(2)  
Outputs are servo arm and engage commands (ALCS and ARGS), mode status (MCP), F/D roll commands (EADI), and Flight Mode Annunciations (EADI FMA). Cross-channel data is provided to and from each of the other FCCs.

 2.  Component Details
_________________
 A.  AIRPLANES WITH CONTROL WHEEL STEERING;
 Aileron Control Force Transducer (Fig. 2A)

 (1)  General Description
 (a)  
The aileron control force transducer provides an analog input to each FCC proportional to force applied to the control wheel. One transducer unit is installed on the pilot's and one on the F/O's aileron drum assembly. A lost motion arm couples forces applied at the control wheel to the drive drum. A 0.065 inch gap on each side of the arm allows for movement of the transducer before the arm moves the drum.

 (b)  
Three separate differential transformers are housed within each unit. A microadjustment rod end connects the movable portion of the transducer to the crank on the aileron drum assembly. The housing mount bearing is attached to the drive drum. The unit is installed with 2 mounting bolts/nuts which must have a slip-fit through the bearings to ensure no loads are applied during installation. Temporary shims are used to center the lost motion arm and the microadjustable rod end is adjusted until the slip fit is obtained. Three 30 inch cables, each with a 6 pin connector, exit the transducer. Cables are supported with standard clamps.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
INPUTS  OUTPUTS
FLIGHT DIRECTOR ON
HEADING SELECTED
BANK ANGLE LIMITS

LOCALIZER MODE (A/O)
HEADING SELECT MODE REQUEST

APPROACH MODE (A/O)
HEADING HOLD MODE REQUEST

LNAV MODE OPERATE
LNAV MODE REQUEST

HEADING HOLD MODE OPERATEAPPROACH MODE REQUESTLOCALIZER MODE REQUESTMODE CONTROL PANEL
MODE CONTROL PANEL
TRUE AIRSPEEDIMPACT PRESSURE
AIR DATA COMPUTER (L&R)
LOCALIZER DEVIATIONSELECTED RUNWAY HEADINGTUNE INHIBITED
ILS RECEIVER (L)
HORIZONTAL STEERING COMMANDSRUNWAY LENGTH
FLIGHT MANAGEMENT COMPUTER (L&R)
CROSS-CHANNEL DATACROSS-CHANNEL DATAFLIGHT CONTROL COMPUTER (R)FLIGHT CONTROL COMPUTER (R)CROSS-CHANNEL DATA CROSS-CHANNEL DATAFLIGHT CONTROL COMPUTER (C) FLIGHT CONTROL COMPUTER (R)ALONG-TRACK HORIZONTAL ACCELERATION FLIGHT DIRECTOR ROLL BAR COMMAND
CROSS-TRACK HORIZONTAL ACCELERATION ROLL ARMED MODE ANNUNCIATION
BODY LATERAL ACCELERATIONROLL ENGAGED MODE ANNUNCIATION
BODY PITCH RATE
BODY YAW RATE

EFIS SYMBOL GENERATORS (L, R & C)
ROLL ATTITUDE
MAGNETIC HEADING
TRUE HEADING
MAGNETIC TRACK
TRACK ANGLE (TRUE & MAG)
GROUND SPEED

INERTIAL REFERENCE UNIT (L) FLIGHT CONTROLCOMPUTER (L)

AIRPLANES WITH CONTROL WHEEL STEERING
FCC Roll and Yaw Axes - Control Inputs and Outputs
Figure 2

A
757
MAINTENANCE MANUAL

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
INPUTS
RADIO ALTITUDE
TEST INHIBITED

RADIO ALTIMETER RECEIVER/TRANSMITTER (L)
FLAP POSITION
SLAT EXTENDED

FLAP/SLAT ELECTRICAL UNIT
AILERON SURFACE POSITIONAILERON SERVO POSITION
A/P LATERAL CONTROL SERVO (L)CWS WHEEL FORCE

AILERON CONTROL FORCE TRANSDUCER
RUDDER SURFACE POSITIONRUDDER SERVO POSITION
A/P ROLLOUT GUIDANCE SERVO (L)
GO-AROUND
THRUST LEVER ASSEMBLY-GO-AROUND SWITCH (L&R)

OUTPUTS
AILERON CONTROL FORCE TRANSDUCER
AILERON HYDRAULICS ARMAILERON SERVO DETENT ENGAGETRANSFER VALVE (EHSV)LVDT EXCITATION
A/P LATERAL CONTROL SERVO (L)
RUDDER HYDRAULICS ARMRUDDER SERVO DETENT ENGAGETRANSFER VALVE (EHSV)LVDT EXCITATION
A/P ROLLOUT GUIDANCE SERVO (L)

ROLL/YAWAXISCONTROLFUNCTIONS

FLIGHT CONTROLCOMPUTER (L)

G23168
A

757 MAINTENANCE MANUAL
CONTROL COLUMN
ASEE FORCE TRANSDUCER AILERON CONTROL  BSEE FORCE TRANSDUCER AILERON CONTROL  CABLE ELECTRICAL TRANSDUCER FORCE 
　
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