D.  Serrations in serrated hinge (1) must be seated in serrated plates (8). Tighten bolts (7).
E.  With 0.050-inch shims between forward doorstops, adjust serrated latch plate so that door will latch. Door should rest on shims but latch pin (5) should not force door against shims except to overcome resistance of seal (3). Remove shims.
F.  Install guide pin (6) on door.
(1)  
Loosen screw to allow guide pin assembly to slide into slotted hole in guide pin plate.

(2)  
Close door, position door in center of opening and latch. This wil1 position guide to match guide pin plate on door frame.

(3)  
Carefully open door and tighten guide pin, attach screw.

NOTE: Gap between door and fuselage skin should be 0.12 +0.06 inch.
G.  Check operation of door warning system (Ref 52-71-0, Door Warning System).
H.  Close and latch lower nose compartment access door.
501 
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500  Lower Nose Compartment Access Door Installation 
May 15/68  Figure 401  52-48-31 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

ELECTRONIC EQUIPMENT COMPARTMENT EXTERNAL ACCESS DOOR -DESCRIPTION AND OPERATION

1. General
A.  The electronic equipment compartment external access door is a plug type, inward opening, sliding door in the lower fuselage aft of the nose wheel well. (See figure 1.) The door is operated from outside the fuselage and it is included in the door warning system, sharing a common warning light in the control cabin with the lower nose compartment access door. A door track installation inside the fuselage structure allows the door to be pushed inward, up, and to slide to the right of the door opening in the fuselage when entry is desired.
B.  The door is of alclad frame and skin construction. Around the periphery of the door a continuous seal prevents loss of cabin air when the airplane is in flight. Pressurization loads on the door are transmitted to the fuselage by the four latch pins. The stop fittings on the door and the door lock fittings on the structure through which the latch pins pass are so designed that, if the pins should accidentally be left unlatched, the fittings will bear against each other and so transmit pressurization loads safely.
2.  Latching Mechanism
A.  The door latching mechanism consists of four latch pins (13, figure 1), which project through stop fittings (24, detail D), on the four edges of the door and engage corresponding door lock fittings (16, detail B), in the fuselage structure surrounding the door. The latch pins are actuated by a common rack and pinion mechanism. (See detail C.) The inner end of each pin is in the form of a rack and all four racks engage with a pinion on the central actuator shaft (21). The shaft has an outer handle (17, detail A) by means of which the door is operated from outside the airplane.
3.  Operation
A.  The means by which the door is moved inward, up and to the right of the door opening in the fuselage to its stowed position is provided by door tracks (8), a lower web (12), upper web (11) with eight rollers (9), a spring spool assembly (4), track attach brackets (19), uplatch (23, view 1), and the necessary stops to limit travel of components of the installation. The door tracks are inclined upward and outboard from door opening. Near the door opening, door tracks are attached to electronic rack supports (2) and outboard and upward from the opening they are attached to electronic rack stanchions (3). The lower web
500 
Aug 15/67  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-48-41 Page 1 

Electronic Equipment Compartment External Access Door  500 
52-48-41  Figure 1 (Sheet 1)  May 15/69 
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500  Electronic Equipment Compartment External Access Door 
May 15/69  Figure 1 (Sheet 2)  52-48-41 
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Electronic Equipment Compartment External Access Door  500 
52-48-41  Figure 1 (Sheet 3)  May 15/69 
Page 4 
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500  Electronic Equipment Compartment External Access Door 
May 15/69  Figure 1 (Sheet 4)  52-48-41 
Page 5 
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