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27-81-00-710-801 Leading Edge Flap and Slat System Standby Actuation Operational
Test (P/B 501)
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. Consumable Materials
Reference Description Specification
A00247 Sealant - Pressure And Environmental - Chromate
Type
BMS5-95
D00633 Grease - Aircraft General Purpose BMS3-33
G01912 Lockwire - Monel (0.032 In. Dia.) NASM20995N~
C32
(QQ-N-281)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
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
D. Leading Edge Flap Actuator Installation
SUBTASK 27-81-31-420-001
(1) If the hydraulic lines are not installed on the actuator [11] or [12], connect the hydraulic lines [4],
[9] and [10]:
(a) Remove the caps from the hydraulic ports in the actuator [11] or [12].
(b) Remove the plugs from the hydraulic lines [4], [9] and [10].
(c) Install the hydraulic lines [4], [9] and [10] in the ports on the actuator [11] or [12].
(d) Install lockwire on the nuts for the hydraulic lines [4], [9] and [10].
SUBTASK 27-81-31-420-002
(2) Install the leading edge flap actuator [11] or [12]:
(a) Put the actuator [11] or [12] in its location on the structure.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-81-31
Page 407
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(b) Install the bushing [15], washer [14], bolt [13], washer [16] and nut [17].
NOTE: On the left wing, the bolt [13], washer [14] and bushing [15] are installed on the
outboard side of the fitting. On the right wing, the bushing [15] is installed on the
inboard side of the fitting, and the head of the bolt [13] can be inboard or outboard.
The countersunk washer [14] must be installed on the side of the fitting next to the
head of the bolt [13].
(c) Tighten the nut [17] to 660-980 pound-inches (74.6-110.7 newton-meters).
(d) Connect the three hydraulic lines [4], [9] and [10]:
1) Remove the plugs from the hydraulic lines [4], [9] and [10].
2) Remove the caps from the hydraulic fittings [3].
3) Connect the hydraulic lines [4], [9] and [10] to the hydraulic fittings [3].
4) Install lockwire, G01912 on the nuts for the hydraulic lines [4], [9] and [10].
5) Install the clamps [5], screws [6] and nuts [7] that attach the hydraulic line [4] to the
bracket [8].
SUBTASK 27-81-31-860-006
(3) To pressurize hydraulic system B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
SUBTASK 27-81-31-860-007
(4) Move the flap control lever to the 1-unit detent to extend the actuator [11] or [12].
SUBTASK 27-81-31-860-008
(5) To remove power from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-81-31-420-003
(6) Connect the actuator [11] or [12] to the leading edge flap:
(a) Align the rod end of the actuator [11] or [12] with the clevis on the leading edge flap.
(b) Apply grease, D00633 on the mating surfaces of the bolt [18] or [25].
(c) Install the bushing [21], bolt [18], washer [20], washer [22], washer [23] and nut [24] to
connect the actuator [11] to the No. 1 leading edge flap [1].
1) You can bond the washer [22] to the leading edge flap [1] with sealant, A00247 for
easier installation.
(d) Install the bushing [28], bolt [25], washer [27], washer [29], washer [22] and nut [30] to
connect the actuator [12] to the No. 2 leading edge flap [2].
1) You can bond the washer [22] to the leading edge flap [2] with sealant, A00247 for
easier installation.
(e) Tighten the nut [24] or [30] to 660-980 pound-inches (74.6-110.7 newton-meters).
(f) Align the cotter pin hole in the bolt [18] or [25] with the slot in the nut [24] or [30].
(g) Install the pin [19] or [26].
SUBTASK 27-81-31-080-001
WARNING: CAREFULLY REMOVE THE LEADING EDGE FLAP ACTUATOR LOCK TO PREVENT
ACCIDENTAL OPERATION OF THE LEADING EDGE FLAPS. THE LEADING EDGE
FLAPS CAN MOVE QUICKLY. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE
TO EQUIPMENT.
(7) Do this task: Leading Edge Flap and Slat Locks Removal, TASK 27-81-00-080-801.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-81-31
Page 408
Feb 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-81-31-710-001
(8) Do a test of the actuator [11] or [12]:
　
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