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Aviation safety reports, made easier to study

NTSB Reports is an independent research and search tool for public aviation accident and incident records. It brings NTSB aviation reports, structured fields, docket files, extracted figures, photos, videos, and update history into one searchable interface.

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November 4, 1988 · Aerospatiale AS-355F-1 · N355EH

W. Cameron 617

Overview

Report Status
Probable Cause
Event Type
Accident
Date
November 4, 1988
Injury Outcomes
6 injuries (4 fatalities, 2 serious injuries)
Location
W. Cameron 617
Aircraft
Aerospatiale AS-355F-1
Tail Number
N355EH
Injuries
Fatal
Aircraft Damage
Destroyed
NTSB Number
FTW89FA013

ACFT WAS DEPARTING AN ELEVATED HELIDECK ON AN OFFSHORE PRODUCTION PLATFORM WHEN IT EXPERIENCED A COMPLETE LOSS OF TAIL ROTOR THRUST AND ACFT CONTROL DUE TO A FAILURE OF THE TAIL ROTOR DRIVE SHAFT. THE FAILURE OCCURRED AS THE PLT INITIATED HIS TAKEOFF WITH THE ACFT HAVING JUST CLEARED THE DECK AND RECOVERY WAS NOT POSSIBLE. INVESTIGATION REVEALED THAT THE DRIVE SHAFT HAD FAILED AS A RESULT OF FATIGUE CRACKING IN AN AREA OF FRETTING WHERE THE SHAFT WAS BONDED AND BOLTED TO ITS COUPLING. THIS AND PREVIOUS FAILURES IN THE SAME AREA INDICATED THAT THE SHAFT WAS UNDER DESIGNED FOR THE APPLICATION AND NORMAL OPERATING STRESSES. SHAFT WAS SUBSEQUENTLY RE-DESIGNED AND THE FLEET RETROFITTED.

NTSB Probable Cause

THE LOSS OF CONTROL OF THE AIRCRAFT WHICH OCCURRED WHEN THE TAIL ROTOR DRIVE SHAFT EXPERIENCED A FATIGUE INDUCED MATERIAL FAILURE AND TAIL ROTOR THRUST WAS LOST. EVIDENCE INDICATED THAT THE SHAFT WAS UNDER DESIGNED FOR THE LOADS THAT WERE ENCOUNTERED DURING NORMAL OPERATIONS.

Full Narrative

ACFT WAS DEPARTING AN ELEVATED HELIDECK ON AN OFFSHORE PRODUCTION PLATFORM WHEN IT EXPERIENCED A COMPLETE LOSS OF TAIL ROTOR THRUST AND ACFT CONTROL DUE TO A FAILURE OF THE TAIL ROTOR DRIVE SHAFT. THE FAILURE OCCURRED AS THE PLT INITIATED HIS TAKEOFF WITH THE ACFT HAVING JUST CLEARED THE DECK AND RECOVERY WAS NOT POSSIBLE. INVESTIGATION REVEALED THAT THE DRIVE SHAFT HAD FAILED AS A RESULT OF FATIGUE CRACKING IN AN AREA OF FRETTING WHERE THE SHAFT WAS BONDED AND BOLTED TO ITS COUPLING. THIS AND PREVIOUS FAILURES IN THE SAME AREA INDICATED THAT THE SHAFT WAS UNDER DESIGNED FOR THE APPLICATION AND NORMAL OPERATING STRESSES. SHAFT WAS SUBSEQUENTLY RE-DESIGNED AND THE FLEET RETROFITTED.

Flight

Event TypeAccident
Event Time12:51 UTC
Nearest AirportW. Cameron 617 (0nm N)
Runway0
Flight Plan FiledCvfr
Aircraft FireNo
Aircraft ExplosionNo

Aircraft

AircraftAerospatiale AS-355F-1
Tail NumberN355EH
Aircraft CategoryHeli
DamageDestroyed
Operating RulePart 135
Engines2
Engine TypeTurboshaft
Engine DetailsAllison · 250-C20F · Turboshaft · 425
Seats6

People & Injuries

Injury Summary6 injuries (4 fatalities, 2 serious injuries)
Fatal4
Serious2
Minor0
Uninjured0
Total6
Crew 1Age 43 · First Class

Conditions

ConditionsVMC
LightDaylight
Wind180° @ 25 kt, gusting 35 kt
Visibility10 sm
CeilingBroken clouds 1500 ft
Temperature / Dew Point0 C / 0 C
Altimeter29.00 inHg
Observation Time12:00
Weather SourceWFAC

Appendix: Source Data