(2)
 Carefully disengage the VELCRO tapes and remove the insulation mat from the inner side of the door.

 1EFF : 301-399, 1 52-22-11Page 402 1 1 May 01/04 1 1 1CES 1 Subtask 52-22-11-860-050

 D. Aircraft Maintenance Configuration
 (1)
 Attach the SLING - PASSENGER DOOR (98A52108004001) as follows: (Ref. Fig. 401/TASK 52-22-11-991-001)

 (a)
 Attach the sling (5) to the crane, minimum capacity 90 kg (198.4 lb.), and put it in position at the door.

 (b)
 Remove and discard the self-adhesive patches (1) from the plastic plugs (2).

 (c)
 Remove the plastic plugs (2) from the hoist fittings (3) and install the hoisting lugs (4) with the eye-ends outboard.

 (d)
 Attach the fasteners (6) to the eye-ends of the hoisting lugs (4).

 (2)
 Operate the crane carefully to remove the weight of the door from the support arm.

 4. Procedure
_________ Subtask 52-22-11-020-051
 A. Removal of the applicable Door
 (1) Remove the wire harness (18) and the bonding straps (23) between the door and the fuselage frame as follows: (Ref. Fig. 402/TASK 52-22-11-991-002)
 (a) Disconnect the connector (14) of the wire harness (18) from the receptacle (13) of the fuselage strucutre (refer to the subsequent table):
 ----------------------------------------------------------| DOOR | CONNECTOR | RECEPTACLE | FRAME | CABLE LOOM | __________________________________________________________
 | FWD LH  | 2821VC-A  |  2821VC  | FR35  |  4251VB  |
 | FWD RH  | 2820VC-A  |  2820VC  | FR35  |  4250VB  |
 | AFT LH  | 6721VC-A  |  6721VC  | FR47.2|  4253VB  |
 | AFT RH  | 6720VC-A  |  6720VC  | FR47.2|  4252VB  |

 ----------------------------------------------------------
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 Attachment of the Sling
 Figure 401/TASK 52-22-11-991-001
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1  1  May 01/04
 1  1
 1CES  1

 INTENTIONALLY BLANK

 1 1
52-22-11Page 405
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 Electrical Components
 Figure 402/TASK 52-22-11-991-002- 12 (SHEET 1)

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 Electrical Components
 Figure 402/TASK 52-22-11-991-002- 22 (SHEET 2)

 1EFF : 301-399, 1 52-22-11Page 407 1 1 May 01/04 1 1 1CES 1

 (b)
 Remove the nuts (30), the washers (26), the screws (27), the spacers (28) and the clamps (25) from the fuselage structure (29).

 (c)
 Remove the nuts (17), the washers (16), the screws (20) and the clamps (19) from the support arm (15).

 (d)
 Disconnect the connector (11) of the wire harness (18) from the receptacle (12) of the door damper and emergency operation cylinder (referred to as door damper) (refer to the subsequent table):

 ---------------------------------------------------------| DOOR | CONNECTOR | DOOR DAMPER | FRAME | CABLE LOOM | _________________________________________________________
 | FWD LH | 360RH5-A  |  1600WM  | FR35  |  4251VB  |
 | FWD RH | 360RH6-A  |  1600WM  | FR35  |  4250VB  |
 | AFT LH | 360RH7-A  |  1600WM  | FR47.2|  4253VB  |
 | AFT RH | 360RH8-A  |  1600WM  | FR47.2|  4252VB  |

 ----------------------------------------------------------
(e)
 Temporarily attach the cable loom to the door structure.

 (f)
 Remove the nuts (24), the washers (24), the bolts (21) and the bonding straps (23) from the support arm (15).

 (2) Disconnect the upper and lower guide arms (35) and (36) from the guide fitting (33) of the door as follows: (Ref. Fig. 403/TASK 52-22-11-991-003)
 (a)
 Remove and discard the cotter pins (39) from the castle nuts (38).

 (b)
 Remove the castle nuts (38), the washers (32), the bush (37) and the bolt (31) from the guide fitting (33).

 (c)
 Disconnect the eye-ends of the guide arms (35) and (36) from the fork ends of the guide fitting (33).

 (d)
 Temporarily attach the guide arms (35) and (36) to the door frame.
　
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