C.  Two independent DFCS channels are provided. Flight director indications for the captain are from flight control computer A; flight director indications for the first officer are from flight control computer B. No flight director switching between A and B system is available for the captain and first officer; flight director command signals are connected directly to the attitude director indicators (ADI's) on the P1 and P3 panels (Fig. 1). The flight control computers use analog and digital input signals which are digitally processed to provide guidance commands for the autopilot and flight director systems. Either autopilot A and/or autopilot B can be engaged for autopilot control of the airplane to pilot selected guidance commands on the mode control panel. Both autopilot channels may be engaged simultaneously to accomplish automatic approaches. Control wheel steering (CWS) is used for manual control of the airplane through the autopilot system. Autopilot actuators for pitch and roll are connected to the appropriate control system linkage.
 D.  Independence of each system channel is assured by isolation of power supplies, sensors, computers, airplane wire bundles and shelf wiring harnesses. Separate hydraulic systems supply pressure for the autopilot actuators as well as the flight control power control units (PCU's) (Ref Chapters 27 and 29).
 E.  The system components are located as shown on Fig. 1. A brief description of the physical and electrical characteristics of the major units is provided. Additional components which are part of other systems or are relatively simple and direct in operation are described in the operation section of this manual.
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A 737-300/400/500MAINTENANCE MANUAL

FLIGHT MODE ANNUNCIATOR FLIGHT MODE ANNUNCIATOR (TEST 1 OPERATED)

(TEST 2 OPERATED)

STABILIZER OUT OF STAB OUT
TRIM ANNUNCIATOR OF TRIM

DFCS Component Location
Figure 1 (Sheet 1)

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A
737-300/400/500MAINTENANCE MANUAL
FLIGHT MANAGEMENT AUTO THROTTLE COMPUTER ROLL AXIS A/P ENGAGE ARMING SWITCH MODE SELECT SWITCH SWITCHES

CAPT COURSE  AUTO THROTTLE F/O F/D SPEED SELECT CHANGE PITCH AXIS SWITCHES
FLIGHT LEVEL MODE SELECT
SELECT SWITCH CONTROL CONTROL AND MODE MODE SELECT SWITCH SELECT SWITCHES
MODE CONTROL PANEL (TYPICAL)

E
CONTROL WHEEL STEERING
PITCH AND ROLL FORCE
TRANSDUCERS AND FORCE
LIMITER

SEE

ELEVATOR NEUTRAL  STABILIZER POSITION 
SHIFT SENSOR  SENSORS 
SEE  N  SEE  N 
DFCS Component Location 
Figure 1 (Sheet 2) 

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A
737-300/400/500MAINTENANCE MANUAL
FLT CONTROL STANDBY
AB
HYD
STDBY STDBY

LOW
QUANTITY

RUD RUD A
LOW
OFF OFF

PRESSURE
A
A ON B ON
ALTERNATE FLAPS
LOW

LOW
OFF UP
PRESSURE PRESSURE
A A
SPOILER OFF
AB

DOWNARM
AURAL ALERT UNIT
OFF OFF
FEEL DIFF
PRESS A

D
ON ON
SPEED TRIM
SPEED TRIM
FAIL A
FAIL ANNUNCIATOR
MACH TRIM
YAW DAMPER
FAIL A
YAW

AUTO SLAT
MACH TRIM
TO/GA SWITCHES
DAMPER A FAIL A
FAIL ANNUNCIATOR
OFF

ON AUTO STAB TRIM CUTOUT SWITCH FLIGHT CONTROL MODULE (P5)
D
　
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