At present, there appear to be two schools of thought in the airplane structural field, at least in this country; the first of which believes more aerodynamic data have been accumulated and are available than have ever been efficiently utilized by the structural engineer; the second of which believes there is little or no really exact knowledge of either the magnitudes or distribution of the loads on an airplane; and which feels that to introduce excessive requirements of analysis as has been frequently been recommended by the first group, will be futile. The authors of the present report belong to the latter school. The fact that the same ancient chart for relative distribution of load on the wings of a biplane is still in use by the military services indicates that the aerodynamics experts have themselves made scant use of this knowledge. It appears that there is a real need for further pressure distribution work, to determine both total loads, and distribution of these total loads to the component parts of the structure. The present report will deal, therefore, both with the consideration of total loads, and the distribution of these loads over the structure of the airplane.