A vane ring for a gas turbine engine, comprising: a multiple of airfoil fairing shells each with an airfoil section between an outer vane endwall and an inner vane endwall, at least one of said outer vane endwall and said inner vane endwall of each of the multiple of airfoil fairing shells forms a mateface, each of said multiple of airfoil fairing shells adjacent to another one of said multiple of airfoil fairing shells at said mateface; and a structural support (110, 112), characterised in that: at least one of said outer vane endwall and said inner vane endwall of each of the multiple of airfoil fairing shells includes a thickened region comprising step transitions, the thickened region forming a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face configured to react in-plane loads formed by the step transitions; said suction side tangential attachment face downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil fairing shell such that the in-plane loading to the reaction forces on said suction side tangential attachment faces is compressive; and the structural support (110, 112) includes a multiple of lugs, the suction side tangential attachment face of each of said multiple of airfoil fairing shells interfacing with one of the multiple of lugs to provide a primary reaction load, and the axial attachment face of each of said multiple of airfoil fairing shells interfacing with the structural support (110, 112) to provide a secondary reaction load. a multiple of airfoil fairing shells each with an airfoil section between an outer vane endwall and an inner vane endwall, at least one of said outer vane endwall and said inner vane endwall of each of the multiple of airfoil fairing shells forms a mateface, each of said multiple of airfoil fairing shells adjacent to another one of said multiple of airfoil fairing shells at said mateface; and a structural support (110, 112), characterised in that: at least one of said outer vane endwall and said inner vane endwall of each of the multiple of airfoil fairing shells includes a thickened region comprising step transitions, the thickened region forming a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face configured to react in-plane loads formed by the step transitions; said suction side tangential attachment face downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil fairing shell such that the in-plane loading to the reaction forces on said suction side tangential attachment faces is compressive; and the structural support (110, 112) includes a multiple of lugs, the suction side tangential attachment face of each of said multiple of airfoil fairing shells interfacing with one of the multiple of lugs to provide a primary reaction load, and the axial attachment face of each of said multiple of airfoil fairing shells interfacing with the structural support (110, 112) to provide a secondary reaction load. at least one of said outer vane endwall and said inner vane endwall of each of the multiple of airfoil fairing shells includes a thickened region comprising step transitions, the thickened region forming a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face configured to react in-plane loads formed by the step transitions; said suction side tangential attachment face downstream of an aerodynamic center of a resultant aerodynamic load generated by said airfoil fairing shell such that the in-plane loading to the reaction forces on said suction side tangential attachment faces is compressive; and the structural support (110, 112) includes a multiple of lugs, the suction side tangential attachment face of each of said multiple of airfoil fairing shells interfacing with one of the multiple of lugs to provide a primary reaction load, and the axial attachment face of each of said multiple of airfoil fairing shells interfacing with the structural support (110, 112) to provide a secondary reaction load.