(d)  
An elevator position transmitter is located at each elevator to provide elevator surface position indications on the auxiliary EICAS display when the Flight Control Maintenance Page is selected.

 (2)  Autopilot Input
 (a)  
Autopilot inputs from the FCCs are made through the EASs. These servos are connected to the aft quadrant. When the autopilot is engaged, the servos move the same point in the control system as the pilot's manual input. The control columns are also back-driven.

 (b)  
The three autopilot servos provide a parallel input to the elevator control system at the aft quadrant. For multi-channel operation, the autopilot servos are force-voted with the feel system for elevator control.

 C. Rudder Control System (Fig. 16)
 (1)  
Manual Input

 (a)  
Manual input for rudder control is from the captain's or first officer's rudder pedals. Rudder pedals input is transmitted to the aft quadrant through cables. Control inputs are conditioned by the feel and centering mechanism which provides artificial feel and centering as well as trim.

 (b)  
Movement of the rudder pedals is sent through the rudder ratio changers, which programs rudder command as a function of impact pressure, to the RPCMs. The RPCMs supply control hydraulic pressure to the rudder actuators which move the rudders.

 (c)  
A rudder position transmitter is located at each rudder to provide rudder surface position indications on the auxiliary EICAS display when the Flight Control Maintenance Page is selected.

 (2)  
Autopilot Input

 (a)  Autopilot inputs from the FCCs are made through the RPCPs. These RPCPs are connected to the feel and centering mechanism through the override mechanism. When the autopilot is engaged in rollout control, the RPCPs move the same point in the control system as the pilot's manual input. The rudder pedals are also back-driven.
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Rudder Control System
Figure 16

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 (b)  During multi-channel engagement, the autopilot servos are force-voted similar to the elevator control.
 (3)  Yaw Damper Input
 (a)  Yaw damper inputs from the yaw damper modules are made through the RPCMs. The yaw damper actuators are integrated with the RPCMs. Commands are introduced to the RPCM control valve through a summing lever.
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 AUTOPILOT/FLIGHT DIRECTOR SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________________
 1.  General_______
 A.  The Autopilot/Flight Director System (AFDS), as part of the overall flight management system, is a triple-channel system that operates as a single-channel system for cruise and approach, controlling the pitch and roll axis of the aircraft and providing pitch and roll flight director commmands. The autopilot system also operates as a dual or triple multi-channel system for approach, land, rollout, and go-around controlling the pitch, roll, and yaw axis of the aircraft.
 B.  The AFDS has three digital Flight Control Computers (FCCs), one Mode Control Panel (MCP), and interfaces with two Primary Flight Displays (PFDs), airplane sensors and interfacing components and two Central Maintenance Computers (CMCs). The system is capable of providing autopilot/flight director guidance and control for Autoland Category III operations. Extensive internal monitors and self-tests provide continuous fault detection and storage.
　
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