(7)
Make sure that the hinge pins (24) are clean and in the correct condition.
(8)
Apply COMMON GREASE (Material No. 04-011) to the bushes of all piano hinges and to the hinge pins (24).
(9)
Apply SEALANTS (Material No. 09-005) to the countersink of the screws (31).
(10) Prepare the shims (29) as follows:
(a)
Put the shims (29) and the end fitting (30) in posotion to the fuselage.
(b)
Measure the offset between the end fittings (30) and the remaining piano hinge halves of the fuselage.
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(c) Prepare the shims (29) until the end fittings (30) are align with the remaining piano hinge halves.
NOTE : A tolerance of 0.2 mm (0.0078 in.) is permitted.
____
(d) Apply SEALANTS (Material No. 09-005) to the mating surface of the shim (29) and the fuselage.
(11) Apply COMMON GREASE (Material No. 04-011) to the actuator bolt. Subtask 52-32-11-420-050-B
B. Installation of the Cargo Door
(1)
Move the replacement cargo door into its correct installation position.
(2)
Make sure that you align the piano hinge half of the cargo door with the piano hinge half of the fuselage.
(3)
Install the hinge pins (24) with EXTRACTOR - HINGE PINS, CARGO DOOR (98D52307523000) to connect both piano hinge halves.
(4)
Adjust the lateral gaps 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 and put the door locking handle in the LOCKED position.
(c)
Make sure that the lateral gaps 'A' thru 'D' are correct.
(d)
Measure the gaps 'G' between the piano hinge of the cargo door and the piano hinge of the fuselage.
(e)
Pull out the hinge pins (24) approximately 150 mm (5.9055 in.) and install the correct washers (25), (26), (27), (28). Refer to the subsequent table for the selection of the correct washers. Do this between FR54 and FR54A.
Table for Selection of Washers (Item 25 thru Item 28)
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R GAP 'G' IN mm (in.) | ITEM 25 | ITEM 26 | ITEM 27 | ITEM 28 | THICKNESS R --------------------------|---------|---------|---------|---------|------------
R 0.0 (0.000) - 0.3 (0.011) | -| -| -| _ | _ R 0.3 (0.011) - 0.4 (0.015) | 1 | -| -| _ | 0.3 (0.011) R 0.4 (0.015) - 0.5 (0.020) | -| 1 | -| _ | 0.4 (0.015) R 0.5 (0.020) - 0.6 (0.024) | -| -| 1 | _ | 0.5 (0.020) R 0.6 (0.024) - 0.7 (0.028) | 2 | -| -| _ | 0.6 (0.024) R 0.7 (0.028) - 0.8 (0.031) | 1 | 1 | -| _ | 0.7 (0.028) R 0.8 (0.031) - 0.9 (0.035) | -| 2 | -| _ | 0.8 (0.031) R 0.9 (0.035) - 1.0 (0.039) | -| 1 | 1 | _ | 0.9 (0.035) R 1.0 (0.039) - 1.1 (0.043) | -| -| 2 | _ | 1.0 (0.039) R 1.1 (0.043) - 1.2 (0.047) | 1 | 2 | -| _ | 1.1 (0.043) R 1.2 (0.047) - 1.3 (0.051) | 1 | 1 | 1 | _ | 1.2 (0.047) R 1.3 (0.051) - 1.4 (0.055) | 1 | -| 2 | _ | 1.3 (0.051) R 1.4 (0.055) - 1.5 (0.059) | -| 1 | 2 | _ | 1.4 (0.055) R 1.5 (0.059) - 1.6 (0.063) | -| -| 3 | _ | 1.5 (0.059) R 1.6 (0.063) - 1.7 (0.067) | 2 | -| 2 | _ | 1.6 (0.063) R 1.7 (0.067) - 1.8 (0.071) | 1 | 1 | 2 | _ | 1.7 (0.067) R 1.8 (0.071) - 1.9 (0.075) | -| 2 | 2 | _ | 1.8 (0.071) R 1.9 (0.075) - 2.0 (0.079) | -| 1 | 3 | _ | 1.9 (0.075) R 2.0 (0.079) - 2.1 (0.083) | -| -| -| 1 | 2.0 (0.079) R 2.1 (0.083) - 2.2 (0.087) | 2 | -| 3 | -| 2.1 (0.083) R 2.2 (0.087) - 2.3 (0.091) | 1 | 1 | 3 | -| 2.2 (0.087) R 2.3 (0.091) - 2.4 (0.095) | 1 | -| -| 1 | 2.3 (0.091) R 2.4 (0.095) - 2.5 (0.098) | -| 1 | -| 1 | 2.4 (0.095) R 2.5 (0.098) - 2.6 (0.102) | -| -| 1 | 1 | 2.5 (0.098) R 2.6 (0.102) - 2.7 (0.106) | 2 | -| -| 1 | 2.6 (0.102) R 2.7 (0.106) - 2.8 (0.110) | 1 | 1 | -| 1 | 2.7 (0.106) R 2.8 (0.110) - 2.9 (0.114) | -| 2 | -| 1 | 2.8 (0.110) R 2.9 (0.114) - 3.0 (0.118) | -| 1 | 1 | 1 | 2.9 (0.114)
R NOTE : The THICKNESS column refers the total thickness of the
____ R applicable washers in mm (in.) .
R (5) Install the hinge pins (24) again and make sure that the lateral gaps R 'A' thru 'D' are correct.
R (6) Open the cargo door with the crane until the door opening angle is R between 135 and 136 degrees.
R (7) Install the SUPPORT STRUT - CARGO DOORS (98D52307524000) to safety R the opened cargo door.
R (8) Remove the sling (5) from the cargo door.
R (9) Attach the end-fittings (30) and the related shims (29) with the R screws (31) to the fuselage structure.
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(10)
Connect the piston eye ends (18) to the actuator attachment fittings
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