<p>The present study has suggested an improved methodology for carrying out the required precision machining of aero engine turbine blades using the creep feed grinding technique. Novel features of this methodology include the use of the transfer of 3–2-1 reference from the airfoil to the platform region of the component. Such reference transfer helps reduce the necessity of clamping of the blade in the critical airfoil region, which can potentially cause undesirable localized mechanical deformation in this region. In addition, the important step of realizing the required throat correction in the blade during the machining of the fir-tree has also been suggested. The efficacy of the methodology has been demonstrated by carrying out machining on multiple blade castings and realizing the dimensions of machined firtree within specified tolerances levels.</p>