| Crash location | 35.210556°N, 113.875556°W
Reported location is a long distance from the NTSB's reported nearest city. This often means that the location has a typo, or is incorrect. |
| Nearest city | Kingman, AZ
35.189443°N, 114.053006°W 10.1 miles away |
| Tail number | N9022N |
|---|---|
| Accident date | 11 Apr 2008 |
| Aircraft type | North American T-28C |
| Additional details: | None |
On April 11, 2008, about 0730 mountain standard time, an experimental North American T-28C, N9022N, experienced a total loss of engine power while cruising about 5 miles east-southeast of the Kingman Airport, Kingman, Arizona. The pilot made a forced landing on open, rocky, desert terrain, and the airplane was substantially damaged. The private pilot was not injured, and the passenger sustained minor injuries. The airplane was owned and operated by the pilot. Visual meteorological conditions prevailed at the time of the personal flight, and no flight plan was filed. The flight was performed under the provisions of 14 Code of Federal Regulations Part 91, and it originated from Kingman about 0715.
The pilot reported to the National Transportation Safety Board investigator that the engine started running rough while cruising about 5,000 feet mean sea level (about 2,000 feet above ground level). The pilot checked the engine gauges and observed that the oil pressure was decreasing and the oil temperature was "maxing out." According to the pilot, the engine then lost all power and he made an intentional gear up landing because the tricycle gear airplane likely would have nosed over during rollout on the soft terrain. The propeller continued to rotate throughout the mishap. The pilot stated that his airplane's Curtis Wright model 1820-86B engine had been operated about 175 hours since receiving an overhaul.
At the direction of the Safety Board investigator, a Federal Aviation Administration (FAA) airworthiness inspector oversaw an examination of the accident engine. In pertinent part, the FAA inspector reported finding "an excessive amount of ferrous and non-ferrous" material in the oil screens. The number 3 cylinder was removed from the crank case and exhibited a bent connecting rod, along with "major damage to its piston and cylinder skirt." Also, numerous pieces of metal were observed in the crankcase that was associated with the number 4 and number 5 cylinders. The internal engine component that initially broke was not identified.
A total loss of engine power during cruise flight due to an undetermined catastrophic internal engine failure.