NTSB CAROL · Event
Event NYC01LA220
Aircraft involved
Probable cause & findings
The pilot's failure to follow the engine manufacturer's descent procedure, which resulted in a lean mixture condition and subsequent engine seizure.
Factual narrative
On September 3, 2001, about 1315 eastern daylight time, an amateur built Mini Max 1500R, N962JA, was substantially damaged during a forced landing near Chesapeake, Virginia. The certificated private pilot was not injured. Visual meteorological conditions prevailed for the flight that departed a private airport in Saluda, Virginia; destined for Hampton Roads Executive Airport (PVG), Chesapeake, Virginia. No flight plan was filed for the personal flight conducted under 14 CFR Part 91. The pilot stated that he began a descent from 5,500 feet, toward PVG. During the descent, he maintained a "moderate cruise" power setting, at 5,500 rpm. About 1,500 feet above the ground, the two cycle 2-cylinder Rotax engine lost all power, and the pilot performed a forced landing to a field. During the landing, the airplane struck small trees and sustained substantial damage to the right wing. The pilot added that the engine experienced a "cold seizure." He believed that the descent at cruise power created a lean fuel/air mixture and subsequent lack of lubrication. A Federal Aviation Administration inspector examined the airplane. The inspector observed that both pistons exhibited scoring. Photographs of the damaged pistons and cylinders were forwarded to a representative from the engine manufacturer. According to the manufacturer representative, the failure was directly in line with the exhaust, which was more indicative of a heat seizure, rather than a cold seizure. The representative further stated that a heat seizure was normally associated with excessive exhaust gas temperature, exceeding 1200 degrees F. He assumed that the engine was operating in a lean condition. An excerpt from the manufacturer's make and model engine manual revealed: "During cruise and descending it is very important not to create a lean condition with high rpm and low throttle opening. The less fresh charge the engine gets, the more hot residual gas remains in the cylinder. This raises the temperatures to a critical level. For this reason, you may also experience higher exhaust gas and cylinder head temperatures at reduced throttle openings." Another excerpt from the manual revealed: "Danger! This engine, by its design, is subject to sudden stoppage! Engine stoppage can result in crash landings. Such crash landings can lead to serious bodily injury or death. Never fly the aircraft equipped with this engine at locations, airspeeds, altitudes, or other circumstances from which a successful no-power landing cannot be made, after sudden engine stoppage. Warning! Although these engine types have undergone considerable durability testing, this engine is not a certified aircraft engine. It has not received any individual safety or durability testing and conforms to no aircraft standards. It is for use in experimental and ultralight uncertified aircraft and vehicles only, in which an engine failure will not compromise safety. User assumes all risk of use and acknowledges by his use the he knows this engine is subject to sudden stoppage." The pilot descended from 5,500 feet to 1,500 feet, at a moderate cruise power setting, at 5,500 rpm. About 1,500 feet above the ground, the two cycle 2-cylinder engine lost all power, and the pilot performed a forced landing to a field. The pilot believed that the descent at cruise power created a lean fuel/air mixture. Examination of the engine revealed scoring on both pistons, which was directly in line with the exhaust. According to a representative from the engine manufacturer, that type of failure was indicative of a heat seizure, normally associated with an excessive exhaust gas temperature, exceeding 1200 degrees F. The representative assumed that the engine was operating in a lean condition. According to the manufacturer's engine manual, during cruise and descents, it was very important that to avoid creating a lean mixture condition with high rpm and low throttle opening. Additionally, the manual warned that the engine was subject to sudden stoppage, and conformed to no aircraft standards. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_2001_NYC01LA220.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
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Related research
What the literature says.
Academic papers and agency reports matching this event's aircraft type or causal vocabulary (engine failure). Sourced from NASA NTRS, NTSB Safety Studies, FAA CAMI, AOPA Air Safety Institute, Embry-Riddle Scholarly Commons, arXiv, and the Semantic Scholar academic graph.
- arXiv 2022 · arXiv preprint
Multi-level Adaptation for Automatic Landing with Engine Failure under Turbulent Weather
This paper addresses efficient feasibility evaluation of possible emergency landing sites, online navigation, and path following for automatic landing under engine-out failure subject to turbulent wea…
- NASA NTRS 2019 · Conference Paper
Simulation of Liquid Rocket Engine Failure Propagation Using Self-Evolving Scenarios
Traditional probabilistic risk assessment approaches often require failure scenarios to be explicitly defined through event sequences that are then quantified as part of the integrated analysis.
- NASA NTRS 2019 · Conference Paper
Rocket engine failure detection using system identification techiques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Conference Paper
Rocket engine failure detection using system identification techniques
The theoretical foundation and application of two univariate failure detection algorithms to Space Shuttle Main Engine (SSME) test firing data is presented.
- NASA NTRS 2019 · Technical Memorandum (TM)
A simulator investigation of engine failure compensation for powered-lift STOL aircraft
A piloted simulator investigation of various engine failure compensation concepts for powered-lift STOL aircraft was carried out at the Ames Research Center.
- Semantic Scholar 2019 · Article (AIAA Scitech 2019 Forum)
Impact of Engine Failure Constraints on the Initial Sizing of Hybrid-Electric GA Aircraft
Potential advantages of hybrid-electric aircraft are fuel savings, lower emissions, and reduced noise. Since these aircraft generally apply multiple power sources, they can also be designed to sustain…
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