Abstract This paper deals with accelerated creep properties of thermal barrier coated (TBC) Superni C263 alloy used as a candidate material in combustion chamber of aero engines. Results reveal that the life of the TBC composite under accelerated creep is substantially higher compared to that of the bare substrate. The mode of fracture in the substrate at very high stresses was transgranular whereas that at low stresses was intergranular. Delamination of bond coat, oxidation of the substrate and spallation of the ceramic layer were evident at very high stress. It was evident that the substrate has negligible estimated rupture strength after 10,000 h of service exposure.