NTSB Identification: CHI84LA279.
The docket is stored on NTSB microfiche number 26061.
Accident occurred Wednesday, July 04, 1984 in DETROIT, MI
Aircraft: BELL 47G2, registration: CFISH
Injuries: 3 Serious.

NTSB investigators may not have traveled in support of this investigation and used data provided by various sources to prepare this aircraft accident report.

THE ACFT LANDED IN THE DETROIT RIVER AFTER THE ENGINE SPUTTERED AND THE ACFT VIBRATED. THE PLT REDUCED PWR & COLLECTIVE AND PUSHED THE CYCLIC FORWARD. THE RPM REDUCED FROM 3000 TO 2500 BUT THE ROTOR AND ENGINE RPM REMAINED MARRIED. THE PLT ADJUSTED DESCENT WITH COLLECTIVE, FORWARD SPEED WITH CYCLIC AND PULLED ALL COLLECTIVE JUST PRIOR TO IMPACT. THE ACFT WAS AT ABOUT 150 FT AGL WHEN THE ENGINE SPUTTERED. ONE PASSENGER DESCRIBED A SPUTTERING NOISE BUT SAID THE ENGINE WAS RUNNING UNTIL IMPACT. ANOTHER PASSENGER DESCRIBED THE ENGINE NOISE AS A MUFFLED MISFIRING SOUND. THE PASSENGERS ALSOSAID THE PLT DID NOT MENTION THE PROBLEM TO THEM AND THE HELICOPTER SEEMED UNDER CONTROL UNTIL IMPACT. POST ACCIDENT EXAMINATION OF THE ENGINE AFTER RECOVERY FROM THE WATER SHOWED THAT THE SPARK PLUGS WERE WORN AND CONTAINED A HEAVY BUILD-UP OF CARBON AND LEAD. NEAR THE OPERATORS HANGER WERE 5 SEALED AND 1 UNSEALED FUEL DRUMS WITH STANDING WATER ON THE TOPS. NO OTHER EVIDENCE WAS FOUND TO INDICATE ANY MALFUNCTION OF THE ACFT.

The National Transportation Safety Board determines the probable cause(s) of this accident to be:

IGNITION SYSTEM,SPARK PLUG..CORRODED

The National Transportation Safety Board determines the probable cause(s) of this accident to be:

IGNITION SYSTEM,SPARK PLUG..WORN

The National Transportation Safety Board determines the probable cause(s) of this accident to be:

ADEQUATE ROTOR RPM..NOT MAINTAINED..PILOT IN COMMAND

The National Transportation Safety Board determines the probable cause(s) of this accident to be:

THROTTLE/POWER CONTROL..IMPROPER USE OF..PILOT IN COMMAND


Contributing Factors

TERRAIN CONDITION..WATER,ROUGH



Contributing Factors

LANDING GEAR,FLOAT ASSEMBLY..BURST


Contributing Factors

THROTTLE/POWER CONTROL..REDUCED..PILOT IN COMMAND


Contributing Factors

PILOT IN COMMAND


Contributing Factors

PANIC..PILOT IN COMMAND

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