Display Apparatus And Method For Monitoring The Structural Integrity Of A Repair Location

A method for monitoring the structural integrity of a repair location, wherein the repair has been carried out on a laminate structure produced from a composite material, wherein the laminate structure is part of an aircraft outer skin, wherein the laminate structure is subjected to loads during a flight of the aircraft, wherein the method comprises:

• (a) applying an adhesive film to a repair location of a base structure of composite material, wherein the adhesive film extends on an outermost layer of composite material of the base structure at least partially beyond the repair location into a region of extent;
• (b) gluing a repair patch to the adhesive film at the repair location;
• (c) curing the adhesive joint;
• and
• (d) applying an indication device having an indicator strip to the region of extent, wherein the indicator strip is configured to indicate a predefined residual strength of the adhesive joint of the repair patch to the surrounding composite material.