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Fatigue of Aircraft Structures

The Journal of Institute of Aviation

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Online
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2300-7591
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Selected Aspects Related to the Applied Loads Control During Fatigue Tests of a Metallic Airframe

Józef Brzęczek / Jerzy Chodur / Janusz Pietruszka
Published Online: 2015-06-30 | DOI: https://doi.org/10.1515/fas-2014-0010

Abstract

Service life of the PZL M28 is computed based on the results of the full-scale fatigue tests of the structure [1]. As the PZL M28 is a commuter category airplane according to the 14 CFR Part 23 and CS-23 regulations, the test objects are: (1) wing and wing load carry-through structure, (2) empennage and attached fuselage structure. Additionally, there are fatigue tests carried out for the landing gear and other selected elements including control system elements. The aircraft load carry-through structure is metallic and the cabin is unpressurized. The fatigue tests are conducted stage-by-stage. As tests progress, it is possible to extend the aircraft target service life, applying the safe life philosophy with reference to the primary components of the load carry-through structure.

The article brings into attention the issue of the applied loads control in conducting fatigue tests of the metallic airframe.

Keywords: metallic airframe structure; full scale fatigue tests

REFERENCES

  • 1. J. Pietruszka “Full-Scale Fatigue Tests of PZL M28 05 SKYTRUCK Aircraft”. Transactions of Institute of Aviation, 1/2009 (196). Warsaw, 2009.Google Scholar

  • 2. J. Brzęczek, J. Chodur, J. Pietruszka “Selected Aspects Related to Metallic Airframe Fatigue Tests Preparation”. Fatigue of Aircraft Structures, Issue 2014, Institute of Aviation. Warsaw, 2015.Google Scholar

About the article

Published Online: 2015-06-30

Published in Print: 2014-06-01


Citation Information: Fatigue of Aircraft Structures, ISSN (Online) 2300-7591, DOI: https://doi.org/10.1515/fas-2014-0010.

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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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