SEA05LA049

The pilot reported that shortly after takeoff, while in a climb configuration, the airplane's engine began to lose manifold pressure and engine RPM. Concurrent with the loss of engine power, the pilot noted a loss of oil pressure and elected to land the airplane, off-airport, in a wooded area. Post accident examination of the engine revealed that the distal end of the number 5 piston pin was fractured. Further examination revealed that the inner aluminum piston pin insert fractured-off just inboard of where the pin begins to taper outward. The fracture face was flat and perpendicular to the outer surface of the steel housing. Both fracture surfaces (inner and outer) sustained extensive smearing type damage and metal loss so significant that an analysis of the fracture surfaces could not be completed. Heavy scoring was noted to the wall of the number five cylinder assembly and piston. Extensive mechanical damage was observed to the relief area of the piston. The bottom piston ring was seized in place. Removal and examination of the oil sump revealed that the sump contained oil, as well as a large amount of metallic type particles. The oil pickup tube and screen was intact and also contained a significant amount of metallic like particles similar to the material found in the oil sump. The amount of metallic particles in the pickup tube and screen was sufficient enough to restrict the oil flow passage. The metallic particles were non-magnetic.

On February 16, 2005, about 1030 Pacific standard time, a Mooney M20K airplane, N1147D, sustained substantial damage following a loss of engine power and subsequent off airport forced landing approximately five miles northwest of Roseburg, Oregon. The airplane is registered to a private party in Umpqua, Oregon, and was being operated by the pilot as an instrument flight rules (IFR) cross-country flight in accordance with Title 14, CFR Part 91. The private pilot and the two passengers aboard the airplane were not injured. Visual meteorological conditions prevailed and an IFR flight plan was activated for the flight that originated from Roseburg approximately 10 minutes prior to the accident. The flight-planned destination for the flight was Lewiston, Idaho.

During a telephone conversation with the National Transportation Safety Board (IIC) on February 16, the pilot reported that shortly after takeoff, while in a climb configuration, the airplane's engine began to lose manifold pressure and engine RPM. Concurrent with the loss of engine power, the pilot noted a loss of oil pressure and elected to land the airplane, off-airport, in a wooded area near Roseburg.

Post accident examination of the engine, by personnel from the National Transportation Safety Board and Teledyne Continental Motors, revealed that the distal end of the number 5 piston pin was fractured. Further examination revealed that the inner aluminum piston pin insert fractured-off just inboard of where the pin begins to taper outward. The fracture face was flat and perpendicular to the outer surface of the steel housing. Both fracture surfaces (inner and outer) sustained extensive smearing type damage and metal loss so significant that an analysis of the fracture surfaces could not be completed.

Heavy scoring was noted to the wall of the number five cylinder assembly and piston. Extensive mechanical damage was observed to the relief area of the piston. The bottom piston ring was seized in place. The connecting rod was intact, however the piston end of the rod was discolored.

Removal and examination of the oil sump revealed that the sump contained oil, as well as a large amount of metallic type particles. The oil pickup tube and screen was intact and also contained a significant amount of metallic like particles similar to the material found in the oil sump. The metallic particles were non-magnetic.

Aircraft records indicated that the airplane was originally type certificated with a Lycoming TSIO-360 engine rated at 210 horsepower. In December 2001, the airplane was modified to accommodate an overhauled Continental TSIO-520-NB (rated at 305 horsepower) utilizing Rocket Engineering Supplemental Type Certificate (STC) SA5691NM.

Maintenance records indicated that the Continental TSIO-520-NB was overhauled prior to the installation. A logbook entry corresponding with the overhaul indicated that the total time of the engine was "unknown" and the time since major overhaul was "0".

The final assembly records for the engine overhaul indicated that "new" Superior piston pins (part number SA630046) were used for the overhaul.

The engine had accrued approximately 370 hours from the time of overhaul to the time of the accident.