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737-300/400/500MAINTENANCE MANUAL
G. The CPU 1 software executes periodic self-tests to detect failures in software execution or in RAM or ROM access. During autoland and autopilot go-around modes, CPU 1 software monitors surface commands generated by CPU 2 for comparison with CPU 1 commands (and visa versa) to detect unacceptable discrepancies. Failure in the self-test or in cross-CPU redundancy monitoring are recorded by the continuous monitor.
H. 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.
3. Mode Control Panel (MCP)________________________
A. The mode control panel (MCP) 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 MCP provides the primary interface between the pilots and the DFCS. The MCP contains the engagement control, mode selection control and control parameter selection associated with the Altitude Alert, A/P, F/D, Autothrottle, and, to a limited extend, the FMCS. Interconnection to airplane wiring is by 3 connectors located on the rear panel. The panel also provides control of preset heading, preset course, altitude select engage control and speed selection.
B. The A/P (autopilot) ENGAGE switches (A and B) are 3-position paddle switches that are solenoid-held in OFF, CWS, and CMD positions. If proper logic is made, the solenoid releases the switch allowing movement from the OFF position. These switches allow engagement of the desired autopilot channel, A or B in CWS (control wheel steering) mode or engagement of A or B or both during approach in CMD (command) mode. If engage logic is satisfied, then the switch will hold 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.
C. The F/D (flight director) ON/OFF switches provide control of the flight director command output to the ADI. Discrete signals are provided to the respective ADI and digital data is provided to the FCCs. A master light (MA) is located above each F/D switch to indicate which system (during slaved operation) is providing mode control.
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A 737-300/400/500MAINTENANCE MANUAL
FCC Simplified Block Diagram
Figure 2
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E.
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737-300/400/500MAINTENANCE MANUAL
The A/T (autothrottle) ARM/OFF switch is a two-position, solenoid-held switch for arming the autothrottle. On the ground, the FMCS must be engaged before the autothrottle can be armed. The ARM position permits A/T control of thrust levers when compatible mode selection exists between the A/P and A/T. The switch controls discrete circuits (AMM 22-31-00).Mode selection is made with momentary pushbuttons. The flight modes are:
V/S - Vertical Speed ALT HOLD - Altitude Hold V NAV - Flight Management Computer LVL CHG - Level Change - Airspeed Hold HDG SEL - Heading Select L NAV - Flight Management Computer VOR LOC - VHF NAV System (VOR, Localizer, Glideslope) APP - Approach SPEED - Autothrottle N1 - Autothrottle
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