In conventional aircraft design engine loads are transferred directly from the engine core and fan case to the pylon via engine mounts. Literature is available on the modelling of individual powerplant components but limited work is available on the whole assembled system (engine, pylon and nacelle). The influence of the structural connections between the components on overall system performance has not been investigated. Herein a Finite Element model is described which can be used to assess connection strategies between powerplant components and if such arrangements can effectively enhance engine performance by reducing detrimental engine structural deformations (engine carcass bending, rotation, ovalization). The method is demonstrated for a generic high bypass ratio engine design, focusing on connections between the engine and thrust reverser unit. The method identifies a modified attachment scheme between the engine rear turbine casing and the inner barrel of the thrust reverser unit, which reduces engine deformations across multiple loading scenarios. Maximum reductions of 97% and 96% have been observed in carcass bending and ovalization respectively.