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At energization, the equipment automatically performs a test and displays a page about the validity of the NAV data base card. To exit this page press momentarily the "ENT" pushbutton. The equipment shifts into satellite acquisition phase and then is ready for operation. If the satellite coverage is marginal, the equipment uses the altitude coding supplied by the encoding altimeter of the aircraft. The COMM./VOR-ILS/ GPS transceiver converts GPS navigation information into DC signals, to actuate the vertical pointer, the "TO/FR" indicator and the warning flag of the course deviation indicator. The COMM.NOR-ILS/ GPS transceiver connected to an equipment of the same type (GNS 430) of the GPS 1 enables, via a RS232 type link, flight plans to be transferred from station to station. AQAQ Validity : GPS 2 - GNS 430 34-57-00Page 5 (Du) JUN 04 AQAQ Validity : GPS 2 - GNS 430 Global Positioning System (GPS) — Schematic Figure 3 34-57-00 (.) Page 6 JUN 04 GLOBAL POSITIONING SYSTEM (GPS) DESCRIPTION AND OPERATION 1. GENERAL (Figure 1) The GPS is a system of radio-navigation by satellites which allows to solve the problem of an aircraft location anywhere (tridimensional positioning : latitude, longitude, altitude). The optional system consists of : - an A78 GPS receiver, - an E48 GPS antenna, - a J89 "data loader" jack, - a removable data card (mounted in the front of the GPS receiver), - an "MSG - WPT" annunciator of M6 advisory panel - refer to 31-50-01. The GPS gets : - altitude coding information from the encoding altimeter - refer to 34-11-00, - data from the optional SHADIN fuel flow system - refer to 73-30-00. The GPS sends an altitude - alert audio signal to the audio control box - refer to 23-11-00. The GPS also uses : - an interface kit used to load the database from a personal computer via the data loader jack, - the blower of the radio air cooling system. VHF transmissions may affect GPS signal reception. Optional filters may be inserted in coaxial line which links transceiver and antenna of COM 1 and COM 2 systems. The GPS system is electrically supplied by "BUS 3" bar via the "GPS" circuit breaker. S / N 1806 The GPS system is electrically supplied by "BUS 1" bar via the "GPS" circuit breaker. AKAK Validity : KLN 89B Stand alone 34-57-00Page 1 (EA) NOV 01 ISSU DU SYSTEME GESTION CARBURANT SHADIN OPTIONNEL FROM OPTIONAL SHADIN FUEL FLOW SYSTEM J89 "DATA LOADER" PRISE DE CHARGEMENT DE DONNEES JACK ALTIMETRE CODEUR ENCODING ALTIMETER ( 34 - 11 - 00 ) 中国通航网 www.ga.cn 通航翻译 www.aviation.cn 本文链接地址：TB20 MAINTENANCE MANUAL 34 导航 TB20飞机维护手册 2(74) |
