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A 737-300/400/500MAINTENANCE MANUAL
 6.  Control Column Shaker
_____________________
 A.  The control column shaker vibrates the control column when activated by the SMC. A shaker is attached to the front of each pilot's control column. Each shaker has a motor geared to a coaxially mounted weighted ring. When the motor is activated, it rotates the out of balance ring, and the resulting vibration shakes the control column. SMC 1 activates the captain's shaker, and SMC 2 activates the first officer's shaker.
 7.  Operation
_________
 A.  Functional Description
 (1)  
The air mode for the stick shaker in the stall management computer is determined by one of these conditions:

 (a)  
Both nose and main gear squat switches indicate "in air".

 (b)  
Either nose or main gear "in air" and 110 Knots IAS.

 (c)  
Neither gear "in air" but 160 Knots IAS.

 (2)  
During takeoff, when the right main gear shock strut extends, the air/ground relays energize to enable the stall warning system. Each SMC receives signals from its angle of airflow sensor and flap position transmitter. These signals are and other flight data are processed by the SMC 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 SMC 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 SMC input/output circuits while the airplane is on the ground. Pressing the STALL WARNING TEST NO. 1 or NO. 2 button will activate the control column shaker unless the SMC 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 STALL MANAGEMENT ú

 27-32-00
 COMPUTER P/N 65-52822  ú CONFIG 2 ú 02 Page 7 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

SELF TEST

STALL MANAGEMENT CAPTAIN'S COMPUTER CONTROL COLUMN NO. 1 SHAKER MOTOR (LEFT)

PITCH LIMIT

CAPTAIN'S EADI
FLAP POSITION
AOA

GROUND DIGITAL PROXIMITY FLIGHT DATA WARNING ACQUISITION COMPUTER UNIT
AOA

FLAP POSITION

PITCH LIMIT
FIRST OFFICER'S EADI
STALL
MANAGEMENT
COMPUTER

FIRST OFFICER'S
NO. 2
CONTROL COLUMN
(RIGHT)
SHAKER MOTOR
SELF TEST

Stall Warning System Block Diagram
Figure 2

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH STALL MANAGEMENT ú

 27-32-00
 COMPUTER P/N 65-52822  ú  CONFIG  2
 ú  07  Page 8
 ú  Nov 15/98 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 STALL WARNING SYSTEM - TROUBLE SHOOTING
_______________________________________
 1.  General_______
 A.  The following trouble shooting procedure contains a BITE test for isolating faults in the stall warning system. A fault exists in the system if the stick shakers do not activate during a stall warning system self-test. A self test is initiated when the STALL WARNING TEST NO. 1 or NO. 2 switch in the flight compartment is pressed.
 NOTE: When airplane is parked and hydraulic power is off, leading edge
____ slats may droop enough from the retracted position to cause an asymmetry signal. This will cause a failed stall warning self-test. This can be corrected by turning hydraulic power on and restoring slats to the retracted position, or by opening the STALL WARNING ASYM circuit breaker on the P18 panel.
　
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