Flight guidance is the core functionality of civil aircraft automatic flight system, which is of great significance to ensure flight safety in complex situations, improve trajectory tracking accuracy, and reduce the pilot’s operational burden. In this paper, the flight guidance laws are designed, including configuration design and parameters design. Subsequently, the flight guidance modes are simply divided into lateral guidance modes and vertical guidance modes, and the scheduling logic between different guidance modes is given. Furthermore, to suppress the adverse transient mutations caused by flight guidance modes switching, synchronous tracking fader is introduced, and the linear attenuation fader and the exponential attenuation fader are designed. Finally, some simulations are operated to illustrate the validity and feasibility.