(3)  Adjust Latch Mechanism (Fig. 503)
(a) 
 Retract lockpins.

(b)  
Rotate latch mechanism to unlatched position and partially open door.

(c)  
Adjust stop bolt at latch actuator bellcrank assembly by removing or adding washers to position bellcrank 0.04+0.03/-0.02 inch overcenter (detail A). 1) Establish overcenter by removing latch actuator and replacing with overcenter

measurement locating tool as shown in Fig. 503. After establishing overcenter, remove tool and replace with actuator.

(d)  
Rotate latching mechanism to the latched position and extend lockpins to locked position.

(e)  
Adjust stop bolt at each latch mechanism bellcrank assembly to provide 0.04 +0.04/-

0.02 gap between rod ends and lockpins. Tighten jamnuts and lockwire (detail B).
NOTE:  The latch bellcrank may be within 0.016 inch of contacting stop bolt. Lockpins are located to position the bellcrank assembly 0.12-inch overcenter when the rod end is bearing against lockpin.
(f)  
Adjust latch hook pushrod to provide 1.009 +0.015/-0.009 inch between latch hook and latch support fitting.

(g)  
Close door and check that latch hooks do not bind on latch pins. Lubricate latch hooks (Ref 12-25-101, Main Cargo Door Lubrication). If binding occurs readjust latch hook pushrods within limits of 1.009 +0.015/0.009.

NOTE:  Binding can also be caused by improperly positioned sill latch fittings. Fittings may be adjusted in or out on serrated plates, and adjusted normal (perpendicular) to body sill by use of laminated shims under fitting.

(h)  
Ensure that door edges are flush with fuselage skin within limits of +0.06 to -0.09 inch. Readjust sill latch fittings as necessary to bring door flush within required tolerance.

514 
52-32-11 Page 508  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/78 

NOTE:  Plus limit indicates door is outside fuselage exterior profile. Negative limit indicates door is inside fuselage exterior profile. Limits may be increased by
0.03 inch in one or more locations, provided the total length to which increased limit applies does not exceed 5% of door periphery.
(i)  
Latch door closed.

(j)  
Ensure clearance between washer, sill latch fitting and latch support fitting bearing cap is 0.08 + 0.01 inch on the four center latch mechanism (detail C).

(k)  
Ensure clearance between washer, sill latch fitting and latch support fitting bearing cap is 0.15 +0.01 inch on the four end latch mechanisms (two on each end) (detail D).

NOTE:  Special washers may be replaced or interchanged to obtain proper clearance. End play of sleeve on sill latch pins shall be 0.01 to 0.03 inch. Ensure that gap between centering roller and centering cam at fore and aft ends of door is 0.087 minimum with the door latched.

(l)  
After all adjustments are completed, check for visual indication of door latch engagement. With the door closed and latched and the outside lock pin handle in the closed position, the painted portion of each latch hook shall be visible through its viewing window.

D.  Restore Airplane to Normal
(1)  
Install door insulation (Ref 52-32-91, Removal/Installation).

(2)  
Install door heating blankets (Ref Chapter 21, Heating).

(3)  
Install door lining (Ref 52-32-81, Removal/Installation).

(4)  
Close main cargo door control circuit breaker on load control center P6.

520 
Aug 15/77  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-32-11 Page 509 

MAIN CARGO DOOR HINGE - REMOVAL/INSTALLATION
1.  General
A.  The main cargo door is supported along the upper edge by a piano-type hinge. The hinge installation consists of a series of hinge segments mounted along the upper edge of the door and a series of mating hinge segments mounted on the upper doorsill. The mating hinge halves are joined together by hinge pins. There is one hinge pin for each segment pair, except there are two hinge pins joining the long door-mounted hinge segment at the forward end of the door to the three mating short sill-mounted segments.
B.  Wear necessitating hinge segment replacement will most likely start in the end hinge lug on the aft sill-mounted hinge segment. The three end hinge segments are located for installation as a one-piece fitting and holes predrilled to mating doorsill structure. Then the hinge is removed and separated into the three segments by sawing at the two saw cut locations. All three of the aft hinge segments have to be replaced at the same time in the manner described. The mating body-mounted door hinge must also be replaced at the same time.
　
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