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Figure 202 (Sheet 2 of 2)/27-81-00-990-802
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Feb 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TASK 27-81-00-080-801
9. Leading Edge Flap and Slat Locks Removal
A. References
Reference Title
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
SWPM 20-60-03 Standard Wiring Practices Manual
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
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
SPL-1675 Assembly - Lock, Flight Controls
(Part #: F80049-18, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
(Opt Part #: F80049-12, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
SPL-1734 Lockout Set - Leading Edge Slats and Krueger Flaps Actuators
(Part #: C27051-29, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
(Opt Part #: C27051-1, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -BBJ)
C. Consumable Materials
Reference Description Specification
G50171 Compound - Corrosion Inhibiting Compound,
Interior Application - D5026NS or ZC-026
D. 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
512 Left Wing - Krueger Flap No. 2
513 Left Wing - Krueger Flap No. 1
522 Left Wing - Slat No. 4
523 Left Wing - Slat No. 3
524 Left Wing - Slat No. 2
525 Left Wing - Slat No. 1
612 Right Wing - Krueger Flap No. 3
613 Right Wing - Krueger Flap No. 4
622 Right Wing - Slat No. 5
623 Right Wing - Slat No. 6
624 Right Wing - Slat No. 7
625 Right Wing - Slat No. 8
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-81-00
Page 218
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
E. Leading Edge Flap and Slat Locks Removal
SUBTASK 27-81-00-080-002
(1) Remove the lockout set, SPL-1734 from the leading edge devices:
(a) If the hydraulic system B is pressurized, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
WARNING: CAREFULLY REMOVE THE LEADING EDGE FLAP AND SLAT ACTUATORS
LOCKOUT SET. THE LEADING EDGE FLAPS AND SLATS CAN MOVE QUICKLY IF
YOU DO NOT REMOVE THE LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
(b) Remove the lockout set, SPL-1734 from the extended actuators of the leading edge flaps
and slats.
(c) Do this task: Leading Edge Flaps and Slats Retraction, TASK 27-81-00-860-804.
SUBTASK 27-81-00-080-003
(2) Remove the lock, SPL-1675 from the standby hydraulic module (Figure 202):
(a) Remove the lockpin.
(b) Remove the lock, SPL-1675 from the standby hydraulic module.
(c) Make sure the override lever at the leading edge standby drive shutoff valve is in position
1.
(d) Before you connect the electrical connector, examine the connector for corrosion.
WARNING: DO THE STEPS BELOW IF THE AIRPLANE OPERATES AT AIRPORTS WHERE
DEICING FLUID THAT CONTAIN POTASSIUM FORMATE IS USED. ALSO DO THE
STEPS FOR ALL AIRPLANES THAT YOU FOUND CORROSION IN THE
ELECTRICAL CONNECTORS IN THE MAIN WHEEL WELL. THE ELECTRICAL
CONNECTOR IS PART OF A SYSTEM THAT IS NECESSARY FOR SAFE FLIGHT.
(e) If there was corrosion, refer to (SWPM 20-60-03) to correct the problem.
(f) Apply the D5026NS or ZC-026 compound, G50171 to the connector (SWPM 20-60-03).
(g) Connect the electrical connector to the leading edge standby drive shutoff valve.
(h) Remove the DO-NOT-OPERATE tag from the ALTERNATE FLAPS arm switch.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-81-00
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Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
LEADING EDGE FLAP AND SLAT - ADJUSTMENT/TEST
1. General
A. This procedure has these tasks:
(1) An adjustment of the leading edge flaps
(2) An adjustment of the leading edge actuators and main track downstops
　
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