N1715Q

HISTORY OF FLIGHT

This report was modified July 20, 2007.

On May 12, 2006, at 1147 eastern daylight time, a Cessna C-150L, N1715Q, registered to an operated by a private owner as a 14 CFR Part 91 personal flight, collided with the ground after departing Mathis Airport (GA27), Cumming, Georgia. The airplane was destroyed by impact forces. Visual meteorological conditions prevailed at the time of the accident. The airline transport (ATP) rated pilot and pilot rated passenger were fatally injured. The flight was originating at the time of the accident.

A witness at the airport stated that on the morning of the accident he spoke to the pilot for about 10 minutes. He watched as the pilot and passenger conducted a preflight inspection of the airplane. After the preflight inspection the pilot taxied the airplane to the fuel pumps, where he topped off both fuel tanks with fuel. He stated that the pilot had the flaps extended between "5 and 10 degrees" prior to take off. The pilot taxied out to runway 21, conducted an engine run-up, and began the take off roll. The witness noted that the take off roll was much longer than he expected. The airplane did not rotate and climb until it reached the end of the of the runway. The airplane was in a climb attitude and the airspeed was slow. According to the witness "the airplane just failed to climb". The airplane reached an altitude of approximately 50 feet, and was not going to clear the hill and trees directly off the end of the runway. The airplane "drifted to the left through a low spot in the tree cover on the southwest boundary of the airport". The witness was concerned about what he had seen, got into his vehicle, and departed the airport, believing that there might have been an accident. Shortly thereafter he heard the sounds of emergency vehicles in the distance.

The Forsyth County Sheriff's Office responded to the crash and located the airplane inverted resting against the side of a house in a residential subdivision approximately 1/4 mile west of the airport.

PERSONNEL INFORMATION

Review of information on file with the FAA airman's Certification Division, Oklahoma City, Oklahoma, revealed that the pilot was issued a flight engineer certificate on April 23, 1982, with ratings for turbojet-powered aircraft. The pilot was issued an airline transport pilot certificate on December 10, 2002, with ratings for airplane single engine and multi-engine land. The pilot's aircraft ratings were for the B-727, B-757, B-767, G-S2, MD-11, and B-777. The pilot held a first class medical issued on November 17, 2005, with limitations for lenses that correct for distant vision and possession of glasses that correct for near vision. The pilot's logbooks were not recovered for review.

Review of information on file with the FAA airman's Certification Division, Oklahoma City, Oklahoma, revealed the passenger was issued a private pilot certificate on August 2, 2002. The certificate revealed he had ratings for rotorcraft-helicopter, and 153 hours of civilian flight time. The pilot held a third class medical certificate issued on June 2, 2005, with no medical restrictions.

AIRCRAFT INFORMATION

The airplane is a 1972 Cessna 150L, serial number 15073015. It is a two-seat, high-wing airplane of predominantly aluminum construction with fixed tricycle landing gear. The powerplant is a Teledyne Continental Motors O-200-A, engine serial number 67377-7-A. A review of the maintenance logbooks revealed that the last annual inspection was conducted on January 18, 2006, at an indicated tachometer time of 344.1 hours, and a total time in service of 4952.5. On January 15, 2001, a new tachometer was installed in the airplane at a tachometer time of 4572.57 hours. At the time of the accident the tachometer time indicated a total of 357.6 hours. The Hobbs meter at the accident site indicated 4542.3 hours. The total time since major overhaul was 1008.04 hours. Review of the tachometer time revealed that there were 13.5 hours since the last annual inspection.

METEORLOGICAL INFORMATION

The nearest weather reporting facility at the time of the accident was the Gwinnett County Airport-Briscoe Field (LZU), Lawrenceville, Georgia, located 12 nautical miles southeast of GA27. The 1050 surface weather observation was: wind 310 degrees at 10 knots gusting to 16 knots, visibility 10 statute miles; clouds scattered at 2,900 feet, temperature 61 degrees Fahrenheit, altimeter 29.87. Witnesses present at GA27 stated that the winds were very gusty.

AIRPORT INFORMATION

The Mathis Airport, GA27 has a paved 1,550-foot long runway that is 20 feet wide with an elevation of 1,170 feet. Runway 21, the departing runway has 75-100 foot trees at the departure end with an uphill grade. During an inspection of the runway, it was noted that it curves slightly to the right at the departure end.

