Aileron Control Force Transducer
Figure 2A
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH CONTROL ú
22-13-00
WHEEL STEERING ú ú 04 Page 6 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(c) Each differential transformer primary winding uses 26 vac from the associated FCC. Center tapped secondary windings are wound to provide output signals that are in phase. The output voltage is linearly proportional to the manual force applied at the control wheel.
(2) Access and Location
(a) The aileron force transducer is located on the aileron control drum forward of the nose wheel well under the flight deck floor. The transducer is on the aft side of the assembly. Access is through the main E/E equipment compartment.
B. A/P Lateral Control Servos - Location and Linkages (Fig. 3)
(1)
The left and center ALCSs are located in the main landing gear wheel well, left of the keel beam (left ALCS forward; center ALCS aft). The right ALCS is located to the right of the keel beam. They are installed with four mounting bolts. Two hydraulic lines and an electrical connector complete the installation. Left, center, and right ALCSs are controlled by L, C, and R FCCs and powered by the L, C, and R hydraulic systems respectively.
(2)
Outputs from the left and center servos are mechanically linked to the feel, centering, and trim assembly. The right servos output is linked directly to the override mechanism and, indirectly to the feel, centering and trim assembly through a bus cable, quadrant, and linkage. Servo output as a result of autopilot command is fed back to the control wheels through the feel, centering, and trim assembly.
C. A/P Rollout Guidance Servos - Location and Linkage (Fig. 4)
(1)
Three autopilot rollout guidance servos (ARGSs) are side by side at the base of the vertical stabilizer immediately forward of the rudder hinge line. Each servo has an output rod connected to the rudder feel, centering and trim mechanism on the aft quadrant. Access to the servos is through a removable panel on the lower left side of the vertical stabilizer.
(2)
Each ARGS has its own drive linkage to the aft quadrant which provides feedback to the rudder pedal. The rudder control system has dual mechanical drive links to the ratio changer mechanism with primary and backup linkages to the yaw damper summing lever. There is no feedback from the yaw damper to the rudder pedals. Three power control actuators (PCAs) use a common mechanical input to deflect the rudder surface.
D. Autopilot Servo Components (Fig. 5)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-00
ALL ú ú 06 Page 7 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-00
ALL ú ú 04 Page 8 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ALCS (3)SEE A
CABLES TO F/O'SCONTROL WHEEL
CABLES TO CAPTAIN'SCONTROL WHEEL
RIGHT AILERON
KEEL
LEFT AILERONQUADRANT
BEAM
CONTROL ROD
QUADRANT LEFTAILERONCONTROL
RIGHT CABLES
AILERONCONTROLCABLES CONTROL ROD RIGHT ALCS OUTPUTCENTER ALCSRIGHTCRANK AND CONTROL
(LEFT ALCS FORWARD) ALCS
ROD (HIDDEN) CENTER ALCSOUTPUT CRANK
A
ALCS Location and Linkage
Figure 3
A
757
MAINTENANCE MANUAL
(1)
Each A/P servo (ALCS and ARGS) contains two solenoid valves, an electrohydraulic servo valve (EHSV), two linear variable differential transducers (LVDTs), and a pressure regulator/relief valve. Hydraulic power is applied through pressure and return ports at one end of the servo. A 25-micron filter is in the hydraulic input port of unit.
中國航空網 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(158)
