1.0
(0.039) - 1.1 (0.043) | -| -| 2 | _ | 1.0 (0.039)
1.1 (0.043) - 1.2 (0.047) | 1 | 2 | -| _ | 1.1 (0.043)
1.2 (0.047) - 1.3 (0.051) | 1 | 1 | 1 | _ | 1.2 (0.047)
1.3 (0.051) - 1.4 (0.055) | 1 | -| 2 | _ | 1.3 (0.051)
1.4 (0.055) - 1.5 (0.059) | -| 1 | 2 | _ | 1.4 (0.055)
1.5 (0.059) - 1.6 (0.063) | -| -| 3 | _ | 1.5 (0.059)
1.6 (0.063) - 1.7 (0.067) | 2 | -| 2 | _ | 1.6 (0.063)
1.7 (0.067) - 1.8 (0.071) | 1 | 1 | 2 | _ | 1.7 (0.067)
1.8 (0.071) - 1.9 (0.075) | -| 2 | 2 | _ | 1.8 (0.071)
1.9
(0.075) - 2.0 (0.079) | -| 1 | 3 | _ | 1.9 (0.075)
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)
R 1EFF : 001-049, 053-099, 101-149, 201-299, 1 52-32-11Page 423 1301-399, 1May 01/05 1 1 1CES 1
GAP 'G' IN mm (in.) | ITEM 25 | ITEM 26 | ITEM 27 | ITEM 28 | THICKNESS --------------------------|---------|---------|---------|---------|------------
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 (30) to the fuselage structure.
(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 fittings (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).
R 1EFF : 001-049, 053-099, 101-149, 201-299, 1 52-32-11Page 424 1301-399, 1May 01/05 1 1 1CES 1
(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 051-052,
Subtask 52-32-11-910-050-B
A. Preparation for the Installation
NOTE : Remove the bonding jumpers (8) if damaged.
____ You do not have to replace the removed bonding jumpers (8).
(1)
Remove the bonding jumpers (8) from the cargo door.
(2)
Clean and paint the contact areas of the bonding jumpers (8) at the cargo door and fuselage side as required (Ref. TASK 52-32-11-100-001).
(3)
Install the bolts (6) and the washers (7) with SEALANTS (Material No. 09-013) into the cargo door and the upper fuselage.
(4)
Clean the component interface and/or the adjacent area.
(5)
Examine the door frame of the fuselage for the correct condition.
(6)
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.
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