Accident Overview
On June 8, 2011, at approximately 0815 central daylight time, a Bellanca 17-30A airplane, registration N93650, lost engine power shortly after departing from Thompson Field Airport (1TA7) in Canton, Texas. The private pilot, who was the sole occupant, received only minor injuries. The airplane was substantially damaged. The aircraft was registered to and operated by a private individual under 14 Code of Federal Regulations Part 91 as a personal flight. Visual meteorological conditions prevailed, and the flight operated without a flight plan. The flight was originating at the time of the accident.
Pilot Report
The pilot reported performing a normal preflight and run-up before departure. During climb-out, the fuel pressure dropped to zero. He switched to the right fuel tank and turned on the boost pump, but fuel pressure did not return. He then turned the airplane back toward the airport and prepared for an engine-out forced landing.
Post-Accident Examination
The responding Federal Aviation Administration (FAA) inspector found fuel present in the airplane’s fuel tanks. The inspector noted that the airplane was heavily damaged during the forced landing, including separation of the right wing from the fuselage.
The wreckage was recovered and examined at a salvage yard. The engine-driven fuel pump was removed; no abnormalities were noted with the pump or its drive coupling, which was intact. The examination found that the rod end connecting the throttle control to the engine’s fuel control was disconnected. The rod end and bolt (AN3) were sent to the NTSB Materials Laboratory for further examination.
Laboratory Findings
The NTSB Materials Laboratory determined that the bolt’s threads were damaged in at least three different patterns. The bolt threads were heavily flattened and deformed for the entire threaded length. Extraneous metal shavings were found in the thread roots, between several wave-deformed threads. The corresponding nut for the AN bolt was not located. No other abnormalities were found with the airplane.
Conclusion
The investigation did not determine a probable cause for the loss of engine power. The disconnected throttle control rod end and damaged bolt hardware were documented, but no causal link was established.