Efficient, cost‐effective repairs to cracks or corrosion in metallic airframe structures can be made using fiber composite patches—such as carbon/epoxy or boron/epoxy, adhesively bonded to the defective region. A brief overview of this technology is provided in this article, addressing most significant issues including design, choice of materials, repair implementation, and, for repairs to primary structure, certification. Two application case histories are briefly described: (i) to the wing skin of a USAF F16 and (ii) to the wing skin of an RAAF F‐111.

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