(5)  
Make sure that a pitch limit symbol shows on the captain's and the first officer's EADI's.

 S 865-097-002

 (6)  
Set IRS L and IRS R mode selector switches (aft P5 panel) to the OFF position.

 P.
SMC Asymmetry Mode Test

 S 865-098-002
 (1)  
Prepare for the asymmetry mode test:

 (a)  
Push the MENU button on the SMC maintenance control panel on the front of each SMC.

 (b)  
Make sure that the display on each computer shows SENSOR TESTS?.

 (c)  
Push the up button on each SMC as many times as necessary until each display shows DISCRETE INPUTS?

 (d)  
Push the YES button on each SMC.

 (e)  
Push each down button as many times as necessary until each display shows ASYMETRY NO.

 (f)  
Close the SMC STALL WARN ASYM MODE circuit breaker on the P18-2 panel.

 (g)  
Move the flaps to the 10-unit position.

 S 745-099-002
 (2)  
Do a check of the asymmetry mode of the SMC:

 (a)  
Set the HYD PUMPS B ELEC 1 switch on the P5 panel to the OFF position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

 27-32-00
 COMPUTER P/N 65-52822  ú CONFIG 2 ú 05 Page 515 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 (b) (c) (d) (e) (f) (g) (h) (i)  Make sure that the HYD PUMPS A ELEC 1 switch is in the OFF position.Set the ALTERNATE FLAPS switch to the ARM position.Hold the UP/OFF/DOWN switch to UP until the flaps are at the 5-unit position.Make sure that the LE flaps stay fully extended.Make sure that the display on each SMC shows ASYMETRY YES.Hold the UP/OFF/DOWN switch to DOWN until the flaps are at the 10-unit position.Set the ALTERNATE FLAPS switch to the NORMAL position.Set the HYD PUMPS B ELEC 1 switch to the ON position.
 S 865-100-002
 (3)  Move the flaps to the UP position.
 S 865-101-002
 (4)  Set the HYD PUMPS B ELEC 1 switch to the OFF position.
 S 865-102-002
 (5)  Push the ON/OFF button on each SMC.
 S 865-103-002
 (6)  Close these circuit breakers: (a) P6 Panel 1) AURAL WARNING (b) P18 Panel 1) L ALPHA VANE HTR 2) R ALPHA VANE HTR
 S 865-104-002
 (7)  Remove electrical power (Ref 24-22-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

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 COMPUTER P/N 65-52822  ú CONFIG 2 ú 03 Page 516 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 ANGLE OF AIRFLOW SENSOR - REMOVAL/INSTALLATION
______________________________________________
 1.  General_______
 A.  This subject contains two tasks, one for the removal and one for the installation of the angle of airflow (AOA) sensor.
 B.  The Angle of Airflow Sensor can also be identified as the Stall Warning Sensor or as the Sensor for the Sensor Instl - Stall Warning.
 TASK 27-32-11-004-021-001
 2.  Angle of Airflow Sensor Removal (Fig. 401)_______________________________
 A.  Access
 (1)  Location Zone
 101, 102 Control Cabin

Angle of Airflow Sensor Installation
Figure 401

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

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 COMPUTER P/N 65-52819  ú CONFIG 1 ú 01 Page 401 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 B. Procedure
 S 864-043-001
 (1)  
Open these circuit breakers and attach DO-NOT-CLOSE tags:

 (a)  
P6 Panel
 1) AUTOSLAT 1 AC
 2) AUTOSLAT 1 DC
　
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