<p>In recent years, electric propulsion has gained increasing importance in space applications driven by the growing availability of onboard electrical power in modern spacecraft. Among the various concepts, Hall thrusters stand out for their relatively high specific impulse, thrust capabilities, and scalability, while magnetic shielding significantly enhances their operational lifetime. An alternative variant is the Thruster with Anode Layer (TAL), which not only offers improved durability but also allows for a more compact design compared to conventional Hall thrusters. In addition, the use of alternative propellants, such as Argon, is being explored to reduce operational costs and increase propellant availability. This work focuses on the scaling of TAL Hall thruster operating at approximately 100 W power level. A scaling methodology based on a phenomenological model was applied to derive two candidate design configurations. The approach was assessed through comparison with experimental data from an available TAL thruster performance database. The comparison shows trends consistent with the reported experimental performance parameters. The resulting designs were further compared with existing TAL thrusters operating at similar power levels, providing comparable estimates in terms of efficiency, specific impulse, and geometric compactness. These results support the applicability of the proposed methodology for preliminary design studies of low-power TAL thrusters and provide a reference framework for future experimental validation. The present study represents the first phase of a broader development effort, which also includes the preliminary design of the two thruster configurations supported by magnetic, thermal and mechanical simulations. Within this subsequent phase, specific design features were considered to potentially facilitate operation with Argon.</p>