Aircraft engine control is a crucial component for the safe and stable operation of gas turbine engines which are complex nonlinear systems. As engines have evolved to higher capabilities it is crucial to update the control strategy to ensure maximum functionality of the engine. Current industrial baseline controllers are based in the Proportional-Integral-Derivative (PID) control scheme along with individual limit controllers having critically damped responses housed in the min-max architecture. In light of the distributed engine control architecture that exploits digital electronics and hence higher on-board computational capabilities, the baseline controller is replaced by a Model Predictive Control (MPC) law with on-line optimization. MPC is a model based control technique that can handle complex constrained dynamics thus allowing the incorporation of component faults in the design process of the controller. Component faults occur during an engine's operation mainly due to fan blade-shroud rubbing, structural wear and tear and foreign object ingestion thus affecting the engine performance. Simulations on the Linear Time Invariant (LTI) as well as the nonlinear turbofan engine of the Commercial Modular Aero-Propulsion System Simulation (C-MAPSS40k) tool are carried out. In the presence of a component fault, active fault tolerant control using the multi-model MPC approach is applied by switching between the MPC blocks, each using its respective LTI reference model.The control of both