N4313E

HISTORY OF FLIGHTOn October 8, 2015, about 1830 eastern daylight time, a Piper PA-38-112, N4313E, operated by Asterix Aviation LLC, was substantially damaged when it impacted terrain after a loss of engine power in Jasper, Georgia. The student pilot was fatally injured. Visual meteorological conditions prevailed, and no flight plan was filed for the local solo instructional flight conducted under the provisions of 14 Code of Federal Regulations (CFR) Part 91, which departed from Pickens County Airport (JZP), Jasper, Georgia, about 1720.

According to the student pilot's flight instructor, the student pilot was on his second supervised solo flight. The instructor reported that he saw the student pilot perform the preflight inspection of the airplane and that the student pilot "reported to him" that 14 gallons of fuel were in the airplane. The flight instructor could not recall if he backed the student up by visually checking the fuel quantity himself and could not recall if the student used a fuel stick when checking the quantity.

The flight school's general manager, who was leaving the airport at the time, saw the flight instructor on the ramp using his mobile phone while the student was performing the preflight inspection.

The flight instructor reported that, after takeoff from JZP, the student flew to the practice area and returned to the airport about an hour later. The student then performed a touch-and-go landing on runway 16. During climb after the touch-and-go, the flight instructor heard the engine suddenly stop running. The airplane then "sunk down," and he saw the airplane turn to the left like the student pilot was going to return to the airport. The airplane then appeared to enter an aerodynamic stall and then spin to the left. It descended rapidly while still in the spin until it was lost from view behind trees, and the flight instructor heard the sound of impact. PERSONNEL INFORMATIONStudent Pilot

According to Federal Aviation Administration (FAA) airman records and pilot records, the student pilot, age 21, held a third-class medical with a student pilot certificate issued on August 24, 2015.

Review of pilot records indicated that he had taken his pre-solo written exam on September 11, 2015. Before the accident flight, he had accumulated 13.5 total hours of flight experience, 1.3 hours of which were in solo flight. His previous supervised solo flight had occurred on September 21, 2015 (17 days before the accident flight). No dual instruction was logged after that date.

Flight Instructor

The flight instructor, age 31, held a commercial pilot certificate with ratings for airplane single-engine land, airplane multi-engine land, and instrument airplane. He also possessed a flight instructor certificate with ratings for airplane single-engine and instrument airplane. He reported that, during the previous year, he had soloed 10 students, and, at the time of the accident, he had accumulated about 3,400 hours of flight experience, 2,900 of which were as flight instructor. AIRCRAFT INFORMATIONThe airplane was a 2-seat, single engine, low-wing, fixed-gear monoplane of conventional metal construction. It was equipped with a 4-cylinder, air-cooled, horizontally opposed, normally aspirated, 112-horsepower Lycoming O-235-L2C engine, driving a metal, two-blade Sensenich 72CK-0-56, fixed pitch propeller.

According to FAA airworthiness records and airplane maintenance records, the airplane was manufactured in 1978. The airplane's most recent annual inspection was completed on October 3, 2015. At the time of the inspection, the airplane had accrued about 3,147 total hours of operation.

Review of the airplane's fuel system indicated that fuel was stored in two 16-gallon (15 gallons usable) fuel tanks, giving the airplane a total capacity of 32 gallons (30 gallons usable). The fuel tank selector control was in the center of the engine control quadrant; the selector had three positions: right, left, and off. A fuel quantity gauge for the left fuel tank was located adjacent to the left side of the fuel selector, and a fuel quantity gauge for the right fuel tank was located adjacent to the right side of the fuel selector.

According to the Piper PA-38-112 Pilot's Operating Handbook (POH), during the preflight inspection, the fuel quantity gauges were to be checked, the fuel tank sumps and fuel strainer were to be drained, and the fuel quantity and color were to be visually checked by opening the fuel tank caps and looking inside each of the fuel tanks.

Review of the POH also indicated that:

- At a power setting of 75%, the engine would consume fuel at a rate of 6.5 gallons per hour (gph).

- At a power setting of 65%, the engine would consume fuel at a rate of 5.75 gph.

- At a power setting of 55%, the engine would consume fuel at a rate of 5.0 gph.

Further review of the POH indicated that, at a 65% power setting, endurance would be about 4.5 hours.

