A hybrid electric propulsion system for an aerial vehicle, the hybrid electric propulsion system comprising: an engine; a first propulsion assembly mechanically coupled with the engine and configured to produce thrust when driven by the engine; an electrical system comprising a first electric machine mechanically coupled with the engine and configured to generate electrical power when driven by the engine, and one or more power consuming loads electrically coupled with the first electric machine and configured to receive electrical power from the first electric machine, the one or more power consuming loads comprising a second electric machine; a second propulsion assembly mechanically coupled with the second electric machine and configured to produce thrust when driven by the second electric machine; one or more sensing devices positionable onboard the aerial vehicle for detecting one or more performance indicators indicative of an electrical load on the engine; a fuel control device configured to selectively control a fuel flow to the engine; one or more controllers communicatively coupled with the one or more sensing devices and communicatively coupled with the fuel control device, the one or more controllers configured to: receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine, based at least in part on the one or more performance indicators, an occurrence of an electrical load change indicating a thrust asymmetry, the electrical load change comprising a load decrease on the engine; and generate, responsive to the occurrence of the electrical load change being a load decrease on the engine, a control action comprising (i) activating the fuel control device to reduce the fuel flow to the engine and (ii) decreasing an efficiency of the first and/or second electric machine; wherein the control action to decrease the efficiency of the first and/or second electric machine is performed for a transient time period sufficient for the engine to reduce its torque output to match the torque load of the electrical system on the engine. an engine; a first propulsion assembly mechanically coupled with the engine and configured to produce thrust when driven by the engine; an electrical system comprising a first electric machine mechanically coupled with the engine and configured to generate electrical power when driven by the engine, and one or more power consuming loads electrically coupled with the first electric machine and configured to receive electrical power from the first electric machine, the one or more power consuming loads comprising a second electric machine; a second propulsion assembly mechanically coupled with the second electric machine and configured to produce thrust when driven by the second electric machine; one or more sensing devices positionable onboard the aerial vehicle for detecting one or more performance indicators indicative of an electrical load on the engine; a fuel control device configured to selectively control a fuel flow to the engine; one or more controllers communicatively coupled with the one or more sensing devices and communicatively coupled with the fuel control device, the one or more controllers configured to: receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine, based at least in part on the one or more performance indicators, an occurrence of an electrical load change indicating a thrust asymmetry, the electrical load change comprising a load decrease on the engine; and generate, responsive to the occurrence of the electrical load change being a load decrease on the engine, a control action comprising (i) activating the fuel control device to reduce the fuel flow to the engine and (ii) decreasing an efficiency of the first and/or second electric machine; wherein the control action to decrease the efficiency of the first and/or second electric machine is performed for a transient time period sufficient for the engine to reduce its torque output to match the torque load of the electrical system on the engine. receive, from the one or more sensing devices, the one or more performance indicators indicative of the electrical load on the engine; determine, based at least in part on the one or more performance indicators, an occurrence of an electrical load change indicating a thrust asymmetry, the electrical load change comprising a load decrease on the engine; and generate, responsive to the occurrence of the electrical load change being a load decrease on the engine, a control action comprising (i) activating the fuel control device to reduce the fuel flow to the engine and (ii) decreasing an efficiency of the first and/or second electric machine; wherein the control action to decrease the efficiency of the first and/or second electric machine is performed for a transient time period sufficient for the engine to reduce its torque output to match the torque load of the electrical system on the engine.