Autothrottle Computer (A/T)

 (1)  
An output of the FMC interfaces with the autothrottle computer (A/T), through an ARINC 429 low-speed DITS. This output from the FMC provides the A/T with climb, cruise, and go-around N1 limits. The output also provides the A/T with gross weight and temperature data.

Digital Flight Control System (DFCS)

 (1)  
The DFCS Mode Control Panel (MCP) provides LNAV and VNAV engage mode logic, altitude select data, and flap position to the FMC, through an ARINC 429 low-speed DITS.

 (2)  
An output of the FMC interfaces with the DFCS Flight Control Computer (FCC), through an ARINC low-speed DITS. This output from the FMC provides the FCC with target airspeed and mach, target altitude, target vertical speed, and roll command.

Electronic Flight Instrument System (EFIS)

 (1)  
The FMC provides Flight Plan, Navigation and Map information to the EFIS. The mode selector on the EFIS control panel allows the EFIS to display either FMC or VHF NAV information.

Engine Instrument System

 (1)  
The FMC provides command N1 to the Engine Instrument System (EIS) through the DAA. The command N1 is displayed on the Primary Engine Display ( PED ) when the manual N1 set knob is pushed in.

 The Thrust Mode Annunciation (TMA ) messages provided by the FMC for display on the PED is the indication of an active N1 limit, or reduced N1 limit. These TMA messages are: TO, R-TO, CLB, R-CLB, CRZ, G/A and CON. The TMA blanks for PED or FMC failure. Dashes show across the TMA, if the FMC sends an NCD signal.
Autoflight Status Annunciator
 (1)  
The Autoflight Status Annunciator is comprised of three warning lights with push to reset (P/RST) features, and a test switch. The FMC warning light illuminates amber when an FMC alerting message is present on the FMC CDU or when the FMC fails.

Mach/Airspeed Indicator

 (1)  
When VNAV is selected on the DFCS mode control panel, the FMC computed target airspeed is displayed on the mach/airspeed indicator. The target airspeed is dependent upon the active flight phase and the pilot selected performance mode for that flight phase.

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 34-62-01
 ú CONFIG ú 03 Page 19 ú Mar 15/96

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 R.  Ground Proximity Warning System (GPWS)
 (1)  An output of the FMC interfaces with the GPWS, through an ARINC 429 Hi-speed DITS. This output from the FMC provides the GPWS with track angle and present position latitude and longitude.
 S.  Stall Management Computer (SMC)
 (1)  An output of the FMC interfaces with the SMC through an ARINC 429 low-speed DITS. This output provides FMC computed gross wieght to the SMC.
 T.  Digital Flight Data Acquisition Unit (DFDAU)
 (1)  An output of the FMC interface with the DFDAU through an ARINC 429 hi-speed DITS. This output provides FMC data to the DFDAU.
 U.  AIRPLANES WITH ACARS;
 ARINC Communications Addressing and Reporting System (ACARS)

 (1)  The FMC transmits and receives data to and from a ground based transmitter/receiver through the ACARS management unit. The data transfer consists of predicted winds, flight plan, preflight load, and request for position. The data is transferred over a low speed digital bus.
 V.  Receptacle for Portable Data Loader
 (1)  A receptacle on the P18 panel allows an external portable data loader to interface with the FMC. The portable data loader is used, as required, to load and update the navigation data base of the FMC.
 W.  Receptacle for Portable Printer (Optional)
 (1)  A receptacle on the P18 panel allows an external portable printer to interface with the FMC. The printer is used, as required, during system maintenance.
 X.  Receptacle for Portable CDU (Optional)
 (1)  A receptacle on the E1-1 shelf allows a portable CDU to interface with the FMC. The portable CDU is used, as required, to access FMS BITE from the E-E bay.
 4.  Control Display Unit (Fig. 7)____________________
 A.  Two Control Display Units (CDUs) are included in the FMCS. The CDUs are physically and functionally identical; these CDUs allow the operator to interface with the FMC. Both CDUs can be used independently or simultaneously for control and display during a flight. Either CDU may be utilized to enter system data. Data entered on one CDU will appear on the corresponding display page of the other CDU except for scratch pad entries on line 14.
　
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