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0.0030 in
#4 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.076 mm
#5 BUSHING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
0.0030 in
#5 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.076 mm
#6 BEARING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
0.0030 in
#6 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
mm
#7 BUSHING I.D. 0.6245 in
15.862 mm
0.6252 in
15.880 mm
0.6258 in
15.895 mm
0.0033 in
#7 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.084 mm
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(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
#8 BUSHING I.D. 0.8745 in
22.212 mm
0.8753 in
22.233 mm
0.8757 in
22.243 mm
0.0027 in
#8 BUSHING O.D. 0.8735 in
22.187 mm
0.8740 in
22.200 mm
0.8730 in
22.174 mm
0.069 mm
#9 BUSHING I.D. 0.6245 in
15.862 mm
0.6252 in
15.880 mm
0.6258 in
15.895 mm
0.0033 in
#9 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.084 mm
#10 BUSHING I.D. 0.8745 in
22.212 mm
0.8753 in
22.233 mm
0.8757 in
22.243 mm
0.0027 in
#10 BUSHING O.D. 0.8735 in
22.187 mm
0.8740 in
22.200 mm
0.8730 in
22.174 mm
0.069 mm
#11 BUSHING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
0.0030 in
#11 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.076 mm
#12 BEARING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
0.0030 in
#12 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.076 mm
SUBTASK 27-81-31-020-007
(4) Do this task: Leading Edge Flap Actuator Installation, TASK 27-81-31-400-801.
------------------------- END OF TASK ---------------------------
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Leading Edge Flap Actuator Wear Limits
Figure 601 (Sheet 1 of 3)/27-81-31-990-802
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EFFECTIVITY
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Leading Edge Flap Actuator Wear Limits
Figure 601 (Sheet 2 of 3)/27-81-31-990-802
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EFFECTIVITY
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Leading Edge Flap Actuator Wear Limits
Figure 601 (Sheet 3 of 3)/27-81-31-990-802
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LEADING EDGE SLAT ACTUATOR - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the actuator of the leading edge slat.
(2) An installation of the actuator of the leading edge slat.
TASK 27-81-41-000-801
2. Leading Edge Slat Actuator Removal
(Figure 401)
A. References
Reference Title
27-81-00-480-801 Leading Edge Flap and Slat Locks Installation (P/B 201)
29-11-00-860-801 Hydraulic System A or B Pressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
B. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(81)
