Although the safe life approach for retiring fatigue life limited components has been employed with success in the rotorcraft industry, it has drawn criticism from many sources, dating back to the 1960's during the development of the Lockheed Cheyenne (AH-56 Helicopter). In recent times both a reliability-based safe life approach and a damage tolerance approach have been suggested as replacement methodologies. Concerns about these alternate approaches include the practicality of applying the damage tolerance approach to rotorcraft dynamic components, the applicability of reliability-based safe life to fatigue loaded components, and a possible increase in cost to adopt these methodologies. This paper shows how the reliability-based safe life methods were successfully employed on the Boeing Model 234 helicopter in conjunction with a limited usage monitoring requirement. Providing the operator with the ability to determine safe retirement lives based upon actual usage of individual aircraft is expected to result in a decrease in operating cost. Future applications are also discussed.
Application of probabilistic methodology in the development of retirement lives of critical dynamic components in rotorcraft
1999
14 Seiten, 14 Quellen
Aufsatz (Konferenz)
Englisch
British Library Conference Proceedings | 1999
|A STUDY OF THE RETIREMENT DATA FOR ROTORCRAFT DYNAMIC COMPONENTS
British Library Conference Proceedings | 2003
|Stochastic Updating of Probabilistic Life Models for Rotorcraft Dynamic Components
Online Contents | 2009
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