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MAINTENANCE MANUAL

 B. Autopilot/Flight Director System (Fig. 2)
 (1)  
The autopilot/flight director system consists of three FCCs and all cross channel data buses, one mode control panel (MCP), and two autoland status annunciators (ASAs).

 (2)  
The FCCs receive and report fault data from the following LRUs.

 (a)  
Inertial Reference Unit (IRU) L,C,R

 (b)  
Instrument Landing System (ILS) Receiver L,C,R

 (c)  
Radio Altimeter (RA) L,C,R

 (d)  
Autopilot Pitch Control Servo (APCS) L,C,R

 (e)  
Autopilot Rollout Guidance Servo (ARGS) L,C,R

 (f)  
Autopilot Lateral Control Servo (ALCS) L,C,R

 (g)  
Air Data Computer (ADC) L,R

 (h)  
Flight Management Computer (FMC) L,R

 (i)  
Stabilizer Trim/Elevator Asymmetry Limit Module (SAM) L,R

 (j)  
Low Hydraulic Pressure Light L,C,R

 (k)  
Flap/Slat Electronic Unit (FSEU -1, -2, -3)

 (l)  
Go-around switch L,R

 (m)  
Heading reference switch

 (n)  
Spoiler Control Module (SCM 3L, 2R, 1L)

 (o)  
F/O and Capt. A/P Disconnect Switch

 (p)  
Elevator Neutral Shift Transducer L,C,R

 (q)  
AIRPLANES WITH CONTROL WHEEL STEERING;
 Aileron Control Force Transducer L,R
 Elevator Control Force Transducer L,R

 C. Thrust Management System (Fig. 3)
 (1)  
The thrust management system consists of one TMC, one MCP, and one thrust mode select panel (TMSP).

 (2)  
The TMC receives and reports fault data from the following LRUs.

 (a)  
Electronic Engine Control (EEC) L,R

 (b)  
Engine Indicating and Crew Alerting System (EICAS) L,R

 (c)  
Inertial Reference Unit (IRU) L,R

 (d)  
Flight Management Computer (FMC) L,R

 (e)  
Flap/Slat Electronic Unit (FSEU -1)

 (f)  
A/T Servo Motor

 (g)  
A/T Disconnect SW

 (h)  
Go-around Switch

 (i)  
Thrust Reverser Switch

 (j)  
Air/Ground System 1

 (k)  
Air Data Computers (ADC) L,R with associated probes

 (l)  
Engine EEC Discrete cards L,R with associated valves, switches, etc.

 (m)  
Power Lever Angle (PLA) Transducers L,R

 D. Flight Management Computer System (Fig. 4)
 (1)  The flight management computer system consists of two FMCs and cross channel data buses, one MCP, and two FMC control display units (CDUs).
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Thrust Management System Bite Interfaces and Sensors
Figure 3

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Flight Management Computer System Bite Interfaces and Sensors
Figure 4

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