NTSB Identification: ERA09LA269
14 CFR Part 91: General Aviation
Accident occurred Tuesday, April 21, 2009 in Frederick, MD
Probable Cause Approval Date: 07/22/2010
Aircraft: CESSNA 208, registration: N208JW
Injuries: 1 Uninjured.
NTSB investigators may not have traveled in support of this investigation and used data provided by various sources to prepare this aircraft accident report.
During the landing roll, with the power lever at idle, the pilot heard a “pop,” followed by indications of the engine “spooling down.” He exited the runway and observed smoke coming from the engine compartment. Thinking this was residual fuel, he “spooled the engine.” Realizing there was a fire, he called for assistance and shut off the fuel selectors and firewall shutoff valve. After the accident, a FAA inspector examined the airplane and reported extensive thermal damage to the fuselage sub-frame and evidence of an engine fire. Numerous engine turbine blades were found on the pavement adjacent to where the fire occurred. A disassembly and inspection of the engine revealed that one or more of the compressor turbine (CT) blades failed. The engine was overhauled about 6 hours prior to the accident. The CT blades were manufactured under the FAA Parts Manufacture Approval (PMA) program. Extreme heat damage obliterated the fracture surfaces of the blades, therefore the reason for the blade failure(s) could not be determined. A functional test of the fuel control unit (FCU) revealed the Sg (specific gravity) dome, high idle stop screw, and minimum flow stop were set above the recommended range, which would result in higher than normal fuel flow. The FCU adjustments appeared to be made after the overhaul, however it could not be determined when the adjustments occurred. Although the higher than normal fuel flow setting probably did not result in the CT blade failures, it could have exacerbated the thermal damage and fire.
The National Transportation Safety Board determines the probable cause(s) of this accident to be: A loss of engine power due to the failure of one or more compressor turbine blades for an undetermined reason. Full narrative available
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