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The additive manufacturing process has allowed for advancement in the rapid development of aircraft gas turbine engine components, due to its rapid prototyping capabilities with the added benefits of geometric design flexibility, and reduced production cost. These turbine engine components often experience a multiaxial stress state at high temperature, in which an understanding of the axial and torsional response exhibited by these additively manufactured materials is of import. The present study is novel in that it assesses the torsional fatigue performance of additively manufactured machined and heat-treated Inconel 718, a metal superalloy commonly used in gas turbine engines, of vertical (Z) build orientation, at an elevated temperature of 650°C. Preliminary findings exhibit a reduction in shear moduli and plastic shear strain absorbing capacity at 650°C compared to room temperature. Also evident was cyclic softening from the first to the stabilized cycle and an approximate torsional fatigue life on the order of 10^3 cycles when cycling at an angle of twist range of Δφ = ±15°.