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This paper presents the functionality of a new software tool for the preliminary estimation of wing and tail weight, based on a quasi-analytical structural sizing method. The implemented method is based on the weight decomposition of each lifting surface into primary and secondary contributions. The primary weight of both wing and tail empennages is estimated by stationary sizing of the torque box structure, based on tension and compression stress analysis of stiffened panels for the lower and upper surfaces, and shear stress analysis for the spar webs. Aerodynamic loads are calculated by a vortex lattice method for various load cases, as specified by airworthiness regulations. Inertial reliefs on loads due to the mass of the lifting surface structure, fuel and engine are taken into account, as well as the weight penalties due to engine mounting, connections and aeroelastic effects at high speeds.