H19367
Elevator Position Sensor Installation 595
22-11-301Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/81
ELEVATOR POSITION SENSOR - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. Elevator Position Sensor Adjustment
A. General
(1) The autopilot system and all elevator rigging must be fully adjusted and operable before the actuator 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 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 +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 -3 test cables, J1 to actuator A and J2 to actuator B on test set.
(11)
Connect VTVM to LVDT FEEDBACK J10A and J11A on test set.
(12)
Disconnect sensor connectors D1711 (A system) or D1679 (B system) and connect to -4 test cable between sensor and J-4 (B SENSOR) on test set.
(13)
Set switches on test set as follows:
(a)
LVDT FEEDBACK switches A ON, B ON.
(b)
LVDT EXCITATION switches A ON, B ON.
Feb 20/93 22-11-301 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(c)
NSS EXCITATION switch B to ON, switch A to OFF.
(d)
NSS FEEDBACK switches to OFF.
(e)
SOLENOID EXCITATION PISTON and ENGAGE switches to ON.
(f)
CURRENT SELECT switch to A T-VALVE.
(g)
A&B SOLENOIDS switches to A NORMAL, B NORMAL and ON.
(h)
ACTUATOR SELECT switch to A&B COMMON.
(i)
POWER switch to ON.
NOTE: All lights should be ON except A NSS excitation.
(14) Position hydraulic system A and B switches on P5 panel to ON and close FLT CONT SYS circuit breaker on P6 load control center.
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 A on test set until meter is at lowest reading (A/P actuators at null).
(2)
Operate position control on test set to move elevator surfaces down until the voltage at Jl0A and J11A increases to 2.00 +0.05 volts.
(3)
Check to ensure right elevator trailing edge is in line with tail cone index +0.06 inch.
(4)
Remove VTVM from Jl0A and J11A and connect VTVM to B NSS FEEDBACK J7B and J8B on test set.
(5)
Loosen screw on sensor clamp only enough to allow sensor to be rotated.
(6)
Rotate sensor housing slowly until 0.48 +0.05 volts is obtained, then tighten clamp screw 8 to 12 pound inches.
(7)
Remove lockwire and turn thumb nut on microadjustment rod until 0.48 +0.03 volts is obtained.
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