Abstract: The attachment for securing the stator vanes to the outer compressor case includes hooks strategically located with one set in the center of a segment and one set each at either end of each segment. The segments are assembled end to end to form a ring of an array of rows of airfoils for directing air to the compressor blades of a gas turbine engine. Each assembled segment may include three rows of vanes. The axial gap between the structure of the upstream stage of the compressor, the axial and circumferential gap of radially extending pins attached to the "floating" lug-nuts assembled in each pair of hooks and the tight fit of the pins in the center pair of hooks allow for axial and circumferential thermal expansion and the bolted lug-nuts and outer case provide radial restraint, all of which combine to reduce stresses on the airfoil during engine transient conditions.