N25490Cessna 152 · 1977

On July 02, 2008, about 1310 Pacific daylight time, a Cessna 152, N25490, was destroyed by impact forces and a post-crash fire following a collision with terrain in Piru, California. Raw Power Aviation, the pilot's company, was operating the airplane under the provisions of 14 CFR Part 91. The commercial pilot, the sole occupant, was killed. The local flight originated from Whiteman Airport, Los Angeles, California, about 1235, for a pipeline surveillance operation. Visual meteorological conditions prevailed, and a flight plan had not been filed.

Several witnesses in the area reported that the airplane was flying low along a road toward an expansive riverbed. The airplane disappeared behind the tree line, and subsequently witnesses observed black smoke emitting from the accident site.

An inspector from the Federal Aviation Administration (FAA) interviewed a witness who lived in a residence south of the accident site. He stated that he was located on his front porch that faces to the north. He observed an airplane flying low from the east and moving to the west at a slow speed. The airplane's left wing suddenly dropped and it dove behind a tree line, out of his sight.

According to the FAA Airman and Medical records files, the 55-year-old pilot held a commercial pilot certificate with a rating for airplane single-engine land. He additionally held an airframe and powerplant mechanic certificate with inspection authorization authority. The pilot was issued a second-class medical certificate in September 2009, with no limitations.

No personal flight records were recovered for the pilot. The family stated that the pilot normally kept his logbooks in the airplane. On the pilot's last application for a medical certificate, he reported having amassed about 6,800 hours of total flight experience.

The airplane was a Cessna 152, serial number 15280690, which was manufactured in 1978. According to the original application for a utility category airworthiness certificate completed by the Cessna factory, the Lycoming O-235-L2C engine was installed at the time of manufacture. Despite numerous attempts, the logbooks for the airplane were not made available for review.

Fuel

Examination of refueling records at the Whiteman Airport disclosed that the airplane was last fueled on the day of the accident, with the addition of 18 gallons of 100LL aviation gasoline. During the removal of the wreckage, aircraft recovery personnel noted the odor of gasoline at the accident site.

Performance

The performance data was calculated using information from the 1977 Cessna 152 Pilot's Operating Handbook (POH), which was applicable to the accident airplane. For the purpose of the calculations, investigators utilized an estimated gross weight at the time of the accident to be 1,326 pounds, which was derived by the assumption of 135 pounds of fuel on board (subtracted full fuel from an estimated .5 hours en route) and a pilot weight of 225 pounds (includes 20 pounds of baggage); the airplane's empty weight was 1,081 pounds. A Safety Board investigator calculated turning performance using the measured distance between the accident site and adjacent mountains, referencing Aerodynamics for Naval Aviators (NAVWEPS 00-80T-80), Figure 2.29, General Turning Performance (Constant Altitude, Steady Turn). The approximate distance from the accident site to the adjacent hillside was about 460 feet when measured using a topological mapping program. With a turn radius of 230 feet and an airspeed of 80 knots (estimated as average patrolling speed), the airplane's bank angle equated to about 65 degrees. At 101 knots (maneuvering airspeed at the maximum gross weight of 1,670 pounds), the airplane's bank angle totals about 74 degrees.

According to stall speed versus angle of bank data in the Cessna POH, at the anticipated weight of the airplane, with flaps set to 0 degrees, the stall speed would be around 67 knots indicated airspeed at 60 degrees of bank.

A routine aviation weather report (METAR) for the Whitman Airport was issued at 1247, 26 minutes prior to the accident. It stated: skies clear; wind from 100 degrees at 7 knots; temperature 87 degrees Fahrenheit; dew point 55 degrees Fahrenheit; and altimeter 29.83 inHg.

A personal weather station (PWS) located about 2 miles northeast of the accident site reported that 2 minutes after the accident, the temperature was 86 degrees Fahrenheit; dew point 50 degrees Fahrenheit; and there was a 12-knot wind from the west, gusting to 17 knots.

The accident site was located on the west slope of a ravine about 22 nautical miles (nm) from Whiteman Airport, on a bearing of 285 degrees. The small north-south oriented ravine was on flat terrain that contained numerous crop fields and an east-west oriented dirt road. The airplane came to rest about 460 feet north from the base of a mountain range that comprised the south wall of a 7,500-foot-wide canyon. Several feet north of the wreckage the terrain plummeted 50 feet where an expansive dry river bed stretched along the middle of the valley floor. The mountain ranges that comprised the canyon walls were about 1,500 feet higher than the vicinity surrounding the accident site.

In character, the dirt road hugged the mountain base with the exception of the area adjacent to the accident site. The mountainous terrain receded in, where a small valley opened to the south. Construction was occurring in the immediate area where the ravine adjoined the dirt road. A massive pipeline was exposed next to the road, located about 400 feet from the wreckage. A complete section of maps and diagrams is contained in the public docket for this accident.

A Ventura County Sheriff's Office coroner performed an autopsy on the pilot. The FAA Toxicology Accident Research Laboratory, Oklahoma City, Oklahoma, performed toxicological testing on the pilot. The specimens tested negative for carbon monoxide, ethanol, and drugs.

A Safety Board investigator examined the wreckage on August 04, 2008, at the facilities of Ray's Aviation, Santa Paula, California. The wreckage had been recovered and placed into a secured storage area prior to the examination.

The crankshaft was rotated via the vacuum pump drive and was free and easy to rotate in both directions. Compression was observed in proper order on all four cylinders. The complete valve train appeared undamaged and was observed to operate in proper order. Normal lift action was observed at each rocker assembly. Clean, uncontaminated oil was observed at all four rockerbox areas. Mechanical continuity was established throughout the rotating group, valve train, and accessory section during hand rotation of the crankshaft.

The top spark plugs were removed, all of which exhibited a dark coloration, consistent with the thermal damage the engine was subjected to during the postcrash fire. The electrodes were oval and gaps were similar. The cylinders' combustion chambers were examined through the spark plug holes utilizing a lighted borescope. The combustion chambers remained mechanically undamaged, and there was no evidence of foreign object ingestion or detonation. The valves were intact and undamaged. There was no evidence of valve to piston face contact observed. The gas path and combustion signatures observed at the combustion chambers and exhaust system components displayed coloration that the Lycoming representative said was consistent with normal operation.

Inspection of the airframe noted that the front section of the airplane was crushed aft. The cabin area and wings were thermally damaged. All flight control surfaces were accounted for and flight control continuity was established.

Investigators found no evidence of preimpact mechanical malfunctions or failures with either the engine or airframe during the examination. The complete examination report with accompanying pictures is contained in the public docket for this accident.

Despite numerous attempts to contact the pilot's employer, the Safety Board failed to determine when the last time the pilot flew that pipeline and whether he had observed the construction prior to the accident.