SEAL ASSEMBLY FOR A GAS TURBINE ENGINE AND CORRESPONDING METHOD OF SEALING

An assembly (60; 160; 560; 660) for a gas turbine engine (20) according to an aspect of the present disclosure includes, among other things, a gas turbine engine component (66; 166; 566) that has a first interface portion (74; 174), and a support (68; 168) that has a mounting portion (76) and a second interface portion (78; 178), the mounting portion (76) attachable to an engine static structure (36), a first retention feature (80; 180; 580) that releasably secures the first interface portion (74; 174) to the support (68; 168) 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). The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component (66; 166; 566) in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine (20) is also disclosed.