An aerofoil assembly for use in a gas turbine engine, the aerofoil assembly comprising: an aerofoil comprising ceramic matrix composite materials and extending radially relative to an axis , the aerofoil having a leading edge , a trailing edge spaced apart axially from the leading edge , a pressure side interconnecting the leading edge and the trailing edge , and a suction side spaced apart circumferentially from the pressure side and interconnecting the leading edge and the trailing edge , the aerofoil shaped to define an inner surface that forms an internal cavity for receiving cooling air therein and an outermost surface configured to interact with hot gases conducted through the gas turbine engine; and a first reinforcement inset at least partially located in the suction side of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly , the first reinforcement inset comprising at least one material different than the ceramic matrix composite materials, wherein the ceramic matrix composite materials of the aerofoil surround the first reinforcement inset such that the entire reinforcement inset is in direct contact with the ceramic matrix composite material of the aerofoil to cause the first reinforcement inset to be insulated from the hot gases; and characterised in that a second reinforcement inset is located in the leading edge of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly , wherein the ceramic matrix composite materials of the aerofoil surround the second reinforcement inset such that the entire reinforcement inset is in direct contact with the ceramic matrix composite material of the aerofoil to cause the second reinforcement inset to be insulated from the hot gases. an aerofoil comprising ceramic matrix composite materials and extending radially relative to an axis , the aerofoil having a leading edge , a trailing edge spaced apart axially from the leading edge , a pressure side interconnecting the leading edge and the trailing edge , and a suction side spaced apart circumferentially from the pressure side and interconnecting the leading edge and the trailing edge , the aerofoil shaped to define an inner surface that forms an internal cavity for receiving cooling air therein and an outermost surface configured to interact with hot gases conducted through the gas turbine engine; and a first reinforcement inset at least partially located in the suction side of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly , the first reinforcement inset comprising at least one material different than the ceramic matrix composite materials, wherein the ceramic matrix composite materials of the aerofoil surround the first reinforcement inset such that the entire reinforcement inset is in direct contact with the ceramic matrix composite material of the aerofoil to cause the first reinforcement inset to be insulated from the hot gases; and characterised in that a second reinforcement inset is located in the leading edge of the aerofoil between the inner surface and the outermost surface to resist damage to the aerofoil assembly due to objects impacting the aerofoil assembly , wherein the ceramic matrix composite materials of the aerofoil surround the second reinforcement inset such that the entire reinforcement inset is in direct contact with the ceramic matrix composite material of the aerofoil to cause the second reinforcement inset to be insulated from the hot gases. <EOS>