A vibroacoustic experiment is planned to be performed on a stand-alone wing of an Airbus A320. During the experiment the operational vibrations of the wing, usually induced by engine vibration loads, will be replicated to investigate the transmission of vibrations throughout the wing. As there is no engine available to introduce these vibrational loads, a previously developed multiaxial shaker system, able to reproduce engine loads in the pylon-wing interface along and about multiple axes simultaneously, will be utilized for structural excitation. However, there are no measured spectra of loads in pylon-wing interfaces available and respective measurements which could identify these loads are currently not realizable.As a consequence, an attempt is made to develop an jet engine vibration model from minimal input data that allows the estimation of interface loads. The approach combines the estimation of worst-case bearing forces in the engine by using design phase data, in-flight data to identify engine properties related to specific flight-conditions, a simple substitute model of an engine and further data from unrelated projects. The future goal of this project is to update a FEM model of the wing to investigate the impact of varying engine locations along it on the resulting cabin noise
