The results of the integration of the TOI-2458 system for the best-fitting initial condition with the orbital eccentricity and nodal longitude of the outer orbit marked with “1”, “2” and “3” in Fig. A.2. The time evolution of selected orbital elements for the Newtonian force is shown in blue, and the Newtonian and GR models are shown in orange, respectively. The integrations were performed with the variable-step, high-accuracy IAS15 integrator.