ASN Wikibase Occurrence # 289130
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 9 July 2011 |
| Time: | 13:30 LT |
| Type: |  Grumman G-164B Tubo Ag-Cat |
| Owner/operator: | Onstott Dusters Inc |
| Registration: | N7503L |
| MSN: | 826B |
| Total airframe hrs: | 10282 hours |
| Engine model: | P&W PT6A-34 |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Yuba City, California -
 United States of America
|
| Phase: | Initial climb |
| Nature: | Agricultural |
| Departure airport: | Yuba City, CA |
| Yuba City, CA | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The pilot reported that, during the initial climb, he heard a "loud pop" and observed fire coming from both exhaust stacks before the engine lost power. He subsequently made an off-airport landing to an adjacent road. During the landing, the airplane slid into a ditch, the landing gear sheared off, and the airplane nosed over. A postaccident engine examination revealed that the blade retaining ring of the 1st-stage compressor blades had fractured into several pieces; about 30 percent of the ring was not recovered. A metallurgical examination of the recovered sections of the retaining ring revealed that all but two of the fractures were due to ductile overload. An examination of the nonoverload fractures revealed fatigue originating from the rivet hole areas, which was indicative of high-cycle fatigue. The power section had been overhauled 747 hours before the accident. According to the overhaul manual current at the time of the overhaul, the blade retaining ring was an on-condition inspection item and not required to be replaced at overhaul. The fatigue fracture of the 1st-stage compressor blade retaining ring likely affected the engine's ability to produce power.
Probable Cause: High-cycle fatigue on the 1st-stage compressor blade retaining ring, which resulted in the ring's fracture and a subsequent loss of engine power.
Accident investigation:
 |
|
Sources:
NTSB WPR11LA320
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 05-Oct-2022 10:10 | ASN Update Bot | Added |
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