What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
(.4)The captain reported that the airplane was at 5,000 feet mean sea level, the propeller RPM was 100 percent, and other engine indications were normal. A loss of power on the number two engine was 'sudden and immediate.' The flightcrew declared an emergency and recovered visually to Grand Forks without further incident. Examination of the airplane revealed eleven impact marks to the right side of the fuselage. Two of the impacts penetrated the fuselage side. Examination of the engine revealed evidence of overload failure and penetration of the gear box. Fatigue fractures in the second stage compressor impeller rim emanated from a heat affected, rubbed area on the impeller blades. A corresponding rubbed area was evident on the impeller shroud, and aluminum material was fused to the titanium impeller. No evidence of material defects were noted. (-23) pilot stated that during climb after departing Grand fork airport, ND the right engine experienced an uncontained failure. Pieces of the rear reduction section punctured the aircraft fuselage. The aircraft returned to Grand Forks airport, ND with no further incident. There were no injuries. Th e pilot information was not available at the time this form was completed. An amended form will be forwarded when the information is received.
As the FAA filed it
(.4)THE CAPTAIN REPORTED THAT THE AIRPLANE WAS AT 5,000 FEET MEAN SEA LEVEL, THE PROPELLER RPM WAS 100 PERCENT, AND OTHER ENGINE INDICATIONS WERE NORMAL. A LOSS OF POWER ON THE NUMBER TWO ENGINE WAS 'SUDDEN AND IMMEDIATE.' THE FLIGHTCREW DECLARED AN EMERGENCY AND RECOVERED VISUALLY TO GRAND FORKS WITHOUT FURTHER INCIDENT. EXAMINATION OF THE AIRPLANE REVEALED ELEVEN IMPACT MARKS TO THE RIGHT SIDE OF THE FUSELAGE. TWO OF THE IMPACTS PENETRATED THE FUSELAGE SIDE. EXAMINATION OF THE ENGINE REVEALED EVIDENCE OF OVERLOAD FAILURE AND PENETRATION OF THE GEAR BOX. FATIGUE FRACTURES IN THE SECOND STAGE COMPRESSOR IMPELLER RIM EMANATED FROM A HEAT AFFECTED, RUBBED AREA ON THE IMPELLER BLADES. A CORRESPONDING RUBBED AREA WAS EVIDENT ON THE IMPELLER SHROUD, AND ALUMINUM MATERIAL WAS FUSED TO THE TITANIUM IMPELLER. NO EVIDENCE OF MATERIAL DEFECTS WERE NOTED. (-23) PILOT STATED THAT DURING CLIMB AFTER DEPARTING GRAND FORK AIRPORT, ND THE RIGHT ENGINE EXPERIENCED AN UNCONTAINED FAILURE. PIECES OF THE REAR REDUCTION SECTION PUNCTURED THE AIRCRAFT FUSELAGE. THE AIRCRAFT RETURNED TO GRAND FORKS AIRPORT, ND WITH NO FURTHER INCIDENT. THERE WERE NO INJURIES. TH E PILOT INFORMATION WAS NOT AVAILABLE AT THE TIME THIS FORM WAS COMPLETED. AN AMENDED FORM WILL BE FORWARDED WHEN THE INFORMATION IS RECEIVED.
NTSB investigation
The NTSB’s investigation of this event, with its probable cause and findings. Matched to this report by N-number and date.
Other reports on N2692P · 2
Matched to the same aircraft by N-number and date.