Abstract
We consider a complex of problems of evaluating the residual lifetime of aircraft constructions after long-term operation. Some results of static and fatigue tests of a D16T-type aluminum alloy (in the as-delivered condition as well as after simulated and operating degradation) in air and a corrosive medium (3% NaCl solution) are presented. We have established characteristics that are the most sensitive to the degradation of constructional materials in the course of long-term operation. We also describe a new approach and correction factors for evaluating the fatigue durability of elements of aircraft constructions with regard for the degradation of materials.
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