An assembly (60; 160; 560; 660) for a gas turbine engine comprising: a gas turbine engine component (66; 166; 566) including a first interface portion (74; 174); a support (68; 168) including a mounting portion and a second interface portion (78; 178), the mounting portion attachable to an engine static structure; a first retention feature (80; 180; 580) that releasably secures the first interface (74; 174) portion to the support in a first installed position of the gas turbine engine component (66; 166; 566); and a second retention feature (82; 182; 582) dimensioned to secure the first interface portion (74; 174) to the second interface portion (78; 178) in a second installed position of the gas turbine engine component (66; 166; 566), wherein the first installed position differs from the second installed position, and the second retention features (82; 182; 582) is dimensioned to carry the gas turbine engine component (66; 166; 566) in response to release of the first retention feature (80; 180; 580); wherein the second retention feature (82; 182; 582) includes an interface flange extending outwardly from the first interface portion (74; 174) and includes a support flange extending from the second interface portion (82; 182; 582), the interface flange is dimensioned to sit on the support flange in the second installed position; wherein the gas turbine engine component (66; 166; 566) is a seal arc segment including a sealing portion (72; 172) dimensioned to bound a gas path surface, the first interface portion (74; 174) includes an interface bore (74B; 174B), the first retention feature (80; 180; 580) includes a retention pin (84; 184) slidably received in the interface bore (74B; 174B) to secure the first interface portion (74; 174) to the support in the first installed position of the seal arc segment, and the interface bore (74B; 174B) is dimensioned such that the seal arc segment sits on an outer periphery of the retention pin (84; 184) in the first installed position, and wherein the first interface portion (74; 174) includes a pair of rails (74R; 174R), the interface bore (74B; 174B) is dimensioned such that the rails (74R; 174R) are spaced apart from a radially inner surface of the retention pin (84; 184) in the first installed position during engine operation, and wherein a position of the first interface portion (74; 174) changes relative to the second interface portion (82; 182; 582) in response to the release of the first retention feature (80; 180; 580) when the gas turbine engine component (66; 166; 566) is situated in the first installed position such that the gas turbine engine component (66; 166; 566) moves in a radially inward direction toward an engine longitudinal axis from the first installed position to the second installed position. a gas turbine engine component (66; 166; 566) including a first interface portion (74; 174); a support (68; 168) including a mounting portion and a second interface portion (78; 178), the mounting portion attachable to an engine static structure; a first retention feature (80; 180; 580) that releasably secures the first interface (74; 174) portion to the support in a first installed position of the gas turbine engine component (66; 166; 566); and a second retention feature (82; 182; 582) dimensioned to secure the first interface portion (74; 174) to the second interface portion (78; 178) in a second installed position of the gas turbine engine component (66; 166; 566), wherein the first installed position differs from the second installed position, and the second retention features (82; 182; 582) is dimensioned to carry the gas turbine engine component (66; 166; 566) in response to release of the first retention feature (80; 180; 580); wherein the second retention feature (82; 182; 582) includes an interface flange extending outwardly from the first interface portion (74; 174) and includes a support flange extending from the second interface portion (82; 182; 582), the interface flange is dimensioned to sit on the support flange in the second installed position; wherein the gas turbine engine component (66; 166; 566) is a seal arc segment including a sealing portion (72; 172) dimensioned to bound a gas path surface, the first interface portion (74; 174) includes an interface bore (74B; 174B), the first retention feature (80; 180; 580) includes a retention pin (84; 184) slidably received in the interface bore (74B; 174B) to secure the first interface portion (74; 174) to the support in the first installed position of the seal arc segment, and the interface bore (74B; 174B) is dimensioned such that the seal arc segment sits on an outer periphery of the retention pin (84; 184) in the first installed position, and wherein the first interface portion (74; 174) includes a pair of rails (74R; 174R), the interface bore (74B; 174B) is dimensioned such that the rails (74R; 174R) are spaced apart from a radially inner surface of the retention pin (84; 184) in the first installed position during engine operation, and wherein a position of the first interface portion (74; 174) changes relative to the second interface portion (82; 182; 582) in response to the release of the first retention feature (80; 180; 580) when the gas turbine engine component (66; 166; 566) is situated in the first installed position such that the gas turbine engine component (66; 166; 566) moves in a radially inward direction toward an engine longitudinal axis from the first installed position to the second installed position.