(b)  
P18 Circuit Breaker panel 1) AUTO FLT CONT SYS A MACH TRIM AC 2) AUTO FLT CONT SYS A SNSR EXC AC 3) AUTO FLT CNT AUTOTHROTTLE AC 4) AUTO FLT CNT YAW DAMPER AC

 D.  Stabilizer Position Sensor Removal
 S 034-005
 (1)  
Disconnect the electrical connectors on the sensor.

 (2)  
Loosen the screw in the crank.

 S 034-004
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-11-31
 ALL  ú ú 01 Page 401 ú Jul 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

SEE A
MICRO ADJUSTING NUT
CRANK ARM
SENSOR
CLAMP
FEEL AND CENTERING UNIT
STABILIZER POSITION SENSOR (RIGHT) (LEFT OPPOSITE) 1
SEE B (RIGHT) FWD CONTROL
SEE C (LEFT)
ROD
A
CRANK
SEE G

ARM
CRANK ARM BOLT
NUT AND WASHER

SEE E
CLAMP BOLT NUT
AND WASHER SENSOR CLAMP

STABILIZER POSITION SENSOR (RIGHT)
B 1
SENSORS LOCATED ON
OPPOSITE SIDES OF FEEL
AND CENTERING UNIT

Stabilizer Position Sensors Installation
Figure 401 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-11-31
 ALL  ú ú 01 Page 402 ú Jul 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
NUT
AND NUT
ZERO REFERENCE
ADJUSTMENT MARK
SENSOR CASE
SENSOR CASE
ZERO INDEX MARK
SENSOR SHAFT

LEFT CRANK ARM RIGHT CRANK ARM

F
G

Stabilizer Position Sensors Installation Figure 401 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-11-31
 ALL  ú ú 01 Page 403 ú Jul 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 034-006
 (3)  
Loosen the screw in the sensor clamp.

 S 024-006

 (4)  
Remove the sensor.

 TASK 22-11-31-424-007
 3. Stabilizer Position Sensor Installation
_______________________________________
 A. References
 (1)  
12-31-01/201, General Zone Diagram

 (2)  
27-31-00/201, Elevator and Tab Control System

 (3)  
27-41-00/501, Horizontal Stabilizer Trim Control System

 B. Access
 (1)  
Location Zone
 705 Tail Cone Access Door

 (2)  
Access Panel
 3802 Tail Cone Access Door

 C. Prepare for Installation
 S 864-008
 (1)  
Set the horizontal stabilizer at 0 degrees (3 units of trim) equal to the "B" dimension of 41.57 |0.05 inches (Ref 27-41-00/501, Horizontal Stabilizer Trim Control System).

 S 864-009

 (2)  
Make sure that the mach trim actuator is nulled.

 NOTE: The actuator is nulled when the voltage measured between the
____ FCC front test connector J6-37 and J6-1 is below 50 mvdc.
 S 824-010
 (3)  
Align the zero index mark on the sensor case with the zero index mark on the sensor shaft.

 (4)  
Install the sensor in the clamp and the sensor shaft in the crank.

 S 824-004

 (5)  
Make sure the zero index mark on the sensor shaft stays aligned with the slot in the crank.

 (6)  
Tighten the crank screw.

 S 434-011
 S 434-005
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 22-11-31
 ALL  ú ú 01 Page 404 ú Jul 15/93
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 2(30)