The introduction of new processing routes such as metal injection moulding (MIM) for aero-engine components requires an extensive material and process validation. Approaches for further material optimization are therefore of special interest. In this study the effect of solution annealing followed by an ageing treatment on the tensile, fatigue and creep properties of metal injection moulded nickel-base superalloy Inconel 713LC (IN 713LC) was investigated. Heat treated MIM IN 713LC is characterized by optimized ?' size (refinement of the initial ?' edge length from approx. 0.6 µm to 0.3 µm) and increased carbide precipitations at the grain boundaries compared to "as sintered" material. Accordingly, the yield strength at room and elevated temperatures as well as the time to rupture is superior for heat treated MIM IN 713LC material. However, the increase of strength is accomplished with reduction of ductility. Fatigue properties equivalent to "as sintered" IN 713LC material are obtained in the heat treated condition.