SOUTH ST PAUL, MN, USA
N35H
CESSNA 310R
AS THE AIRPLANE CLIMBED THROUGH APPROXIMATELY 100 FEET ABOVE THE GROUND AFTER TAKEOFF, TWO PROPELLER BLADES SEPARATED FROM THE RIGHT ENGINE PROPELLER ASSEMBLY, PENETRATING THE NOSE SECTION OF THE AIRPLANE. THE PILOT SHUT DOWN THE RIGHT ENGINE, FEATHERED THE REMAINING PROPELLER BLADE YAND RETURNED TO LAND AT THE DEPARTURE AIRPORT WITHOUT FURTHER INCIDENT. POST-ACCIDENT EXAMINATION REVEALED THE BLADES FAILED DUE TO METAL FATIGUE. AN ENGINE TEARDOWN AND CRANKSHAFT COUNTERWEIGHT INSPECTION REVEALED NO EVIDENCE OF PRE-IMPACT MALFUNCTION/ANOMALY. THE PROPELLER ASSEMBLY HAD A TOTAL TIME OF ABOUT 3,229 HOURS, INCLUDING APPROXIMATELY 295 HOURS SINCE OVERHAUL AND INSTALLATION ON THE ACCIDENT AIRFRAME.
THE INADEQUATE DESIGN OF THE PROPELLER HUB ASSEMBLY WHICH RESULTED IN METAL FATIGUE AND PROPELLER BLADE SEPARATION DURING INITIAL CLIMBOUT.
Source: NTSB Aviation Accident Database
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