• Title/Summary/Keyword: Helicopter Operation Safety

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Establishing Engine Accelerated Mission Test Cycles complying with the CS-E of European Aviation Safety Agency (유럽항공안전청 형식증명 감항기준에 부합하는 엔진가속시험 사이클 수립)

  • Park, Sooyoul;Moon, Gyeongchan;Koo, Hyuncheol
    • Journal of Aerospace System Engineering
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    • v.14 no.1
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    • pp.62-67
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    • 2020
  • The European Aviation Safety Agency (EASA) legislates the CS-E (Certification Specification-Engine) for type certification of aircraft engines. According to the CS-E, engine manufacturers (type certificate holders) the need to show compliance of continued airworthiness of an engine during the overhaul, and the Accelerated Mission Test (AMT) is usually accepted as means of compliance. As a part of the Korean Civil Helicopter program, the engine has been developed with foreign manufacturers to achieve the EASA engine type certificate. In this study, the AMT procedure is planned for the engine to be certified by the EASA, and AMT cycles are also established to meet airworthiness requirements of the CS-E in consideration of the engine design and operation characteristics.

Design Improvement about Abnormal Lighting of Anti-Collision Light for a Rotary-wing Aircraft (회전익 항공기 충돌방지등의 이상점등에 대한 설계 개선)

  • Kim, Young Mok;Seo, Young Jin;Lee, Yoon Woo;Lee, Joo Hyung;Choi, Doo-Hyun
    • Journal of Aerospace System Engineering
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    • v.13 no.5
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    • pp.79-86
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    • 2019
  • An anti-collision light of a rotary-wing aircraft is used for the purpose of preventing collision during the operation of an aircraft and is a key component to ensure flight safety. The anti-collision lights of the Korean Utility Helicopter (KUH) consist of upper and lower lights, and the power supply of anti-collision lights mounted on the aircraft. The anti-collision light is designed as a dual structure capable of brightness control and selective lighting. During the operation after delivery of the aircraft, abnormal lighting of anti-collision light occurred. In this paper, a comprehensive review of the aircraft system and component level was conducted to solve these phenomena at first. Then, the causes of anti-collision light anomalies were analyzed and the design changes are presented. The validity of design changes has been verified through the component and aircraft system ground/flight test.

Flight Safety Assurance Technology for Rotary Aircraft through Optimization of HUMS Vibration Thresholds (회전익항공기 상태감시시스템 임계값 최적화를 통한 비행안전성 확보기술)

  • Jun, Byung-kyu;Jeong, Sang-gyu;Kim, Young-mok;Chang, In-ki
    • Journal of Advanced Navigation Technology
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    • v.20 no.5
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    • pp.446-452
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    • 2016
  • The aircraft has to be considered for safety very importantly because of peculiarity of flight in the air, so it should be retained through proper inspection and maintenance not only in production phase but also in operating phase. Recently, it is using the latest technology as engineering approach not depending on human factor to determine on maintenance needs, and domestic production rotary aircraft also has the health & usage monitoring system to measure and to monitor major components. However, continued vibration exceedance phenomenon occurred in production and operation phase because of inappropriate thresholds, and it confirmed as false alarm which is not necessary to repair. In this paper, it is described that operational concept of HUMS, and especially it contains a study result for efficiency of aircraft operation and ultimately the improvement of flight safety by optimizing HUMS thresholds to determine efficiently necessity of maintenance under limited conditions and by establishing inspection/maintenance procedures when the re-designated thresholds exceedance occurred.