A method for manufacturing a metallic superalloy gas turbine engine component using additive manufacturing techniques, the method comprising the steps of: providing a 3D design model for the gas turbine engine component, the 3D design model comprising an airfoil portion and a base portion, wherein the base portion comprises an attachment surface to which the airfoil portion is attached, wherein the attachment surface forms a thick-to-thin transition region of the base portion; adding two transition region crack resistant features to the 3D design model of the component to produce an enhanced design model, wherein the two transition region crack resistant features comprise both of: (a) a cantilevered wing connected to and metallurgically integral with sides of the attachment surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion, and (b) a lattice structure that is connected to and metallurgically integral with the base portion, said lattice structure extending along the attachment surface of the base portion to at least one further surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion; and manufacturing the gas turbine engine component using an additive manufacturing technique in accordance with the enhanced design model to form a manufactured gas turbine engine component, wherein the two transition region crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured gas turbine engine component. providing a 3D design model for the gas turbine engine component, the 3D design model comprising an airfoil portion and a base portion, wherein the base portion comprises an attachment surface to which the airfoil portion is attached, wherein the attachment surface forms a thick-to-thin transition region of the base portion; adding two transition region crack resistant features to the 3D design model of the component to produce an enhanced design model, wherein the two transition region crack resistant features comprise both of: (a) a cantilevered wing connected to and metallurgically integral with sides of the attachment surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion, and (b) a lattice structure that is connected to and metallurgically integral with the base portion, said lattice structure extending along the attachment surface of the base portion to at least one further surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion; and (a) a cantilevered wing connected to and metallurgically integral with sides of the attachment surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion, and (b) a lattice structure that is connected to and metallurgically integral with the base portion, said lattice structure extending along the attachment surface of the base portion to at least one further surface of the base portion so as to be metallurgically integral with the thick-to-thin transition region of the base portion; and manufacturing the gas turbine engine component using an additive manufacturing technique in accordance with the enhanced design model to form a manufactured gas turbine engine component, wherein the two transition region crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured gas turbine engine component. <EOS>