WPR16LA106

Factual narrative

On May 11, 2016, about 1710 mountain standard time, a Boeing B75N1, N56200, was substantially damaged during a forced landing following a partial loss of engine power during takeoff initial climb at the Winslow-Lindbergh Regional Airport (INW), Winslow, Arizona. The airplane was registered to 3G Classic Aviation LLC., and operated by the pilot under the provisions of Title 14 Code of Federal Regulations Part 91. The private pilot and her passenger were not injured. Visual meteorological conditions prevailed, and no flight plan was filed for the personal flight. The cross-country flight was originating at the time of the accident with an intended destination of Phoenix, Arizona.In a written statement to the National Transportation Safety Board (NTSB) investigator-in-charge (IIC), the pilot reported that prior to takeoff; she conducted an engine run up and pre takeoff checks, which included leaning for density altitude, and conducted a static power check, which was in the normal range. The pilot further reported that during takeoff from runway 29, the airplane accelerated and climbed out normally, with the tachometer indicating 2,250 rpm. As the airplane was about 50 feet above ground level, it began to descend. The pilot stated that in order to avoid powerlines, she performed a left turn to maintain clearance, and verified the throttle, mixture, propeller, fuel, and carburetor heat settings. Subsequently, the airplane struck the ground, rolled about 20 feet, the right main landing gear impacted vegetation, and the airplane cartwheeled. The pilot reported that just prior to landing; she observed the tachometer indicating 2,000 rpm. The pilot added that earlier in the day, they had flown three flights, totaling about 5 hours of flight time. The flights included uneventful takeoffs from two airports with a higher density altitude. Postaccident examination of the airplane by the pilot revealed that all four wings, tail, and fuselage were structurally damaged. The airplane was recovered to a secure location for further examination. Examination of the recovered wreckage revealed that the upper and lower wings were removed by the wreckage recovery company to facilitate wreckage transport. The empennage and right gear leg were also separated from the fuselage. The engine, a Lycoming R-680-E3B, rated at 300 horsepower, remained attached to the fuselage via its mounts. The fuselage was hoisted by a forklift, and the right gear leg was subsequently removed. Throttle, mixture, and propeller control continuity was established from the rear cockpit controls to the engine. The front spark plugs were removed and examined. All nine spark plugs were intact and undamaged. The number one and two spark plugs exhibited black deposits within the electrode area, and the remaining spark plugs exhibited gray deposits within the electrode area. All engine accessories remained attached to the engine, and exhibited no damage. The carburetor was intact, and all linkages were secure. The carburetor fuel screen was removed, and a gray / tan liquid was drained from the carburetor. The fuel screen was free of debris. The liquid smelled similar to 100 Low Lead fuel, and tested negative for water using water finding paste. The air filter was removed, and a red dirt substance was observed within the housing, however, the air filter element appeared to be mostly free of debris. The gascolator screen and bowl was free of debris. The propeller remained attached to the crankshaft, and exhibited an approximate 20 degree bend aft from about mid span on either blade. The spark plugs and carburetor fuel screen were reinstalled. About 8 gallons of fuel was added to the center wing fuel tank. The engine was primed using the airframe fuel pump, and subsequently started. The engine was run for about 10 minutes at various power settings. During the engine run, a maximum power setting of 2,200 rpm and 28 inches of manifold pressure was obtained. A magneto test was performed at 1,500 rpm with a drop of about 75 to 100 rpm noted. The engine was manually shut off using the mixture. Using the reported airport elevation of 4,941 feet, recorded weather conditions from about 14 minutes prior to the accident, the NTSB IIC calculated the density altitude to be about 7,223 feet and a pressure altitude of 4,757 feet. The private pilot reported that, earlier in the day, she had flown three flights, totaling about 5 hours of flight time, which included uneventful takeoffs from two airports with a higher density altitude than that which existed at the accident airport; the calculated density altitude at the time of the accident was about 7,223 ft. The pilot reported that, before takeoff for the accident flight, she conducted an engine run-up and pretakeoff checks, which included leaning the mixture to account for the density altitude. She also conducted a static-power check, which was in the normal range. The pilot reported that, during takeoff for the personal cross-country flight, the airplane accelerated and climbed out normally with the tachometer indicating 2,250 rpm. As the airplane climbed to about 50 ft above ground level, the engine began to lose power, and the airplane started to descend. The pilot turned the airplane left to maintain clearance from obstacles and verified the throttle, mixture, propeller, fuel, and carburetor heat settings. Subsequently, the airplane struck the ground and rolled about 20 ft, the right main landing gear impacted vegetation, and the airplane cart-wheeled. The pilot reported that, just before landing, she observed the tachometer indicating 2,000 rpm. It is likely that the engine's partial loss of power, in combination with the high-density altitude, prevented the airplane from being able to maintain a positive climb rate during takeoff. Postaccident examination of the airplane and engine run did not reveal any evidence of any preexisting anomalies that would have precluded normal operation; therefore, the reason for the partial loss of engine power could not be determined. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

FAA avdata. C = Cause, F = Factor.

• C Not determined-Not determined-(general)-(general)-Unknown/Not determined - C
• — Environmental issues-Conditions/weather/phenomena-Temp/humidity/pressure-High density altitude-Effect on operation