Aviation Crash Map

Piper PA 28-180 N30865

24 October 2013 · Big Creek, California, United States · Serious injuries

Summary

On 24 October 2013 at about 17:00 local time, a Piper PA 28-180 registered N30865, operated by Peterson Arnie D, was involved in an accident near Big Creek, California, United States. One person was on board and one was seriously injured. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

The record

Date
at 17:00
Classification
Accident
Location
Big Creek, California, United States
Coordinates
37.1836, -119.1386
Aircraft
Piper PA 28-180
Registration
N30865
Category
Airplane
Engines
1
Operator
Peterson Arnie D
Operating rule
Part 91: General Aviation
Purpose of flight
Personal
Phase of flight
Not recorded
Route
Bishop → Fresno
Aircraft damage
Substantial
Weather
VMC
Light
Day
NTSB number
WPR14LA031

People

1 person was seriously injured.

On board Died Serious Minor Uninjured
1 0 1 0 0

Probable cause

The loss of engine power due to the improper installation of an oil pressure sending unit by the pilot, who was not a certificated mechanic, which resulted in a forced landing in mountainous terrain.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

The pilot, who was a co-owner of the airplane, reported to an air traffic controller about 1 hour into a cross-country flight over mountainous terrain that the engine had lost oil pressure and then power. The pilot performed a forced landing into trees. Postaccident examination revealed that the loss of engine power resulted from oil starvation due to oil leaking from a fractured fitting at the oil pressure gauge/sending unit port on the engine's rear accessory case. An oil pressure sending unit, which the pilot, who was not a certificated mechanic, had installed at this location just before the accident flight, was found dangling by its electrical wiring harness and not supported. The sending unit was not approved for installation on this airplane. It is likely that the fitting fractured because of vibration due to the sending unit's lack of support. The engine operating time between the installation of the sending unit and the fitting fracture was about 1 hour.

Quoted verbatim from the NTSB record.

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