Abstract: A method for repairing an aircraft structure made of composite material which comprises a damaged zone having at least one bend. The method comprises the stacking of at least two sheets of composite material, which each have a thickness allowing manual deformation thereof, a first sheet being applied to the damaged zone and shaped manually so as to follow said at least one bend of the zone, a second sheet being applied to the first sheet and shaped manually so as to follow the shape of the first sheet thus shaped. The use of individual sheets makes it possible to bend them to the desired bend without tools and the resulting stack provides the desired rigidity.

Abstract: A method for repairing damage to the coating of an aircraft fuselage, the coating being made of fiber-reinforced composite material. This method comprising making a cut-out in the fuselage with a substantially parallelepipedal outline around the damage and drilling a circular hole substantially centered on the intersection of the sides of the outline of the parallelepiped of the cut-out at each of the corners of the outline before the cutting out operation.

Abstract: A method for designing repair kits for a predefined area of the external/internal structure of an aircraft, the repair kits each including an external/internal structural part having predefined shape and size, suitable for being placed within the existing external/internal structure, instead of an equivalent shape including a damaged area, which can be removed or not, the method including creating a range of standardised repair kits, optimized according to an estimate of the most likely types of accidental damage in the studied area.

Abstract: The invention relates to a method for repairing aircraft primary structures. More specifically, the invention relates to a method for repairing damage to the coating of an aircraft fuselage, which coating is made of fiber-reinforced composite material. This method comprises a step consisting of making a cut-out in the fuselage with a substantially parallelepipedal outline around the damages and of drilling a circular hole substantially centered on the intersection of the sides of the outline of the parallelepiped of the cut-out at each of the corners of said outline before the cutting out operation.