Nowadays in the aeronautic field, the majority of civil aircraft are equipped with many electro-hydraulic actuation systems (EHSA) for primary flight controls. The only exceptions are the Airbus A380 and A350, which use an electro-hydrostatic actuation system but only as a backup in case of failure of the electro-hydraulic actuator. The purpose of this thesis work is to identify an alternative system for primary flight controls for the reference regional aircraft, within the wider framework of more-electric configuration. In particular, this work is aimed at integrating the models created within the Leonardo Labs Digital Flight Lab platform for aircraft-level architectural simulation of the interaction between the various on-board systems.