Reinforcing arrangement (1, 20) for an opening in an aircraft fuselage structure, having - a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and - a reinforcing structure (4, 21, 42) having a thickening section (10, 50) and at least one projecting profile, wherein the first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface on an opening edge region, which has a thickness that equals a thickness of the fuselage skin surrounding the opening edge surface, wherein the thickening section (10, 50) has a bearing surface matched to the opening edge surface and has a receiving section which faces away from the bearing surface and surrounds a second opening, wherein the at least one projecting profile is arranged on the receiving section and extends in a direction away from the bearing surface, wherein the reinforcing structure (4, 21, 42) is in one piece, wherein the fuselage skin and the reinforcing structure (4, 21, 42) are composed of a fibre-reinforced plastic containing reinforcing fibres (12, 14) embedded in a plastic matrix, wherein the bearing surface is in surface contact with the opening edge surface, and the reinforcing structure (4, 21, 42) is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other, wherein a plurality of first reinforcing fibres extends both within the bearing surface and within the projecting profile, and wherein a plurality of second reinforcing fibres extends exclusively within the bearing surface and overlaps or is interleaved with the first reinforcing fibres. - a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and - a reinforcing structure (4, 21, 42) having a thickening section (10, 50) and at least one projecting profile, wherein the first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface on an opening edge region, which has a thickness that equals a thickness of the fuselage skin surrounding the opening edge surface, wherein the thickening section (10, 50) has a bearing surface matched to the opening edge surface and has a receiving section which faces away from the bearing surface and surrounds a second opening, wherein the at least one projecting profile is arranged on the receiving section and extends in a direction away from the bearing surface, wherein the reinforcing structure (4, 21, 42) is in one piece, wherein the fuselage skin and the reinforcing structure (4, 21, 42) are composed of a fibre-reinforced plastic containing reinforcing fibres (12, 14) embedded in a plastic matrix, wherein the bearing surface is in surface contact with the opening edge surface, and the reinforcing structure (4, 21, 42) is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other, wherein a plurality of first reinforcing fibres extends both within the bearing surface and within the projecting profile, and wherein a plurality of second reinforcing fibres extends exclusively within the bearing surface and overlaps or is interleaved with the first reinforcing fibres.