A method for operating a hybrid electric aircraft propulsion system , the method comprising: providing a first electric propulsor and a second electric propulsor with a first source of propulsion power from a generator configured for generating an output of alternating current (AC) electric power; providing the first electric propulsor and the second electric propulsor with a second source of propulsion power from at least one motor inverter (208A,208B;308) operatively coupled to a direct current (DC) power source , the at least one motor inverter (208A,208B;308) configured to convert the DC electric power from the DC power source into a second source of AC electric power; and modulating the second source of AC electric power applied to the first electric propulsor or the second electric propulsor from the at least one motor inverter (208A,208B;308) to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of the generator , characterised by : providing the first source of propulsion power to the first electric propulsor from the generator via a first motor stator of a first electric motor ; providing the first source of propulsion power to the second electric propulsor from the generator via a first motor stator of a second electric motor ; providing the second source of propulsion power to the first electric propulsor from the at least one motor inverter (208A,208B;308) via a second motor stator of the first electric motor ; and providing the second source of propulsion power to the second electric propulsor from the at least one motor inverter (208A,208B;308) via a second motor stator of the second electric motor , such that the first source of propulsion power from the generator is independent of the second source of propulsion power from the at least one motor inverter (208A,208B;308). providing a first electric propulsor and a second electric propulsor with a first source of propulsion power from a generator configured for generating an output of alternating current (AC) electric power; providing the first electric propulsor and the second electric propulsor with a second source of propulsion power from at least one motor inverter (208A,208B;308) operatively coupled to a direct current (DC) power source , the at least one motor inverter (208A,208B;308) configured to convert the DC electric power from the DC power source into a second source of AC electric power; and modulating the second source of AC electric power applied to the first electric propulsor or the second electric propulsor from the at least one motor inverter (208A,208B;308) to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of the generator , providing the first source of propulsion power to the first electric propulsor from the generator via a first motor stator of a first electric motor ; providing the first source of propulsion power to the second electric propulsor from the generator via a first motor stator of a second electric motor ; providing the second source of propulsion power to the first electric propulsor from the at least one motor inverter (208A,208B;308) via a second motor stator of the first electric motor ; and providing the second source of propulsion power to the second electric propulsor from the at least one motor inverter (208A,208B;308) via a second motor stator of the second electric motor , such that the first source of propulsion power from the generator is independent of the second source of propulsion power from the at least one motor inverter (208A,208B;308). <EOS>