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Fatigue of Aircraft Structures

The Journal of Institute of Aviation

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Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests

Józef Brzęczek / Henryk Gruszecki / Leszek Pieróg / Franciszek Deszcz / Janusz Pietruszka
Published Online: 2015-06-30 | DOI: https://doi.org/10.1515/fas-2014-0011


The PZL M28’s service life is determined based on the fatigue tests of the wing and wing loads-carry-through structure. During the fatigue test, the first occurrence of significance was the appearance of a in the area of the wing where loads are applied from the strut. It was demonstrated during further activities that repairs of the wing and other basic assemblies enabled, when performed at an appropriate time, the airplane’s service life to be significantly increase.

In the case of each design change implemented in the airframe subject to the fatigue testing, a stress analysis of the airframe was required in order to check if local changes, i.e. local repairs, did not affect the stress level in other tested areas. This helped to avoid significant stress redistribution in the airframe after the repair, so the fatigue test was still valid for all areas of interest.

Keywords: metallic airframe structure; full scale fatigue tests


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  • 2. “Fatigue, Fail-Safe, and Damage Tolerance Evaluation of Metallic Structure for Normal, Utility, Acrobatic, and Commuter Category Airplanes”. AC 23-13A. FAA. September 29, 2005.Google Scholar

About the article

Published Online: 2015-06-30

Published in Print: 2014-06-01

Citation Information: Fatigue of Aircraft Structures, Volume 2014, Issue 6, Pages 107–112, ISSN (Online) 2300-7591, DOI: https://doi.org/10.1515/fas-2014-0011.

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© Józef Brzęczek et al.. This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License. BY-NC-ND 3.0

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