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This paper describes research related to producing integrated electric motor driven flight control surface actuation systems, for a More Electric Aircraft. The main requirements and motor options are discussed. The advantage of the matrix converter in terms of compactness, due to removal of energy storage elements, is highlighted. However, this advantage is shown to bring with it problems when motors which have pulsed voltage and current waveforms are employed. The resulting discontinuities in power flow during current commutations are reflected at the input terminals to the drive as supply current harmonics.