An aircraft panel with a laminate structure, the laminate structure comprising: - a stack of a plurality of metal sheet layers; - at least one fibre reinforced adhesive layer; and - at least one cover segment; wherein at least one outer layer of the metal sheet layers comprises at least two separate metal sheets (20, 22) that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets; wherein the at least one fibre reinforced adhesive layer comprises fibre elements embedded in a matrix structure; and wherein one of the at least one fibre reinforced adhesive layers is arranged between two adjacent metal sheet layers; wherein the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint; wherein the at least one cover segment comprises at least one layer of reinforcement fibres; wherein the at least one cover segment comprises a fibre/resin prepreg; and wherein the reinforcement fibres of the prepreg are arranged in a unidirectional orientation crosswise to an orientation of the overlapping joint. - a stack of a plurality of metal sheet layers; - at least one fibre reinforced adhesive layer; and - at least one cover segment; wherein at least one outer layer of the metal sheet layers comprises at least two separate metal sheets (20, 22) that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets; wherein the at least one fibre reinforced adhesive layer comprises fibre elements embedded in a matrix structure; and wherein one of the at least one fibre reinforced adhesive layers is arranged between two adjacent metal sheet layers; wherein the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint; wherein the at least one cover segment comprises at least one layer of reinforcement fibres; wherein the at least one cover segment comprises a fibre/resin prepreg; and wherein the reinforcement fibres of the prepreg are arranged in a unidirectional orientation crosswise to an orientation of the overlapping joint. wherein at least one outer layer of the metal sheet layers comprises at least two separate metal sheets (20, 22) that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets; wherein the at least one fibre reinforced adhesive layer comprises fibre elements embedded in a matrix structure; and wherein one of the at least one fibre reinforced adhesive layers is arranged between two adjacent metal sheet layers; wherein the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint; wherein the at least one cover segment comprises at least one layer of reinforcement fibres; wherein the at least one cover segment comprises a fibre/resin prepreg; and wherein the reinforcement fibres of the prepreg are arranged in a unidirectional orientation crosswise to an orientation of the overlapping joint.