Accident Overview
On June 18, 2008, at 1310 eastern daylight time, an amateur-built Lancair IV-P, registration N441L, impacted terrain adjacent to runway 11 at Lebanon-Springfield Airport (6I2) in Springfield, Kentucky, during an emergency landing. The airplane was substantially damaged in the accident, and the pilot was killed. Visual meteorological conditions prevailed, and no flight plan was filed. The flight was operated under Title 14 Code of Federal Regulations Part 91.
Flight History
The pilot departed Blue Grass Airport (LEX) in Lexington, Kentucky, at 1300. Shortly after departure, he contacted air traffic control to report a loss of engine oil pressure. At 1305, he requested radar vectors to the nearest airport and was informed that Lebanon-Springfield Airport was the closest, located 8 miles at his 12 o'clock position. At 1306, he reported that his windscreen was covered with oil. The controller advised he was 4 miles from the airport, but the pilot stated he did not have visual contact. At 1308, radar and communications contact were lost.
Witness Observations
A witness reported seeing an airplane flying overhead and hearing it backfire. The witness observed smoke coming from underneath the airplane and noted that the engine appeared to be running at full power while continuing to backfire and emit smoke until the aircraft vanished from sight.
Aircraft Information
The Lancair IV-P, serial number LIV-177, was manufactured in 1997. It was a four-seat, low-wing, retractable-gear airplane powered by a Teledyne Continental Motor TSIO-550-B engine producing 350 horsepower, equipped with a three-bladed Hartzell constant-speed propeller. A conditional inspection was completed on February 29, 2008, at an airframe total time of 313 hours. The most recent logbook entry, dated May 6, 2008, recorded a total time of 351.1 hours. The pilot's logbook indicated he flew approximately 18.5 hours since the last recorded inspection.
Wreckage Examination
The wreckage was located at the approach end of runway 11, with a debris line approximately 200 feet long on a magnetic heading of 150 degrees. A postcrash fire consumed the composite airframe. All flight control surfaces were found at the site, and flight control continuity was confirmed. Examination of the airframe and flight control system revealed no evidence of preimpact mechanical malfunction.
Engine Examination
The engine and its accessories were separated from the firewall and airframe. Examination of the propeller and system components showed no preimpact mechanical malfunction. Visual inspection of the engine revealed that the No. 1, 2, and 5 connecting rods were broken, and the No. 2 connecting rod had penetrated the top of the aft section of the engine case. The accessory case included a Supplemental Type Certificate (STC) SE5743NM Aviation Development Corporation (ADC) oil filter adapter. Inspection of the ADC oil filter adapter found the O-ring seal between the mating surfaces extruding 3/4 inch. The O-ring was leaking oil, dry-rotted, and brittle. Review of the ADC STC indicated the installed O-ring was incorrect. The engine and airframe logbooks did not record when the improper O-ring installation occurred.
Medical Information
An autopsy performed on the pilot determined the cause of death as "Generalized Blunt-force Trauma." Forensic toxicology detected no ethanol in the liver or muscle, but quinine was found in the urine.