N803FCBeech 76 · 1979

On May 10, 2018, about 2031 Pacific daylight time, a Beech BE76 airplane, N803FC, collided with mountainous terrain while maneuvering near Julian, California. The flight instructor, pilot receiving instruction, and passenger were fatally injured. The airplane was destroyed by a postimpact fire. The airplane was registered to and operated by Scandinavian Aviation Academy of El Cajon, California, as a Title 14 Code of Federal Regulations (CFR) Part 91 instructional flight. Night visual meteorological conditions prevailed for the cross-country flight, and no flight plan was filed. The flight originated from Apple Valley Airport (APV), Apple Valley, California, about 1932 and was destined for Gillespie Field Airport (SEE), El Cajon, California.

The purpose of the flight was for the pilot receiving instruction to complete two back-to-back cross-country flights of at least 2 hours in duration, and a total straight line distance of more than 100 nautical miles (nm) each. The first 2-hour flight was to be accomplished under daytime conditions, and the second 2-hour flight was to be conducted under nighttime conditions. The flight to APV was conducted during the day, and the return flight to SEE was to be conducted at night. The course syllabus for the 2 flights identified several tasks that were to be accomplished during the flights. A representative of the operator reported that maneuvers are usually performed to facilitate a 2-hour flight. All flight is prohibited below 500 ft above ground level (agl) and minimum cruise altitude of 2,000 ft agl in mountainous terrain.

Review of Federal Aviation Administration (FAA) radar data identified the airplane near Ramona Airport (RMN), Ramona, California, about 2009. The radar track showed that the airplane traveled east and climbed to an altitude of about 5,600 ft mean sea level (msl) with the groundspeed varying from 116 to 133 knots for about 14 miles. The airplane then began to slow, and it made a left turn maneuver from about a 48° course heading to about a 176° course heading. Throughout the turn, the airplane's altitude remained about 5,600 ft msl, and the groundspeed decreased to 55 knots. At the completion of the turn, the groundspeed increased to about 67 knots, and the airplane began to climb to 6,600 ft msl while continuing to the southwest on a course heading of about 195°. The airplane then made a right turn course reversal to an easterly heading and proceeded in that direction for about 10 miles.

The radar data then depicted the airplane initiated a second left 180° turn maneuver at an altitude of 6,200 ft msl and a groundspeed of about 121 knots. At the apparent apex of the turn, the airplane was at 6,100 ft msl and a groundspeed of 50 knots. The airplane then began to descend, and the groundspeed increased to 74 knots and then decreased to 50 knots. The last radar return, which was recorded about 2031, showed the airplane at an altitude of 5,700 ft msl and a groundspeed of 67 knots near the accident site. Figure 1 shows the flight tracks for both maneuvers, and figures 2 and 3 show the flight track for the first and second maneuvers, respectively, along with relevant airplane and terrain information.

Figure 1. First and second maneuver.

Figure 2. Radar track for the first maneuver along with relevant airplane and terrain information.

Figure 3. Radar track for the second maneuver along with relevant airplane and terrain information.

Flight Instructor

The flight instructor, age 28, held an airline transport pilot certificate with a rating for airplane multiengine land and a commercial pilot certificate with privileges for single-engine land. He also held a flight instructor certificate with ratings for airplane single engine, multiengine and instrument airplane. He held an FAA first-class medical certificate dated May 10, 2018, with no limitations.

According to a resume provided by the operator, the flight instructor reported 2,000 hours of total flight experience, including 1,500 hours as pilot-in command, 150 hours in multiengine airplanes, 170 hours of instrument flight, and 125 hours at night. The instructor's flight logbook was not located. The operator reported that the instructor was newly hired, and that the accident flight was his first instructional flight with the company.

Pilot Receiving Instruction

The pilot receiving instruction, age 24, held a private pilot certificate with airplane single-engine land and instrument airplane ratings. The pilot received his instrument airplane rating on April 9, 2018. He held an FAA second-class medical certificate dated February 24, 2017, with no limitations. According to the operator, the pilot had 190 hours of total flight experience, including 7 hours in multiengine airplanes, 7 hours in the accident airplane make and model, and 13 hours at night. In the preceding 90 days, the pilot logged a total of 50 flight hours, including 7 hours in the accident airplane make and model and 2 hours at night.

Review of the maintenance logbook records revealed that the most recent annual inspection was completed on March 3, 2018, at a recorded tachometer time of 2,130.1 hours and an airframe total time of 14,150.9 hours.

The 1953 automated weather observation from RMN, located about 18 miles northwest of the accident site, included winds from 290° at 7 knots, visibility of 10 statute miles, clear sky, temperature 16°C, dew point 13°C, and an altimeter setting of 29.86 inches of mercury.

An active AIRMET, issued at 1945, indicated moderate turbulence below 12,000 ft for the region where the accident occurred. Also, the National Weather Service Area Forecast discussed the following gusty surface wind conditions for the mountains/deserts in the region where the accident occurred: "Gusty west winds through 08Z Friday from 15-25 mph gusting 35-45 mph." In addition, High-Resolution Rapid Refresh model data for the period surrounding the accident time identified wind magnitudes of about 35 knots from the west-southwest near 6,100 ft. Notably at 6,100 ft, resided near the top of a temperature inversion present in the lower altitudes. The upset occurred immediately downwind of relatively high terrain, inside of the temperature inversion. Temperature inversions can promote wave action and turbulence.

