曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(Continued)
NAME OF THE PARTS
THAT ARE IN CONTACT
DIM.
DIAMETER DESIGN LIMITS WEAR LIMITS
MINIMUM
inches/mm
MAXIMUM
inches/mm
PERMITTED
MAXIMUM I.D./
MINIMUM O.D. OF
WORN PART
MAXIMUM
SERVICE
DIAMETRIC
CLEARANCE
#7 BOLT O.D. 0.3735 in
9.4869 mm
0.3745 in
9.5123 mm
0.3723 in
9.4564 mm
0.0127 mm
#8 BEARING I.D. 0.3745 in
9.5123 mm
0.3750 in
9.5250 mm
0.3772 in
9.5809 mm
0.0000 in
#8 BOLT O.D. 0.3735 in
9.4869 mm
0.3745 in
9.5123 mm
0.3723 in
9.45642mm
0.0000 mm
#9 BUSHING I.D. 0.3750 in 0.3755 in 0.3777 in
9.5250 mm 9.5377 mm 9.5936 mm 0.0005 in
#9 BOLT O.D. 0.3735 in 0.3745 in 0.3723 in 0.0127 mm
9.4869 mm 9.5123 mm 9.4564 mm
#10 BUSHING I.D. 0.3750 in
9.5250 mm
0.3756 in
9.5402 mm
0.3778 in
9.5961 mm
0.0005 in
#10 BOLT O.D. 0.3735 in
9.4869 mm
0.3745 in
9.5123 mm
0.3723 in
9.4564 mm
0.0127 mm
#11 BEARING I.D. 0.3745 in
9.5123 mm
0.3750 in
9.5250 mm
0.3772 in
9.5809 mm
0.0000 in
#11 BOLT O.D. 0.3735 in
9.4869 mm
0.3745 in
9.5123 mm
0.3723 in
9.4564 mm
0.0000 mm
#12 BUSHING I.D. 0.5620 in
14.2748 mm
0.5627 in
14.2926 mm
0.5645 in
14.3383 mm
0.0005 in
#12 BUSHING O.D. 0.5610 in
14.2494 mm
0.5615 in
14.2621 mm
0.5595 in
14.2113 mm
0.0127 mm
SUBTASK 27-11-11-020-006
(4) Do this task: Aileron Installation, TASK 27-11-11-400-801.
------------------------- END OF TASK ---------------------------
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EFFECTIVITY
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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron Wear Limits
Figure 601 (Sheet 1 of 3)/27-11-11-990-803
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AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron Wear Limits
Figure 601 (Sheet 2 of 3)/27-11-11-990-803
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron Wear Limits
Figure 601 (Sheet 3 of 3)/27-11-11-990-803
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
AILERON POWER CONTROL UNIT LINKAGE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the aileron power control unit linkage
(2) An installation of the aileron power control unit linkage.
B. The aileron power control unit linkage is referred to as the linkage [1] or linkage [2] in this procedure.
C. This procedure is applicable for system A and B linkages.
TASK 27-11-14-000-801
2. Aileron Power Control Unit Linkage Removal
(Figure 401)
A. References
Reference Title
27-11-71-000-801 Aileron Power Control Unit Removal (P/B 401)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
B. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
211 Flight Compartment - Left
212 Flight Compartment - Right
C. Prepare for the Removal
SUBTASK 27-11-14-480-001
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEARS.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEARS COULD RETRACT AND
CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed on all the landing gears, do this task: Landing Gear
Downlock Pins Installation, TASK 32-00-01-480-801.
SUBTASK 27-11-14-020-001
(2) Do this task: Aileron Power Control Unit Removal, TASK 27-11-71-000-801.
D. Aileron Power Control Unit Linkage Removal
SUBTASK 27-11-14-020-002
(1) Remove the linkage [1] or linkage [2]:
(a) Disconnect the cable ABSA [19] and cable ABSB [22] at the turnbuckles [3].
(b) Remove the nuts [18], washers [17], washers [16] and bolts [15] to remove the retaining
　
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