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This paper presents an analysis approach to investigate wing leading edge static charge dissipation caused by frictional electrification. The static charge is normally dissipated through the anti-static coating layer beneath the topcoat to the aircraft structure, and subsequently is dissipated into the air via the static discharge system on the trailing edge. Composite leading edges that have non-conductive coating materials pose a unique static charge dissipation design problem. When the induced static charge exceeds the dielectric strength of the nonconductive coating, discharge to the structure can damage the coatings. This paper describes the anti-static system design analysis performed to develop a system design solution.