Abstract: A component of an aircraft engine includes an annular flange disposed about a radially outer surface of the component. the annular flange includes an annular wall extending radially outwardly from the radially outer surface of the component. The annular wall includes radially-extending supports circumferentially spaced apart and extending radially between the radially outer surface of the component and a circumferentially uninterrupted radially outer rim of the annular wall. The annular wall includes one or more arcuate cutouts defined circumferentially between adjacent radially-extending supports and radially inwards of the radially outer rim of the annular wall. The radially-extending supports include fastener openings defined axially therethrough. A spigot extends axially from the radially outer rim of the annular wall and circumferentially about an entire circumference of the radially outer rim of the annular wall.