Abstract: The invention relates to a method for repairing a damaged point of a fiber composite component which is formed from at least one fiber ply of a fiber material of a fiber composite substance and a matrix material of the fiber composite substance, in which matrix material the fiber material is embedded, wherein the method comprises the following steps: removing the damaged point from the fiber composite component and producing a repair cavity in the fiber composite component, introducing at least one reparative fiber ply of a fiber material into the repair cavity produced in the fiber composite component, and curing the matrix material, in which the fiber material of the reparative fiber ply is embedded, after introducing the reparative fiber ply into the repair cavity of the fiber composite component, wherein at least one reparative fiber ply having a ply thickness that is smaller than the ply thickness of the fiber plies of the rest of the fiber composite component is introduced into the repair cavity.

Abstract: The invention relates to a method for repairing an aircraft component (10) of fiber reinforced plastic, with the steps of: cutting out a damage site (12) by creating a hole (14), which (i) has a first extent (A1) in a first direction and (ii) has a second extent (A2), which is greater than the first extent (A1), in a second direction, extending transversely in relation to the first direction, and (iii) has a scarfed rim (16), guiding through the hole (14) an inner patch (36), which is formed so as to cover the hole (14) completely from an inner side of the aircraft component (10), closing the hole (14) with a middle patch (26), which has a scarfed rim, the rim of the patch complementing the rim (16) of the hole, and adhesively bonding the patches (26, 36) to the aircraft component (10).