The object of this report is to compare the load factors for wing design obtained from the French S. T. Ae. formula with those obtained by the United States Air Service, and to study the theoretical basis of the French formula in order to determine whether or not the French formula or one of its type should be adopted by the Air Service. The load factors computed from the S. T. Ae. formula agree fairly well in most specific cases with those used by the Air Service. Where there is much difference between the French and American values, it is considered that the American values are the more reasonable.