Accident Overview
On an unspecified date, a Cessna T210F (serial number 21082298), operated as a private flight, departed from Oscar Machado Zuloaga International Airport in Charallave, Miranda State, with a local visual flight plan. The aircraft had two persons on board (pilot and passenger) and carried fuel for four hours, with one hour planned en route. During the final approach to Metropolitan Airport in Ocumare del Tuy, Miranda State, the engine lost power, and the aircraft descended into the runway 08 safety area.
Aircraft and Engine Details
The single-engine land aircraft, manufactured by Cessna Aircraft Co., model T210F, was equipped with a retractable tricycle landing gear. The engine was a Continental Model TSIO-520-C, rated at 310 hp. The aircraft had valid registration, airworthiness, and radio station certificates issued by the Venezuelan Civil Aeronautics Authority (INAC). Its insurance was current at the time of the event.
The aircraft's last scheduled preventive maintenance was performed by OMAC No. 641 Wing Air Company 2000, C.A., located at Metropolitan Airport.
Pilot Information
The 35-year-old pilot held a valid medical certificate, aeronautical license, and ratings for instrument flight, single-engine land (C150, C172, C182, C206, C210), multi-engine land (DA42, BE58), BE20 second-in-command, and C208 captain.
Weather Conditions
Meteorological conditions at the time were calm winds (0 KT), unlimited visibility, and generally good weather throughout the day.
Investigation Activities
The investigation committee, from the Civil Aviation Accident and Incident Investigation Board (JIAAC), conducted the following:
- Notified of the event.
- Requested maintenance records.
- Reviewed crew documents (identity card, license, medical certificate, flight log).
- Requested operator documents (registration, airworthiness, maintenance compliance, noise certification).
- Transferred to the impact site: the runway 08 threshold safety area. Photographs documented the impact trail: initial contact with a tree outside the airport, second contact with a mound where the left wingtip fuel tank detached, third contact where the propeller assembly struck the taxiway edge and entangled with the safety area fence, and final resting position in the runway 08 safety area.
Technical Inspection Findings
Inspection of the engine revealed spark at the spark plugs and cylinder compression; however, a test bench run was deemed necessary to fully evaluate functionality. Fuel system inspection found no modifications to the tank system, but the auxiliary fuel pump was inoperative. The electric pump (part number 18000B) was bench-tested and showed erratic, intermittent operational behavior, falling outside established safety parameters. Although the manufacturer's manual specified a service life limit of 1,500 hours, the unit had accumulated 1,319.3 hours, remaining within its legal operating time.
Probable Cause
Based on the evidence, the primary causal factor was determined to be a functional degradation of the electric auxiliary fuel pump. This mechanical failure limited the constant fuel supply, compromising the aircraft's thrust generation and leading to a sustained loss of power.
The investigation was closed by the General Directorate of the Administrative Office for Transportation Safety.