There is provided a method for repairing a member comprising a fiber-reinforced plastic, which method can repair a through hole easily at a low cost. When a through hole 20 is repaired, a temporary hole 11 is formed, a fabric sheet 30 comprising reinforcing fibers is rolled into a cylindrical shape and inserted into the temporary hole 11, the fabric sheet 30 is impregnated with a resin, the resin is cured, and a new through hole 20 is formed.

A method for repairing an element of composite material, the method comprising, upon detection of an internal damaged area within the element of composite material, infusing a resin into the internal damaged area of the element of composite material, wherein the method further comprises: drilling on the element of composite material at least one first non-through hole and at least one second non-through hole, each of the non-through holes running from one face of the element of composite material up to the internal damaged area, and; applying vacuum at the at least one second non-through hole and infusing the resin from the at least one first non-through hole until the resin fills at least the internal damaged area of the element of composite material.

The disclosed embodiments relate to a method for repairing a damage to a thermoplastic composite element, in particular an aircraft component, wherein a socket is milled at the site of damage to the thermoplastic composite element. Then, in the socket a patch is formed from a thermosetting material containing a reinforcing phase of fabric layers and a matrix of thermosetting resin, the patch having a shape and size corresponding to the socket geometry. In the next step, the patch is cured, and finally the cured patch is glued into the socket by means of an adhesive.