I am working on an airplane design that is, for the most part, standard aluminum construction. The general description is a 2 seat tandem configuration with a rear mounted 220 HP 4 cylinder engine and CS prop. The airplane will have a GW of 1800 lbs and planned cruise speed of 200 kts plus. The wing mounted booms are located 4' from center line and extend rearward about 8'. The horizontal tail will have an 8' span and 2' chord'. 2 vertical tails will be mounted behind each boom. Because the booms taper and have a complex form, I have decided it would be best to construct them from composite materials. My first estimate of the bending force required would be about 1000 lbs per boom at maneuvering speed ( 6G airplane ). Looking for help with the overall design, especially the attachment points to the aluminum tail and wing structure. Any help would be greatly appreciated. Mike