MIA05LA021 · J.D. Calhoun, Inc. Vans ACFT RV6A

The pilot-rated passenger stated that before takeoff of the accident flight, her husband inspected the nose strut and wheel due to roughness at touchdown on 3 separate landings immediately before the accident flight; no discrepancies were reported. The flight deparated and remained in the traffic pattern where her husband performed a go-around due to a "...roughness and bounce" at touchdown. The flight returned and after touchdown, the airplane nosed over and came to rest inverted. Several witnesses on the airport reported the landing immediately before the accident appeared normal. Examination of the runway revealed a fresh furrow in the grass measuring approximately 100 feet in length associated with the nose landing gear. Propeller slash marks and portions of the nose landing gear fairing were noted along the length of the furrow. Examination of the airplane revealed the nose landing gear was displaced aft; the nose gear leg was bent, and the canopy bubble was shattered. The F-631 frame (inverted "U" shaped structure which is vertically oriented and located immediately aft of the pilot and co-pilot seats) designed to protect the flight crew in the event of a nose-over ground accident, was crushed down. A longitudinally oriented structural member (F-632A channel brace) that provides structural support to the F-631 frame and also to the F-606 bulkhead located aft of the pilot and co-pilot seats, was separated at the F-606 bulkhead (pictures of the separated channel brace are located in the NTSB Docket for this case). Examination of the aft end of the channel brace (F-632A), revealed the edge margin of 2 of the 5 rivet holes was zero, and the edge margin of the remaining 3 rivet holes was estimated to be less than .050 inch (pictures of the aft end of the channel brace showing the rivet hole edge margin are located in the NTSB Docket for this case). By design, the edge margin should be no less than .1875 inch, or 3/16 inch. The 5 holes in the horizontal portion of F-632B angle which secure the longitudinally oriented channel brace to the vertically oriented F-606 bulkhead, were in close proximity to the bend radius. By design, the 5 holes in the F-632B angle are to be located approximately 5/8 inch aft of the forward edge or 3/8 inch forward of the aft faying surface. Reportedly, during construction of the airplane, the pilot contacted the designer and spoke with an individual about the longitudinally oriented channel brace (F-632A), the angle (F-632B), and the channel brace attachment to the F-606 bulkhead. The pilot reportedly completed as instructed the attachment of the longitudinally oriented F-632A channel brace and F-632B angle to the F-606 bulkhead. NTSB examination of the nose gear leg revealed no cracks or fractures; the material met the hardness specified by the airplane designer. The engine installed at the time of the accident was the make and horsepower engine specified in the airplane builders manual. At the time of the accident, the airplane weight and center of gravity were within limits.

Verbatim NTSB analysis and probable cause from the NTSB dataset