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Printed page 1. PDF page 9.
engine. 1.4. The blade failure was a result of fatigue cracking. The Commission was unable to definitively determine when the fatigue cracking originated. 1.5. The engine failure occurred within four flying hours of the engine having been overhauled. 1.6. TheOpen final report at PDF page 9ATR72-600, ZK-MVL Engine fire and evacuation Wellington 1 September 2024
Printed page 30. PDF page 38.
low-pressure turbine blade also had evidence of fatigue. 4.5. While the Commission was unable to definitively determine when the fatigue cracking originated, it was likely that the fatigue on both LPT blades was present when the engine was recently overhauled.Open final report at PDF page 38ATR72-600, ZK-MVL Engine fire and evacuation Wellington 1 September 2024