(2)
On 10-61072-7 or -8 transducer, wrap cable approximately seven turns.
L. Rotate control wheel in direction to tighten cable around spool then clamp cable on bracket. Rotate control wheel both directions several times and verify that cable does not restrict movement. Relocate cable in bracket clamps if required and recheck.
M. Connect force transducer connectors to airplane wiring.
N. Close access door.
O. Remove control column tag.
P. Test roll control wheel steering force transducer (Ref Adjustment/Test).
580
Oct 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-112 Page 403
ROLL CONTROL WHEEL STEERING FORCE TRANSDUCER - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. General
A. These procedures are intended to verify the force transducer is adjusted and operating properly. The adjustment of the force transducer is fairly critical. If not adjusted properly, the autopilot may not engage.
2. Roll Force Transducer Adjustment
A. Equipment and Materials
(1)
Test box F80218-42
(2)
Adapter Cables F80218-44
(3)
VTVM - HEWLETT Packard, Model 410C
(4)
Shims (2) - 0.021 +0.003/-0.0 inch
B. Prepare for Adjustment
(1)
Provide electrical power and energize load control center P6 and P18.
(2)
Pressurize hydraulic systems A and B (Ref 29-11-0 MP and 29-12-0 MP).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(3)
Ensure hydraulic power is applied to both aileron power control units.
(4)
Rotate control wheel 士30 degrees and gradually center control wheel. Tag control wheel indicating it should not be moved.
NOTE: Power control units must be operative to ensure cables are aligned properly in relation to force transducer.
(5)
Remove system A and B hydraulic power (Ref 29-11-0 and 29-12-0).
(6)
Open autopilot circuit breakers P6 panel and P18 panel.
(7)
Open lower nose access door 1103 (Ref Chapter 12, Access Doors and Panels).
C. Adjust Roll Force Transducer (Fig. 501)
(1) Disconnect force transducer connectors from airplane wiring.
Feb 20/93 22-11-112 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H19325
Roll Force Transducer Adjustment 580
22-11-112 Figure 501 Feb 20/86
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2)
Insert shims between shaft and drum. Gap settings should be 0.021 +0.003/-0.0 inch.
(3)
Remove bolt from adjustable end of force transducer.
(4)
Connect force transducer to the captain connector with adapter cable and energize test box. Allow transducer to warm up and stabilize for 15 minutes.
CAUTION: USE ONLY 115 VOLTS, 400 HZ AC. USE OF 60 HZ VOLTAGE MAY DAMAGE TRANSDUCER.
(5)
Position the system A-system B switch in the system A position.
(6)
Position test box selector switch to CAPT and measure and record sum of output voltage at static conditions. The output sum should not exceed 160 mv. If the null is higher, loosen electrical cable to determine if null can be lowered by an adjustment to the cable installation. Tighten cable clamps.
NOTE: The fine and coarse adjustments should be checked for some threads showing. If voltages recorded prior to installation, equal voltages should be obtained. If dc analog voltage was recorded on FCC test connector J7-63, adjusting to equal voltage assures proper null.
(7)
Repeat step with the system A-system B switch in the system B position. After the step is completed return the switch to the system A position.
(8)
Remove lockwire from locknuts, fine adjustment nut, and washer tab on adjustable rod end. Adjust course fitting on each force transducer until mounting bolt can be easily inserted. Install bolt, washer, and nut.
NOTE: Coarse adjustment is approximately 0.016 inch per turn. Fine adjustment is approximately 0.006 inch per turn. 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(12)
