(c)
Adjust latch cam fittings (2, detail B) vertically so that all latch rollers (9) enter latch cam fittings with equal clearance when door is operated to closed position. 1) Latch cam fittings are serrated. Loosen screw and move cam fitting up to
decrease clearance or down to increase clearance.
(d)
Install adjustable guide (21, detail E) on door and adjust position on serrated plate
(20) to allow engagement of centering guide pin (23) with centering guide track (3) on doorjamb.
(3)
Adjust the following to fair door with fuselage external profile.
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52-11-0 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/93
CAUTION: DO NOT CLOSE A NEW DOOR UNTIL DOOR HAS BEEN TRIMMED TO FIT IN DOOR OPENING. DOOR CLOSING AND SKIN TRIM MUST BE DONE SIMULTANEOUSLY.
NOTE: Measurements of flushness should only be made at points along straight sections between rounded corners of door skin. Measure between door outer skin and normal body outer skin surface. Measurements at skin splices must subtract additional skin and bonding film thickness.
(a)
Adjust forward and aft latch cam fittings (2) on serrated latch plates attached to doorjambs so that when door is closed and latched, outside surface of door along forward and aft edges is flush with fuselage external profile within the flushness requirements called out in Fig. 502.
NOTE: Each latch location has a different cam shape and it is necessary that when replacing any of the four fittings installed on the door, replacement fittings used are of same cam shape as existing ones.
(b)
Adjust upper and lower gate control rods (Fig. 501) so that with door closed and latched, outside surface of upper and lower gates are recessed below fuselage exterior profile as shown in Fig. 502.
NOTE: Lengthen the four gate stop rods as required to prevent interference with adjustment of gate control rods.
(c)
With door closed and latched, adjust the four gate stop rods by screwing rod end in until shoulder on rod just contacts bearing plate; then back off to nearest locking notch, tighten checknut and lockwire.
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Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-11-0 Page 506A
(4)
Adjust guide arm (10) length at rod end bearing (12) by removing guide arm attachment bolt (14) so that both fore and aft latch rollers (9) enter latch cam fittings (2) at same time when door is operated to closed position. Aft rollers may be allowed to lead forward rollers slightly to improve clearance on forward edge of door. Tighten rod end bearing checknut (11).
(a) On airplanes with keeper installed, make fine adjustment by removing keeper (11A) and loosen checknut (11). Rotate adjustment fitting. Tighten checknut and install keeper.
(5)
Check latch roller (9) engagement with latch cam fittings (2).
(a)
Latch rollers should engage latch cam fittings with no lateral interference between roller retainers and latch cam fittings.
(b)
Close and lock door and check that all latch rollers engage latch cam fitting surfaces.
(c)
Check that width of contact surface between latch roller and latch cam fitting is 0.25 inch minimum. 1) Add or subtract shims behind roller to obtain clearance.
(d)
Check that clearance between latch roller and latch cam fitting, when door is closed and locked, is as shown in view 1.
NOTE: The last two checks may be made by using modeling clay or any other approved method.
(e)
After adjusting upper forward latch fitting, recheck the operation of the door warning sensor (Ref 52-71-0 A/T).
(6)
With door closed and latched, screw door stop pins (1, Detail A) out until they just contact frame stop buttons. Back off stop pins half a turn, then further to nearest locking groove and lock them with lock springs (5). Check that stop pins contact frame stop button within limits shown in section A-A. The check may be made by using modeling clay or any other approved method.
(7)
With door closed and latched, adjust length of pushrod (34, Detail F) so that it just fits between cocking crank (33) and torque tube crank (32). Then unlatch door, shorten pushrod by one-half turn of rod end bearing (35), tighten checknut and reinstall.
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500 Forward Entry Door Flushness Requirements
Feb 20/91 Figure 502 52-11-0
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 艙門 DOORS(25)