Examination of fuel receipts revealed that the airplane had last been refueled on October 5, 2015. Examination of the "Time Sheet" (aircraft flight log) that was recovered from the wreckage indicated that the airplane's recording hour meter read 1,533.0 at the time of the last refueling. The sheet further indicated that the airplane had been flown on four other flights before the accident flight and that, when the accident occurred at an hour meter reading of 1,537.9, the airplane had been operated about 4.9 hours since the last refueling. METEOROLOGICAL INFORMATIONThe recorded weather at JZP, at 1835, about 5 minutes after the accident, included: calm winds, 10 miles visibility, clear skies, temperature 24°C, dew point 12°C, and an altimeter setting of 30.15 inches of mercury. AIRPORT INFORMATIONThe airplane was a 2-seat, single engine, low-wing, fixed-gear monoplane of conventional metal construction. It was equipped with a 4-cylinder, air-cooled, horizontally opposed, normally aspirated, 112-horsepower Lycoming O-235-L2C engine, driving a metal, two-blade Sensenich 72CK-0-56, fixed pitch propeller.

According to FAA airworthiness records and airplane maintenance records, the airplane was manufactured in 1978. The airplane's most recent annual inspection was completed on October 3, 2015. At the time of the inspection, the airplane had accrued about 3,147 total hours of operation.

Review of the airplane's fuel system indicated that fuel was stored in two 16-gallon (15 gallons usable) fuel tanks, giving the airplane a total capacity of 32 gallons (30 gallons usable). The fuel tank selector control was in the center of the engine control quadrant; the selector had three positions: right, left, and off. A fuel quantity gauge for the left fuel tank was located adjacent to the left side of the fuel selector, and a fuel quantity gauge for the right fuel tank was located adjacent to the right side of the fuel selector.

According to the Piper PA-38-112 Pilot's Operating Handbook (POH), during the preflight inspection, the fuel quantity gauges were to be checked, the fuel tank sumps and fuel strainer were to be drained, and the fuel quantity and color were to be visually checked by opening the fuel tank caps and looking inside each of the fuel tanks.

Review of the POH also indicated that:

- At a power setting of 75%, the engine would consume fuel at a rate of 6.5 gallons per hour (gph).

- At a power setting of 65%, the engine would consume fuel at a rate of 5.75 gph.

- At a power setting of 55%, the engine would consume fuel at a rate of 5.0 gph.

Further review of the POH indicated that, at a 65% power setting, endurance would be about 4.5 hours.

Examination of fuel receipts revealed that the airplane had last been refueled on October 5, 2015. Examination of the "Time Sheet" (aircraft flight log) that was recovered from the wreckage indicated that the airplane's recording hour meter read 1,533.0 at the time of the last refueling. The sheet further indicated that the airplane had been flown on four other flights before the accident flight and that, when the accident occurred at an hour meter reading of 1,537.9, the airplane had been operated about 4.9 hours since the last refueling. WRECKAGE AND IMPACT INFORMATIONThe airplane came to rest in a small, grass-covered, automobile parking area located about 1,687 ft from the departure end of runway 16. All major components of the airplane were identified on site. The initial impact point was located 36 ft on a 252° magnetic heading from where the airplane had come to rest. There was no discernable wreckage path, and numerous components were spread throughout the area of the accident site.

Examination of the wreckage revealed that the aft fuselage was almost completely separated from the cabin. The engine was separated from the firewall; the propeller was separated from the engine; and the wings remained attached to their fittings.

Examination of the flight control system revealed no evidence of any preimpact failures or malfunctions, and control continuity was established from the rudder, elevator, and ailerons to the cockpit controls. The wing flaps were in the 34° (fully extended) position.

Examination of the cabin revealed that the master switch was in the "ON" position, and the magneto switch was in the "BOTH" position. The throttle was full forward; the mixture was full rich; and the primer was in and locked. The electric fuel pump was in the "OFF" position. The recording hour meter indicated 1,537.9 operating hours. A broken fuel stick made from a wooden dowel was found in the cabin. The dowel had the airplane registration number hand-written on it in ink, as well as a hand-drawn graduated scale. It also contained the hand-written words: "BOTTOM OF TANK IS 4 GAL."

Examination of the propeller revealed that damage to the nose spinner was concentrated on one side where it displayed crush and compression damage. Both propeller blades displayed minimal aft bending, minimal rotational scoring, and no evidence of leadin...