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24-22-00-860-811 Supply Electrical Power (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)
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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B. Consumable Materials
Reference Description Specification
G50170 Compound - Corrosion Inhibiting Compound, Soft
Film, Exterior Use - AV25
C. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
211 Flight Compartment - Left
212 Flight Compartment - Right
D. Leading Edge Standby Shutoff Valve Motor Test
SUBTASK 27-81-91-860-008
(1) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-81-91-860-009
(2) Open this circuit breaker and install safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
SUBTASK 27-81-91-710-001
(3) Do the test for the valve [13]:
(a) Make sure the manual override lever [4] is at position 1.
(b) To pressurize hydraulic system B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
(c) Make sure the flap control lever is in the UP detent.
(d) Set the alternate flaps arm switch, on the P5 Flight Controls panel, to the ARM position.
1) Make sure the STANDBY HYD LOW PRESSURE light comes on.
2) Make sure the standby hydraulic pump starts.
3) Make sure the STANDBY HYD LOW PRESSURE light is off.
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LEADING
EDGE FLAPS AND SLATS. THE LEADING EDGE FLAPS AND SLATS CAN MOVE
QUICKLY. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
(e) Set the alternate flaps control switch, on the P5 Flight Controls panel, to the DOWN position.
1) Make sure the manual override lever [4] is at position 2.
2) Make sure the leading edge flaps and slats fully extend.
(f) Set the alternate flaps control switch to the OFF position.
1) Make sure the leading edge flaps and slats do not move.
737-600/700/800/900
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EFFECTIVITY
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WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LEADING
EDGE FLAPS AND SLATS. THE LEADING EDGE FLAPS AND SLATS CAN MOVE
QUICKLY. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
(g) Set the alternate flaps arm switch to the OFF position.
1) Make sure the manual override lever [4] moves to position 1.
2) Make sure the leading edge flaps and slats fully retract.
NOTE: The leading edge flaps and slats retract because of the pressurization of
hydraulic system B.
SUBTASK 27-81-91-210-001
(4) Make sure there is no hydraulic fluid leakage from the valve hydraulic fittings.
SUBTASK 27-81-91-860-010
(5) Remove the safety tag and close this circuit breaker:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 13 C00841 FLIGHT CONTROL ALTN T.E. FLAP DRIVE
SUBTASK 27-81-91-860-011
(6) To remove power from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-81-91-212-001
(7) Apply the AV25 compound, G50170 to the mated electrical connector assembly completely, until
the compound drips from the connector.
NOTE: Do not remove the excess corrosion inhibiting compound.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
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EFFECTIVITY
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Alternate Flaps Control Switches
Figure 202/27-81-91-990-802
737-600/700/800/900
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EFFECTIVITY
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LEADING EDGE AUTOSLAT SYSTEM - ADJUSTMENT/TEST
1. General
A. This procedure has these tasks:
(1) Test of the autoslat system indicator light.
(2) Operational test of the leading edge autoslat system.
TASK 27-83-00-720-801
2. Autoslat System Indicator Light - Functional Test
(Figure 501)
A. References
Reference Title
24-22-00-860-813 Supply External Power (P/B 201)
24-22-00-860-814 Remove External Power (P/B 201)
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(100)
