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Inspectability Criteria for Airframes Designed to Fatigue/Fail-Safe Requirements
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English
Abstract
This paper covers inspection programs which will become a part of small airplane certification and operation as a result of Amendment 7 to FAR 23. Amendment 7 adds fatigue evaluation to wings and associated structure, reference paragraph 23.572.
Paragraph 23.572 allows two basic methods of providing the required fatigue evaluation fatigue strength investigation or fail-safe strength investigation.
The fail-safe strength investigation allows compliance with the regulations without running long and expensive fatigue analyses and/or tests but must be supplemented with proper inspections for complete FAR 23 compliance. Designing for inspectability and inspection methods will be covered.
Authors
Citation
Weaver, R., "Inspectability Criteria for Airframes Designed to Fatigue/Fail-Safe Requirements," SAE Technical Paper 720310, 1972, https://doi.org/10.4271/720310.Also In
References
- “Airworthiness Standards-Normal, Utility, and Aerobatic Category Airplanes.” Federal Aviation Agency February 1 1965
- “Airplane Airworthiness: Transport Categories.” Federal Aviation Agency September 1962
- Anderjaska Arnold E. “Fatigue Substantiation Procedures For General Aviation Aircraft Structures.” Paper 710404 SAE National Business Aircraft Meeting Wichita March 1971
- Bruhn E. F. “Analysis and Design of Flight Vehicle Structures.” Tri-State Offset Co. Cincinnati 1965
- Jowitt Peter “Case Study.” Shell Aviation News 399 1971 14 17
- Hallamby D. C. “Investigation into the Feasibility of Using a Radiographic Method of Inspection to detect Fatigue Damage . . . .” Commonwealth of Australia, Dept. of Civil Aviation Melbourne July 1970