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)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
22-11-00
ú ú 02 Page 4 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
22-11-00
ú ú 02 Page 5 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
22-11-00
ú ú 02 Page 6 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
22-11-00
ú ú 02 Page 7 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(10)
