ASN Wikibase Occurrence # 353522
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| Date: | Tuesday 1 December 1998 |
| Time: | 18:00 LT |
| Type: |  Grumman G-164B Turbo Ag-Cat |
| Owner/operator: | Thrash Aviation Inc |
| Registration: | N6630Q |
| MSN: | 154B |
| Total airframe hrs: | 6055 hours |
| Engine model: | Garrett TPE331-6-252M |
| Fatalities: | Fatalities: 0 / Occupants: 1 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Fort Gains, GA -
 United States of America
|
| Phase: | Take off |
| Nature: | Agricultural |
| Departure airport: | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The flight was loaded with fertilizer and had taken off, when the engine lost power. The pilot made a forced landing, and the airplane's landing gear went into a ditch and separated. The pilot had made 3 previous takeoffs under similar load conditions without incident. The pilot said, 'initially during the takeoff roll the aircraft accelerated normally.' However, immediately after breaking ground, during the initial climbout, the engine began to loose power, and the aircraft began to loose lift. The airplane continued to sink with partial power until impact. Examination of the engine revealed no exterior damage. The engine teardown revealed that improper atomization of the fuel resulted in a non-atomized fuel stream at the first-stage turbine rotor. The subsequent atomization and ignition of this fuel resulted in a localized area of increased temperature and non-uniform thermal damage to the second- and third-stage turbine stators. The localized area of increased temperature resulted in thermal damage to the second- and third-stage turbine rotors, and increased second- and third-stage turbine rotor blade tip clearance, rendering the engine incapable of producing full power. There was no evidence that the engine control system components contributed to the loss of engine power reported during the accident flight.
Probable Cause: a power loss due to internal damage to the second- and third- stage turbine rotor blades, due to thermal heat, rendering the engine incapable of producing full power, resulting in a forced landing, and subsequent impact with the terrain.
Accident investigation:
 |
|
Sources:
NTSB MIA99LA041
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 10-Mar-2024 07:42 | ASN Update Bot | Added |
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