A gas turbine engine comprising: a shroud segment extending circumferentially about an engine axis and including a tab projecting radially outward, wherein the tab includes opposing first and second rims (88, 90) extending circumferentially and a base portion spanning radially between the first and second rims (88, 90) with the base portion and the rims (88, 90) defining a channel in the tab and wherein the rims (88, 90) are radially spaced apart by a rim distance; a case orientated about the engine axis and spaced radially outward from the shroud segment, the case including an annular flange projecting radially inward and biased against the first and second rims (88, 90) and at least in-part exposed to the channel; a shaft extending along a centerline disposed parallel to the engine axis, and wherein the shaft extends through a first hole in the flange and a second hole in the base portion and centered between the first and second rims (88, 90); and an anti-rotation feature rigidly engaged to the shaft and projecting radially outward in diametrically opposed directions with respect to the centerline, the anti-rotation feature having diametrically opposite arcuate first and second edges (128, 132) each having an equivalent radius of curvature measured through the centerline and wherein a ratio of the rim distance over the radius of curvature is equal to or less than 0.28; wherein said gas turbine engine further comprises: a first nut threadably engaged to a first end portion of the shaft that projects outward from the flange opposite the tab; a bushing disposed about the shaft and axially biased against the tab opposite the flange; and a second nut threadably engaged to a second end portion of the shaft opposite the first end portion and that projects outward from the bushing, and wherein a depth of the channel is greater than an axial width of the anti-rotation feature; wherein a first flanking location of the first edge contacts the first rim and a second flanking location of the second edge contacts the second rim when the anti-rotation feature is rotated about the centerline from a disengaged state to an engaged state. a shroud segment extending circumferentially about an engine axis and including a tab projecting radially outward, wherein the tab includes opposing first and second rims (88, 90) extending circumferentially and a base portion spanning radially between the first and second rims (88, 90) with the base portion and the rims (88, 90) defining a channel in the tab and wherein the rims (88, 90) are radially spaced apart by a rim distance; a case orientated about the engine axis and spaced radially outward from the shroud segment, the case including an annular flange projecting radially inward and biased against the first and second rims (88, 90) and at least in-part exposed to the channel; a shaft extending along a centerline disposed parallel to the engine axis, and wherein the shaft extends through a first hole in the flange and a second hole in the base portion and centered between the first and second rims (88, 90); and an anti-rotation feature rigidly engaged to the shaft and projecting radially outward in diametrically opposed directions with respect to the centerline, the anti-rotation feature having diametrically opposite arcuate first and second edges (128, 132) each having an equivalent radius of curvature measured through the centerline and wherein a ratio of the rim distance over the radius of curvature is equal to or less than 0.28; wherein said gas turbine engine further comprises: a first nut threadably engaged to a first end portion of the shaft that projects outward from the flange opposite the tab; a bushing disposed about the shaft and axially biased against the tab opposite the flange; and a second nut threadably engaged to a second end portion of the shaft opposite the first end portion and that projects outward from the bushing, and wherein a depth of the channel is greater than an axial width of the anti-rotation feature; a first nut threadably engaged to a first end portion of the shaft that projects outward from the flange opposite the tab; a bushing disposed about the shaft and axially biased against the tab opposite the flange; and a second nut threadably engaged to a second end portion of the shaft opposite the first end portion and that projects outward from the bushing, and wherein a depth of the channel is greater than an axial width of the anti-rotation feature; wherein a first flanking location of the first edge contacts the first rim and a second flanking location of the second edge contacts the second rim when the anti-rotation feature is rotated about the centerline from a disengaged state to an engaged state.