737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(23)

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Flap Position Transmitter
_________________________
 A.  The flap position transmitter for each system provides a signal which represents trailing edge flap position. The transmitters are located on the wing rear spars between the two outboard flap tracks. Each transmitter provides outputs to the stall warning system, the autopilot system, and the pilots' trailing edge flaps position indicator.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú CONFIG 1 ú 03 Page 1 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL

ANGLE OF AIRFLOW SENSOR

Stall Warning System Component Location
Figure 1 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú  CONFIG  1
 ú  01  Page 2
 ú  Mar 15/90 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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

737-300/400/500
MAINTENANCE MANUAL

 

B

C

Stall Warning System Component Location
Figure 1 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú CONFIG 1 ú 01 Page 3 ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
BITE INSTRUCTIONS ì PRESS START BITE ì ALL LIGHTS WILL GLOW FOR TWO SECONDS ì SUSTAINED LIGHT INDICATES FAILED LRU
START BITE
(TO CLEAR FAULT
MEMORY, PUSH FOR
10-20 SECONDS)
CAPTAIN'S CONTROL COLUMN
INTERNAL
CONTROL COLUMN SHAKER
FAILURE
AIR DATA COMPUTER
FIRST OFFICER'S
AOA SENSOR
CONTROL COLUMN
FLAP POSITION
CONTROL COLUMN SHAKER N 1
N 2
DISCRETE
IRU 1
CABIN FLOOR
DIGITAL STALL WARNING COMPUTER
D P/N 65-52819-
S/N
E
1 ALL EXCEPT AIRPLANES WITH 65-52819-3 0R 65-52819-10 STALL WARNING COMPUTER
Stall Warning System Component Location
Figure 1 (Sheet 3)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH DIGITAL STALL WARNING ú

 27-32-00
 COMPUTER P/N 65-52819  ú  CONFIG  1
 ú  01  Page 4
 ú  Mar 15/90 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 4.  Digital Stall Warning Computer (Fig. 2)
______________________________
 A.  The stall warning computer for each system uses the signals from the AOA sensor, the flap position transmitter, and other airplane systems to determine whether to activate the control column shaker. The computers are located on the E1-1 electronics shelf. Refer to applicable wiring diagram for details of wire routing.
 B.  Stall warning computer No. 1 controls the captain's control column shaker. Computer No. 1 is powered by 28 volts dc and 115 volts ac through circuit breakers on the P18-2 panel from the standby bus. Inputs to computer No. 1 come from the following sources:
 (1)  
Left AOA sensor

 (2)  
Right flap position transmitter

 (3)  
N1 and N1 valid tachometer indicator for engine No. 1

 (4)  
N2 tachometer indicator for engine No. 2

 (5)  
Air/ground relays on E-11 shelf

 (6)  
Leading edge light module

 (7)  
Left digital air data computer (DADC 1) on ARINC 429 bus

 (8)  
STALL WARNING TEST NO. 1 switch on P5-18 module
　
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