fuselage.
(e) Pull out the hinge pins (24) approximately 150 mm (5.906 in.) and install the washers (25), (26), (27) and (28) between FR57 and FR58. Refer to the subsequent table for the selection of the correct washers.
(5) Open the cargo door with the CRANE 200KG (440 LB) until the door opening angle is between 135 and 136 degrees.
(6) Install the 98D52307524000 STRUT-SUPPORT,CARGO DOORS to safety the opened cargo door (Ref. AMM TASK 52-30-00-480-001).
(7) Attach the end-fittings (30) with the screws (31) on the fuselage structure.
(8) Connect the door actuator (18) to the actuator attachment fittings (13) of the cargo door as follows:
(a) If removed, install the bushes (22) and (23) into the actuator attachment fitting (13).
(b) Put the eye-end of the door actuator (18) into the actuator attachment fitting (13) and install the bolt (14) with the washer (15).
(c) If you cannot install the bolt (14) easily, adjust the length of the door actuator (18) (Ref. AMM TASK 52-32-11-820-004).
(d) Install the washer (15) and the nut (16) on the bolt (14).
(e) TORQUE the nut (16) to between 1.35 and 1.0 m.daN (119.47 and 88.50 lbf.in ).
(f) Safety the nut (16) with the new AIPC 52-36-04-08-080 COTTER PIN (17).
(g) Install the bonding jumpers (10) with the bolts (12), the washers (11) and the nuts (9) at the actuator attachment fitting (13) (Ref. AMM TASK 20-28-00-912-802).
(9) Install wire harness 4613VB (21) to the ceiling lining and connect the connector (20) to the receptacle (19) (Ref. AMM TASK 52-32-24-400-001).
Subtask 52-32-11-910-050-C ** ON A/C NOT FOR ALL (1) Put the replacement cargo door in its correct installation position. Make sure that you align the piano hinge halves of the cargo door with the piano hinge halves of the fuselage.
(2) Install the hinge pins (24) with 98D52307523000 EXTRACTOR-HINGE PINS,CARGO DOOR to connect the two parts of the piano hinge halves.
(3) Adjust the lateral clearances between the cargo door and the fuselage as follows:
(a) Make sure that the door locking handle is in the UNLOCKED position.
(b) Close the cargo door carefully with the CRANE 200KG (440 LB) and put the door locking handle in the LOCKED position.
(c) Make sure that the lateral clearances A thru F are correct.
(d) Measure the clearances K between the heads of the shouldered bushings in the piano hinge halves of the cargo door and the fuselage.
(e) Pull out the hinge pins (24) approximately 150 mm (5.906 in.) and install the washers (25), (26), (27) and (28) between FR57 and FR58. Refer to the subsequent table for the selection of the correct washers.
| Table for the Selection of the Washers (Item 25 thru Item 28) |
| CLEARANCE K | ITEM 25 | ITEM26 | ITEM 27 | ITEM 28 | THICKNESS |
|---|---|---|---|---|---|
| 0.0 mm (0.000 in.) to 0.29 mm (0.011 in.) | - | - | - | - | - |
| 0.3 mm (0.012 in.) to 0.4 mm (0.016 in.) | 1 | - | - | - | 0.3 mm (0.012 in.) |
| 0.4 mm (0.016 in.) to 0.5 mm (0.020 in.) | - | 1 | - | - | 0.4 mm (0.016 in.) |
| 0.5 mm (0.020 in.) to 0.6 mm (0.024 in.) | - | - | 1 | - | 0.5 mm (0.020 in.) |
