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A
747-400 MAINTENANCE MANUAL
 STALL WARNING SYSTEM - DESCRIPTION AND OPERATION
________________________________________________
 1.  General (Fig. 1)_______
 A.  Two stall warning systems alert the pilots of an approaching stall condition by shaking the pilots' control columns. Components for each stall warning system include a stall warning management computer and a control column shaker. The stall warning management computers are part of the Modularized Avionics and Warning Electronics Assembly (MAWEA) (Ref 31-51-00).
 B.  Each stall warning management computer (SWMC) is supplied with leading and trailing edge flap position along with other flight information. From this data the SWMC calculates the maximum value of airplane angle of attack allowed before approaching a stall condition. If this maximum value is exceeded by the angle of attack, the SWMC activates both control column shakers to warn the pilots.
 2.  Stall Warning Management Computer_________________________________
 A.  Each stall warning management computer uses data from the air data computers, the flap control units, and other airplane systems to determine whether to activate the control column shaker. The computer is a circuit card in the MAWEA card file located in the compartment on the right side of the nose gear wheel well. The computer is powered by +5 volts dc and |12 volts dc from the two MAWEA power supply units.
 B.  Each SWMC receives two separate sets of data for flap position, minimum buffet onset speed, nose gear status, and air/ground from the two Master Monitor Cards in the MAWEA. A third set of flap position data are provided to each SWMC by the center flap control unit.
 (1)  
Master Monitor Card A receives information from the following sources:

 (a)  
Left Flap Control Unit
 1) Leading edge flap position
 2) Trailing edge flap position

 (b)  
Proximity Switch Electronics Unit
 1) Air/Ground mode
 2) Main gear down/lock
 3) Nose gear compressed
 4) Nose gear down/lock

 (c)  
Left Flight Management Computer
 1) Minimum buffet onset speed

 (2)
Master Monitor Card B receives inputs from the following sources:

 (a)  
Right Flap Control Unit
 1) Leading edge flap position
 2) Trailing edge flap position

 (b)  
Proximity Switch Electronics Unit
 1) Air/Ground mode
 2) Main gear down/lock
 3) Nose gear compressed

 

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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

747-400 MAINTENANCE MANUAL
SEE A
CONTROL COLUMN 
SEE  B  CONTROL COLUMN SHAKER 
LEFT STALL WARNING MANAGEMENT COMPUTER  RIGHT STALL WARNING MANAGEMENT COMPUTER  A 

MAWEA CARD FILE
B

Stall Warning System Component Location
Figure 1

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 4) Nose gear down/lock
 (c)  
Right Flight Management Computer
 1) Minimum buffet onset speed

 (3)  
Each SWMC receives inputs from both Master Monitor Cards and from the following sources:

 (a)  
Center Flap Control Unit
 1) Leading edge flap position
 2) Trailing edge flap position

 (b)  
Selected Inertial Reference Unit
 1) Body pitch rate
 2) Body longitudinal acceleration
 3) Body normal acceleration
 4) Pitch angle

 (c)  
Selected Air Data Computer
 1) Angle of attack
 2) True Airspeed
 3) Mach number
 4) Computed airspeed
 5) Altitude
 6) Vmo/Mmo discrete

 (d)  
AFCS Mode Control Panel
 1) Speed Brake Control Lever Position
　
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