A hybrid electric engine control module configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the hybrid electric engine control module being configured to receive a torque command and split output power between the electric motor system and the heat engine system, characterised in that: the hybrid electric engine control module further comprises a torque splitting module configured to: receive a total torque value; determine a torque split of the total torque value between the electric motor system and the heat engine system; and control the electric motor system and the heat engine system to produce the total torque value in accordance with the determined torque split; and the hybrid electric engine control module further comprises a total torque module configured to: receive one or more input values including at least a power lever setting; determine the total torque value as a function of the one or more input values; and output the total torque value to the torque splitting module, wherein the total torque module is configured to match or approximate the total torque value to a second total torque of a second aircraft powerplant at a same power lever setting, to balance a total torque against the second total torque of the second aircraft powerplant. the hybrid electric engine control module further comprises a torque splitting module configured to: receive a total torque value; determine a torque split of the total torque value between the electric motor system and the heat engine system; and control the electric motor system and the heat engine system to produce the total torque value in accordance with the determined torque split; and receive a total torque value; determine a torque split of the total torque value between the electric motor system and the heat engine system; and control the electric motor system and the heat engine system to produce the total torque value in accordance with the determined torque split; and the hybrid electric engine control module further comprises a total torque module configured to: receive one or more input values including at least a power lever setting; determine the total torque value as a function of the one or more input values; and output the total torque value to the torque splitting module, wherein the total torque module is configured to match or approximate the total torque value to a second total torque of a second aircraft powerplant at a same power lever setting, to balance a total torque against the second total torque of the second aircraft powerplant. receive one or more input values including at least a power lever setting; determine the total torque value as a function of the one or more input values; and output the total torque value to the torque splitting module, wherein the total torque module is configured to match or approximate the total torque value to a second total torque of a second aircraft powerplant at a same power lever setting, to balance a total torque against the second total torque of the second aircraft powerplant.