An assembly for use in a gas turbine engine comprising a ceramic matrix composite panel

An assembly for use in a gas turbine engine has an underlying metal sheet (22), and at least one ceramic matrix composite tile (24) attached to the underlying metal sheet (22) with at least one fastener assembly (26). The panel fastener assembly (26) includes a fastener (30) having a threaded portion extending rearwardly from a head (28), which has a frustoconical surface (31) facing the threaded portion. The frustoconical surface (31) is received in a frustoconical bore (432) in the ceramic matrix composite panel (24). A bushing (138) is positioned on an opposed side of the metal sheet (22) from the ceramic matrix composite panel (24). The bushing (138) has a flange (144) extending away from the metal sheet (22). A sleeve (34) is received about the threaded portion of the fastener (30), and extends away from the panel (24), beyond the metal sheet (22). The sleeve (34) has a lip (145) extending radially outwardly toward the flange (144) on the bushing (138), such that the flange (144) on the bushing (138) extends beyond a space defined between the lip (145) and a seating surface (142) on the bushing (138). A wave spring (36) is received within the cavity.