A vane for a gas turbine engine, comprising: an airfoil extending along a camber line between a leading edge and a trailing edge , the airfoil extending along a span line between an inner end and an outer end , the airfoil extending laterally between a first side and a second side , and the airfoil including a base section , a first side section , a second side section and a sheath ; the base section extending along the span line between the inner end and the outer end , the base section laterally between the first side section and the second side section , and the base section comprising metal material; the first side section connected to the base section and partially forming the first side of the airfoil , the first side section comprising first non-metal material, optionally fiber-reinforced composite material; the second side section connected to the base section and partially forming the second side of the airfoil , the second side section comprising second non-metal material, optionally fiber-reinforced composite material; and the sheath at least partially forming an edge of the airfoil , wherein the edge is the leading edge or the trailing edge of the airfoil , characterised in that : the base section has a first portion and a second portion aligned along the camber line; the first portion is between the second portion and one of the inner end and the outer end along the span line ; the first portion has a first lateral thickness; the second portion has a second lateral thickness that is less than the first lateral thickness; and at least one of the first side section or the second side section overlaps and is connected to the first portion and the second portion. an airfoil extending along a camber line between a leading edge and a trailing edge , the airfoil extending along a span line between an inner end and an outer end , the airfoil extending laterally between a first side and a second side , and the airfoil including a base section , a first side section , a second side section and a sheath ; the base section extending along the span line between the inner end and the outer end , the base section laterally between the first side section and the second side section , and the base section comprising metal material; the first side section connected to the base section and partially forming the first side of the airfoil , the first side section comprising first non-metal material, optionally fiber-reinforced composite material; the second side section connected to the base section and partially forming the second side of the airfoil , the second side section comprising second non-metal material, optionally fiber-reinforced composite material; and the sheath at least partially forming an edge of the airfoil , wherein the edge is the leading edge or the trailing edge of the airfoil , characterised in that : the base section has a first portion and a second portion aligned along the camber line; the first portion is between the second portion and one of the inner end and the outer end along the span line ; the first portion has a first lateral thickness; the second portion has a second lateral thickness that is less than the first lateral thickness; and at least one of the first side section or the second side section overlaps and is connected to the first portion and the second portion. the base section has a first portion and a second portion aligned along the camber line; the first portion is between the second portion and one of the inner end and the outer end along the span line ; the first portion has a first lateral thickness; the second portion has a second lateral thickness that is less than the first lateral thickness; and at least one of the first side section or the second side section overlaps and is connected to the first portion and the second portion. <EOS>