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NTSB Report
March 6, 1992 · Bell 214B-1 · N314RM
Hobart Bay, AK
Overview
Report Status
Probable Cause
Event Type
Accident
Date
March 6, 1992
Injury Outcomes
2 injuries (2 serious injuries)
Location
Hobart Bay, AK
Aircraft
Bell 214B-1
Tail Number
N314RM
Operator
Rocky Mountain Aerologging
Injuries
Serious
Aircraft Damage
Substantial
NTSB Number
ANC92FA044
THE HELICOPTER WAS HOVERING APPROX 200 FT ABOVE THE LOG WHICH WAS BEING ATTACHED TO THE CARGO HOOK. THE PILOTS HEARD A LOUD BANG FOLLOWED BY A LOSS OF ENGINE POWER. THE HELICOPTER AUTOROTATED INTO STEEP UNEVEN TERRAIN, THE ONLY AREA AVAILABLE. EXAMINATION OF THE ENGINE REVEALED FATIGUE FAILURE OF THE CENTRIFUGAL IMPELLER ENCOMPASSING A 60 DEG ARC. THIS SECTION SEPARATED FROM THE ENGINE AND HELICOPTER. ANALYSIS OF THE IMPELLER SHOWED THAT THE COOLING HOLES, ASSOCIATED ONLY WITH THE T5508D ENGINE, DID NOT HAVE THE PRESCRIBED RADIUS, AND CRACKS WERE FOUND EMANATING FROM THE OTHER COOLING HOLES. THE ENGINE RECORDS SHOW THAT THE IMPELLER HAD 5592.0 CYCLES WHEN INSTALLED IN THIS ENGINE IN APRIL 1991. THE COMPONENT SERVICE LIFE LIMIT OF THE IMPELLER IS 16,600 CYCLES.
NTSB Probable Cause
FATIGUE FAILURE OF THE COMPRESSOR ASSEMBLY IMPELLER, AND INADEQUATE QUALITY CONTROL BY THE MANUFACTURER. A FACTOR WHICH CONTRIBUTED TO THE ACCIDENT WAS THE MOUNTAINOUS/HILLY TERRAIN.
Full Narrative
THE HELICOPTER WAS HOVERING APPROX 200 FT ABOVE THE LOG WHICH WAS BEING ATTACHED TO THE CARGO HOOK. THE PILOTS HEARD A LOUD BANG FOLLOWED BY A LOSS OF ENGINE POWER. THE HELICOPTER AUTOROTATED INTO STEEP UNEVEN TERRAIN, THE ONLY AREA AVAILABLE. EXAMINATION OF THE ENGINE REVEALED FATIGUE FAILURE OF THE CENTRIFUGAL IMPELLER ENCOMPASSING A 60 DEG ARC. THIS SECTION SEPARATED FROM THE ENGINE AND HELICOPTER. ANALYSIS OF THE IMPELLER SHOWED THAT THE COOLING HOLES, ASSOCIATED ONLY WITH THE T5508D ENGINE, DID NOT HAVE THE PRESCRIBED RADIUS, AND CRACKS WERE FOUND EMANATING FROM THE OTHER COOLING HOLES. THE ENGINE RECORDS SHOW THAT THE IMPELLER HAD 5592.0 CYCLES WHEN INSTALLED IN THIS ENGINE IN APRIL 1991. THE COMPONENT SERVICE LIFE LIMIT OF THE IMPELLER IS 16,600 CYCLES.
Flight
Event TypeAccident
Event Time06:30 AKST
Nearest Airport0nm N
Runway0
Flight Plan FiledCvfr
Aircraft FireNo
Aircraft ExplosionNo
Aircraft
AircraftBell 214B-1
Tail NumberN314RM
Aircraft CategoryHeli
DamageSubstantial
OperatorRocky Mountain Aerologging
Operating RulePart 133
Engines1
Engine TypeTurboshaft
Engine DetailsLycoming · T5508D · Turboshaft · 2950
Seats11
People & Injuries
Injury Summary2 injuries (2 serious injuries)
Fatal0
Serious2
Minor0
Uninjured0
Total2
Crew 1Age 46 · Second Class
Conditions
ConditionsVMC
LightDaylight
WindCalm
Visibility99 sm
CeilingNone
Temperature / Dew Point45 C / 0 C
Altimeter29.00 inHg
Weather SourcePILO