VHF Navigation Receivers
(1)
The VHF navigation receivers provide deviation and bearing information to the FMC, through the DAA. When manual tuning is selected on the VHF navigation control panel, a manually selected VHF frequency is tuned. If automatic tuning is selected, the VHF navigation receivers are tuned by signals from the FMC, and station selection is determined by the FMC, using navigation and station geometry information.
Fuel Quantity
(1)
The fuel summation unit processes and sums signals from individual fuel tank indicators, to determine total fuel. The summation unit provides this total fuel information to the FMC, through the DAA.
Inertial Reference System (IRS)
(1)
The IRS is the primary component on the airplane for attitude measurement, and position determining. The IRS utilizes a ring laser as its means of inertial reference. Each IRS provides present position, heading, attitude, velocity, altitude, ground speed, and vertical speed to the FMC; through an ARINC 429 high-speed Digital Information Transfer System (DITS).
(2)
An output ARINC 429 channel from the FMS allows the user to initialize the IRS on the ground through the CDU by entering the airplane present position latitude and longitude values.
Digital Air Data Computer System (DADC)
(1)
Two DADC interface with the FMC. The DADC system provides altitude, DADC, airspeed, mach, and temperature information to the FMC: through an ARINC 429 low-speed DITS.
Captain's Clock
(1)
The clock provides an output of Greenwich Mean Time (GMT), or GMT and date (if GMT and date clock is installed) to the FMC. This interface is in accordance with ARINC 429 low-speed DITS.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
34-62-01
AND A SINGLE FMC ú CONFIG 1 ú 05 Page 14 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
J. K. Discrete Signals (1) The FMC accepts discrete input signals from wing anti-ice, engine anti-ice, and engine bleed systems. These systems when activated cause an engine thrust reduction. The FMC uses these discrete signals to provide corresponding reductions to calculated performance values.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.
L. M. N. 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.
O. P. Q. 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.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.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú 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 导航 NAVIGATION 5(30)
