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F/O Electrical System Panel, P6-2
Row Col Number Name
B 14 C01070 FLIGHT CONTROL AUTOSLAT DC 2
(a) Make sure the slats move to the full extend position.
(b) Make sure the LE FLAPS EXT light is on and the LE FLAPS TRANSIT light is off.
SUBTASK 27-83-00-860-011
(9) Open this circuit breaker and install safety tag:
F/O Electrical System Panel, P6-2
Row Col Number Name
B 14 C01070 FLIGHT CONTROL AUTOSLAT DC 2
(a) Make sure the slats move to the flaps 1 (mid-extend) position.
SUBTASK 27-83-00-820-003
(10) Turn the Left and right AOA vanes to 0 degrees (Figure 502).
SUBTASK 27-83-00-820-004
(11) Put the flap lever in the UP position.
F. Return the airplane to its normal condition.
SUBTASK 27-83-00-840-005
(1) Remove the safety tags and close these circuit breakers:
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 4 C01392 STICK SHAKER LEFT
F/O Electrical System Panel, P6-1
Row Col Number Name
B 6 C01393 STICK SHAKER RIGHT
F/O Electrical System Panel, P6-2
Row Col Number Name
B 14 C01070 FLIGHT CONTROL AUTOSLAT DC 2
C 14 C01068 FLIGHT CONTROL AUTOSLAT DC 1
SUBTASK 27-83-00-840-010
(2) Do this task: Return the Airplane Systems Back to Their Normal On Ground Condition,
TASK 32-09-00-840-802.
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SUBTASK 27-83-00-840-007
(3) Push the ON/OFF switch on the SMYD to turn off the SMYD display.
(a) Push the YES switch to verify that you want to turn off the display.
SUBTASK 27-83-00-840-008
(4) If hydraulic power is no longer necessary, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-83-00-840-009
(5) If electrical power is no longer necessary, do this task: Remove External Power,
TASK 24-22-00-860-814.
SUBTASK 27-83-00-940-001
(6) Close this access panel:
Number Name/Location
117A Electronic Equipment Access Door
------------------------- END OF TASK ---------------------------
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Angle of Attack (AOA) Sensor
Figure 502/27-83-00-990-802
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AUTOSLAT CONTROL VALVE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) Removal of the autoslat control valve.
(2) Installation of the autoslat control valve.
B. There are solenoids installed on the autoslat control valve. It is not necessary to remove the
solenoids to remove the control valve.
TASK 27-83-21-000-801
2. Autoslat Control Valve Removal
(Figure 401)
A. References
Reference Title
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
B. Location Zones
Zone Area
192 Lower Wing-To-Body Fairing - Under Wing Box
C. Access Panels
Number Name/Location
192BR ECS Ram Air Inlet Mixing Duct Panel - Forward
D. Prepare for the Removal
SUBTASK 27-83-21-480-001
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR COULD RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed on the main and nose landing gear, do this task: Landing
Gear Downlock Pins Installation, TASK 32-00-01-480-801.
SUBTASK 27-83-21-860-001
(2) Do this task: Hydraulic System A or B Power Removal, TASK 29-11-00-860-805.
SUBTASK 27-83-21-010-001
(3) To gain access to the autoslat control valve,
Remove this access panel:
Number Name/Location
192BR ECS Ram Air Inlet Mixing Duct Panel - Forward
E. Autoslat Control Valve Removal
SUBTASK 27-83-21-860-002
(1) Open these circuit breakers and install safety tags:
F/O Electrical System Panel, P6-2
Row Col Number Name
B 14 C01070 FLIGHT CONTROL AUTOSLAT DC 2
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Row Col Number Name
C 14 C01068 FLIGHT CONTROL AUTOSLAT DC 1
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737-600-700-800-900 飞机维护手册7 AIRCRAFT MAINTENANCE MANUA(103)
