he paper presents a fairly extensive review of the procedures and recommendations for checking the damaged repair area of various composite structures (such as sandwich or honeycomb structures) of airframe elements in military and civil airplanes (especially Boeing and Airbus airplanes and sailplanes). The presented requirements for the inspection and assessment of damage (e.g. delamination in layers or in the honeycomb, internal delamination in the laminate, and damaged fibers) should not exceed the permissible damage limits (PDL). The repair requirements (to ensure the continuing airworthiness of the structure) are largely dependent on the classification of the structure under consideration. In these analyses, a fairly important function is performed by non-destructive methods (such as ultrasonic bond testing or using eddy currents), thus assessing the degree of damage and the ongoing maintenance process.