ASN Wikibase Occurrence # 288287
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: | Saturday 24 July 2010 |
Time: | 13:00 LT |
Type: | Bell 47G-4A Soloy |
Owner/operator: | Scotts Helicopter Services Inc |
Registration: | N124SH |
MSN: | |
Year of manufacture: | 1967 |
Total airframe hrs: | 15020 hours |
Engine model: | Allison 250-C10D |
Fatalities: | Fatalities: / Occupants: 0 |
Aircraft damage: | Unknown |
Category: | Accident |
Location: | Rochester, MN -
United States of America
|
Phase: | Manoeuvring (airshow, firefighting, ag.ops.) |
Nature: | Agricultural |
Departure airport: | |
Destination airport: | |
Investigating agency: | NTSB |
Confidence Rating: | Accident investigation report completed and information captured |
Narrative:A witness reported that the agricultural helicopter was refueled and that the hopper was loaded with chemical before departure. He reported that he saw the helicopter depart, that the engine sounded normal, and that the helicopter's departure and flightpath appeared normal. He then saw a "brown puff of smoke" come from the helicopter, and it subsequently descended and impacted a hill. A postaccident engine examination revealed that the compressor rotor assembly had failed. The metallurgical examination of the compressor rotor assembly revealed that a single first-stage compressor blade had fractured in high-cycle fatigue. The microstructure, hardness, and chemistry of the first-stage compressor wheel conformed to the requirements of the engineering drawing. No evidence of corrosion was found near the fracture origin. The engine was installed on the helicopter during the last annual maintenance inspection conducted 3 days before the accident. Evidence indicated that the engine was installed properly. The reason for the fracture could not be determined.
Probable Cause: The total loss of engine power due to a high-cycle fatigue fracture of a first-stage compressor blade. The reason for the fracture could not be determined during postaccident examination.
Accident investigation:
|
| |
Investigating agency: | NTSB |
Report number: | CEN10LA431 |
Status: | Investigation completed |
Duration: | 3 years and 7 months |
Download report: | Final report |
|
Sources:
NTSB CEN10LA431
Location
Revision history:
Date/time | Contributor | Updates |
04-Oct-2022 20:51 |
ASN Update Bot |
Added |
The Aviation Safety Network is an exclusive service provided by:
CONNECT WITH US:
©2024 Flight Safety Foundation