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 (57, 58); 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 (57, 58) 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 (57, 58); 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 (57, 58) 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.