Seriously hope there's no thoughts of flying the 10...PFI constructed a production configuration left side fuselage tail boom, complete with vertical and horizontal tail components. The unit was built to the same configuration as the accident aircraft components. This assembly was then mounted on a test fixture, with strain gages installed on the vertical stabilizer spars. The vertical tail was then loaded to failure. The failure mode and separation point was the same as that seen on the accident aircraft left vertical tail assembly. The test revealed that the vertical stabilizer spars began to yield at 40 percent of the failure load limit supplied by BJC (see AIRCRAFT INFORMATION section). Spar failure occurred at 65 percent of the BJC supplied load limit.