The flight control system serves as the key airborne system for electric vertical takeoff and landing (eVTOL) aircraft, necessitating safety standards akin to those applied to civil aircraft. This study introduces redundancy design technology for the flight control computer, sensor and actuator in eVTOL aircraft flight control systems. It proceeds to design an architecture adhering to safety requirements in accordance with airworthiness regulations. The rotor configuration of eVTOL aircraft is considered, and typical functional hazards are analyzed. Safety analysis is carried out using fault tree analysis technology. The results show that the flight control system architecture designed in this study can effectively address the typical functional hazards, meeting the stipulated failure probability requirements.