F.  Secure main cargo door lifting device to main cargo door as follows:
(1)  
Remove eight countersunk screws from lifting device attachment points at body stations 380 and 480.

(2)  
If SYME 65-54916 cargo door sling is used, attach sling to door using two NAS1304-7 bolts in each of the upper and lower attachment pads.

(3)  
If F70250-3 lifting fixture is used, proceed as follows:

(a)  
Position two curved spreader fittings at forward and aft attach points on door and secure to door with special bolts stowed on spreader bars adjacent to attach points.

(b)  
Attach curved spreaders at cable attachment rings to hooks at either end of horizontal spreader bar.

G.  Support weight of door with crane by taking up cable slack. Tension in each sling cable should be approximately equal.
CAUTION: DOOR MAY BE DAMAGED IF CRANE LIFTS DOOR.
H.  Open the following circuit breakers on load control center P18:
(1)  
COVER LTS - LEFT

(2)  
CEIL LTS - L FWD

(3)  
READING LT - LEFT

(4)  
NO SMOKING

(5)  
PASS SIGN CONTROL

(6)  
FASTEN SEAT BELT

(7)  
PASS AND CREW CALL

I.  Open the following circuit breakers on load control center P6:
(1) 
 PASSENGER ADDRESS

(2)  
MAIN CARGO DOOR CONTROL

J.  Actuate the manual override on control valve to POS-2.
511 
Aug 01/74  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-32-11 Page 403 

Main Cargo Door Hinge Installation  599 
52-32-11  Figure 402  Aug 15/77 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

4. Remove Main Cargo Door

A  Disconnect and cap both flexible hydraulic lines on the cargo door.
NOTE:  A container should be used to catch draining hydraulic fluid. Refer to Chapter 12, Cleaning and Washing, for cleaning of spilled hydraulic fluid.
B.  Disconnect and cap the flexible oxygen line on the cargo door.
C.  Disconnect wiring from terminal strip above door at body station 460. Pull wiring out of ceiling through grommet. 
NOTE:  Tag wires for proper reconnection.
D.  Remove cotter pin, nut, bolt and washers and disconnect outboard link from door.
E.  Remove the diaphragm seal from the door hinge (Ref 52-09-111, Diaphragm Seals).
F.  Remove the attaching bolts of each forward and aft hinge fairing plate and remove the fairing plates.
G.  Remove the attaching bolts and remove the two hinge segments adjacent to the end hinges (Fig. 402).
H.  Using a drift and a light hammer or pneumatic hammer, drift the segmented hinge pin from the forward and aft hinge sections.
I.  Drift out the remaining hinge pins from each hinge section, removing hinge sections as necessary.
CAUTION:  RESTRAIN THE CARGO DOOR TO PREVENT SWINGING AS HINGE PINS AND DRIFT ARE REMOVED FROM THE HINGE.
J  Remove door from airplane.
K.  If new door is not to be installed immediately, install cargo door personnel safety barrier across door opening.
L.  If a new door is to be installed, remove the following components for reinstalling on new door.
(1)  Hatracks overhead stowage compartment on airplanes with New Look Interior and passenger service units (Ref Chapter 25).
Aug 01/74 52-32-11 Page 405 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(2)  
Cove assembly (Ref Chapter 25)

(3)  
Door lining (Ref 52-32-81, Main Cargo Door Lining)

(4)  
Door insulation (Ref 52-32-91, Main Cargo Door Insulation)

(5)  
Latch actuator (Ref 52-32-21, Main Cargo Door Latch Actuator)

(6)  
Heating blankets (Ref Chapter 21)

(7) 
 Wiring bundles

(8)  
Gasper air, hydraulic and oxygen tubing

5.  Prepare for Installation
A. If a new door is to be installed, the following components must be installed on the door:
(1)  
Gasper air, hydraulic and oxygen tubing

(2)  
Wiring bundles (some permanent splices will have to be broken)

B.  Install cargo door sling or lifting fixture assembly (Fig. 401).
C.  Thoroughly clean dirt from hinge pins and hinge pin holes. Remove grease or oil with BMS 3-2 solvent.
D.  The following conditions must be satisfied only while door is being closed for the purpose of marking door skin for trimming operation and for checking skin gap between door and fuselage. Refer to steps E and M of par. 6.
　
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