Abstract
A spectrum wave pattern for a plane is a load form based on the data in which many external forces including uncertain elements were collected from many flights. After overloading in a spectrum wave pattern, the delay of the fatigue crack growth may occur. In this study, the model spectrum wave was made by eliminating amplitude of little crack growth from the original spectrum wave pattern, in consideration of the crack opening point after overload. The crack growth behavior obtained from both waves were similar trend and were grouped to three crack growth rate regions such as 1) crack growth acceleration just after the maximum overload in overloads 2) crack growth by overloads after the maximum overload and retardation 3) retardation after the maximum overload. From three crack growth rates, the crack growth curve was able to be predicted.
