B.  Install New Cargo Door
(1)  
Position door in opening so that stop pins are centered on stop pads within 0.15 inch (Detail C, Fig. 401).

(2)  
Adjust stop pins until door is recessed as shown in Fig. 402. Door must not protrude beyond fuselage exterior.

NOTE:  If necessary trim door skin to clear body skin; however, final clearance must be per step (10) with door closed and latched.

(3)  
Attach hinge arms to door; shim between door and hinge arm as required. Maintain position and recess per steps (1) and (2). Observe special bolt installation instructions specified in par. 3.B. (3).

(4)  
Using door support brace, position door as necessary and connect snubber (16) to bracket on door with bolt (17). Check that snubber restrains free fall of door from open position.

WARNING:  TO AVOID INJURY TO PERSONNEL WORKING ON OR NEAR DOOR, ALWAYS USE RED COLORED DOOR SUPPORT BRACE TO HOLD DOOR OPEN WHEN DOOR BALANCE MECHANISM AND SNUBBER ARE DISCONNECTED.

(5)  
Install door balance mechanism (Ref 52-31-11 R/I).

(6)  
Install centering pads on door frames 2 places (Detail B). Shim as required to have rollers free to rotate at all times with maximum clearance of 0.02 inch; delaminate shims if necessary to obtain required dimension.

(7)  
Back off stop pins and install roller stop fittings with serrated plates. Shim to provide 0.03 ±0.01 inch clearance between stop fitting and latch roller arm (Detail A). Install door warning switch on forward latch fitting.

(8)  
Adjust roller stop fittings inboard or outboard on serrated plates so that with door closed and latched, door recess is again as shown in Fig. 402 and latch roller clearance is 0.16 ±0.09 inch as shown in Fig. 401, Detail A. Both rollers must engage roller stop fitting inner surfaces and torque tube must rotate freely in bearings (Detail A).

(9)  
If required conditions (step 7) cannot be achieved by adjusting roller stop fittings, remove access panel (9) and adjust length of latch mechanism control rod.

CAUTION:  AFTER ADJUSTMENT OF CONTROL ROD, BE SURE TO RESAFETY CONTROL ROD AS SHOWN IN VIEW 3, FIG. 401. FAILURE TO PROPERLY SAFETY WIRE CONTROL ROD MAKES IT POSSIBLE FOR ROD ADJUSTMENT TO CHANGE WHICH COULD RESULT IN DOOR UNLATCHING DURING UNPRESSURIZED FLIGHT (TAKEOFF OR LANDING).

(10)
Close and latch door. Check that gap between door outer skin and fuselage outer skin is as follows; trim door as necessary.

(a)  
Forward door: top, forward, and aft edge 0.06 to 0.15 inch; lower sill 0.22 to 0.28 inch.

(b)  
Aft door: top and forward edges 0.06 to 0.15 inch; aft edge 0.15 to 0.21 inch; lower sill 0.23 to 0.28 inch.

(11)
With door closed and latched, check that torque necessary to operate door handle does not exceed 400 pound-inches applied to outer handle or 300 pound-inches applied to inner handle. Adjust roller stop fittings if necessary.

(12)
With door closed and latched, screw stop pins (Detail C) down until they just contact stop fittings on airframe structure. Open door and back off each stop pin half a turn; then turn the pin to nearest groove in bushing that lines up with a groove in pin and install lockspring.

(13)
Install latch mechanism access panel in door.

(14)
Install door lanyard assembly (14).

(15)
Install latch support clip (13) on overhead floor beam (1). The clip was removed as a safety precaution.

(16)
Latch door in open position and adjust latch hook bracket as necessary to obtain 0.06 +0.03 inch dimension (Detail D). Tighten screws after making adjustments.

(17)
Check seating of door seal.

(18)
Check door warning system for correct operation and adjust if required (52-71-0, Door Warning System).

(19)
Check balance mechanism for correct operation. When door is opened and released using outside handle it should move smoothly upward to or near its up-latched position.

551 
52-31-0 Page 408  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/77 

NOTE:  Roller and stop fitting engagement can be checked using modeling clay or similar approved method.

526  Cargo Compartment Door Flushness Requirements 
Feb 20/91  Figure 402  52-31-0 
Page 409 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

501 
52-31-0 Page 410  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/92 

CARGO COMPARTMENT DOORS - APPROVED REPAIRS
1. General
A.  Repair of cargo compartment doors fuselage mounted doorstops may be accomplished as a basic repair (Ref par. 3).
　
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