Georgia

According to Atlanta Air Route Traffic Control Center (ARTCC) personnel, the pilot was given the current weather information before attempting his first instrument approach into Gwinnett County Airport-Briscoe Field (LZU), Lawrenceville, Georgia, which included: winds calm, visibility 1/2-mile in fog, and ceiling 100 feet. The pilot acknowledged the current weather information and elected to continue for the instrument landing system (ILS) runway-25 approach. During the first landing attempt, the pilot reported that he was going to execute a missed approach, but that he saw the airport below and wanted to attempt another approach. The ARTCC controller provided the pilot with radar vectors back to the ILS runway-25 approach and again updated the pilot with current weather conditions. During the second approach the tower controller advised the pilot that he was left of the runway-25 centerline. Shortly after the pilot acknowledged that he was left of the centerline, the tower controller saw a bright "orange glow" off of the left side of the approach end of runway 25. Although the weather conditions were below approach minimums for the runway 25-approach, the pilot elected to attempt the landing. A flight inspection of the ILS was completed on December 26, 2006, and the results of the inspection revealed that the ILS runway-25 approach system was satisfactory. Examination of the airframe, flight control system components, engines and system components revealed no evidence of preimpact mechanical malfunction.

The crew departed Chattanooga-Lovell Field on a training flight to Pensacola-Forrest Sherman Field NAS, Florida. About 20 minutes into the flight, while cruising at low altitude, the aircraft contacted a tree and crashed a mile further on the slope of Mt Johns, near Villanow, Georgia. All four occupants were killed.

While executing an instrument approach to land on runway 25, the airplane collided with the runway, and collapsed the right main landing gear. The airplane subsequently burst into flames after the pilot and passenger exited the airplane. Post-accident examination of the engines found both the left and right engine fuel controls in a low power setting. Examination of the propeller control found both propellers at 30-degrees. The pilot did not report any flight control or mechanical problems during flight.

Upon arriving at the destination airport, the controller cleared the flight for localizer 32 approach and informed the pilot that radar service was terminated and a frequency change was approved, report canceling IFR this frequency. The pilot acknowledged the clearance. A review of radar data revealed that the airplane was on course and lined up with the runway when the airplane collided with trees and the ground one mile south of runway 32. A review of information on file with Southeastern Air Charter, Inc., the operator of the accident airplane, found that the pilot's most recent Airman Competency/Proficiency Check was conducted in a Cessna 210. There were no records to indicate the pilot had undergone a flight-check in the Beech 200, as outlined in the Corporations FAA Approved Operational Specifications. Examination of the airframe and engines found no pre-existing discrepancies that would have precluded the airplane from operating properly prior to impact. Surface Weather Observations reported near the time of the accident. was visibility 1 to 1¼ miles; ceiling 200 feet overcast. A review of the approach plate found the minimum descent altitude for the approach to be 325 AGL and visibility 1 mile.

A witness at the airport stated the airplane appeared to use half of the 8,000-foot runway on takeoff roll, and the climb out appeared "very flat." During climbout, the pilot reported to the tower controller the airplane "lost an engine," and he announced intentions to return to the runway. The controller stated he noticed the airplane continued straight out and appeared to be losing altitude. Witnesses north of the airport observed the airplane flying low and described its engine noises as "erratic," "skipping," "sputtering," and "some sort of backfire." One witness stated the airplane was moving slowly to the north with a high nose-up angle, and the airplane "appeared to stall" then dove vertically into the trees. Examination of the accident site revealed wreckage debris and broken trees were scattered approximately 120 feet. The airframe, engines, and the right propeller sustained fire damage. The left propeller, top forward portion of the left engine case, and the left propeller gear shaft and bearings were not located. Examination of recovered components revealed no evidence of mechanical malfunction could be determined. According to the Pilot's Operating Handbook for the Piper PA-31P, the stall speed for the airplane with the gear and flaps up is: "(7800 lbs) 80 KCAS, 81 KIAS."

