Event Description
During the takeoff phase, an uncontained failure of the left engine occurred. Examination of the engine revealed a fatigue fracture that propagated through a rear flange bolt hole of the combustion chamber outer case. The fracture was located at the three o'clock position of the engine.
Inspection History
The engine had been inspected in accordance with an applicable airworthiness directive. However, the fracture occurred 2,060 cycles prior to the next scheduled inspection under that directive. Following the examinations of the engine and the fracture, additional inspection requirements were established.
Findings
The metallurgical examination identified the fracture as a fatigue failure. The source does not specify any other contributing factors.
Conclusion
The uncontained failure was directly attributed to the fatigue fracture at the described location. No further details regarding the aircraft, operator, or injuries were provided in the source.