Development of inspection program for limitation of fatigue failure probability (FFP) of fatigueprone aircraft (AC) and fatigue failure rate (FFR) of airline (AL) is a problem of high priority. This problem is aggravated by stringent limitation of number of full-scale fatigue tests (only one or two airframe are tested). In previous authors publications [1-2] minimax solution of the problem was offered in assumption that in exponential approximation of fatigue crack size growth function, a(t) = a0 exp(Qt), only one parameter of fatigue crack trajectory (PFCT) is unknown. Here we consider the case of two unknown parameters
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