Accident Details
On August 19, 2010, at approximately 1408 Alaska daylight time, a Cessna U206G airplane, registration N9815M, sustained substantial damage during an off-airport emergency landing about 18 miles east of Homer, Alaska. The aircraft was operated by Homer Air Inc., Homer, as a visual flight rules (VFR) sightseeing flight under 14 Code of Federal Regulations Part 135. Visual meteorological conditions prevailed, and VFR company flight following procedures were in effect. The flight departed Homer around 1050.
Pilot Report
According to a written statement from the pilot dated August 23, the airplane experienced a sudden and complete loss of power while at an altitude of 5,000 feet msl about 18 miles east of Homer. He reported switching fuel tanks and activating the fuel boost pump, but the windmilling engine did not restart. During the emergency landing on the Grewink Glacier, the airplane encountered a crevasse and nosed over. After exiting, the pilot observed fuel leaking from both wing-top fuel caps and the engine cowl. The airplane sustained substantial damage to the wings and vertical stabilizer.
Post-Accident Examination
An FAA inspector who was present during the airplane's recovery told the NTSB investigator-in-charge (IIC) that after righting the airplane, he removed about 8 gallons of fuel from each main fuel tank. The fuel appeared clear and free of water and other contaminants. Fuel flow was established from the tanks to the engine.
Fuel System
The airplane was refueled before the flight. Fuel samples from the commercial fuel facility were clear, free of water and sediment, and had the appropriate color and smell. No fuel contamination reports were received by the supplier. The NTSB IIC removed and examined the fuel system; no anomalies were found with the fuel and vent systems, and the fuel tanks and lines were free of contamination.
Engine Test
On November 10, 2010, under the supervision of the NTSB IIC and an engine manufacturer representative, the engine was removed and installed on a test stand. It was successfully run through various power settings without leaks or mechanical anomalies.
Ignition System
The ignition system was examined by the IIC. All wire bundles and connections appeared intact. The ignition switch was bench tested and found to function properly, with no anomalies.
Conclusion
No evidence of preimpact mechanical abnormalities was discovered during any of the postaccident examinations. A review of the engine and airframe logbooks by the IIC and FAA disclosed no mechanical anomalies.