N4216JPiper PA-28-140 · 1966

On June 25, 2021, about 1000 central daylight time, a Piper PA-28-140, N4216J, was substantially damaged when it was involved in an accident near North Houston Airport (9X1), Porter, Texas. The pilot and passenger were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

According to the pilot and the pilot-rated passenger the preflight, taxi, and run-up checks were normal. The airplane was lined up on the runway for takeoff, full engine power was applied with the brakes held, and the engine instruments were checked before takeoff. After the brakes were released, the airplane accelerated to takeoff speed, and they rotated and began to climb. During the initial climb, the airspeed was not increasing, and the pilot made a right turn to avoid trees. The pilot subsequently landed on a nearby construction site, and the airplane struck an embankment, which damaged the fuselage and left wing.

A flight school owner was on the airport ramp and heard the airplane take off. He estimated the engine was only making about 2,000 rpm during the takeoff roll. He wondered why the airplane was taking off under partial engine power and noted that the airplane rotated about 1,800 ft down the runway. It climbed into ground effect and stayed in ground effect. He lost sight of the airplane and did not hear or see the accident. He also noted that he did not see or hear the pre-takeoff engine check.

The airport manager heard the engine run-up and thought the engine ran rough during the magneto check. He noted that the engine did not sound unusual except when the magneto check was performed and then it would run rough. He reported that the airplane’s flaps were extended but he could not tell how much. He watched the airplane as it took off and noted that the takeoff started with non-aggressive throttle application and the airplane moving slowly down the runway. He thought that the pilot might have been taxiing the airplane back to the ramp area, but the takeoff continued. He did not think it was at full power and thought the pilot was attempting to clear the magnetos. He stated that the airplane became airborne about midfield and he continued to watch thinking the pilot would land straight ahead. The airplane continued to climb slowly, and he did not think it would clear the trees on the south end of the airport property. The airplane started a right turn toward the west and disappeared from his view.

It was reported that the purpose of the flight was to relocate the airplane to another airport since 9X1 was to be permanently closed. The airport permanently ceased operations the day after the accident.

A postaccident examination showed that the front of the airplane incurred heavy impact damage. The engine was tilted down, and the carburetor was partially broken from the engine sump due to impact. A visual inspection of the engine did not reveal any preimpact anomalies. One propeller blade had gentle bending in the aft direction. The engine could be rotated by hand and continuity of the engine valve train and accessory section was confirmed. The upper set of spark plugs was removed and appeared normal. with a light gray color. The engine produced suction and compression during rotation. The engine-driven fuel pump was removed and actuated by hand and appeared to function. The gascolator was damaged and was open due to the accident but had a small amount of debris present. The throttle and mixture controls were connected at the carburetor. The left magneto impulse coupling was very faint when rotated. Spark was observed on the top set of spark plugs. Engine ignition timing was checked and was found to be 25° before top center (BTC) on the right magneto, and about 20° BTC on the left magneto. There was a “SCAT” tube on the engine induction that was crushed. It could not be determined if the SCAT tubing had collapsed before the accident or if the crush-damage was solely a result of impact. The examination of the airplane did not reveal any anomalies that the reported loss of engine power could be attributed to.

According to the Lycoming Operator’s Manual for the O-320 series engine, the ignition timing specification was 25° BTC, for an O-320-E2A, as was installed on the accident airplane

The weather conditions about the time of the accident included a temperature of 31° Celsius (C), dewpoint 24° C, and an altimeter setting of 29.99 inches of mercury. Based on this data and the airport elevation of 125 ft msl, the calculated density altitude at the time of the accident was 1,985 ft. These weather conditions were conducive for light induction icing at cruise and descent power settings.