A turbine vane assembly (10, 210) adapted for use in a gas turbine engine, the turbine vane assembly (10, 210) comprising: a metallic spar (12, 212) that extends radially inwardly relative to an associated turbine case arranged around a central reference axis, the metallic spar (12, 212) being configured to support other components of the turbine vane assembly (10, 210) relative to the associated turbine case; a turbine vane (14, 214) comprising ceramic matrix composite materials that is supported by the metallic spar (12, 212), the turbine vane (14, 214) shaped to include an airfoil (20, 220) configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly (10, 210), an outer vane mount (26, 226) arranged radially outward of the primary gas path, and an inner vane mount (28, 228) arranged radially inward of the primary gas path, wherein the turbine vane (14, 214) is shaped to define a passageway (18, 218) extending radially therethrough and the metallic spar (12, 212) extends from a radially-outer end of the turbine vane (14, 214) to a radially-inner end of the turbine vane (14, 214); and load transfer pins (16, 216) that couple the turbine vane (14, 214) to the metallic spar (12, 212), the load transfer pins (16, 216) including an outer mount pin (34, 234) that extends away from the metallic spar (12, 212) and through an outer aperture (30, 230) in the outer vane mount (26, 226) of the turbine vane (14, 214) and an inner mount pin (36, 236) that extends away from the metallic spar (12, 212) and through an inner aperture (32, 232) in the inner vane mount (28, 228) of the turbine vane (14, 214), characterised in that one of the outer aperture (30, 230) and the inner aperture (32, 232) is sized to allow radial movement of the corresponding outer mount pin (34, 234) or inner mount pin (36, 236) to create a sliding support that transfers loading of the turbine vane (14, 214) to the metallic spar (12, 212) while accounting for different amounts of thermal growth due to material mismatch of the metallic spar (12, 212) and the turbine vane (14, 214) during operation of the turbine vane assembly (10, 210) at various temperatures. a metallic spar (12, 212) that extends radially inwardly relative to an associated turbine case arranged around a central reference axis, the metallic spar (12, 212) being configured to support other components of the turbine vane assembly (10, 210) relative to the associated turbine case; a turbine vane (14, 214) comprising ceramic matrix composite materials that is supported by the metallic spar (12, 212), the turbine vane (14, 214) shaped to include an airfoil (20, 220) configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly (10, 210), an outer vane mount (26, 226) arranged radially outward of the primary gas path, and an inner vane mount (28, 228) arranged radially inward of the primary gas path, wherein the turbine vane (14, 214) is shaped to define a passageway (18, 218) extending radially therethrough and the metallic spar (12, 212) extends from a radially-outer end of the turbine vane (14, 214) to a radially-inner end of the turbine vane (14, 214); and load transfer pins (16, 216) that couple the turbine vane (14, 214) to the metallic spar (12, 212), the load transfer pins (16, 216) including an outer mount pin (34, 234) that extends away from the metallic spar (12, 212) and through an outer aperture (30, 230) in the outer vane mount (26, 226) of the turbine vane (14, 214) and an inner mount pin (36, 236) that extends away from the metallic spar (12, 212) and through an inner aperture (32, 232) in the inner vane mount (28, 228) of the turbine vane (14, 214), characterised in that one of the outer aperture (30, 230) and the inner aperture (32, 232) is sized to allow radial movement of the corresponding outer mount pin (34, 234) or inner mount pin (36, 236) to create a sliding support that transfers loading of the turbine vane (14, 214) to the metallic spar (12, 212) while accounting for different amounts of thermal growth due to material mismatch of the metallic spar (12, 212) and the turbine vane (14, 214) during operation of the turbine vane assembly (10, 210) at various temperatures.