H19295
Pitch Force Transducer Installation 580
22-11-92Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/86
500 Pitch Transducer Rigging Pin Locations
Feb 20/86 Figure 402 22-11-92
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
B. Hold pitch force transducer in position and install with bolts, washers, and nuts to quadrant assembly.
NOTE: Adjustable end should face forward on right quadrant. Adjustable end should face aft on left quadrant.
C. Adjust force transducer (Ref Pitch Control Wheel Steering Force Transducer -Adjustment/Test).
D. Install lockwire through locknuts, fine adjustment nut, and washer tab on adjustable rod end.
E. Clamp force transducer cables to structure.
NOTE: Verify that cable clamping does not preload transducer.
F. Connect force transducer connectors to airplane wiring.
G. Remove rigging pins.
H. Close access doors.
512
22-11-92 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/86
PITCH CONTROL WHEEL STEERING FORCE TRANSDUCER - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. General
A. Each control column has a pitch force transducer installed on elevator control quadrant assembly. Two force transducers are installed opposite to each other and are electrically 180 degrees out of phase to reduce null error voltage to the autopilot system. Following procedures are intended to verify force transducers are adjusted and operating properly. Adjustment of force transducers is fairly critical and if not adjusted properly, autopilot may not engage.
2. Pitch Force Transducer Adjustment
A. Equipment and Materials
(1)
Test box F80218-42
(2)
Adapter Cables (2 required) F80218-44
(3)
Rigging Pins E1 and E5 - 0.309 +0.003/-0.0-inch diameter, 6.0-inch minimum length (MS20392-4)
(4)
Rigging pins E2 and E3 (2) - 0.4941 士0.0004-inch diameter, 1.5-inch minimum length
(5)
VTVM - Hewlett Packard Model 410C
B. Prepare for Adjustment
(1)
Provide electrical power and energize load control center P6 and P18.
(2)
Ensure elevators are properly rigged (Ref Chapter 27, Elevator and Tab Control System)
(3)
Open autopilot circuit breakers on P6 and P18 panels.
(4)
Open lower nose access door 1103 and tail cone access door 3802 (Ref Chapter 12, Access Doors and Panels).
Feb 20/93 22-11-92 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Adjust Pitch Force Transducer (Fig. 501)
(1)
Install rigging pin E1 in forward left control quadrant and rigging pin E5 in right aft control quadrant (Fig. 502).
NOTE: Rigging pins should fit freely.
(2)
Disconnect both force transducer cable connectors from airplane wiring for each transducer.
(3)
Remove bolt, washer, and nut from adjustable end of force transducers.
(4)
Remove shoulder bolts from quadrant assemblies and install rigging pins E2 and E3.
NOTE: Rigging pin locations are labeled on quadrant assembly. If cables are rigged properly, the rigging pins should be easily installed.
(5)
Connect captain's force transducer to the captain's connector on the test box with adapter cable.
(6)
Connect first officer's force transducer to the first officer's connector on the test box with adapter cable.
(7)
Energize test box and allow force transducers to warm up and stabilize for 15 minutes.
CAUTION: USE ONLY 115 VOLTS, 400 HZ AC. USE OF 60 HZ VOLTAGE WILL DAMAGE TRANSDUCERS.
(8)
Position the SYSTEM A-SYSTEM B switch in the SYSTEM A position.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) AUTO FLIGHT 自動(dòng)飛行 2(5)
