C.  
On airplanes with stick nudger installed, ensure stick nudger actuator is fully extended (Ref Chapter 27, Elevator and Tab Control Systems).

D.  
Align index marks on sensor housing and sensor shaft.

E.  
Install sensor in sensor clamp with index mark in vertical position relative to mounting position of sensor clamp.

F.  
Tighten screw in sensor clamp 8 to 12 pound-inches.

G.  
Install sensor clamp removed in step 2.F.

H.  
Without disturbing position of sensor, install sensor crank on sensor shaft.

I.  
Tighten screw in sensor crank and tighten nut 8 to 12 pound-inches.

J.  
Close autopilot AC circuit breakers.

K.  
Adjust neutral shift sensor (Ref Elevator Neutral Shift Sensor - Adjustment/Test).

L.  
Replace access panel.

Feb 20/84 22-11-122 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

H19334
Elevator Neutral Shift Sensor Installation  580 
22-11-122Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/85 

ELEVATOR NEUTRAL SHIFT SENSOR - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1.  Elevator Neutral Shift Sensor Adjustment
A.  General
(1)  The autopilot system and all elevator rigging must be fully adjusted and operable before the neutral shift sensor can be adjusted. The mach trim system must also be operable and the actuator fully extended.
B.  Equipment and Materials
(1)  
VTVM - Hewlett Packard, Model 410C

(2)  
Test Set - Autopilot Elevator/Rudder/Aileron Control Unit - P/N F80217-125

C.  Prepare to Adjust Sensor
(1)  
Provide electrical power and hydraulic power.

(2)  
Position hydraulic system A and B switches on P5 panel to OFF and open FLT CONT SYS circuit breaker on P6 load control center.

WARNING:  PRESSURIZING HYDRAULIC SYSTEMS WILL SUPPLY POWER TO RUDDER, AILERON, ELEVATOR, SPOILER AND SPEED BRAKE SYSTEMS. CARE SHOULD BE TAKEN TO ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.

(3)  
Open autopilot circuit breakers on P6 and P18 load control centers.

(4)  
Close mach trim circuit breakers on P6 load control center.

(5)  
Remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).

(6)  
Set horizontal stabilizer to 3 units of trim equal to B dimension of 41.57 士0.05 inches (Ref Chapter 27, Horizontal Stabilizer Trim Control System).

(7)  
Ensure mach trim actuator is fully extended (Ref Chapter 27, Elevator and Tab Control System).

(8)  
On airplanes with stick nudger installed, ensure stick nudger actuator is fully extended (Ref Chapter 27, Elevator and Tab Control System).

(9)  
Connect power cable between test set and D152 electronic equipment rack service outlet.

(10)
Disconnect D1681 (A system) and D1687 (B system) connectors from autopilot actuators and connect test set to actuator A and actuator B.

(11)
Connect VTVM to LVDT FEEDBACK J10A and J11A on test set.

(12)
Disconnect neutral shift sensor connector D1829 (A system) or D1677 (B system) and connect to test cable between sensor and (A SENSOR) on test set.

Feb 20/93 22-11-122 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(13) Set switches on test set as follows:
(a)  
LVDT FEEDBACK switches A, B to ON.

(b)  
LVDT EXCITATION switches A, B to ON.

(c)  
NSS EXCITATION switch A to ON, B to OFF.

(d)  
NSS FEEDBACK switches A, B to OFF.

(e)  
SOLENOID EXCITATION switches Piston and Engage, A and B to ON.

(f)  
CURRENT SELECT switch to A T-VALVE.

(g)  
A&B SOLENOIDS switches to A NORM, B NORM and ON.

(h)  
ACTUATOR SELECT switch to A+B COMMON.

(i)  
POWER switch to ON.

NOTE:  All lights on except NSS EXCITATION B.
(14) Turn on hydraulic systems A and B by closing hydraulic system A and B switches on P5 panel and closing FLT CONT SYS circuit breaker on P6 panel.
WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
D.  Adjust Sensor
(1)  
Operate position control knob A on test set until meter is at lowest reading (A/P actuators at null).

(2)  
Operate position control knob A on test set to move elevator surfaces down until the voltage at J10A and J11A increases to 2.00 +0.05 volts and lock knob in place.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 AUTO FLIGHT 自動飛行 2(16)