Dornier 328Jet - Ignition System

Transcription

1 Engine Start Panel Page 1

2 Indications on EICAS MAIN Page Page 2

3 Indications/Messages on ENGINE Page EFFECTIVITY : ALL Page 3 Feb 11/02 Page 3

4 RMU Engine Backup Page EFFECTIVITY : ALL Page 4 Feb 11/02 Page 4

5 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 ), 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. Page 5

6 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. TR Page 6

7 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 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. Page 7