The VFR repositioning flight departed Rome, Georgia en route to Canton, Georgia but never arrived. Late on the evening of April 10, 2003, the pilot's spouse contacted the local authorities when her husband did not arrive at home or call. The spouse stated that her husband flew out of Rome early Thursday morning headed to Augusta, Georgia to pick up an unknown number of passengers and fly them back to Rome, Georgia. The authorities confirmed that the passengers had arrived at their destination. The Civil Air patrol began a search and located the airplane on the side of "Bear Mountain" in Canton, Georgia, on April 11, 2003. The wreckage site was located 11.3 nautical miles west of Cherokee County Airport, Canton, Georgia, and 26 nautical miles east of Rome, Georgia on the west side of Bear Mountain. The mountains ridgeline runs northeast and southwest, near the town of Waleska, Georgia. The field elevation at the crash site was 1,750 feet above mean sea level (msl) and the peak of Bear Mountain was 2,268 feet msl. The upslope of the terrain at the site was estimated at 30-40 degrees. Examination of the airframe, flight controls, engine assembly and accessories revealed no anomalies.

The flight was in cruise flight at 27,000 feet when the airplane encountered unforecasted severe turbulence. The pilot made a "mayday" on the airplane radio to Jacksonville Center. Within several seconds the airplane accelerated from 175 knots through 300 knots ground speed and descended from 27,000 feet to 16,500 feet. The airplane disappeared from radar coverage and was located by Sheriff Department personnel 15 miles north of Homerville, Georgia, in a swampy area. Airframe components recovered from the accident site were submitted to the NTSB Materials laboratory for examination. The examinations revealed all failures were due to overload. Examination of the airframe revealed that the airframe design limits were exceeded. The pilot did not obtain a weather briefing before the flight departed.

The airplane was equipped with two experimental Engine AIR Power Systems TSIVD-427, 500-horsepower, liquid-cooled, turbocharged, V8 engines. During previous flights, the right engine lost boost then overboosted intermittently, and attempted repairs were unsuccessful. The pilot elected to fly the airplane to its home base for further troubleshooting. During cruise flight, the pilot reported an engine was surging, declared an emergency, and received vectors toward the airport. The airplane collided into a field beside the airport runway and caught fire. The airplane had a total of 8 to 10 hours of flight time at the time of the accident. Records revealed that two days after the airplane's first test flight, the pilot flew the airplane from Melbourne, Florida, to an airport 336 nm miles away, then flew it to Canada to display it at a fly-in.The FAA operating limitations for the airplane restricted its operation to flight test only, which was proposed to consist of 100 flight hours, since the installation of the modified engines. No single-engine performance data was available for this airplane. Examination of the engines and accessories revealed extensive fire and impact damage. Continuity of the crankshaft, valves, rods, and pistons was established for the right engine by manually rotating the propeller reduction control unit.

The flight made two instrument approaches to minimums and executed two missed approaches before the crew elected to land about 25 miles south and wait for the low ceiling condition to improve. An hour later, having topped off fuel tanks, confirmed by telephone that destination weather was improving, the flight re-launched to their original destination. They executed a GPS-A, (circling) instrument approach, broke out of instrument conditions about 100 ft. above minimums, (600 feet, agl) and about one mile from the runway, and started a right downwind turn to enter a left base leg for landing runway 30. During the turn to final approach, the crew extended the landing gear and flaps for landing, and according to the copilot, the pilot flew through the extended runway centerline requiring a, " teardrop turn back toward the runway. In the turn the bank angle was about 45 degrees, the descent rate increased rapidly and a faint warning [stall warning] sounded, the nose then pitches down and [the PIC] screams as he shoves both throttles full forward and using both hands pulls the yoke back and as soon as the nose came above the horizon the plane impacted the ground wings were fairly level mains hit first and we paralleled the runway about fifty feet or so to the right of the runway". The impact sheared the landing gear, shed the propellers, broke the engines from their mounts, started a fire in the left engine, and broke open the fuselage 3 feet aft of the cabin pressure bulkhead. The two pilots and three of four passengers received minor injuries, and one passenger received serious injuries. The cockpit voice recorder was shipped to the NTSB Vehicle Recorders Laboratory in Washington, DC. Readout of data recorded from the cockpit area microphone revealed that 6.4 seconds before impact the stall warning sounded, and 4.4 seconds before impact the altitude alerter sounded.

The DC-3 experienced an in-flight engine fire, and made a forced landing at nearby airport, following the separation of the right engine assembly from the airframe. According to the pilot, during cruise flight, at 5000 feet, he heard a loud "bang" and saw a reflection of fire on his left engine nacelle. Fire damage was found on the trailing edge of the right wing and on the landing gear assembly. The engine examination also showed that No. 12 cylinder had separated from the main case. Evidence of oil from the No. 12 cylinder was found across engine and exhaust systems. Further examination revealed Nos. 7, 8 and 9 cylinders also failed and separated, and the engine seized and separated from the airframe.