Accident Sequence
On October 16, 2018, at 2210 central daylight time, a Cessna 182P (registration N9398G) sustained substantial damage after colliding with trees during a forced landing in Opelika, Alabama. The forced landing followed a loss of engine power about 6 minutes after departure from Auburn University Regional Airport (AUO) in Auburn, Alabama. The pilot was seriously injured, and two passengers were not injured. Night visual meteorological conditions prevailed, and no flight plan was filed. The flight was conducted under 14 CFR Part 91 as a personal flight.
The pilot reported that during climb after takeoff, he noticed a drop in engine oil pressure. He reversed course to return to AUO. Almost immediately, the engine ran roughly, lost power, sparks "flew" from beneath the cowling, and the engine stopped producing power. While maneuvering at low altitude and low airspeed, the pilot rejected one roadway as a landing site, maneuvered toward a four-lane divided highway, and selected the grass area adjacent to an exit ramp for the forced landing. After touchdown, the airplane slid backward down a grade, struck trees, and came to rest upright. The occupants exited without assistance.
Aircraft and Pilot Information
The pilot held a commercial pilot certificate with ratings for airplane single-engine land, multiengine land, and instrument airplane. His FAA second-class medical certificate was issued December 12, 2017, and he reported 13,422 total hours of flight experience at that time.
According to FAA records, the airplane was manufactured in 1971 and had accrued 5,398.9 total aircraft hours. Its most recent annual inspection was completed June 4, 2018, at 5,338.8 total aircraft hours. The engine had accrued 400.3 hours since its last overhaul, which was completed April 22, 2013. The three most recent annual inspections were performed by the same mechanic.
Weather and Environment
At 2146, weather recorded at AUO included scattered clouds at 700 feet, wind from 020° at 5 knots, temperature 22°C, dew point 21°C, and altimeter setting 30.17 inches of mercury.
Damage and Engine Examination
The airplane's wings, fuselage, and empennage all sustained substantial impact damage. Holes were observed in the top of both engine crankcase halves on either side of the fuel manifold. A fractured connecting rod was visible outside the engine case, wedged between the No. 1 and No. 3 cylinders.
Examination of the engine revealed that the No. 2 and No. 4 connecting rods were separated from their respective rod journals. All rod journals were absent of lubrication and displayed heat damage. Disassembly of the engine and separation of the case halves showed abnormal wear and damage consistent with a loss of lubrication. Examination and testing of engine accessories revealed no anomalies that would have prevented normal operation.
The engine was equipped with a spin-on oil filter adaptor (STC SE09356SC). Installation instructions directed threading the oil transfer cylinder into the oil screen housing, torqued to 65 ft-lbs. The adaptor on the accident engine was found loose and could be easily rotated by hand through a 90° arc. Oil was observed on the rear of the engine in the area surrounding the oil filter adaptor attachment point.
Maintenance instructions for the adaptor prescribed inspection for oil seepage, security and integrity of safety wire, and "integrity of fit" at each annual or 100-hour inspection.