Cessna 208 N208JW

Summary

On 21 April 2009 at about 17:55 local time, a Cessna 208 registered N208JW, operated by Greystoke Engineering Inc, was involved in an accident near Frederick, Maryland, United States. One person was on board and nobody was injured. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

21 April 2009 at 17:55

Classification

Accident

Location

Frederick, Maryland, United States

Nearest airport

Frederick Municipal (FDK)

Coordinates

39.4175, -77.3744

Aircraft

Cessna 208

Registration

N208JW

Category

Airplane

Engines

1

Operator

Greystoke Engineering Inc

Operating rule

Part 91: General Aviation

Purpose of flight

Ferry

Phase of flight

Not recorded

Route

Winchester → Frederick

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

ERA09LA269

Nobody was injured.

A loss of engine power due to the failure of one or more compressor turbine blades for an undetermined reason.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

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.

Quoted verbatim from the NTSB record.