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Printed page 27. PDF page 27.
a fracture of a rotor blade in the LPC2. The rotor blade fractured as a result of a high-cycle fatigue crack, which had initiated from a subsurface location and progressed due to mechanical resonance at 26 000 rpm. 2.2 UseOpen official document at PDF page 27Air Transportation Safety Investigation Report A23P0020: Engine compressor failure and fire
Printed page 30. PDF page 30.
in the 2nd stage low- pressure compressor. The rotor blade fractured as a result of a high-cycle fatigue crack, which had initiated from a subsurface location and progressed due to mechanical resonance at 26 000 rpm. 2. The engine controlOpen official document at PDF page 30Air Transportation Safety Investigation Report A23P0020: Engine compressor failure and fire