Patent ID: 8413485

Claim:
A method for detecting a defective sandwich component in aircraft construction, wherein the method comprises the following steps: forming at least one measuring chamber in a core arrangement of a sandwich component, wherein the sandwich component comprises two cover layers and the core arrangement comprising a core, wherein the at least one measuring chamber having a closed end and another outwardly open end; connecting a detection device with the open end of the measuring chamber; subjecting the at least one measuring chamber with a predetermined pressure by means of the detection device; and detecting and evaluating the pressure which forms in the at least one measuring chamber by means of the detection device, a passage of the at least one measuring chamber within a damaged area in the core of the sandwich component being detected if the predetermined pressure does not form in the at least one measuring chamber; or a passage of the at least one measuring chamber within an intact region of the core of the sandwich component being detected if the predetermined pressure forms in the at least one measuring chamber.