B.  
Procedure

 (1)
See Figure 601.

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MAINTENANCE MANUAL

10R 
9R  A A  A A  A A  11 A  A A  10L 
8R  A  9L 
6R 5R 7R C  1 THRU 8, L AND R) ASEE 8L LATCH FITTING 7L (EXAMPLE FOR LOCATIONS 
4R C  6L 
3R B 2R B  5L 4L 3L 
1R  2L 
1L 
LATCH LOCATIONS 
Portal Latch Fitting Wear Limits Figure 601 (Sheet 1) 

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MAINTENANCE MANUAL

1. BEARING/FITTING
A-A
Portal Latch Fitting Wear Limits Figure 601 (Sheet 2)
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MAINTENANCE MANUAL

NO. INDEX  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  PART WORN REPLACE  PART WORN REPAIR  INSTR REPAIR 
DIAMETER  PER-MITTED WEAR DIM.  ANCE CLEAR-MAX DIA 
MIN  MAX 
1  BEARING 1  ID  1.3997  1.4018  1.4070  0.0600 2  X 
FITTING 1  OD  1.3511  1.3516  1.3470  X 
2  FITTING  ID  1.3050  1.3060  1.3100  0.0060  3 
BUSHING  OD  1.3066  1.3074  1.3040  X 
3  BUSHING  ID  1.1270  1.1280  1.1320  0.0110  X 
LATCHPIN  OD  1.1245  1.1250  1.1210  X 
4  BEARING  ID  1.1745  1.1750  1.1780  0.0570  X 
LATCHPIN  OD  1.1245  1.1250  1.1210  4 
5  FITTING  ID  1.9999  2.0005  2.0070  0.0100  X 
BEARING  OD  1.9995  2.0000  1.9970  X 

MEASURE DIAMETER AT LOCATION SHOWN ON FIG. 601.
MEASURE AT ANY POINT SURFACES ARE PARALLEL.
OVERSIZE HOLE TO 1.3442. INSTALL BUSHING WITH 0.0006 TO 0.0024

INTERFERENCE FIT.
RESTORE CHROME PLATING PER VENDOR OVERHAUL MANUAL.

Portal Latch Fitting Wear Limits
Figure 601 (Sheet 3)

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 NOSE CARGO DOOR PUSH-PULL CAM MECHANISM - REMOVAL/INSTALLATION
______________________________________________________________
 1.  General
_______
 A.  This procedure has two tasks:
 (1)  
The removal of the push-pull cam mechanism on the nose cargo door

 (2)  
The installation of the push-pull cam mechanism on the nose cargo door

 B.  
The push-pull cam mechanism consists of the following components which can be removed and installed separately: push-pull cam support fitting, cam actuator, cam and cam roller support fitting. The adjustment of the push-pull cam mechanism after replacement of a component is to be done with the airplane on its landing gears.

 TASK 52-31-09-404-001
　
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