3.  Install Wheel Well Doors (Fig. 401)
A.  Pressurize hydraulic System A (Ref 29-11-0 MP).
WARNING:  CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN MAIN LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR EQUIPMENT COULD RESULT IF GEAR RETRACTS.
B.  Retract nose landing gear.
C.  Position door for installation and install close tolerance bolts (18) with thin anodized aluminum alloy washer (17) under head in forward and aft hinges.
D.  Install nut on each bolt with corrosion resistant steel cotter pin.
E.  Close door by hand and adjust forward and aft stops until forward and aft external surface edges of door fair with adjacent surfaces of fuselage skin within 0.03 inch when door fairs inside fuselage skin and 0.06 inch when it fairs outside, and external inboard edges of doors fair within 0.06 inch.
Nose Wheel Doors Installation  500 
32-22-11 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/87 

500  Nose Wheel Doors Installation 
Jun 20/92  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-22-11 Page 403 

F.  Adjust door for proper clearances.
(1)  
Remove bolts (20) from forward hinge bracket (12).

NOTE:  Plate nuts (24) are on opposite side of bulkhead from hinge bracket (12) for the hinge bracket mounting bolts.

(2)  
Remove existing shims or add proper thickness of laminated aluminum alloy shim or shims (23), as necessary, under the serrated forward hinge bracket plate (22) to adjust door for a clearance of 0.20 + 0.05/-0.02 inch between outboard edge of door and adjacent fuselage skin, with bolts installed and tightened moderately and doors closed by hand. Use this same adjustment procedure to adjust for a clearance of 0.10 + 0.10/-0.04 inch between inboard edges of the doors.

NOTE:  Peel laminated shim or shims, if necessary, for proper thickness to obtain correct adjustment.

(3)  
Repeat steps (1) and (2) for aft hinge.

G.  Fair external outboard surface of door with adjacent fuselage skin surface.
(1)  
Loosen four bolts (20) in each of the forward and aft door hinge brackets (12) (detail B).

(2)  
Move each hinge bracket so serrations, on back of hinge bracket come to the position, up or down, over mating serrations in hinge bracket plate (22) so the outboard external edge of door fairs with adjacent fuselage skin. A maximum of 0.06 inch mismatch adjacent to door hinges and door brackets respectively is allowable.

(3)  
Tighten the four bolts (20) in each of the forward and aft hinge brackets (12).

H.  Connect door center hinge (4) to center hinge bracket (2). Remove bolts (8) from center hinge bracket (2) (detail A).
NOTE:  Plate nuts (11) are on the opposite side of bulkhead from hinge bracket (2) for the hinge bracket mounting bolts (8). The hinge bracket must be removed and reinstalled, after it has been attached to the door center hinge, to ensure alignment with door center hinge.
(1)  
Position hinge bracket (2) on center door hinge (4) and insert center hinge close tolerance bolt (6).

(2)  
Position center hinge bracket plate (7, detail A) by mating proper serrations of the hinge bracket plate and those on back of hinge bracket (2) so holes align for installation of hinge bracket bolts (8).

(3)  
Tape the hinge bracket plate in this position.

(4)  
Install aluminum alloy laminated shim or shims (9), as necessary, so that center hinge bolt

500 
32-22-11 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/81 

(6) can be slid into center hinge bracket and on through center hinge of door and the hinge bracket by hand pressure.
NOTE:  Peel laminated aluminum alloy shim or shims (9), that are to be installed, to obtain this adjustment.
(5)  
Install four close tolerance bolts (8) of proper length, with anodized aluminum alloy washers (10) under the heads, through the elongated holes in hinge bracket (2), hinge bracket plate (7), the laminated shim or shims (9), and each bolt screwed into the floating, self-sealing, self-locking plate nuts (11) which are mounted on outboard sides of wheel well side bulkheads.

NOTE:  The center hinge bolt (6) should be free to move by hand pressure after the above bolts (8) are tightened.

(6)  
Install close tolerance center hinge bolt (6) with aluminum alloy, anodized, thin washer under bolt head with castellated nut and corrosion resistant steel cotter pin.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 起落架 LANDING GEAR(75)