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Deformation and damage predictions for aero engine components require a good understanding of the time-dependent inelastic material behaviour under elevated temperature exposure. Life limiting component areas are often associated with stress concentration features such as cooling holes in combustors. Various Low Cycle Fatigue (LCF) tests on two types of featured specimens of the nickel base alloy Nimonic C263 have been analysed by Finite Element Analyses using the unified Chaboche model. This material model was fitted to tensile and LCF plain specimen test results on C263. For crack initiation lifing various damage parameters based on plastic strain range and plastic strain energy density have been applied and correlated to LCF plain specimen data over a wide range of temperatures. The fitted damage parameters were used for LCF life predictions ofibe featured specimens based on the stabilized cyclic stress--strain response from the FE analyses. Finally, a comparison between predicted undexperimentally derived crack initiation lives iuperformed.