| 0.6 mm (0.024 in.) to 0.7 mm (0.028 in.) | 2 | - | - | _ | 0.6 mm (0.024 in.) |
| 0.7 mm (0.028 in.) to 0.8 mm (0.031 in.) | 1 | 1 | - | - | 0.7 mm (0.028 in.) |
| 0.8 mm (0.031 in.) to 0.9 mm (0.035 in.) | - | 2 | - | - | 0.8 mm (0.031 in.) |
| 0.9 mm (0.035 in.) to 1.0 mm (0.039 in.) | - | 1 | 1 | - | 0.9 mm (0.035 in.) |
| 1.0 mm (0.039 in.) to 1.1 mm (0.043 in.) | - | - | 2 | - | 1.0 mm (0.039 in.) |
| 1.1 mm (0.043 in.) to 1.2 mm (0.047 in.) | 1 | 2 | - | - | 1.1 mm (0.043 in.) |
| 1.2 mm (0.047 in.) to 1.3 mm (0.051 in.) | 1 | 1 | 1 | - | 1.2 mm (0.047 in.) |
| 1.3 mm (0.051 in.) to 1.4 mm (0.055 in.) | 1 | - | 2 | - | 1.3 mm (0.051 in.) |
| 1.4 mm (0.055 in.) to 1.5 mm (0.059 in.) | - | 1 | 2 | - | 1.4 mm (0.055 in.) |
| 1.5 mm (0.059 in.) to 1.6 mm (0.063 in.) | - | - | 3 | - | 1.5 mm (0.059 in.) |
| 1.6 mm (0.063 in.) to 1.7 mm (0.067 in.) | 2 | - | 2 | - | 1.6 mm (0.063 in.) |
| 1.7 mm (0.067 in.) to 1.8 mm (0.071 in.) | 1 | 1 | 2 | - | 1.7 mm (0.067 in.) |
| 1.8 mm (0.071 in.) to 1.9 mm (0.075 in.) | - | 2 | 2 | - | 1.8 mm (0.071 in.) |
| 1.9 mm (0.075 in.) to 2.0 mm (0.079 in.) | - | 1 | 3 | - | 1.9 mm (0.075 in.) |
| 2.0 mm (0.079 in.) to 2.1 mm (0.083 in.) | - | - | - | 1 | 2.0 mm (0.079 in.) |
| 2.1 mm (0.083 in.) to 2.2 mm (0.087 in.) | 2 | - | 3 | - | 2.1 mm (0.083 in.) |
| 2.2 mm (0.087 in.) to 2.3 mm (0.091 in.) | 1 | 1 | 3 | - | 2.2 mm (0.087 in.) |
| 2.3 mm (0.091 in.) to 2.4 mm (0.094 in.) | 1 | - | - | 1 | 2.3 mm (0.091 in.) |
| 2.4 mm (0.094 in.) to 2.5 mm (0.098 in.) | - | 1 | - | 1 | 2.4 mm (0.094 in.) |
| 2.5 mm (0.098 in.) to 2.6 mm (0.102 in.) | - | - | 1 | 1 | 2.5 mm (0.098 in.) |
| 2.6 mm (0.102 in.) to 2.7 mm (0.106 in.) | 2 | - | - | 1 | 2.6 mm (0.102 in.) |
| 2.7 mm (0.106 in.) to 2.8 mm (0.110 in.) | 1 | 1 | - | 1 | 2.7 mm (0.106 in.) |
| 2.8 mm (0.110 in.) to 2.9 mm (0.114 in.) | - | 2 | - | 1 | 2.8 mm (0.110 in.) |
| 2.9 mm (0.114 in.) to 3.0 mm (0.118 in.) | - | 1 | 1 | 1 | 2.9 mm (0.114 in.) |
NOTE: The THICKNESS column refers to the total thickness of the applicable washers in mm (in.).
(4) Install the hinge pins (24) again and make sure that the lateral clearances A thru F are correct. (5) Open the cargo door with the CRANE 200KG (440 LB) until the door opening angle is between 135 and 136 degrees.
(6) Install the 98D52307524000 STRUT-SUPPORT,CARGO DOORS to safety the opened cargo door (Ref. AMM TASK 52-30-00-480-001).
(7) Attach the end-fittings (30) with the screws (31) on the fuselage structure.
(8) Connect the door actuator (18) to the actuator attachment fittings (13) of the cargo door as follows:
(a) If removed, install the bushes (22) and (23) into the actuator attachment fitting (13).
(b) Put the eye-end of the door actuator (18) into the actuator attachment fitting (13) and install the bolt (14) with the washer (15).
(c) If you cannot install the bolt (14) easily, adjust the length of the door actuator (18) (Ref. AMM TASK 52-32-11-820-004).
(d) Install the washer (15) and the nut (16) on the bolt (14).
