Cessna 208B N1241X

Summary

On 12 April 2005 at about 14:50 local time, a Cessna 208B registered N1241X, operated by MN Aviation, was involved in an incident near Roosevelt Roads, United States. 4 people were on board and nobody was injured. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

12 April 2005 at 14:50

Classification

Incident

Location

Roosevelt Roads, United States

Nearest airport

Roosevelt Roads Airport (TJNR)

Coordinates

18.2450, -65.6433

Aircraft

Cessna 208B

Registration

N1241X

Category

Airplane

Engines

1

Operator

MN Aviation

Operating rule

Part 135: Air Taxi & Commuter

Phase of flight

Not recorded

Route

Vieques → San Juan

Aircraft damage

Not recorded

Weather

VMC

Light

Day

NTSB number

SEA05FA074

Nobody was injured.

The fracture of multiple compressor turbine blades while the airplane was in a cruise flight configuration resulting in a loss of engine power. Sulphidation type corrosion was a factor in failure of the blades.

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

Read the full NTSB narrative

The airplane experienced a total loss of engine power during a domestic passenger cross-country flight. Following the loss of power, the pilot successfully landed the airplane at a nearby Naval Air Station. The pilot reported that during cruise flight, he heard a loud bang and oil became visible on the aircraft's windshield. He stated that concurrent with the loud bang, the propeller came to an abrupt stop. Postaccident examination of the engine revealed extensive corrosion and mechanical damage throughout the compressor and power turbine assemblies. The compressor disk assembly was essentially intact, however, all of the compressor turbine blades were fractured and displaced. The fracture surfaces were all approximately .250 inches above the corresponding blade platform. Examination of the fractured compressor turbine blades revealed the blades fractured in a tensile overload condition. The overload fractures associated with the compressor turbine blades was due to a weakening of the underlying base material due to the presence of sulphidation corrosion. The sulphidation corrosion was evident through approximately half of the thickness of the blades airfoil reducing the blades effective load bearing capabilities. The material composition of the turbine blades met drawing requirements and no metallurgical anomalies were found.

Quoted verbatim from the NTSB record.