During service, blade-disc contact interfaces of an aero-engine undergo combination of partial slip and gross slip. Generally, fretting wear is observed in the gross slip regime while fretting fatigue occurs in partial and mixed regime. Extent for fretting damage is significantly affected by fretting regime. In the present work, finite element analysis of flat and rounded contact geometry has been carried to identify the transition between different sliding regimes. The results of analysis are proposed to be validated with available experimental data from literature. © 2017 Chinese Society of Theoretical and Applied Mechanics. All Rights Reserved.