This paper presents the authors experience concerning essentially long crack variable amplitude behavior in selected aluminum alloys. Different kinds of tests, such as single overloads, block programmed tests and tests using a transport aircraft wing loading are presented and discussed with respect to material behavior. The anomalous behavior of an Aluminum Lithium alloy is also briefly discussed. In the second part of the paper, fatigue crack initiation life at a notch tip is analyzed using the short crack kinetics. It is shown that acceptable results can be obtained under variable amplitude loadings, using certain simple hypotheses.
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