ASN Wikibase Occurrence # 302944
This information is added by users of ASN. Neither ASN nor the Flight Safety Foundation are responsible for the completeness or correctness of this information.
If you feel this information is incomplete or incorrect, you can submit corrected information.
| Date: | Tuesday 2 November 2021 |
| Time: | |
| Type: |  Bell 206L |
| Owner/operator: | Henley Air |
| Registration: | ZS-HDX |
| MSN: | 45538 |
| Year of manufacture: | 1980 |
| Fatalities: | Fatalities: 0 / Occupants: 2 |
| Aircraft damage: | Unknown |
| Category: | Accident |
| Location: | 16nm south-west of Foch Ville -
 South Africa
|
| Phase: | En route |
| Nature: | Ferry/positioning |
| Departure airport: | Johannesburg/Germiston-Rand Airport (QRA/FAGM) |
| Buffels Mine | |
| Investigating agency: | CAA S.A. |
| Confidence Rating: |  Accident investigation report completed and information captured |
Approximately 35 minutes into the flight during the cruise phase the pilot noticed an engine out warning light which was followed by the indication of zeros for oil pressure, torque and gas generator (Ng); the rotor revolutions per minute (RRPM) and transmission oil temperature (TOT) gauges read normal. Thereafter, a loud bang was heard from the engine compartment, and the low rotor RPM warning activated. The helicopter entered autorotation, and the pilot reacted by turning the helicopter into wind in preparation for a forced landing. All pedal controls lost effectiveness, but the pilot was able to execute a successful forced landing, thereafter, he shut down the helicopter engine. Fire erupted in the engine bay and the pilot used the portable fire extinguisher to put it out. The pilot and the passenger did not sustain any injuries. The helicopter sustained damage to the engine, cowling, fuselage, tail rotor drive shaft and one main rotor blade.
Metallurgical examination and analysis of the engine components revealed that the engine failure was due to the gas producer bearing thrust plate anti-rotation tab that separated and travelled through the oil system and finally lodged between the oil pump scavenge gear and the wall. As a result, the oil pump could not provide adequate lubrication to the number 6 and 7 bearings. Therefore, the number 6 and 7 bearings failed due to thermal damage, as well as the subsequent damage to other turbine parts.
Accident investigation:
 |
|
Sources:
S.A. CAA
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 28-Nov-2023 14:55 | harro | Updated [Other fatalities] |
Corrections or additions? ... Edit this accident description
The Aviation Safety Network is an exclusive service provided by:
Quick Links:
| ASN Home | Send Correction / Feedback |
| FSF Home | Disclaimer | Copyright |
| Contact Us | Privacy Policy |
| Press / Media |
CONNECT WITH US:
©2024 Flight Safety Foundation