A review of the Los Angeles sectional chart, which was valid through June 21, 2018, revealed a caution block near the Julian VOR that read, "Caution: Extreme turbulence and severe up and down drafts during high wind conditions."

Review of the maintenance logbook records revealed that the most recent annual inspection was completed on March 3, 2018, at a recorded tachometer time of 2,130.1 hours and an airframe total time of 14,150.9 hours.

The accident site was located less than 1 mile southeast of the Julian VOR in mountainous terrain near the bottom of a draw at an elevation of about 4,200 ft. The elevation of the terrain within a 2-mile radius of the accident site ranged from 3,700 to 5,300 ft. The initial impact was in a westerly direction and the wreckage debris was in a path to the east. The wreckage was contained within about a 150-ft circumference around the initial impact point. The piece of wreckage located the farthest (downslope) from the initial impact was the right propeller. All structural components were located at the accident site. The airframe and engines were examined at the facilities of Air Transport, Phoenix, Arizona.

Fuselage

The fuselage, empennage, and wings were destroyed by the postimpact fire. Flight continuity was established for all flight controls. All flight control system cables were either cut during recovery or exhibited tension overload-type separations. Both elevator trim tab actuators and the rudder trim tab actuator exhibited extensive thermal damage, precluding a determination of the trim tab settings. The flap actuator was observed in the fully extended position, which, according to the manufacturer, is the flaps retracted position.

Engines

Left Engine

The engine remained attached to the airframe firewall by the engine mount. The engine and attached components had sustained severe thermal damage.

The single drive-dual magneto, carburetor, fuel pump and a significant section of the accessory case and oil sump had been consumed by the fire. Impact damage and deformation was noted at the right upper section of the engine encompassing the No. 1 cylinder fins, exhaust pushrod and rocker cover.

The spark plugs were secure at each position and displayed extensive impact and thermal damage.

The various fuel supply lines at the engine and firewall were subjected to the forces of impact energy and the thermal effects of the post impact fire. There was no fuel observed.

The carburetor had been partly consumed by the thermal effects of the post impact fire. The throttle/mixture controls were found securely attached at their respective control arms of the carburetor.

Rotation of the crankshaft was precluded due to impact damage to the engine case and crankshaft at the nose of the engine. The rocker covers were removed. The complete valve train within the rocker box areas remained intact and appeared to be free of any preaccident mechanical malfunction. The combustion chamber of each cylinder was 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. 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 spark plugs, combustion chambers and exhaust system components displayed coloration consistent with normal operation. There was no oil residue observed in the exhaust system gas path.

Holes were drilled through the engine case material in various locations and in-line with the rotational plane of each connecting rod. A lighted borescope was inserted to visualize each connecting rod, crankshaft and camlobes at the respective cylinder position. There was no evidence of lubrication depravation or contamination found. The crankshaft and attached connecting rods remained free of heat distress. The camshaft was intact and each of the camlobes appeared normal in their shape.

Right Engine

The engine remained attached to the airframe firewall by the engine mount. The engine and attached components had sustained extensive thermal damage. The single drive-dual magneto, carburetor, fuel pump and a significant section of accessory case had been consumed by the fire.

The spark plugs were secure at each position and had been subjected to impact and thermal damage.

Rotation of the crankshaft was precluded due to impact damage to the engine case and crankshaft at the nose of the engine. The No 4. aluminum cylinder head was separated from the barrel threads. The rocker covers were removed. The complete valve train within the rocker box areas appeared to be free of any preaccident mechanical malfunction. The combustion chamber of each cylinder was 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. 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 spark plugs, combustion chambers and exhaust system components displayed coloration consistent with normal operation. There was no oil residue observed in the exhaust system gas path.

Holes were drilled through the engine case material in-line with the rotational plane of each connecting rod. A lighted borescope was inserted to visualize each connecting rod, crankshaft and camlobes at the respective cylinder position. There was no evidence of lubrication depravation or contamination found. The crankshaft and attached connecting rods remained free of heat distress. There were no signatures or conditions observed consistent with any preaccident catastrophic mechanical malfunction. The camshaft was intact and each of the camlobes appeared normal in their shape.

Propellers

The two bladed constant speed propellers along with the attached crankshaft flange were displaced from the engine. The crankshaft fracture surface exhibited signatures consistent with torsional overload. The propeller blades remained attached at the hub.

Both blades on both propellers had fractured pitch change knobs as well as counterweight punctures in the cylinder. Impact marks on the preload plates indicated blade angles were at or near the low pitch stop of about 12°. The bearing races were found fractured with ball bearing imprints. Both the left and right side propeller blades displayed similar damage, including leading edge gouges, chordwise/rotational scoring, and bending opposite rotation.

Autopsies for the flight instructor and the pilot receiving instruction were performed by County of San Diego Medical Examiner's Department, San Diego, California. The autopsies found that the cause of death for both pilots was multiple blunt force and thermal injuries.

Toxicology testing performed at the FAA Forensic Sciences Laboratory for both pilots was negative for drugs and alcohol.