(e) TORQUE the nut (16) to between 1.35 and 1.0 m.daN (119.47 and 88.50 lbf.in )
. (f) Safety the nut (16) with the new AIPC 52-36-04-08-080 COTTER PIN (17).
(g) Install the bonding jumpers (10) with the bolts (12), the washers (11) and the nuts (9) at the actuator attachment fitting (13) (Ref. AMM TASK 20-28-00-912-802).
(9) Install wire harness 4613VB (21) to the ceiling lining and connect the connector (20) to the receptacle (19) (Ref. AMM TASK 52-32-24-400-001).
C. Preparation for Installation
(1) Clean the component interfaces and the adjacent area.
(2) Examine the door frame of the fuselage for the correct condition.
(3) Examine the bushes in the piano hinges of the fuselage for possible damage. If necessary, replace the applicable piano hinges halves.
(4) Make sure that the hinge pins (24) are clean and in the correct condition.
(5) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the countersink of the screws (31).
(6) Prepare the shims (29) as follows:
(a) Put the shims (29) and the end fitting (30) in position to the fuselage.
(b) Measure the offset between the end fittings (30) and the remaining piano hinge halves of the fuselage.
(c) Prepare the shims (29) until the end fittings (30) align with the remaining piano hinge halves.
(7) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bolt (14).
Subtask 52-32-11-420-050-C ** ON A/C NOT FOR ALL (1) Clean the component interfaces and the adjacent area.
(2) Examine the door frame of the fuselage for the correct condition.
(3) Examine the bushes in the piano hinges of the fuselage for possible damage. If necessary, replace the applicable piano hinges halves.
(4) Make sure that the hinge pins (24) are clean and in the correct condition.
(5) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the countersink of the screws (31).
(6) Prepare the shims (29) as follows:
(a) Put the shims (29) and the end fitting (30) in position to the fuselage.
(b) Measure the offset between the end fittings (30) and the remaining piano hinge halves of the fuselage.
(c) Prepare the shims (29) until the end fittings (30) align with the remaining piano hinge halves.
NOTE: A tolerance of 0.2 mm (0.008 in.) is permitted.
(d) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the mating surface of the shim (29) and the fuselage. (7) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) to the bolt (14).
D. Installation of the Cargo Door
(1) Put the replacement cargo door in its correct installation position. Make sure that you align the piano hinge halves of the cargo door with the piano hinge halves of the fuselage.
(2) Install the hinge pins (24) with the 98D52307523000 EXTRACTOR-HINGE PINS,CARGO DOOR to connect the two parts of the piano hinge halves.
(3) Adjust the lateral clearances between the cargo door and the fuselage as follows:
(a) Make sure that the door handle is in the UNLOCKED position.
(b) Close the cargo door carefully with the CRANE 200KG (440 LB) and put the door handle in the LOCKED position.
(c) Make sure that the lateral clearances A thru F are correct.
(d) Measure the clearances K between the heads of the shouldered bushings in the piano hinge halves of the cargo door and the fuselage.
(e) Pull out the hinge pins (24) until the shouldered bushings are free. Install the washers (25), (26), (27) and (28) between FR54 and FR55. Refer to the subsequent table for the selection of the correct washers.
(5) Open the cargo door with the CRANE 200KG (440 LB) until the door opening angle is between 135 and 136 degrees.
(6) Install the 98D52307524000 STRUT-SUPPORT,CARGO DOORS to safety the cargo door in open position (Ref. AMM TASK 52-30-00-480-001).
(7) Attach the end-fittings (30) and the related shims (29) with the screws (30) on the fuselage structure.
(8) Connect the door actuator (18) to the actuator attachment fittings (13) of the cargo door as follows:
(a) If removed, install the bushes (22) and (23) into the actuator attachment fittings (13).
(b) Put the eye-end of the door actuator (18) into the actuator attachment fitting (13). Install the bolt (14) with the washer (15).
(c) If you cannot install the bolt (14) easily, adjust the length of the door actuator (Ref. AMM TASK 52-32-11-820-004).
(d) Install the washer (15) and the nut (16) on the bolt (14).
(e) TORQUE the nut (16) to between 1.35 and 1.0 m.daN (119.47 and 88.50 lbf.in ).
(f) Safety the nut (16) with the new AIPC 52-36-04-08-080 COTTER PIN (17) or AIPC 52-36-84-40-080 COTTER PIN (17).
