CONTROL STAND
G
CAPTAIN'S CONTROL WHEEL (TYPICAL FOR FIRST OFFICER'S)
F
CONNECTORS (3) BENCH TEST  H FLIGHT CONTROL COMPUTER  I AFC ACCESSORY UNIT
DFCS Component Locations Figure 1 (Sheet 3) 

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A 737-300/400/500MAINTENANCE MANUAL
COLUMN SWITCHING MODULE
ELEV CONTROL TORQUE TUBE
CONTROL WHEEL COLUMN SWITCHES
PITCH FORCE TRANSDUCERS
CONTROL COLUMN - PITCH J
TO F/O CONTROL COLUMN
BUS DRUM
CWS ROLL FORCE TRANSDUCER
CABLES TO POWER CONTROL UNIT
CONTROL DRUM
AILERON
FORCE LIMITER

CONTROL COLUMN - ROLL
J

DFCS Component Locations Figure 1 (Sheet 4)
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A

737-300/400/500
MAINTENANCE MANUAL

A/P ACTUATOR B  ACTUATOR  DETENT 
ELECTRICAL CONNECTOR  TRANSFER VALVE  SWITCH PRESSURE  SOLENOID  SOLENOID A/P ACTUATOR A 
DETENT 
SOLENOID 
ACTUATOR  PRESSURE 
SOLENOID  SWITCH  AILERON 
POSITION 
LVDT  SENSOR 

PCU INPUT LEVER
ROLL CHANNEL A/P ACTUATORS AND POSITION SENSOR K
SPOILER
SPOILER
POSITION
SENSOR

SPOILER NO.2 SHOWN, SPOILER NO.7 OPPOSITE
L
DFCS Component Locations
Figure 1 (Sheet 5)

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A
737-300/400/500MAINTENANCE MANUAL
AUTOPILOT  MACH TRIM 
B ACTUATOR  ACTUATOR 
OUTPUT 
SHAFT QUADRANT  NEUTRAL SHIFT SENSOR 

ELEVATOR
CONTROL
ARM
AUTOPILOT A ACTUATOR
SEE N
ELEVATOR
ELEVATOR A PCU
B PCU
STABILIZER INPUT A/P ACTUATOR B
POSITION SENSORS QUADRANT (RH) (LH OPPOSITE) SHAFT PRESSURE SWITCH
ELEVATOR POSITION SENSORTRANSFER VALVE FWD
ELEVATOR CHANNEL POSITION SENSORS,
ELECTRICALMACH TRIM ACTUATOR CONNECTOR
DETENT SOLENOID STABILIZER LVDT JACKSCREW
HYDRAULIC LINE MAIN ELECTRIC TRIM SERVO AUTOPILOT TRIM SERVO A/P ACTUATOR A LVDT
INPUT QUADRANT SHAFT MANUAL TRIM DRIVE CABLE DRUM
LOWER TORQUE TUBE LEVER
ELEVATORS CHANNEL A/P ACTUATORS STABILIZER TRIM
NM
DFCS Component Locations Figure 1 (Sheet 6)
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A
737-300/400/500MAINTENANCE MANUAL
 F. Altitude Alert System
 (1)  The altitude alert system compares the airplane altitude with the altitude selected on the mode control panel. A visual and aural warning is provided when the airplane approaches (option) or departs from the selected altitude. No warnings are issued while the airplane is within perscribed limits from the selected altitude. The warning is inhibited during approach by flap position logic.
 G. Mach Trim System
 (1)  The mach trim system provides automatic elevator quadrant displacement as a function of mach number in the mach tuck (nosedown) region. Mach data from the air data computer is used to generate a servo position command signal. This signal is applied to the mach trim actuator. The actuator provides elevator pitch-up position to maintain the correct attitude when airplane mach tuck speed is attained. The mach trim actuator changes the position of the column neutral point without altering feel/force characteristics.
　
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