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1
Content available The Fatigue Life of Cables in Aircraft Flight Control Systems
Kubryn M., Gruszecki H., Pieróg L., Chodura J., Pietruszka J., Brzęczek J.
Fatigue of Aircraft Structures
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2018
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Iss. 10
53--62
EN
The cable flight control systems are commonly used for the control of small airplanes. In these systems, the cables are the only elements transmitting loads from the pilot to the control surfaces. During a flight the cables are moving through pulleys and are subjected to variable loads. A simple analysis of stress in the cable shows that the stress generated by the cyclical bending on the pulleys causes the fatigue of the wires. This phenomenon was noticed on a military aircraft of the M28 family during periodic maintenance inspection in 2007. The endurance tests of KSAN cables of the diameter equal to 3.5 mm and 1.8 mm were performed at the PZL MIELEC. The tests showed the limited fatigue life of the cables due to a progressive increase in the number of broken wires.
2
Content available Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests
Brzęczek J., Gruszecki H., Pieróg L., Deszcz F., Pietruszka J.
Fatigue of Aircraft Structures
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2014
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Iss. 6
107--112
EN
The PZL M28’s service life is determined based on the fatigue tests of the wing and wing loadscarry-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.
3
Content available Selected Aspects Related to Preparation of a Fatigue Test Plan of a Metallic Airframe
Brzęczek J., Gruszecki H., Pieróg L., Pietruszka J.
Fatigue of Aircraft Structures
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2014
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Iss. 6
88--94
EN
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 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 tests progressed, it was possible to extend the aircraft target service life, applying the safe-life philosophy with reference to the primary components of the load carrythrough structure. The article brings into attention selected issues related to the fatigue tests plan preparation, with focus on wing and wing load carry-through structure test.
4
Content available Full Scale Fatigue Test of New Undercarriage for Commuter Aircraft
Brzęczek J., Gruszecki H., Pieróg L., Pietruszka J.
Fatigue of Aircraft Structures
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2012
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Iss. 4
70--75
EN
Fatigue testing of the new main landing gear for the PZL M28 aircraft was conducted in Polskie Zakłady Lotnicze Sp. z o.o. in Mielec using MTS Aero 90-LT system. The test was conducted in a flight-by-flight manner with loads resulting from landing, taxiing, maneuvering and braking. The undercarriage structure is made of high tensile strength low alloy steel. FEM analyses were performed before the tests in order to find critical points and to obtain information about loads which may be neglected. During the test fatigue damage was observed, which led to splitting the test into two separate tests performed in independent rigs: the test of the undercarriage leg and the test of the shock absorber.
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