(g) Install the bonding jumpers (10) with the bolts (12), the washers (11) and the nuts (9) at the actuator attachment fitting (13) (Ref. AMM TASK 20-28-00-912-802).
(9) Install wire harness 4613VB (21) to the ceiling lining and connect the connector (20) to the receptacle (19) (Ref. AMM TASK 52-32-24-400-001).
Subtask 52-32-11-080-050-A (1) Put the replacement cargo door in its correct installation position. Make sure that you align the piano hinge halves of the cargo door with the piano hinge halves of the fuselage.
(2) Install the hinge pins (24) with the 98D52307523000 EXTRACTOR-HINGE PINS,CARGO DOOR to connect the two parts of the piano hinge halves.
(3) Adjust the lateral clearances between the cargo door and the fuselage as follows:
(a) Make sure that the door handle is in the UNLOCKED position.
(b) Close the cargo door carefully with the CRANE 200KG (440 LB) and put the door handle in the LOCKED position.
(c) Make sure that the lateral clearances A thru F are correct.
(d) Measure the clearances K between the heads of the shouldered bushings in the piano hinge halves of the cargo door and the fuselage.
(e) Pull out the hinge pins (24) until the shouldered bushings are free. Install the washers (25), (26), (27) and (28) between FR54 and FR55. Refer to the subsequent table for the selection of the correct washers.
| Table for the Selection of the Washers (Item 25 thru Item 28) |
| CLEARANCE K | ITEM 25 | ITEM26 | ITEM 27 | ITEM 28 | THICKNESS |
|---|---|---|---|---|---|
| 0.0 mm (0.000 in.) to 0.29 mm (0.011 in.) | - | - | - | - | - |
| 0.3 mm (0.012 in.) to 0.4 mm (0.016 in.) | 1 | - | - | - | 0.3 mm (0.012 in.) |
| 0.4 mm (0.016 in.) to 0.5 mm (0.020 in.) | - | 1 | - | - | 0.4 mm (0.016 in.) |
| 0.5 mm (0.020 in.) to 0.6 mm (0.024 in.) | - | - | 1 | - | 0.5 mm (0.020 in.) |
| 0.6 mm (0.024 in.) to 0.7 mm (0.028 in.) | 2 | - | - | - | 0.6 mm (0.024 in.) |
| 0.7 mm (0.028 in.) to 0.8 mm (0.031 in.) | 1 | 1 | - | - | 0.7 mm (0.028 in.) |
| 0.8 mm (0.031 in.) to 0.9 mm (0.035 in.) | - | 2 | - | - | 0.8 mm (0.031 in.) |
| 0.9 mm (0.035 in.) to 1.0 mm (0.039 in.) | - | 1 | 1 | - | 0.9 mm (0.035 in.) |
| 1.0 mm (0.039 in.) to 1.1 mm (0.043 in.) | - | - | 2 | - | 1.0 mm (0.039 in.) |
| 1.1 mm (0.043 in.) to 1.2 mm (0.047 in.) | 1 | 2 | - | - | 1.1 mm (0.043 in.) |
| 1.2 mm (0.047 in.) to 1.3 mm (0.051 in.) | 1 | 1 | 1 | - | 1.2 mm (0.047 in.) |
| 1.3 mm (0.051 in.) to 1.4 mm (0.055 in.) | 1 | - | 2 | - | 1.3 mm (0.051 in.) |
| 1.4 mm (0.055 in.) to 1.5 mm (0.059 in.) | - | 1 | 2 | - | 1.4 mm (0.055 in.) |
| 1.5 mm (0.059 in.) to 1.6 mm (0.063 in.) | - | - | 3 | - | 1.5 mm (0.059 in.) |
| 1.6 mm (0.063 in.) to 1.7 mm (0.067 in.) | 2 | - | 2 | - | 1.6 mm (0.063 in.) |
| 1.7 mm (0.067 in.) to 1.8 mm (0.071 in.) | 1 | 1 | 2 | - | 1.7 mm (0.067 in.) |
| 1.8 mm (0.071 in.) to 1.9 mm (0.075 in.) | - | 2 | 2 | - | 1.8 mm (0.071 in.) |
| 1.9 mm (0.075 in.) to 2.0 mm (0.079 in.) | - | 1 | 3 | - | 1.9 mm (0.075 in.) |
| 2.0 mm (0.079 in.) to 2.1 mm (0.083 in.) | - | - | - | 1 | 2.0 mm (0.079 in.) |
