B.
Procedure
(1)
See Figure 601.
S 226-002
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A
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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)
B26919
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MAINTENANCE MANUAL
1. BEARING/FITTING
A-A
Portal Latch Fitting Wear Limits Figure 601 (Sheet 2)
B26921
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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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747-400 MAINTENANCE MANUAL
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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