Dornier 328Jet - Ignition System - IGNITION SYSTEM General The ignition system is a dual channel ignition

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  • Engine Start Panel

    Dornier 328Jet - Ignition System

    Page 1

  • Indications on EICAS MAIN Page

    Dornier 328Jet - Ignition System

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  • Feb 11/02

    EFFECTIVITY : ALL 12–74–01–00 Page 3

    Indications/Messages on ENGINE Page

    Dornier 328Jet - Ignition System

    Page 3

  • Feb 11/02

    EFFECTIVITY : ALL 12–74–01–00 Page 4

    RMU Engine Backup Page

    Dornier 328Jet - Ignition System

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  • IGNITION SYSTEM

    General The ignition system is a dual channel ignition system, which gives a quick light–off capability over a wide temperature range. It is energized from the airplane 28 VDC electrical supply. The main components of the system are:

    – two ignition exciter units – two ignition cable assemblies – two spark igniters

    The ignition system provides ground start, auto–relight and continuous ignition operations. Ground start and auto relight are controlled by the FADEC system (refer to 12–73–02–00), continuous ignition is set manually and overrides FADEC control.

    Ignition Exciter Unit The ignition exciter units transform the DC input to a pulsed high voltage output. The ignition exciter units are mounted on the right–hand side of the bottom section of the outer bypass duct.

    Ignition Cables The ignition cable assemblies carry the high voltage output from the ignition exciters to the engine mounted spark igniters. They are connected between the ignition exciter unit and spark igniter by coupling nuts. Each ignition cable assembly consists of an electrical lead encased in a flexible metal braiding.

    Spark Igniters Two spark igniters, located at 4 and 5 o’clock positions respectively on the combustion chamber outer case, are screwed through bosses on the case to locate in the combustion chamber. When energized, they operate at a rate of four sparks (discharges) each seconds.

    Ground Start Operation For ground starts both ignitors can be manually selected by pushing the CONT IGN button. During a ground start, FADEC commands ignition by alternate selection of the igniters between 5,2 % N2 and 40 % N2.

    Auto–relight Operation Auto–relight is armed with weight off wheels. It is activated if the engine N2 decreases by more than 2% below flight idle or if there is a flame–out. When it is activated the FADEC energizes relays, which provide electrical power to the applicable ignition system and both igniters operate. Auto–relight is on, until the required thrust is attained, then the FADEC de–energizes the relays to stop the igniters.

    Dornier 328Jet - Ignition System

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  • TR 05 03

    Continuous Ignition Operation Continuous ignition is selected manually via the IGN button on the ENGINE panel. It overrides FADEC control and operates both igniters at the same time. Continuous ignition is used for takeoff and landing on contaminated runways and in adverse weather conditions. Fire Protection If the ENG FIRE button is operated during a ground start or auto–relight ignition cycle, relays open to de–energize the igniters. If continous ignition is selected, when the FIRE button is pushed, the igniters will remain on until the IGN button is pushed again. Indications The operating condition of the ignition system is indicated by captions in the IGN button as follows:

    – CONT and IG1 and IG2, continuous ignition selected, – IG1 and IG2, auto–relight active, – IG1 or IG2, ground start cyle, continous ignition not selected.

    At the same time the blue status message IGN for the applicable engine is displayed on the EICAS MAIN and ENGINE pages and also on the RMU Backup Engine Page 1.

    Dornier 328Jet - Ignition System

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  • Continuous Ignition Operation Continuous ignition is selected manually via the IGN button on the ENGINE panel. It overrides FADEC control and operates both igniters at the same time. Continuous ignition is used in adverse weather conditions and for engine relights above 35 000 ft, it is only available with the airplane weight–off–wheels. Fire Protection If the ENG FIRE button is operated during a ground start or auto–relight ignition cycle, relays open to de–energize the igniters. If continous ignition is selected, when the FIRE button is pushed, the igniters will remain on until the IGN button is pushed again. Indications The operating condition of the ignition system is indicated by captions in the IGN button as follows:

    – CONT and IG1 and IG2, continuous ignition selected, – IG1 and IG2, auto–relight active, – IG1 or IG2, ground start cyle.

    At the same time the blue status message IGN for the applicable engine is displayed on the EICAS MAIN and ENGINE pages and also on the RMU Backup Engine Page 1.

    Dornier 328Jet - Ignition System

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