| 2.1 mm (0.083 in.) to 2.2 mm (0.087 in.) | 2 | - | 3 | - | 2.1 mm (0.083 in.) |
| 2.2 mm (0.087 in.) to 2.3 mm (0.091 in.) | 1 | 1 | 3 | - | 2.2 mm (0.087 in.) |
| 2.3 mm (0.091 in.) to 2.4 mm (0.094 in.) | 1 | - | - | 1 | 2.3 mm (0.091 in.) |
| 2.4 mm (0.094 in.) to 2.5 mm (0.098 in.) | - | 1 | - | 1 | 2.4 mm (0.094 in.) |
| 2.5 mm (0.098 in.) to 2.6 mm (0.102 in.) | - | - | 1 | 1 | 2.5 mm (0.098 in.) |
| 2.6 mm (0.102 in.) to 2.7 mm (0.106 in.) | 2 | - | - | 1 | 2.6 mm (0.102 in.) |
| 2.7 mm (0.106 in.) to 2.8 mm (0.110 in.) | 1 | 1 | - | 1 | 2.7 mm (0.106 in.) |
| 2.8 mm (0.110 in.) to 2.9 mm (0.114 in.) | - | 2 | - | 1 | 2.8 mm (0.110 in.) |
| 2.9 mm (0.114 in.) to 3.0 mm (0.118 in.) | - | 1 | 1 | 1 | 2.9 mm (0.114 in.) |
NOTE: The THICKNESS column refers to the total thickness of the applicable washers in mm (in.).
(4) Install the hinge pins (24) again and make sure that the lateral clearances A thru F are correct. (5) Open the cargo door with the CRANE 200KG (440 LB) until the door opening angle is between 135 and 136 degrees.
(6) Install the 98D52307524000 STRUT-SUPPORT,CARGO DOORS to safety the cargo door in open position (Ref. AMM TASK 52-30-00-480-001).
(7) Attach the end-fittings (30) and the related shims (29) with the screws (30) on the fuselage structure.
(8) Connect the door actuator (18) to the actuator attachment fittings (13) of the cargo door as follows:
(a) If removed, install the bushes (22) and (23) into the actuator attachment fittings (13).
(b) Put the eye-end of the door actuator (18) into the actuator attachment fitting (13). Install the bolt (14) with the washer (15).
(c) If you cannot install the bolt (14) easily, adjust the length of the door actuator (Ref. AMM TASK 52-32-11-820-004).
(d) Install the washer (15) and the nut (16) on the bolt (14).
(e) TORQUE the nut (16) to between 1.35 and 1.0 m.daN (119.47 and 88.50 lbf.in )
. (f) Safety the nut (16) with the new AIPC 52-36-04-08-080 COTTER PIN (17) or AIPC 52-36-84-40-080 COTTER PIN (17).
(g) Install the bonding jumpers (10) with the bolts (12), the washers (11) and the nuts (9) at the actuator attachment fitting (13) (Ref. AMM TASK 20-28-00-912-802).
(9) Install wire harness 4613VB (21) to the ceiling lining and connect the connector (20) to the receptacle (19) (Ref. AMM TASK 52-32-24-400-001).
E. Removal of the Hoisting Sling
(1) Remove the end of the ropes (6) from the hooks of the turnbuckles (7).
(2) Remove the ropes (6) from the rings of the ring bolts (5).
(3) Remove the rings of the turnbuckles (7) from the hooks of the three-leg sling (8).
(4) Remove the ring bolts (5) with the rubber washers (4) from the hoisting points (3).
(5) Remove the ring of the three-leg sling (8) from the crane.
(6) Install the plastic caps (2) into the hoisting points (3).
(7) Install the new self-adhesive disk (1) on the hoisting points (3) (Ref. AMM TASK 11-00-00-400-022).
Subtask 52-32-11-865-064-A (1) Remove the end of the ropes (6) from the hooks of the turnbuckles (7).
