Composite material is a material made from two or more constituent materials with different physical and mechanical properties that, when merged, interact to give the new material its own unique set of properties. The advantages of composite materials are many; including lighter weight; high strength; corrosion resistance and the ability to tailor lay-ups. Because of specific properties they can offer, the use of high performance composites is increasing, especially in the construction of aircraft structures. To be competitive the aircraft structure must be light enough, because any increase of weight leads to a increase of fuel consumption and reduction of payload. In order to meet the targets, new generation large aircraft are designed with all composite fuselage and wing structures. The properties of the large composite structure in the aeronautical constructions has improved and will certainly keep on improving over the time. With the increasing use of composite materials in aircraft structures it is important to identify the typical types of damage and how they affect composites. A structural damage found on an in-service aircraft must be corrected through the application of an appropriate maintenance program that will restore the part to an airworthy condition. The repair of these advanced composite materials requires an in-depth knowledge of composite structures, materials, and tooling. A brief review of some of the fundamentals of composite materials and the application in aircraft construction, is included as theoretical part of this thesis. Experimental part aims to give a general approach to bonding repair in aircraft structure. Adhesive bonding is a modern method for joining parts and is applied for connecting different types of structure in aircraft maintenance. Bonded repair procedure is summerized throught six-step bonded repair procedure on the sample of honeycomb floor panel, according to the Aircraft Structural Repair Manual (SRM).