A method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the method may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by heating the airfoil to no more than 750 degrees F. while applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. The load is up to 6000 lbf. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.