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 A.  A self-test pushbutton switch for each computer is located on the STALL WARNING TEST module installed in the P5 overhead panel. Pressing the No. 1 or No. 2 test button will activate the corresponding control column shaker. If the stall warning computer has detected any fault, the test button will not activate the shaker. Once the fault is corrected, the self-test will again activate the shaker. The stall warning computer will turn off the shaker motor if the test switch is held on for more than 20 seconds.
 6.  Control Column Shaker
_____________________
 A.  The control column shaker vibrates the control column when activated by the stall warning computer. A shaker is clamped to the front of each pilot's control column. Each shaker consists of a motor geared to a coaxially mounted weighted ring. Energizing the motor rotates the out of balance ring, and the resulting vibration shakes the control column. Stall warning computer No. 1 activates the captain's shaker, and computer No. 2 activates the first officer's shaker.
 7.  Operation
_________
 A.  Functional Description
 (1)  
The stall warning systems are in their normal operating mode when airplane weight is off the main landing gear.

 (2)  
During takeoff, when the right main gear shock strut becomes uncompressed, the air/ground relays energize to enable the stall warning system. Each computer receives signals from its angle of airflow sensor and flap position transmitter. These signals are processed by the computer along with other flight data to determine if the airplane is approaching a stall condition.

 (3)  
When airplane flight conditions approach a stall due to a high angle of attack or a low airspeed, an output relay in the computer is turned on to supply 28 volts dc to the shaker motor. The motor rotates the weighted ring in the shaker which vibrates the control column.

 (4)  
Normally, both computers will activate their respective shakers simultaneously, however, if one is not activated, both control columns will still shake since they are connected together by the torque tube.

 (5)  
The stall warning self-test switches allow a check of each shaker motor and computer input/output circuits while the airplane is on the ground. Pressing the No. 1 or No. 2 STALL WARNING TEST button will activate the control column shaker unless the computer detects a fault with the system or has a fault stored from the previous flight.

 B.  
Control

 (1)  
Operation of the stall warning systems is automatic. No control functions are exercised.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú CONFIG 1 ú 01 Page 9 ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

N1 ENGINE 1
ENGINE N1 VALID
INDICATING
N2 ENGINE 2

SYSTEM
LEFT
ANGLE OF ATTACK
AOA SENSOR
RIGHT FLAP FLAP POSITION POSITION XMTR

AIRSPEED
LEFT DADC

ON GND
AIR GND IN AIRRELAYS

STALL WARNING SELF TEST TEST SWITCH 1

LEADING EDGE
ASYMMETRY
INDICATION
MODULE

N1 ENGINE 2
ENGINE N1 VALID
INDICATING
N2 ENGINE 1

SYSTEM
RIGHT
ANGLE OF ATTACK
AOA SENSOR
LEFT FLAP FLAP POSITION POSITION XMTR

AIRSPEED
RIGHT DADC

ON GND
AIR GND IN AIRRELAYS

STALL WARNING SELF TEST TEST SWITCH 2

LEADING EDGE
ASYMMETRY
INDICATION
MODULE

 

STALL WARNING COMPUTER NO. 1 (LEFT)
STALL WARNING COMPUTER NO. 2 (RIGHT)

CAPTAIN'S CONTROL COLUMN SHAKER MOTOR

FIRST OFFICER'S CONTROL COLUMN SHAKER MOTOR
Stall Warning System Block Diagram
Figure 2

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú  CONFIG  1
 ú  08  Page 10
 ú  Mar 15/91 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
 1.

2.

3.

A
737-300/400/500MAINTENANCE MANUAL
　
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