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MAINTENANCE MANUAL
TO A/P DISCANNUNCIATOR,EICAS, MASTERWARNING
TO AUTOPILOTCAUTIONANNUNCIATORAND EICAS
TO EFISSYMBOLGENERATORS
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TO A/P DISCANNUNCIATOR,EICAS, MASTERWARNING
TO AUTOPILOTCAUTIONANNUNCIATORAND EICAS
TO EFISSYMBOLGENERATORS
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MAINTENANCE MANUAL
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MAINTENANCE MANUAL
b) Simultaneous ILS data failure for more than four seconds c) Automatic stabilizer trim failure in all three FCCs
(b) EADI Failure Annunciation
1) The Electronic Flight Instrument System (EFIS) EADI autopilot failure is indicated with a yellow line through the engaged mode display. A line through the CMD annunciation on the EADI occurs when the following conditions exist: a) GUN 001-050, 052-999;
A NO AUTOLAND or NO LAND 3 determination
b) GUN 051;
A MANUAL LND determination
c) Loss of local ILS data during a single channel approach
2) AIRPLANES WITH CONTROL WHEEL STEERING; a line through the CWS annunciation displayed on the EADI occurs when a CWS force transducer failure is detected (CWS must be engaged).
3) A line through the active pitch or roll mode displayed on the EADI occurs when the following conditions exist: a) A failure of applicable outer-loop data when the servos
are armed
b) An elevator or aileron servo out-of-detent for more than five seconds when the servos are engaged
c) An automatic stabilizer trim failure when the servos are engaged (pitch only)
d) An engage inhibit signal when the servos are armed
4) Invalid local input signals required for any F/D mode causes the flight director bars to be removed from view on the EADI.
(6) Autopilot Warning Annunciation
(a) General
1) Disengagement of the only engaged channel causes the following: a) The A/P DISC warning light illuminates b) The master WARNING light illuminates c) The EICAS computer displays an AUTOPILOT DISC message.
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d) GUN 001-050, 052-999; a siren sounds e) GUN 051; a wailer aural warning sounds
2) Two WARN outputs are generated for each of these warning functions. One WARN output uses software logic and is inhibited by a loss of normal power or a computer failure. The second WARN output uses hardware logic that is powered by 28 vac standby power. This ensures a valid warning if normal power is lost.
(b)
Signal Generation
1) Latches are set when the FCC is engaged. If the channel subsequently disengages, the warning is issued providing no other channels are engaged. All outputs are generated anytime either autopilot disengage switch is operated. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：757 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 2(15)
