A breakage phenomenon of a M6×30 35CrMnSiA fastening screw is found in the process of repair at a certain type of an aircraft. This case affecting the use safety of the aircraft, the chemical composition, macro and micro fracture, microstructure and mechanical properties of the broken fastening screw are verified and analyzed. The fracture form of the screw is confirmed as fatigue fracture, and there are no metallurgical defects, heat treatment defects and processing defects. The main reasons for the crack are preliminarily inferred by the machining mode of the screw. Subsequently, the fatigue performance of screws with the same material formed by screw rolling is verified. The same batch of materials as the broken fastening screws and the same processing technology except screw rolling are selected to conduct a comparative analysis of pull pull fatigue test for the reproduced fastening screws. Three parallel samples are selected for each processing method, and the test method is GJB 715.30A—2002 \[Fastener Test Method for Tensile Fatigue\]. The test results showed that The fatigue life of the rolling screw reaches 500,000 times without any damage, while the thread fracture occurs when the fatigue life of the machining thread is 50 200 times, and the fracture is similar to the fracture of the fastening screw in service. The fatigue performance of the screw formed by rolling wire is much better than that of the screw made by thread turning. In order to eliminate the follow up risks, the paper suggests to improve the screw forming process and stop using this batch of screws. The research results provide a basis for the optimization of screw and the improvement of technological method, and are of great significance for the improvement of aircraft safety.