Leading Edge Autoslat System Schematic
Figure 4

A12604
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH AUTOSLAT ú

 27-83-00
 COMPUTER P/N 65-52818  ú  CONFIG  1
 ú  02  Page 11
 ú  Nov 15/93 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 LEADING EDGE AUTOSLAT SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________
 1.  General (Fig. 1)_______
 A.  The leading edge autoslat system automatically extends the leading edge slats from the intermediate extend position to the full extend position to provide additional lift without changing trailing edge flap position. The system consists of an autoslat valve which can be activated independently by either stall management computer. Each stall management computer (Ref 27-32-00) receives inputs from an angle of airflow sensor, a flap position transmitter, and the E-11 landing gear logic shelf.
 B.  The leading edge slats are normally at the intermediate extend position during takeoff. When the airplane reaches a predetermined angle of attack, the stall management computer activates the autoslat valve, which causes the slats to move to the full extend position. The slats automatically retract to the intermediate extend position when the angle of attack is reduced.
 C.  Each stall management computer supplies signals to the autoslat valve, to the flight control module for fault indication, and to the flap/slat indication module.
 2.  Stall Management Computer (Fig. 1)_________________________
 A.  Each stall management computer (SMC) performs calculations to determine when to activate and deactivate the autoslat valve. Either SMC can activate the control valve. The SMC's are located on the E1-1 electronics shelf.
 B.  SMC 1 is powered by 28v dc through a circuit breaker on the P18-2 panel. The autoslat output is powered by a circuit breaker on the P6-2 panel. SMC 1 uses the following inputs for its autoslat control function:
 (1)
Left Angle of Airflow Sensor

 (2)
Right Flap Position Transmitter

 (3)
E-11 Landing Gear Logic Shelf

 C.  
SMC 2 is powered by 28v dc through a circuit breaker on the P6-1 panel. The autoslat output is powered by a circuit breaker on the P6-2 panel. SMC 2 uses the following inputs for its autoslat control function:

 (1)
Right Angle of Airflow Sensor

 (2)
Left Flap Position Transmitter

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

 27-83-00
 COMPUTER P/N 65-52822  ú CONFIG 2 ú 01 Page 1 ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

Leading Edge Autoslat System - Component Location Figure 1 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

 27-83-00
 COMPUTER P/N 65-52822  ú CONFIG 2 ú 01 Page 2 ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
FLT CONTROL STANDBY A B HYD

SEE MASTER CAUTION

FLAP POSITION INDICATOR
SEE

STDBY
RUD
OFF
A ON

OFF
OFF
QUANTITY A LOW 
APRESSURE LOW 

D

LE FLAPS  LE FLAPS 
ATRANSIT  GEXT 

A
MASTER CAUTION
PUSH TO RESET

ELEC
IRS
APU
FUEL
OVHT/DET

Leading Edge Autoslat System - Component Location
Figure 1 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

 27-83-00
　
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