(d)  
AUTOPILOT amber caution light - P1-3

 (e)  
A/P disengage switches - Inboard side of outboard horn on each control wheel

 (f)  
AFDS go-around switches - One for each FCC and TMC on each thrust lever

 (6)  
The below-deck components of the AFDS are located as follows:

 (a)  
Flight Control Computers (FCCs-3) - on main Electrical/Electronics (E/E) racks (E3-1, E3-2, and E3-3)

 (b)  
AIRPLANES WITH CONTROL WHEEL STEERING; aileron control force transducer (CFTs) (2) - on the forward aileron quadrant.

 (c)  
AIRPLANES WITH CONTROL WHEEL STEERING; elevator control force transducers (2) - on the forward elevator quadrants.

 (7)  
The Autopilot flight control servos are located as follows:

 (a)  
Autopilot Lateral Control Servos - Left (L) and Center (C) in the left wing root, Right (R) in the right wing root.

 (b)  
Autopilot Pitch Control Servos - L, C, and R aft of the horizontal stabilizer

 (c)  
Autopilot Rollout Guidance Servos - L, C, and R in the lower area of the vertical stabilizer.

 D. Interfacing Components (Fig. 1)
 (1)  
Each FCC provides an output to a Stabilizer Trim/Elevator Asymmetry Limit Module (SAM) for automatic trim of the stabilizer when an autopilot is engaged. The SAMs (2) are on main E/E racks E3-1 and E4-1 (Ref 22-22-00, Automatic Stabilizer Trim System).

 (2)  
Each FCC also provides fault data to the Maintenance Control Display Panel(MCDP) and performs ground tests when requested by the MCDP. The MCDP is on main E/E rack E4-2 (Ref 22-41-00, Maintenance Monitor).

 (3)  
The F/D source select switches on P1-1 and P3-3 allows each pilot to select which FCC to use for Flight Director Commands on his EADI (Ref 34-22-00, Flight Instrument System).

 E. Indications
 (1)  The AFDS condition and status is indicated by various lights and displays as follows:
 (a)  
The mode select switch/lights on the MCP have identifying legends in the upper half of the switch cover. The legends light when panel lights power is applied to the panel. A dot-bar matrix on the lower half lights when the FCC has accepted the associated mode request. Digital readouts on the MCP indicate selected airspeed, selected vertical speed, selected heading, and selected altitude. Panel legends identify the status of the F/D, A/T (auto throttle), and bank angle (B/A) limit switches.

 (b)  
The Electronic Attitude Director Indicator (EADI) provides Flight Director displays and Flight Mode Annunciation (FMA) armed or engaged roll and pitch modes.

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 (c)  
A red autopilot disconnect (A/P DISC) light and an amber AUTOPILOT caution light are on the captain's instrument panel (P1-3).

 (d)  
A caution and warning system consists of a warning horn, master WARN lights, and an A/P DISC (Red) message on the Engine Indicating and Crew Alerting System (EICAS) (Ref 31-51-00, Warning System).

Autopilot/Flight Director System Mode Control Panel Interfaces Schematic (Fig. 3)
 (1)  
Autopilot (A/P) and flight director (F/D) engage requests are generated by the Mode Control Panel (MCP) and are sent to the Flight Control Computers (FCCs). Once accepted, the requests can result in the arming and engaging of the A/P servos.

 (2)  
Mode requests for both A/P and F/D are generated at the MCP and transmitted on an ARINC 429 digital data bus to the FCCs.

 (3)  
GUN 001-050, 052-999; the A/P disengage bar logic tells the FCC if the bar is up or down. This allows the FCC to enable or disable the A/P servos.

 (4)  
GUN 051; the FCCs provide engage and mode status to the MCP. Mode status is indicated by the dot-bar matrix on the A/P mode select switch/lights. Mode status is also indicated on the EADIs (Ref 22-14-00).

 (5)  
GUN 001-050, 052-999; the FCCs provide engage and mode status to the MCP. Mode status is indicated by the dot-bar matrix on the A/P engage and mode select switch/lights. Mode status is also indicated on the EADIs (Ref 22-14-00).

FCC Input Discretes From Remote Switches
　
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