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(a) To pressurize hydraulic sytem B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
CAUTION: CAREFULLY WATCH THE FLAP NOSE CLEARANCE AND THE ACTUATOR
CLEARANCES DURING THE FLAP EXTENSION AND RETRACTION. IF THERE IS
NOT SUFFICIENT CLEARANCE, YOU CAN CAUSE DAMAGE TO STRUCTURE.
(b) Operate the leading edge flap through a minimum of two cycles to bleed air from the
system.
NOTE: Leave the flaps in the extended position.
(c) Make sure there are no hydraulic leaks from the actuator [11] or [12] or the hydraulic lines
[4], [9] and [10].
(d) Move the flap control lever to the UP position to retract the leading edge flaps.
(e) To remove power from system B, do this task: Hydraulic System A or B Power Removal,
TASK 29-11-00-860-805.
SUBTASK 27-81-31-720-001
(9) Do this task: Leading Edge Flap and Slat Timing Test in Primary Mode,
TASK 27-81-00-700-802.
SUBTASK 27-81-31-710-002
(10) Do this task: Leading Edge Flap and Slat System Standby Actuation Operational Test ,
TASK 27-81-00-710-801
E. Put the Airplane Back to Its Usual Condition
SUBTASK 27-81-31-860-009
(1) Remove the safety tags and close these circuit breakers:
F/O Electrical System Panel, P6-2
Row Col Number Name
A 15 C01081 HYDRAULIC SYSTEM PTU VALVE CONT 1
A 16 C01085 HYDRAULIC SYSTEM PTU VALVE CONT 2
------------------------- END OF TASK ---------------------------
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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
LEADING EDGE FLAP ACTUATOR - INSPECTION/CHECK
1. General
A. This procedure contains the task to do a check of the leading edge flap actuator.
TASK 27-81-31-200-801
2. Leading Edge Flap Actuator Inspection
(Figure 601)
A. General
(1) This task gives wear limits and repair data for the leading edge flap actuator inspection.
B. References
Reference Title
27-81-31-000-801 Leading Edge Flap Actuator Removal (P/B 401)
27-81-31-400-801 Leading Edge Flap Actuator Installation (P/B 401)
C. Tools/Equipment
Reference Description
STD-1096 Micrometer - Depth, 0-1 Inch, Readable to 1/1000 Inch
STD-1097 Caliper - Vernier, 0-6 Inch, Readable to 1/1000 Inch
D. Location Zones
Zone Area
512 Left Wing - Krueger Flap No. 2
513 Left Wing - Krueger Flap No. 1
612 Right Wing - Krueger Flap No. 3
613 Right Wing - Krueger Flap No. 4
E. Procedure
SUBTASK 27-81-31-020-004
(1) Do this task: Leading Edge Flap Actuator Removal, TASK 27-81-31-000-801.
SUBTASK 27-81-31-020-005
(2) Use these tools to do a check for wear on the parts of the leading edge flap actuator:
(a) micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096
(b) readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
SUBTASK 27-81-31-020-006
(3) Examine the parts of the leading edge flap actuator for worn areas:
(a) Remove the parts you want to do a check.
(b) Measure the parts with a micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096 or a
readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
(c) Compare the dimensions you measured with the permitted wear dimensions.
(d) If the parts are out of tolerance, replace or repair the parts if it is necessary.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Table 601/27-81-31-993-801
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
#1 BUSHING I.D. 0.6245 in 0.6252 in 0.6258 in
15.862 mm 15.880 mm 15.895 mm 0.0033 in
#1 BOLT O.D. 0.6230 in 0.6240 in 0.6225 in 0.084 mm
15.824 mm 15.850 mm 15.812 mm
#2 BUSHING I.D. 0.8745 in
22.212 mm
0.8753 in
22.233 mm
0.8757 in
22.243 mm
0.0027 in
#2 BUSHING O.D. 0.8735 in
22.187 mm
0.8740 in
22.200 mm
0.8730 in
22.174 mm
0.069 mm
#3 BUSHING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
0.0030 in
#3 BOLT O.D. 0.6230 in
15.824 mm
0.6240 in
15.850 mm
0.6225 in
15.812 mm
0.076 mm
#4 BEARING I.D. 0.6245 in
15.862 mm
0.6250 in
15.875 mm
0.6255 in
15.888 mm
　
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