(2) Remove the ropes (6) from the rings of the ring bolts (5).
(3) Remove the rings of the turnbuckles (7) from the hooks of the three-leg sling (8).
(4) Remove the ring bolts (5) with the rubber washers (4) from the hoisting points (3).
(5) Remove the ring of the three-leg sling (8) from the crane.
(6) Install the plastic caps (2) into the hoisting points (3).
(7) Install the new self-adhesive disk (1) on the hoisting points (3) (Ref. AMM TASK 11-00-00-400-022).
F. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 52-32-11-860-061-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N30 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N31 |
| ** ON A/C ALL | |||
| 122VU | DOORS/CARGO | 1MJ | T12 |
| 123VU | Y HYD/ELEC/PUMP | 3802GX | AB06 |
| 123VU | Y HYD/ELEC/ELEC PUMP/NORM | 3801GX | AB03 |
G. Preparation for the Test
(1) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002).
(2) Lubricate the cargo door seal (Ref. AMM TASK 12-22-52-640-017).
Subtask 52-32-11-860-061-C ** ON A/C NOT FOR ALL (1) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002).
(2) Lubricate the cargo door seal (Ref. AMM TASK 12-22-52-640-017).
NOTE: For lubrication of the cargo door seal, refer to the latest revision of EASA AD 2021-0049.
(3) Remove the 98D52307524000 STRUT-SUPPORT,CARGO DOORS from the cargo door and the fuselage frames (Ref. AMM TASK 52-30-00-080-001).G. Preparation for the Test
(1) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002).
(2) Remove the 98D52307524000 STRUT-SUPPORT,CARGO DOORS from the cargo door and the fuselage frames (Ref. AMM TASK 52-30-00-080-001).
Subtask 52-32-11-710-050-A (1) Pressurize the Yellow hydraulic system (Ref. AMM TASK 29-10-00-863-002).
(2) Remove the 98D52307524000 STRUT-SUPPORT,CARGO DOORS from the cargo door and the fuselage frames (Ref. AMM TASK 52-30-00-080-001).
H. Operational Test of the Cargo Door
(1) Close the cargo door (Ref. AMM TASK 52-30-00-860-002) and make sure that it moves smoothly and easily.
(2) Make sure that the cargo door is correctly adjusted (Ref. AMM TASK 52-32-11-820-001).
(3) Make sure that the proximity switch 32WV of the cargo door is correctly adjusted (Ref. AMM TASK 52-71-00-820-003).
(4) Make sure that the cargo door seal is compressed around its length.
(5) Open the cargo door (Ref. AMM TASK 52-30-00-860-001) and make sure that it moves smoothly and easily.
5. Close-up(1) Close the cargo door (Ref. AMM TASK 52-30-00-860-002) and make sure that it moves smoothly and easily.
(2) Make sure that the cargo door is correctly adjusted (Ref. AMM TASK 52-32-11-820-001).
(3) Make sure that the proximity switch 32WV of the cargo door is correctly adjusted (Ref. AMM TASK 52-71-00-820-003).
(4) Make sure that the cargo door seal is compressed around its length.
(5) Open the cargo door (Ref. AMM TASK 52-30-00-860-001) and make sure that it moves smoothly and easily.
NOTE: Because of manufacturing tolerances, it is possible that the door structure shows signs of chafing at the door frame fittings.
It is possible that corrosion is caused as a result and this must be removed with the standard procedures SRM 534611.
It is possible that corrosion is caused as a result and this must be removed with the standard procedures SRM 534611.
Subtask 52-32-11-910-051-A
A. Put the aircraft back to the serviceable condition.
(1) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) around the end fittings (30).
(2) Apply Corrosion Preventive Compound-Water Displacing Oily Film System (Material No.12ABE2) to all components which have no other surface protection.
Subtask 52-32-11-410-056-A (1) Apply a bead of Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) around the end fittings (30).
(2) Apply Corrosion Preventive Compound-Water Displacing Oily Film System (Material No.12ABE2) to all components which have no other surface protection.
B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the cargo door (Ref. AMM TASK 52-30-00-860-002).
(3) Remove the access platform(s).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the cargo door (Ref. AMM TASK 52-30-00-860-002).
(3) Remove the access platform(s).