2.0
 (0.079) - 2.1 (0.083) | -| -| -| 1 | 2.0 (0.079)

 2.1 (0.083) - 2.2 (0.087) | 2 | -| 3 | -| 2.1 (0.083)
 2.2 (0.087) - 2.3 (0.091) | 1 | 1 | 3 | -| 2.2 (0.087)
 2.3 (0.091) - 2.4 (0.095) | 1 | -| -| 1 | 2.3 (0.091)
 2.4 (0.095) - 2.5 (0.098) | -| 1 | -| 1 | 2.4 (0.095)
 2.5 (0.098) - 2.6 (0.102) | -| -| 1 | 1 | 2.5 (0.098)
 2.6 (0.102) - 2.7 (0.106) | 2 | -| -| 1 | 2.6 (0.102)
 2.7 (0.106) - 2.8 (0.110) | 1 | 1 | -| 1 | 2.7 (0.106)
 2.8 (0.110) - 2.9 (0.114) | -| 2 | -| 1 | 2.8 (0.110)
 2.9 (0.114) - 3.0 (0.118) | -| 1 | 1 | 1 | 2.9 (0.114)
 NOTE : The THICKNESS column refers the total thickness of the
____ applicable washers in mm (in.) .
 (5)
 Install the hinge pins (24) again and make sure that the lateral gaps 'A' thru 'D' are correct.

 (6)
 Open the cargo door with the crane until the door opening angle is between 135 and 136 degrees.

 (7)
 Install the SUPPORT STRUT - CARGO DOORS (98D52307524000) to safety the opened cargo door.

 (8)
 Remove the sling (5) from the cargo door.

 (9)
 Attach the end-fittings (30) and the related shims (29) with the screws (31) to the fuselage structure.

R 1EFF : 151-199, 401-499, 1 52-32-11Page 430 1 1 Aug 01/05 1 1 1CES 1

 (10)
 Connect the piston eye ends (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 piston eye end (18) to the actuator attachment fitting

 (13) and install the bolt (14) with the washer (15).

 (c)
 If you cannot install the bolt (14) easily, you must adjust the length of the door actuator (Ref. 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 1.0 and 1.35 m.daN (88.49 and

 119.46 lbf.in) and safety it with the new cotter pin (17).

 (f)
 Install the bonding jumpers (10) with the bolts (12), the washers

 (11) and the nuts (9) at the actuator attachment fitting (13) (Ref. TASK 20-28-00-912-004).

 (11)
 Install the wire harness 4613VB (21) to the ceiling lining and connect the connector (20) to the receptacle (19)(Ref. TASK 52-32-24-400-001).

 **ON A/C ALL
 Subtask 52-32-11-865-064
 C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1MJ, 3801GX, 3802GX, 3803GX
 Subtask 52-32-11-860-061
 D. Preparation for the Test
 (1)
 Pressurize the Yellow hydraulic system (Ref. TASK 29-10-00-863-002).

 (2)
 Remove the SUPPORT STRUT - CARGO DOORS (98D52307524000) from the cargo door.

 1EFF : ALL 1 52-32-11Page 431 1 1 May 01/05 1 1 1CES 1 Subtask 52-32-11-710-050

 E. Operational Test of the Cargo Door.
 (1)
 Close the cargo door (Ref. TASK 52-30-00-860-002).

 -Make sure that the cargo door closes smoothly and easily.

 (2)
 Make sure that the cargo door is correctly adjusted (Ref. TASK 52-32-11-820-001).

 (3)
 Make sure that the proximity switch 32WV of the cargo door is correctly adjusted (Ref. TASK 52-71-00-820-003).

 (4)
 Open the cargo door (Ref. TASK 52-30-00-860-001).

 -Make sure that the cargo door opens smoothly and easily.
 5. Close-up
________ Subtask 52-32-11-910-051
 A. Put the aircraft back to the serviceable condition.
 (1)
 Remove the hoisting lugs (2) from the cargo door and install the plastic caps again.

 (2)
 Apply a bead of SEALANTS (Material No. 09-016) around the end fittings (23).

 (3)
 Apply SPECIAL MATERIALS (Material No. 05-027) to all components which have no other surface protection.

 Subtask 52-32-11-410-056
 B. Close Access
 (1)
 Make sure that the work area is clean and clear of tool(s) and other items.

 (2)
 Close the cargo door (Ref. TASK 52-30-00-860-002).

 (3)
 Remove the access platform(s).

 1EFF : ALL 1 52-32-11Page 432 1 1 May 01/05 1 1 1CES 1 DOOR - CARGO COMPARTMENT - ADJUSTMENT/TEST

__________________________________________
 TASK 52-32-11-820-001
　
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