A method of repairing a damaged airfoil removed from service, comprising the steps of: stripping thermal barrier coatings from the airfoil; locally grit blasting a fillet radius portion (20, 50) of the airfoil to remove cracks from the fillet radius portion, while locally removing a bond coating from the fillet radius portion; removing damaged material from an airfoil tip portion (18, 58); replacing superalloy material on the airfoil tip portion (18, 58); thermally etching the airfoil; applying platinum plating over the locally removed bond coat and over the replaced superalloy material; diffusion heat treating the platinum plated airfoil; and vapor phase aluminiding the airfoil to form a PtAl coating over the applied platinum coating; wherein the step of applying platinum plating over the replaced superalloy material on the airfoil tip portion (18, 58) and over the grit blasted fillet radius portion (20, 50) of the airfoil includes placing the airfoil in a non-conductive plating tool that selectively coats and restores plating thickness to the airfoil tip portion and the fillet radius portion of the airfoil, the plating tool further including a first mesh screen adjacent the fillet radius portion (20, 50) of the airfoil and at least one second mesh screen adjacent the airfoil tip portion (18, 58); further including connecting a power supply to the first and second mesh screens (200, 202) and the airfoil, applying power to the airfoil from the power supply, wherein platinum plating is applied from a plating solution to the airfoil tip portion (18, 58) and to the fillet radius portion (20, 50) of the airfoil, plating also being applied to regions of the airfoil in the plating solution adjacent the airfoil tip portion and the fillet radius portion, the amount of plating applied to the adjacent regions decreasing with increasing distance from the mesh screen, the amount of plating deposited adjacent the tip portion being further restricted by at least one opening adjacent tip portion. stripping thermal barrier coatings from the airfoil; locally grit blasting a fillet radius portion (20, 50) of the airfoil to remove cracks from the fillet radius portion, while locally removing a bond coating from the fillet radius portion; removing damaged material from an airfoil tip portion (18, 58); replacing superalloy material on the airfoil tip portion (18, 58); thermally etching the airfoil; applying platinum plating over the locally removed bond coat and over the replaced superalloy material; diffusion heat treating the platinum plated airfoil; and vapor phase aluminiding the airfoil to form a PtAl coating over the applied platinum coating; wherein the step of applying platinum plating over the replaced superalloy material on the airfoil tip portion (18, 58) and over the grit blasted fillet radius portion (20, 50) of the airfoil includes placing the airfoil in a non-conductive plating tool that selectively coats and restores plating thickness to the airfoil tip portion and the fillet radius portion of the airfoil, the plating tool further including a first mesh screen adjacent the fillet radius portion (20, 50) of the airfoil and at least one second mesh screen adjacent the airfoil tip portion (18, 58); further including connecting a power supply to the first and second mesh screens (200, 202) and the airfoil, applying power to the airfoil from the power supply, wherein platinum plating is applied from a plating solution to the airfoil tip portion (18, 58) and to the fillet radius portion (20, 50) of the airfoil, plating also being applied to regions of the airfoil in the plating solution adjacent the airfoil tip portion and the fillet radius portion, the amount of plating applied to the adjacent regions decreasing with increasing distance from the mesh screen, the amount of plating deposited adjacent the tip portion being further restricted by at least one opening adjacent tip portion.