The airplane was manufactured in 1958, and was equipped with a Lycoming O-540 series piston engine. Landing Gear Type: Retractable - TricycleĪirframe Total Time: 2918 Hours as of last inspection His most recent FAA third-class medical certificate was issued in November 2015. His most recent flight review was completed in December 2017. He reported a total flight experience of about 250 hours, including about 87 hours in complex airplanes, and about 9 hours in the accident airplane make and model. The pilot held a private pilot certificate with a single-engine land rating. Medical Certification: Class 3 With Waivers/Limitationsįlight Time: (Estimated) 250 hours (Total, all aircraft), 9 hours (Total, this make and model) Subsequent examination by Federal Aviation Administration (FAA) inspectors determined that the there was substantial damage to the airplane fuselage structure. The airplane was lifted and towed to a secure location on the airport. About the intersection of runway 30R and taxiway Echo, when the airplane was traveling about 30 mph, the landing gear "suddenly collapsed." The airplane slid on its belly, and came to a stop approximately 150 ft beyond taxiway Echo.Īfter the ATCT controllers determined that the airplane was immobilized, and verified that the pilot was uninjured, the controllers dispatched airport safety personnel to assist. The approach and touchdown were normal and uneventful, and the pilot then began to brake the airplane. He confirmed with SJC ATCT that he was cleared to land, and turned final for runway 30R. The pilot began a descent and turned onto base leg, and then again verified that the landing gear was down and locked. Once stabilized on the downwind leg, the pilot reduced the engine power, extended the landing gear, and verified that the landing gear position indicator light was illuminated green, which denoted that the landing gear was down and locked into position. After he crossed over the airport, he entered a right downwind leg for runway 30R. Near the "Pruneyard" visual flight rules (VFR) reporting point, he contacted the SJC air traffic control tower (ATCT), and was instructed to cross midfield at 2,000 ft. He departed F70 that afternoon, destined for SJC. Early on the day of the accident, the pilot flew the airplane from CRQ to F70, and landed uneventfully. The flight had originated from French Valley Airport (F70), Murrieta/Temecula, California about 1730.Īccording to the pilot, he had rented the airplane from Plus One Flyers, located at McClellan-Palomar Airport (CRQ), Carlsbad, California. Visual meteorological conditions prevailed at the time of the accident and no flight plan was filed. The airplane was registered to two private individuals, and was operated by the pilot as a Title 14 Code of Federal Regulations Part 91 personal flight. Mineta San Jose International Airport (SJC), San Jose, California. On May 20, 2018, about 1950 Pacific daylight time, a Piper PA24-250 airplane, N244TW, sustained substantial damage shortly after landing at Norman Y. Investigation Docket - National Transportation Safety Board: įlight Conducted Under: Part 91: General Aviation - Personal The large-displacement, horizontally-opposed eight-cylinder piston engine was built specifically for the PA-24-400.The National Transportation Safety Board did not travel to the scene of this accident.įederal Aviation Administration / Flight Standards District Office San Jose/Los Angeles, CaliforniaĪviation Accident Factual Report - National Transportation Safety Board: It was powered by the Lycoming IO-720 engine rated at 400 horsepower. In 1964, Piper Aircraft introduced the PA-24-400. In 1962, electrically-operated flaps were developed. In 1961, newer versions were equipped with auxiliary fuel tanks. Early PA-25-250s were the same PA-24-180 built with manually-actuated flaps and had a fuel capacity of 60 US gallons. ![]() The variant had a maximum cruise speed of 160 knots. It was powered by a Lycoming O-540 engine with a maximum thrust of 250 horsepower. In 1958, the second version designated as PA-24-250 was introduced. ![]() The PA-24-180 had a cruise speed of 116 to 139 knots and a travel range of 700 nautical miles. The normal fuel capacity of the variant was 60 US gallons. It was designed with a swept tail, an all-moving stabilator, and manually-actuated flaps. Several production versions were Designated as PA-24-180, and were powered by a Lycoming O-360-A1A engine rated at 180 horsepower. On October 21, 1957, the initial production variant of the Comanche conducted its maiden flight. Several production versions were produced. On June 20, 1956, the first of the two prototypes of the Comanche was completed.
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