(1)
Each of the two elevator control force transducers provides an analog input to each FCC. The input is proportional to force applied to the control column. One transducer is installed at each end of the elevator torque tube. The torque tube is connected to the captain's and first officer's control columns. The transducer is installed between a crank assembly and an arm assembly. The crank assembly is attached directly to the torque tube. The arm assembly is attached via a rod to the cable tension regulator and cables.
(2)
Three separate differential transformers are housed in each transducer housing. A microadjustment rod end connects the moveable portion of the transducer to the arm assembly. The housing mount bearing is attached to the crank assembly. The unit is installed with bolts, washers and nuts. The bolts must have a slip-fit through the bearings to ensure no loads are applied during installation. A temporary bushing is used to center the arm assembly in the crank assembly and the microadjustable rod end is adjusted until a slip fit is obtained. Three cables, each with a 6 pin connector, exit the transducer. Cables are supported with standard clamps.
(3)
Each differential transformer primary winding uses 26 vac from the associated FCC. Center tapped secondary windings are wound to provide output signals that are inphase. The output voltage is linearly proportional to the manual force applied at the control column.
(4)
The elevator force transducers are forward of the nose wheel well under the flight deck floor. Access is through the main E/E equipment compartment or through the external access door forward of the nose wheel well.
B. Autopilot Pitch Control Servo Locations and Linkages (Fig. 3)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
INPUTS OUTPUTSINPUTS OUTPUTS
VERTICAL NAV MODE REQUESTFLIGHT LEVEL CHANGE MODE REQUESTALTITUDE HOLD MODE REQUESTVERTICAL SPEED MODE REQUESTALTITUDE SELECTEDSPEED SELECTEDMACH SELECTEDVERTICAL SPEED SELECTEDAPPROACH MODE REQUEST
AFDS MODE CONTROL PANEL
VERTICAL STEERING RATEVERTICAL STEERINGSELECTED AIRSPEEDSELECTED ALTITUDESELECTED MACH
FLIGHT MANAGEMENT COMPUTER (L&R)
ALTITUDE - BAROMETRICALTITUDE - 29.29 (CORRECTED)ALTITUDE RATEIMPACT PRESSUREMACHINDICATED ANGLE OF ATTACKCOMPUTED AIRSPEEDTRUE AIRSPEEDMAX OPERATING SCHEDULE
AIR DATA COMPUTER (L&R)
BODY NORMAL ACCELERATIONROLL ANGLEFLIGHT PATH ACCELERATIONBODY YAW RATEBODY PITCH RATEINERTIAL VERTICAL SPEEDINERTIAL ALTITUDEPITCH ATTITUDE RATEINERTIALLY FILTERED ALTITUDE RATEGROUND SPEEDVERTICAL ACCELERATION
INERTIAL REFERENCE UNIT (L)
STABILIZER POSITION
STABILIZER POSITION MODULE
AUTOTRIM VALID
STABILIZER TRIM AND ELEVATOR ASYMMETRYLIMIT MODULE
FLIGHT CONTROL STABILIZER TRIM AND ELEVATORCOMPUTER - LEFT ASYMMETRY LIMIT MODULE
AIRPLANES WITH CONTROL WHEEL STEERING
Flight Control Computer Pitch Axis Control Inputs and Outputs
Figure 2
G23153
A
757
MAINTENANCE MANUAL
CAPTAIN F/O
TRANSDUCER SEE
L FCC
C FCC
R FCC
TRANSDUCER
FINE ADJUSTMENT
Elevator Control Force Transducer
Figure 2A
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
SEE A
TORQUE
TORQUE
TUBES
BOX
SEE B
SEE B
SEE B
FEEL AND FWD
CENTERING UNIT
ASSEMBLY
(REF) OUTBD
A
Autopilot Pitch Control Servo Locations and Linkages 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：757 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 1(117)
