Accident
On September 1, 2013, at approximately 10:30 a.m. eastern daylight time, an Aeronca 65CA, registration N31915, was substantially damaged during a forced landing after a total loss of engine power shortly after takeoff. The accident occurred at a private airfield in Hardwick, Vermont. The certificated private pilot and a passenger sustained serious injuries. Visual meteorological conditions prevailed, and no flight plan was filed for the personal flight conducted under 14 CFR Part 91.
According to the pilot, a preflight inspection revealed no anomalies. The fuel tank contained 6.5 gallons of fuel, and a fuel sample showed no contaminants. The engine started without abnormal gauge indications, and a run-up check revealed no issues. Using a short-field takeoff procedure from the turf runway, the airplane lifted off, but shortly thereafter the engine began misfiring and lost all power. The pilot maintained a straight-ahead trajectory, and the airplane struck the base of a large tree, resulting in substantial damage to the forward fuselage, engine firewall, and left wing.
Aircraft Information
The tailwheel-equipped airplane was manufactured in 1941 and purchased by the pilot in September 2008. Its most recent annual inspection was completed on May 6, 2013, at a total airframe time of 1,533.56 hours and a tachometer time of 215.36 hours. Maintenance logs indicated that an overhauled carburetor, new mixture control cable, and new carburetor heat control cable were installed on June 22, 2013, followed by a test run with no anomalies. No documentation was found regarding when or by whom the carburetor overhaul was performed. At the time of the accident, the airplane had accumulated about 7.5 hours since the annual inspection.
Pilot Information
The pilot held a private pilot certificate with a single-engine land rating. His most recent FAA third-class medical certificate was issued August 2, 2013. The pilot reported 92.5 total flight hours, including 46.8 hours in the accident airplane make and model.
Examination
Postaccident examination by an FAA inspector revealed that the airplane struck a tree approximately 3 feet in diameter. Fuel odor was present at the site. Flight control continuity from the cockpit to all surfaces was confirmed. The engine was significantly damaged; the crankshaft could not be rotated by hand, but visual inspection of cylinders showed no anomalies. Both magnetos produced spark at all terminal leads when their drives were rotated. Spark plugs were removed, exhibiting black sooty deposits, and several were loose enough to be removed by hand. The carburetor filter was free of debris.
The front/pilot seat assembly separated from the airframe during impact, but seatbelt webbing remained intact and attached to anchor points, with latching mechanisms operating normally.
The carburetor was removed, disassembled, and examined. When vacuum was applied to the fuel inlet, the float needle seated improperly, and the manufacturer's specified float level of 13/32 inch could not be maintained. Application of 0.5 psi fuel pressure filled the carburetor bowl, with the needle/float unable to prevent an excessively rich mixture condition. The float was within weight specification and showed no leaks when immersed in water at 212°F. Main jet, air bleed, and idle air tube orifices were unobstructed and met dimensional specifications.
The airplane was subject to FAA Airworthiness Directive (AD) 47-30-08, requiring modification of seat belt anchorage. Records showed compliance with the AD, and examination revealed L-shaped gussets welded onto the seat tube support structure as specified.