Selected Aspects Related to Preparation of Fatigue Tests of a Metallic Airframe

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Abstract

The basis for the computation of the service life of the PZL M28 was 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 were: (1) wing and wing load carry-through structure, (2) empennage and attached fuselage structure. Additionally, there were 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 were conducted stage-by-stage. As the tests progressed, it was possible to extend the aircraft’s target service life, applying a safe life philosophy with reference to the primary components of the load carry-through structure.

This paper brings into attention selected issues related to the fatigue tests preparation (the stage following the preparation of the test plan), with focus on the wing and wing load carry-through structure.

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

2. J. Brzęczek, H. Gruszecki, L. Pieróg, J. Pietruszka “Selected Aspects Related to Preparation of a Fatigue Test Plan of a Metallic Airframe”. Fatigue of Aircraft Structures, Issue 2014, Institute of Aviation. Warsaw, 2015.

3. J. Pietruszka „Fatigue Test of Full Scale Braced Wing and Wing Carry-Through Structure of a Commuter Aircraft” in A. Niepokólczycki ed. “Review of Aeronautical Fatigue Research and Development in Poland during the Period 1999 to 2002”. Transaction of the Institute of Aviation, 173 – 173. Warsaw, 2003.

Fatigue of Aircraft Structures

The Journal of Institute of Aviation

Journal Information

SCImago Journal Rank (SJR) 2017: 0.102

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