# Accident 19980810025129A: Cessna 150M, Santa Paula, CA, August 10, 1998

- Type: FAA accident report (Accident/Incident Data System), as reported
- Date: August 10, 1998, 08:30 local time
- Place: Santa Paula, CA
- Damage: Substantial damage
- Phase of flight: Fcd/Prec Ldg From Cruise
- Operating rules: General operating rules (Part 91)
- Location: 34.3997° N, 119.0709° W: From the FAA, an estimate near the named town, within about 3 miles
- Nearby events: https://openairdocs.org/map.md?lat=34.3997&lon=-119.0709&mi=10
- Aircraft: N704UV, a cancelled registration (https://openairdocs.org/deregistered/N704UV-2012-05-30) (OpenAirDocs)
- Registry model: Cessna 150M (registry code 2071830, https://openairdocs.org/model/cessna-150m) (OpenAirDocs)
- Reported make and model: CESSNA 150M
- Reported engine: CONT O200A
- People aboard: 1
- Fatal injuries: 0
- Pilot flight hours: 39 total, 27 in this make and model, 18 in the last 90 days
- NTSB investigation: [NTSB LAX98LA262](https://openairdocs.org/ntsb/LAX98LA262) (OpenAirDocs)
- FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/)
- Page: https://openairdocs.org/incident/19980810025129A

## Narrative

As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^.

(-23) ON AUGUST 10, 1998 AT 0815 N704UV MADE A FORCED LANDING IN A RIVERBED WEST OF THE CITY OF FILMORE. THE STUDENT PILOT EXPLAINED THAT HIS ENGINE STARTED RUNNING ROUGH AND HE WAS GETTING SMOKE IN THE COCKPIT.  HE THEN EXECUTED AN OFF FIELD LANDING THAT DESTROYED THE AIRCRAFT.  PERFORMED AN ENGINE TEARDOWN AND FOUND THE #1 CYLINDER TO BE CRACKED THREE QUARTERS AROUND AT THE MID BARRELL LOCATION, AND SUBSEQUENT FAILURE OF THE OIL RING. (.4) THE STUDENT PILOT WAS ON A LOCAL SOLO FLIGHT.  AFTER PRACTICING VARIOUS MANEUVERS THE ENGINE BEGAN TO RUN ROUGH, VIBRATE, AND SMOKE.  THE PILOT MADE A FORCED LANDING INTO A RIVERBED AND CAME TO REST INVERTED.  THE NUMBER ONE CYLINDER WAS FOUND TO HAVE A CIRCUMFERENTIAL CRACK EXTENDING APPROXIMATELY 325 DEGREES AROUND THE BARREL BETWEEN THE 8TH AND 9TH COOLING FINS.  THE CYLINDER WAS FURTHER EXAMINED BY A METALLURGIST, WHO REPORTED THAT THE BARREL FINS WERE COVERED WITH AN IRON OXIDE.  THE EXAMINATION FURTHER REVEALED A FATIGUE CRACK THAT EMANATED FROM CORROSION PITS AT THE ROOT RADIUS BETWEEN THE 8TH AND 9TH COOLING FINS.  THE REMAINING PORTION OF THE FRACTURE EXHIBITED AN OVERSTRESS SEPARATION.

## The NTSB's investigation of this event (1)

From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model.

- [NTSB LAX98LA262](https://openairdocs.org/ntsb/LAX98LA262), Aug 10, 1998: Cessna 150M (N704UV), Santa Paula, CA, substantial damage. Probable cause: Failure of the number one cylinder due to a fatigue crack that had originated from corrosion pits at the cooling fin.

From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record.

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