An apparatus comprising: a gas turbine engine having a pair of gas turbine engine blade track coupling members useful for securing a blade track at an upstream end and a downstream end, each of the pair of blade track coupling members having a circumferentially extending channel (76; 78) shaped to receive the respective upstream and downstream ends of the blade track, a flexible gas turbine engine clip (80a; 80b) extending in an arc and structured to fit within one of the circumferentially extending channels, the engine clip having an opening (82a; 82b) to receive one of the upstream end and downstream end of the blade track, the opening being disposed between a top end (86a; 86b) and a bottom end (88a; 88b) of a curvilinear clip body operable to flex when the blade track is inserted through the opening, wherein at least one of the pair of blade track coupling members includes a coupling member anti-rotation member structured to discourage circumferential movement of the at least one of the pair of blade track coupling members relative to a static structure of a gas turbine engine; and wherein the gas turbine engine blade track includes a plurality of blade tracks characterised in that at least one of the pair of blade track coupling members includes a blade track anti-rotation member (90a; 90b) structured to discourage circumferential movement of the blade track, wherein at least some of the plurality of blade tracks include a cutout (92; 94) structured to engage the blade track anti-rotation member, further including a spring clip located between the blade track anti-rotation member and at least one of the plurality of blade tracks. a gas turbine engine having a pair of gas turbine engine blade track coupling members useful for securing a blade track at an upstream end and a downstream end, each of the pair of blade track coupling members having a circumferentially extending channel (76; 78) shaped to receive the respective upstream and downstream ends of the blade track, a flexible gas turbine engine clip (80a; 80b) extending in an arc and structured to fit within one of the circumferentially extending channels, the engine clip having an opening (82a; 82b) to receive one of the upstream end and downstream end of the blade track, the opening being disposed between a top end (86a; 86b) and a bottom end (88a; 88b) of a curvilinear clip body operable to flex when the blade track is inserted through the opening, wherein at least one of the pair of blade track coupling members includes a coupling member anti-rotation member structured to discourage circumferential movement of the at least one of the pair of blade track coupling members relative to a static structure of a gas turbine engine; and wherein the gas turbine engine blade track includes a plurality of blade tracks characterised in that at least one of the pair of blade track coupling members includes a blade track anti-rotation member (90a; 90b) structured to discourage circumferential movement of the blade track, wherein at least some of the plurality of blade tracks include a cutout (92; 94) structured to engage the blade track anti-rotation member, further including a spring clip located between the blade track anti-rotation member and at least one of the plurality of blade tracks.