The accommodation of Electric Propulsion and the associated Power Processing Units within a Spacecraft must lead to an integrated system providing full function and performance. This process starts with a proper specification of the electrical interface between thrusters and electronics, the handling of high voltages in a distributed harness, the insurance of redundancies, the coverage of complex EMC aspects, and the avoidance of interference of the thrusters with other spacecraft functions. Possible interferences include that of the magnetic field upon the satellite’s attitude control system and that of plasma upon RF communication. Choosing of an adequate grounding concept in early project phases is important to avoid significant impact upon the performance of the spacecraft in flight. Endto-end testing of the propulsion subsystem is limited, as it is not possible to run the thruster together with the spacecraft in a vacuum facility.