While on final approach for landing on Runway 32 at CNC4, the aircraft rapidly pitched down from approximately 500 feet and crashed into a wooded area 1 nautical mile from the runway. The aircraft was destroyed and the pilot, who was the sole occupant, was fatally injured.
A structural inspection of the aircraft's tail section revealed inconsistencies between the actual assembly and the applicable drawing set. Inconsistencies with acceptable methods, techniques, and practices for inspection, repair or alteration, as outlined in Federal Aviation Administration Advisory Circulars 43.13 1B and 2B, were also identified. The complete tail assembly was sent to the TSB Laboratory in Ottawa for further analysis.
As per the drawing (Figure 1), the horizontal stabilizer forward structural attachment is designed to be constructed by riveting two aluminium angles (attachment bracket 6-T-2-1 and attachment doubler 6-T-2-2) with three rivets back-to-back and connecting the attachment bracket to the front surface of the forward spar (6-T-1-3) with five rivets.
In the actual installation, the three rivets connecting each attachment bracket to the associated attachment doubler were missing and the required holes were not drilled. Four additional holes were drilled through the left attachment bracket and continued through the forward spar. Rivets were installed in all or these additional holes; however, they were only installed in one or the five holes specified in the drawing.