The use of a hybrid electric propulsion system for aircraft offers the potential to increase aircraft efficiency, reduce fuel consumption and thus reduce emissions. Design concepts, emission analysis and aircraft performance are being studied extensively. However, how future hybrid electric propulsion systems will change the maintenance, repair and overhaul (MRO) of an aircraft is also an important consideration. This paper examines the effects of hybridisation on a parallel hybrid electric propulsion system of a medium-range aircraft, the Airbus A320, powered by an IAE V2500 engine. The electric motor is powered by a battery and is used to assist the turbofan engine, mainly during the takeoff phase. The additional system components of the chosen hybrid electric propulsion system and their corresponding damage mechanisms are addressed from a maintenance point of view. Challenges for future maintenance are discussed and possible failure modes and failure possibilities are analysed. For this purpose, a Failure Mode and Effects Analysis and a Fault Tree Analysis will be carried out. The results of this analysis can be used to determine how the additional components need to be designed to maintain the overall safety of the propulsion system at the current level. This will also provide needs and ideas for a future design for maintenance
