ASN Wikibase Occurrence # 173829
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| Date: | Saturday 10 January 2004 |
| Time: | 14:25 |
| Type: |  Piper PA-24-260 |
| Owner/operator: | Private |
| Registration: | N1XF |
| MSN: | 24-4479 |
| Year of manufacture: | 1966 |
| Total airframe hrs: | 6214 hours |
| Engine model: | Lycoming IO-540 |
| Fatalities: | Fatalities: 0 / Occupants: 3 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Bradford, PA -
 United States of America
|
| Phase: | Approach |
| Nature: | Private |
| Departure airport: | Syracuse, NY (SYR) |
| Bradford, PA (BFD) | |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
Prior to departing his home airport, the pilot topped off the main fuel tanks. The flight departed with both fuel selectors positioned to "Main." After an approximate 2 hour flight, the pilot was approaching his home airport, and the fuel selectors remained on "Main." While descending from 6,000 feet to 4,000 feet, the engine "hiccupped," and then experienced several minor power surges, before losing total power. The pilot established a proper glide speed, and attempted a straight-in approach for the nearest runway at the home airport. During the glide, the pilot completed the emergency checklist items, which included verification that the electric fuel pump was on, and cycling the fuel selectors through all tanks. The pilot was unable to restart the engine, and continued the glide toward runway 23. The pilot maintained glide speed, but the airplane impacted small trees about 2,500 to 3,000 feet prior to the runway. Examination of the engine did not reveal any pre-impact mechanical malfunctions. Fuel was observed in all fuel tanks, and fuel was present from the selector valve, to the fuel servo, to the flow divider. When power was applied to the electric fuel pump, it operated continuously. Further examination of the engine revealed that the throttle idle adjustment bushing was missing. However, it was unknown if the bushing separated during flight, or during the forced landing. Subsequently, a flow test of the fuel servo and flow divider did not reveal any discrepancies that would have resulted in a total loss of engine power.
Probable Cause: A total loss of engine power for undetermined reasons during approach.
Accident investigation:
 |
|
Sources:
NTSB: https://www.ntsb.gov/_layouts/ntsb.aviation/brief.aspx?ev_id=20040122X00086&key=1
Location
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 14-Feb-2015 15:26 | Noro | Added |
| 21-Dec-2016 19:28 | ASN Update Bot | Updated [Time, Damage, Category, Investigating agency] |
| 07-Dec-2017 17:34 | ASN Update Bot | Updated [Other fatalities, Departure airport, Destination airport, Source, Narrative] |
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