A structural panel for an aircraft nacelle may comprise a first skin, a second skin, and a core sandwiched between them. A disbond may be present between the first skin and the core. A plurality of layers of blueprint film adhesive may be positioned over the disbond. The structural panel may be vacuum bagged, and the blueprint film adhesive may be heated. The blueprint film adhesive may flow through perforations in the first skin and bond the first skin to the core.