WRECKAGE AND IMPACT INFORMATION

The airplane was located resting against the side of a residential home in the Laurel Springs Subdivision in Chaucer Circle. The airplane was in a nose down attitude inverted lying against the sidewall of a local residence. The airplane was approximately 1/4 mile west of the departure end of the runway.

Examination of the airframe revealed the propeller spinner was crushed aft and showed rotational twisting. The engine cowling was crushed around the engine. Removal of the cowling revealed that the engine was displaced aft into the firewall. The firewall was displaced upwards and aft towards the forward doorpost. The nose landing gear assembly was broken away from the nose strut.

The cockpit section was compressed upwards and displaced aft towards the empennage section of the airplane. Both doors were separated from the fuselage, and were buckled upwards. The baggage compartment was crushed to the empennage. The left and right main landing gear struts were attached to the fuselage section of the airplane. The left main landing gear wheel and brake assembly were broken from the landing gear strut. The right main landing gear wheel assembly was connected to the landing gear strut. The right wheel pant was connected to the wheel assembly.

The empennage was broken away from the baggage compartment and was crushed approximately 3-feet aft of the baggage compartment bulkhead. The right horizontal stabilizer exhibited buckling throughout the surface, and the elevator was bent upward on the outboard side of the flight surface. The elevator trim tab was noted in the 2-½ degree tab up position. The left horizontal stabilizer exhibited buckling on the outboard side of the flight surface. The vertical stabilizer was damaged on the top of the stabilizer where the rudder mounted to the stabilizer. The vertical stabilizer and the top of the rudder containing the balance weight were crushed. There were no separated or disconnected flight control cables. Flight control continuity was established from the cockpit controls to all primary and secondary flight control surfaces. The wing flap actuator was found in the retracted position.

The left wing forward spar carry through was broken away from the wing spar. The wing attachment point was connected to the forward spar, and the rear spar. The left wing outboard leading edge was crushed aft. The left wing tip was broken. The left aileron was attached to the wing assembly and exhibited buckling. The left flap was attached to the left flap track and exhibited buckling. The left wing strut was attached to the wing and broken away from the fuselage. Examination of the left fuel tank revealed that it was not breached, and the fuel filler cap was locked. There were blue fuel stains around the fuel filler cap, and the soil under the left wing was heavily soaked with fuel. The vegetation under the wing exhibited browning.

The right wing assembly was attached to the forward spar attachment point. The rear drag spar was broken from the attachment point on the center wing section. The leading edge and wing tip of the wing assembly was crushed aft. The aileron was attached to the wing and the outboard section was bent downward. The flap was attached to the flap track assembly and exhibited buckling. The wing strut was attached to the wing assembly and fuselage. Examination of the right fuel tank revealed that it was not breached and the fuel filler cap was locked. There were blue fuel stains around the fuel filler cap, and the soil under the left wing was heavily soaked with fuel. The vegetation under the wing exhibited browning.

Examination of the fuel selector revealed it was found in the on position. The airplane was inverted for over 24 hours and when turned upright approximately 1 gallon of fuel was drained from the right tank. Approximately 5 gallons of fuel was drained from the left tank, and no fuel was found in the fuel lines. A small amount of fuel was found in the carburetor bowl. All fuel found in the airplane was field-tested with SARGEL and no water was noted. The fuel at the airport was tested with SARGEL and no water was noted in the fuel. Examination of both wing tank fuel finger screens found them free of blockage and debris.

Examination of the engine found it partially attached to the engine mounts on the firewall. Two of the upper engine mounts were broken away from the engine. The exhaust and intake system were impact damaged. The throttle control at the carburetor was at the idle cutoff position, and the carburetor control knob in the cockpit was three inches aft in the idle position. The mixture control cables remained attached to the carburetor, and the control knob in the cockpit was in the locked position. The ignition switch was in the left magneto position. Examination of the magnetos revealed the right hand magneto produced spark on all leads and the impulse coupling engaged when rotated by hand. The left hand magneto produced spark on all leads and impulse coupling engaged when rotated by hand. The ignition wire harness was intact and imp...