(2)
If attach fitting (16) was removed from guide arm (14), connect attach fitting to guide arm rod end bearing (15) by means of guide arm attachment bolt (1).
(3)
Connect attach fitting (16) to hinge support (17) with four bolts.
CAUTION: ATTACH FITTING (16) IS NOT SYMMETRICAL. BE SURE FITTING (16) IS ORIENTED AS SHOWN IN FIG. 401 OR DAMAGE TO HINGE LINKAGE CAN RESULT.
500
Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-11-0 Page 405
C. At upper hinge, apply a coating of grease to the three necks of upper spigot (10) and a coating of corrosion preventive compound to body of upper spigot, assemble compression spring (11), retainer washer (12), and O-ring (13) on upper spigot (10).
D. Engage upper hinge arm (2) with radius links (6), line up hinge pin holes in roller guide plates (5), insert thrust washer (8) between radius links and hinge arm, fill cavity of upper spigot support housing with grease, then insert upper spigot (10). Tighten clamp bolt (7) on upper hinge arm. Wipe off excess grease.
NOTE: Ensure that reference marks on upper hinge arm and upper spigot are aligned.
E. Install snubber (24, detail B).
CAUTION: ATTACH FITTING (25) IS NOT SYMMETRICAL. BE SURE FITTING IS ORIENTED AS SHOWN IN FIG. 401 OR DAMAGE TO SNUBBER CAN RESULT DURING DOOR OPERATION.
CAUTION: INSTALL SNUBBER WITH LUBRICATION FITTINGS (28) ON ROD ENDS INBOARD AND FILLER PLUG SCREW OUTBOARD (27) AS SHOWN IN FIG. 401 OR DAMAGE TO EQUIPMENT CAN OCCUR.
(1)
If attach fitting (25) was removed from snubber (24), connect attach fitting to snubber by installing snubber attachment bolt (18).
(2)
If radius link (21) was removed from snubber (24), connect radius link to snubber by installing bolt (22), washers, nut, and cotter pin.
(3)
Engage radius link (21) with stop plates (20 ) and install attach fitting (25) to hinge support
(26) with four bolts.
F. At lower hinge, engage lower hinge arm (19) with radius link (21) and insert thrust washer (23). Line up hinge pin holes with holes in stop plates (20). Apply coating of grease to necks of spigot.
G. Install assist spring and torque tube (Ref 52-11-41, R/I).
H. If a new door was installed on airplane, install the following components on door.
(1)
Apply wet primer to attachment bolts. Install upper and lower hinge arm covers with attachment bolts.
(2)
Install stop pins on forward and aft edges of door.
NOTE: Install stop pins with thin coating of corrosion preventive compound on both internal and external surfaces of mating threads.
(3)
Install door seal (Ref 52-09-131, R/I).
I. Adjust and test door in accordance with adjustment/test procedures.
500
52-11-0 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
FORWARD ENTRY DOOR - ADJUSTMENT/TEST
1. General
A. This procedure contains an operational test to verify proper door operation in par. 1A. and an adjustment procedure in par. 2.
B. Paragraph 2 is the normal door installation adjustment procedure to be used when installing a new or overhauled door. Paragraph 3 is a special adjustment to be used to re-establish or verify proper overcenter of the door latch torque tubes if the door has been reported to have soft unlatching problems (door comes unlatched). If proper overcenter on the latch torque tubes has been lost, there may not be sufficient latching force to maintain the door in the latched condition.
1A. Operational Test - Forward Entry Door
A. General
(1) The following procedure provides an operational check of the forward entry door to assure satisfactory performance. The operational test is not intended to verify adjustment.
B. Test Forward Entry Door Operation
(1)
Provide electrical power (Ref 24-21-00 and 24-31-00).
(2)
Check that the following circuit breakers on panel P6 are closed:
(a)
MASTER CAUTION BUS-BAT
(b)
DOOR WARNING DC
(c)
DIM AND TEST
(d)
Circuit breakers under heading INDICATOR-MASTER DIM
(3)
Operate forward entry door from airplane interior.
(a)
With door closed, rotate inside handle counterclockwise. Check that door moves inward and FWD ENTRY light on P5 panel comes on.
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 艙門(mén) DOORS(23)
