S 434-013
(3)
Connect the adjustable rod to the hinge access door.
S 824-014
(4)
Adjust the hinge access door (AMM 52-31-00/501).
S 434-015
(5)
Make sure to tighten nut and install lockwire on the adjustable rod.
G.
Put The Airplane Back To Its Usual Condition
S 214-016
(1)
Make sure the nose cargo door is fully closed, latched and locked.
S 084-017
(2)
Remove electrical power, if it is not necessary.
(3)
Remove the safety barrier across the door opening.
(4)
Remove all the support equipment.
S 094-018
S 094-019
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A
747-400 MAINTENANCE MANUAL
NOSE CARGO DOOR HINGE ACCESS CLEARANCE DOOR - INSPECTION/CHECK
______________________________________________________________
1. General_______
A. This procedure only has illustrations and data for the wear limits of the components on the hinge access clearance door . For the removal and installation of the damaged component, refer to AMM 52-31-12/401.
TASK 52-31-12-706-001
2. Examine the Nose Cargo Door Hinge Access Clearance Door________________________________________________________
A. Access
(1)
Location Zone
211 Main deck portal to STA 488, LH
212 Main deck portal to STA 488, RH
(2)
Access Panel
801 Door - Nose Cargo
B.
Procedure
(1)
See Figure 601.
S 226-002
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A
747-400
MAINTENANCE MANUAL
DOOR
FITTING
Hinge Access Clearance Door Wear Limits
Figure 601 (Sheet 1)
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B26934
A 747-400 MAINTENANCE MANUAL
3. BEARING/BOLT
B-B
NO. INDEX PART NAME DIM. DESIGN LIMITS WEAR LIMITS WORN PART REPLACE WORN REPAIR PART REPAIR INSTR
DIAMETER PER-MITTED WEAR DIM. ANCE CLEAR-MAX DIA
MIN MAX
1 HINGE ID 0.093 0.099 0.106 0.026 X
HINGE PIN OD 0.089 0.090 0.080 X
2 FITTING ID 0.3317 0.3322 0.3360 0.0070 1
BUSHING OD 0.3314 0.3319 0.3290 X
3 BEARING ID 0.2495 0.2500 0.2530 0.0060 X
BOLT OD 0.2485 0.2495 0.2470 X
4 BUSHING ID 0.2495 0.2505 0.2530 0.0060 X
BOLT OD 0.2485 0.2495 0.2470 X
MAXIMUM OVERSIZE HOLE TO BE 0.3442 INCH. INSTALL OVERSIZE OD BUSHING WITH 0.0002-INCH INTERFERENCE TO 0.0008-INCH CLEARANCE.
Hinge Access Clearance Door
Figure 601 (Sheet 2)
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