Accident Overview
On June 29, 2012, at approximately 1645 eastern daylight time, a Piper PA-28-140, registration N449FL, was substantially damaged following a partial loss of engine power and subsequent collision with terrain near Lakewood Airport (N12), Lakewood, New Jersey. The certificated airline transport pilot and three passengers were not injured. The airplane was registered to a private individual and operated by the pilot under 14 Code of Federal Regulations Part 91 as a personal flight. Visual meteorological conditions prevailed, and no flight plan was filed. The local flight originated from Lakewood Airport about 1630.
Pilot Report
The pilot reported that he was taking three children for a ride. The gross takeoff weight was 1,987 pounds, with a maximum allowable takeoff weight of 2,150 pounds. The first two takeoffs were uneventful. During the initial climb after the third takeoff, the pilot observed a loss of engine performance and the airplane could not maintain proper climb speed. Unable to continue the climb, he set up for a forced landing past the departure end of the runway. Just prior to ground contact, he pulled the mixture control and turned off the master switch. The airplane struck trees and a fence, resulting in substantial damage to the fuselage and both wings.
Post-Accident Examination
A Federal Aviation Administration (FAA) inspector responded to the accident site and examined the wreckage. The inspector confirmed substantial damage to the wings and fuselage. Flight control continuity was established from the cockpit controls to all flight control surfaces. The wreckage was recovered to a local maintenance facility, where a subsequent examination of the engine was performed. The magnetos were turned and produced spark at each spark plug lead. Fuel was present in the fuel gascolator. The engine crankshaft was turned manually to check for cylinder compression. The number 1, 3, and 4 cylinders produced 68, 74, and 79 pounds per square inch (psi) of compression, respectively. The number 2 cylinder produced only 16 psi. Other than some oil leaking from the cylinder when the lower spark plug was removed, no other anomalies were noted.
Maintenance History and Engine Test
The FAA inspector reported that the number 4 cylinder was replaced in March 2012 at the last annual inspection due to low compression. At that time, the number 2 cylinder produced 75 psi compression. At the time of the accident, the engine total time was 3,571 hours, and 1,276 hours since the last major overhaul. Following the FAA inspector's examination, a test run on the engine was performed by a certificated airframe and powerplant mechanic with inspection authorization. The engine was started several times, and all engine parameters were normal. The engine ran normally using the engine-driven fuel pump. The electric fuel boost pump operated when energized by a battery. Both magneto checks were satisfactory. Oil pressure was observed inside the green arc. After the engine was warmed up, a compression check was accomplished, and all cylinders showed normal compression.