An airfoil component for a gas turbine engine comprising: an airfoil piece formed of a ceramic, the airfoil piece defining a first platform and an airfoil section extending from the first platform, the airfoil section including suction and pressure sides (70d, 70c), a leading end a trailing end, and a trailing end margin that is solid from the suction side to the pressure side, characterised by the trailing end margin having a trailing edge cutback, wherein the airfoil piece includes a fillet joining the first platform and the airfoil section, and the trailing end margin includes a first structural leg extending between the fillet and the trailing edge cutback, wherein the airfoil piece is formed of a laminated ceramic matrix composite, the airfoil piece defining the first platform and a second platform, the airfoil section extending between the first and second platforms (64, 66), wherein the airfoil piece includes a first fillet joining the first platform and the trailing end margin and a second fillet joining the second platform and the trailing end margin, wherein the trailing end margin includes the first structural leg and a second structural leg extending between, respectively, the first fillet and the trailing edge cutback and the second fillet and the trailing edge cutback, wherein the trailing edge cutback includes first and second opposed radial faces (82a, 82b), an axial face, and first and second curved corners (82d, 82e) joining, respectively, the first radial face and the axial face and the second radial face and the axial face, and wherein the trailing edge cutback is radially spaced from the first fillet and from the second fillet such that there are narrow strips that extend between the respective first and second fillets (67a, 67b) and the respective first and second radial faces (82a, 82b) of the trailing edge cutback to form the respective first and second legs (80a, 80b). an airfoil piece formed of a ceramic, the airfoil piece defining a first platform and an airfoil section extending from the first platform, the airfoil section including suction and pressure sides (70d, 70c), a leading end a trailing end, and a trailing end margin that is solid from the suction side to the pressure side, characterised by the trailing end margin having a trailing edge cutback, wherein the airfoil piece includes a fillet joining the first platform and the airfoil section, and the trailing end margin includes a first structural leg extending between the fillet and the trailing edge cutback, wherein the airfoil piece is formed of a laminated ceramic matrix composite, the airfoil piece defining the first platform and a second platform, the airfoil section extending between the first and second platforms (64, 66), wherein the airfoil piece includes a first fillet joining the first platform and the trailing end margin and a second fillet joining the second platform and the trailing end margin, wherein the trailing end margin includes the first structural leg and a second structural leg extending between, respectively, the first fillet and the trailing edge cutback and the second fillet and the trailing edge cutback, wherein the trailing edge cutback includes first and second opposed radial faces (82a, 82b), an axial face, and first and second curved corners (82d, 82e) joining, respectively, the first radial face and the axial face and the second radial face and the axial face, and wherein the trailing edge cutback is radially spaced from the first fillet and from the second fillet such that there are narrow strips that extend between the respective first and second fillets (67a, 67b) and the respective first and second radial faces (82a, 82b) of the trailing edge cutback to form the respective first and second legs (80a, 80b).