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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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