This paper provides an overview of the system and subsystem configuration of the MPCV European Service Module (ESM) at Preliminary Design Review (PDR) stage as well as its perspectives of utilisation within the global space exploration endeavour. The MPCVESM is a cylindrical module with a diameter of 4500 mm and a total length -main engine excluded -of 2700 mm. It is fitted with four solar array wings with a span of 18.8 m. Its dry mass is 3.5 metric tons and it can carry 8.6 tons of propellant. The main functions of the European Service Module are to bring the structural continuity between the launcher and the crew module, to provide propulsion to the MPCV, to ensure its thermal control as well as electrical power and to store water, oxygen and nitrogen for the mission. The current agreement foresees the development and production by Europe of one flight model, with an option for a second one. This module will be assembled in Europe and delivered to NASA in 2016. It will be used for a flight of the MPCV Orion in December 2017. Nomenclature ACS= Auxiliary Control System ATCS = Active Thermal Control System 2 CM = Crew Module CMA = Crew Module Adapter CSM = Crew and Service Module CSS = Consumable Storage System ESA = European Space Agency ESM = European Service Module HDRS = Hold Down and Release System LAS = Launch Abort System MDPS = Micrometeoroid/Debris Protection Shield MMOD = Micrometeoroid/Orbital Debris MPCV = Multi-Purpose Crew Vehicle OMS-E = Orbital Manoeuvring System Engine PIE = Propulsion Isolation Equipment R&R = Retention & Release RCS = Reaction Control System SA = Spacecraft Adapter SADM = Solar Array Drive Mechanism SAJ = Spacecraft Adapter Jettisoned panels SAW = Splar Array Wings SLS = Space Launch System TVC = Thrust Vector Control