737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(55)

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B.  Independence of each AP/FD 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 airplane power control units (Ref Chapter 27 and 29).
C.  The AP/FD components are located as shown on Fig. 1. The following is a brief description of the physical and electrical characteristics of the major units. 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.
2.  AFCS Computer
A.  Two AFCS computers designated as A and B are mounted on the E1-3 shelf in the electrical and electronics equipment bay. The units are retained in the rack by cam-loc handles located on the front of the unit which engage adjustable rack-mounted swivel bolts. The AFCS computers are standard 1 ATR-long boxes. Electrical connections to the units are provided by four DPX2 connectors located on the rear of the unit which mate with rack-mounted DPX2 connectors. Three capped test connectors are located on the front panel of the AFCS computers.
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H87293 H19172 H19151 H19155 H19169
A/P-F/D System Component Location  5GJ 
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595  A/P-F/D System Component Location 
May 20/82  Figure 1 (Sheet 2)  22-11-01 
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A/P-F/D System Component Interface Block Diagram  553 
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553  A/P Mechanical Roll Control Interface Block Diagram 
Sep 20/82  Figure 3  22-11-01 
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A/P Mechanical Pitch Control Interface Block Diagram  591 
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B.  The AFCS computer (FCC) contains keyed plug-in printed circuit cards which are installed vertically within the unit. The cards have built in lever assist handles for ease of removal. The unit power supply consists of plug-in cards located across the rear of the unit. The electronic circuitry on the boards are latest state-of-the-art design with solid state micro-electronics used extensively.
C.  The AFCS computer interfaces with analog and digital data signals. The cruise mode computation is performed by the digital computer, approach mode computation is accomplished using analog computations. Analog to digital (A/D) and digital to analog (D/A) converters within the computer provide system compatibility. The computer is designed to interface with ARINC 429 digital data.
D.  System A interfaces with system A electrical power, system A hydraulic power and the captain's instruments, attitude, compass, air data and navigation systems. System B interfaces with system B electrical power, system B hydraulic power and the first officers instruments, attitude, compass, air data and navigation systems. The systems are isolated to provide two completely independent systems. Both systems operate simultaneously during dual channel approach mode.
E.  An electrical power interlock is provided which prevents engagement of both autopilot systems when the airplane electrical power is from one generator. Dual power source is required for dual channel operation.
3.  AFCS Mode Control Panel
A.  The mode control panel is mounted on the glare shield, accessible to both pilots. The unit is held by four screws located on the face of the unit and two screws located on the bottom of the unit. The panel provides AP/FD engage and mode control. The panel also provides A/T system ARM control, control of preset heading, preset course, altitude select engage control and speed selection.
B.  The AP (autopilot) ENGAGE switches (A and B) are 3-position solenoid held paddle switches, OFF, CWS, and CMD. They allow engagement of the desired autopilot channel, A or B in CWS (control wheel steering) mode or channel A or B or both (during APProach mode) in CMD (command) mode. The switches are electro mechanically held in CWS or CMD position (with override capability) and are spring-loaded to the OFF position when the system is disengaged. The switches control discrete signal lines.
　
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