A gas turbine engine comprising: a compressor section having a plurality of compressor stages; a combustor section fluidly connected to the compressor section; a turbine section fluidly connected to the combustor section and having a plurality of turbine stages; at least one of the turbine sections and the compressor sections including a set of circumferentially arranged rotors and a set of blade outer air seals disposed radially outward of the circumferentially arranged rotors; each blade outer air seal in the set of blade outer air seals including a platform having a leading edge and a trailing edge, and at least one cooling cavity disposed within the platform, a pair of circumferential edges connecting the leading edge and the trailing edge, an end wall protruding radially outward from the platform at the trailing edge, a support hook protruding radially outward from the leading edge of the platform, at least one boss feature protruding radially outward from the platform and defining a solid kinetic energy path from an inner diameter of the platform to a radially outward facing surface of the boss feature, wherein the boss feature extends less than a circumferential length of the platform; an engine case support connecting each blade outer air seal to an engine case, the case support including a connector received in the support hook of each blade outer air seal, characterised in that the case support further includes a first set of radially inwardly protruding tabs comprising at least one tab aligned axially and circumferentially with the corresponding at least one boss feature of each blade outer air seal and a second set of radially inward protruding tabs, and wherein each radially inward protruding tab in the second set is circumferentially aligned with at least one circumferential edge of the pair of circumferential edges of the platform, and wherein each radially inwardly protruding tab of the first set and each corresponding boss feature define a solid kinetic energy path during a blade off event. a compressor section having a plurality of compressor stages; a combustor section fluidly connected to the compressor section; a turbine section fluidly connected to the combustor section and having a plurality of turbine stages; at least one of the turbine sections and the compressor sections including a set of circumferentially arranged rotors and a set of blade outer air seals disposed radially outward of the circumferentially arranged rotors; each blade outer air seal in the set of blade outer air seals including a platform having a leading edge and a trailing edge, and at least one cooling cavity disposed within the platform, a pair of circumferential edges connecting the leading edge and the trailing edge, an end wall protruding radially outward from the platform at the trailing edge, a support hook protruding radially outward from the leading edge of the platform, at least one boss feature protruding radially outward from the platform and defining a solid kinetic energy path from an inner diameter of the platform to a radially outward facing surface of the boss feature, wherein the boss feature extends less than a circumferential length of the platform; an engine case support connecting each blade outer air seal to an engine case, the case support including a connector received in the support hook of each blade outer air seal, characterised in that the case support further includes a first set of radially inwardly protruding tabs comprising at least one tab aligned axially and circumferentially with the corresponding at least one boss feature of each blade outer air seal and a second set of radially inward protruding tabs, and wherein each radially inward protruding tab in the second set is circumferentially aligned with at least one circumferential edge of the pair of circumferential edges of the platform, and wherein each radially inwardly protruding tab of the first set and each corresponding boss feature define a solid kinetic energy path during a blade off event.