Abstract: A method, in which a damaged site of a composite material structure, for example a wing skin on an aircraft, is repaired, includes the steps of repairing the damaged site with repair material, including adhesive, and at the same time bonding a test fixture, for example a button, at a test site next to the repair, by means of material that is the same as the repair material. The conditions to which the damaged site and the test site are subjected are substantially the same. After repair, the strength of the repair bond may be indirectly assessed by applying a torque to the test fixture, so as to assess the bond strength of the test fixture to the structure.

Abstract: A patch of fibre reinforced plastics composite material, a repair kit including such a patch and a method of using such a patch and repair kit are provided. The patch (1) is for attachment to a surface (17) of a fibre reinforced plastics composite structure (11) over an area of damage (10) to the structure. The patch defines an outer surface (3), a bonding surface (4) opposed thereto and a peripheral edge. The patch includes fibre reinforcement and plastics matrix material with the latter being in a final state of hardness. The patch defines a series of small apertures (6) therethrough to allow the passage of gases and other matter through the patch to prevent entrapped air weakening the repair.