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Fatigue and proof testing of an aircraft auxiliary fuel tank

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References

  1. Federal Aviation Regulation, Section 25.571, “Damage Tolerance and Fatigue Evaluation of Structure,” Title 14 Code of Federal Regulations (CFR), Federal Register, December 19, 2000.

  2. Federal Aviation Regulation, Section 25.965, “Fuel Tank Tests,” sub-section b)(2), Title 14 Code of Federal Regulations (CFR), Federal Register, December 19, 2000.

  3. Walker, K., “The Effect of Stress Ratio during Crack Propagation and Fatigue for 2024-T3 and 7075-T6 Aluminum,” in Effects of Environment and Complex Load History on Fatigue Life, ASTM STP 462, American Society for Testing and Materials, Philadelphia, 1970.

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  4. Forman, R. G., Kearney, V. E., and Engle, R. M., “Numerical Analysis of Crack Propagation in a Cyclic-Loaded Structure,” Transactions ASME J Basic Eng., Vol. D89 (3), 1967, pp. 459–464.

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Authors and Affiliations

  1. Department of Mechanical Engineering, University of Maryland Baltimore County, Baltimore, MD, USA

    R. L. Smith (Student), T. Farquhar (SEM Member is an Associate Professor) & D. Arola (SEM Member is an Assistant Professor)

  2. Decrane Aircraft, Columbia, MD, USA

    S. Bhonsale & D. Sullivan

Authors
  1. R. L. Smith
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  2. T. Farquhar
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  3. D. Arola
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  4. S. Bhonsale
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  5. D. Sullivan
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Smith, R.L., Farquhar, T., Arola, D. et al. Fatigue and proof testing of an aircraft auxiliary fuel tank. Exp Tech 26, 19–23 (2002). https://doi.org/10.1111/j.1747-1567.2002.tb00079.x

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  • DOI: https://doi.org/10.1111/j.1747-1567.2002.tb00079.x

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