B. The SP300 Digital Flight Control System (DFCS) is an all digital system that includes the following functions:
Autopilot
Flight Director
Mach Trim
Speed Trim
Altitude Alert
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 electronic attitude director indicators (EADI'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.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
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ú ú 01 Page 1 ú Mar 15/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
DFCS Component Location
Figure 1 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
22-11-01
ú ú 04 Page 2 ú Mar 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FLIGHT MANAGEMENT
AUTO THROTTLE COMPUTER ROLL AXIS
ARMING SWITCH MODE SELECT SWITCH
ALTITUDE SELECT A/P ENGAGE FLIGHT MANAGEMENT CONTROL AND MODE SWITCHES
F/D MASTER COMPUTER PITCH AXIS SELECT SWITCH F/D MASTERLIGHT MODE SELECT SWITCH LIGHT
COURSE A/T IAS/MACH V NAV HEADING L NAV ALTITUDE VERT SPEED A/P ENGAGE COURSE ARM
AB CMD 30 10
DNVOR LOC
F/D
F/D ON OFF
SEL C/0 CWS ON
10 30
N1 SPEED LVL CHG HDG SEL APP ALT HOLD V/S
OFF
DISENGAGEOFFUP
CAPTAIN
HEADING SELECT VERTICAL SPEED FIRST OFFICER F/D SWITCH
CONTROL AND MODE CONTROL AND MODE
COURSE SELECT SELECT SWITCH SELECT SWITCH CONTROLCAPTAIN COURSE RADIO NAVSELECT CONTROL
FIRST OFFICER F/D SWITCH AUTO THROTTLE FLIGHT LEVEL MODE SELECT
SPEED SELECT CHANGE PITCH AXIS SWITCHES
CONTROL AND MODE MODE SELECT SWITCH
SELECT SWITCHES
MODE CONTROL PANEL (EXAMPLE)
D
CONTROL WHEEL STEERING
PITCH AND ROLL FORCE
TRANSDUCERS AND FORCE
SPOILER
LIMITER
ROLL CHANNEL
POSITION
SEE J
A/P ACTUATORS (2) SENSORS
AILERON POSITION SENSOR SEE L
SEE K
MACH TRIM
ACTUATOR
SEE N
SPOILER
POSITION
SENSORS
SEE L
A/P STABILIZER
PITCH CHANNEL
TRIM SERVOMOTOR
A/P ACTUATORS (2) SEE M
SEE N
ELEVATOR NEUTRAL STABILIZER POSITION SHIFT SENSOR SENSORS
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