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Fatigue Evaluation for Light Twin Engined Aircraft
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English
Abstract
In the past, most light twin-engined aircraft have been designed based on the fail-safe concept. The use of these type aircraft by commuter airlines indicates that a safe-life evaluation of the structure can be of use to both the manufacturer and the customer. This paper describes a program to evaluate the safe-life of a light twin-engined aircraft. The program presently being applied to the Cessna Citation executive twin jet aircraft is also presented as an example of the application of the safe-life concept to an aircraft developmental program.
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Citation
Huffman, J., "Fatigue Evaluation for Light Twin Engined Aircraft," SAE Technical Paper 700219, 1970, https://doi.org/10.4271/700219.Also In
References
- Freudenthal A. M. “Fatigue in Aircraft Structures” Academic Press, Inc. New York, N. Y.
- Summary of VGH data on one type of twin jet airliner during airline operations May 1968
- NASA Langley Working Paper 523 - Initial report on operational experiences of general aviation aircraft January 1968
- Airplane strength, rigidity and reliability requirements, repeated loads and fatigue May 1960
- Minor M. A. “Cumulative Damage in Fatigue” Fatigue and Fracture of Metals John Wiley and Sons, Inc. New York, N.Y. 1950