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Abstract

Throughout the life cycle of an aircraft, it is likely that it may encounter an uncontained engine rotor or propeller blade failure due to probable malfunction or failure of single or multiple engine components, inadequate rotor and casing design, fatigue, material imperfections, assembly errors and foreign object ingestion. Uncontained engine rotor or propeller blade failure can lead to catastrophic failure if not addressed adequately during design. To ensure safety of the flight in the event of rotor burst or propeller blade failure federal aviation regulations has set forth compliance requirements (FAR sections 25.903, 25.905.d) which states that the airplane must be capable of successfully completing a flight during which likely structural damage occurs as a result of a propeller blade impact, uncontained fan blade impact, uncontained engine rotor failure or uncontained high energy rotating machinery failure. Aircraft manufactures has to comply with the safety requirements mentioned above. Hence it is required to assess the risk, take adequate design measures to minimize the risk and show compliance by analysis or test that the damage caused is minimal and aircraft is capable of completing safe flight in the event of uncontained rotor failure. This paper demonstrates the methodology to be followed for performing safety assessment of a typical light transport aircraft (LTA) in the event of an uncontained rotor burst and propeller blade failure. Assessment method presented in this paper is generic in nature and can be used to assess the safety of any class of transport aircraft.