NTSB CAROL · Event
Event FTW00LA019
Registry · N4807F
FAA Aircraft Registry record.
Make / Model
CESSNA TU206A
Year of manufacture
1966 · 33 years old at event
Engine
CONT MOTOR GTSIO-520-C (340 hp)
Seats / Engines
6 seats · 1 engine
Last airworthiness date
19660308
ADS-B equipped
Yes — Mode-S A5EBEC
Registrant of record
WINKLER JEFFERY L
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
The total loss of power for undetermined reasons and the pilot's failure to maintain airspeed, while clearing a ditch during a forced landing, resulting in an inadvertent stall. A factor was the ditch.
Factual narrative
On October 23, 1999, at 1250 central daylight time, a Cessna TU206A airplane, N4807F, was substantially damaged when it landed hard during a forced landing following a loss of engine power while in the traffic pattern at the Le Maire Airport, Jeanerette, Louisiana. The airplane was owned by a private individual and operated by Skydive Acadiana. The commercial pilot, sole occupant, was not injured. Visual meteorological conditions prevailed, and a flight plan was not filed for the 14 Code of Federal Regulations Part 91 local flight. The flight carrying parachutists originated from the Le Maire Airport approximately 1220. According to the skydive operator, the airplane was descending after the pilot released the jumpers. During the descent through 4,000 feet msl, the engine lost power. The operator stated that the pilot adjusted the mixture and the engine restarted. While the airplane was on downwind, the engine lost power again. The pilot made a forced landing toward the runway. The plane touched down hard and short of the runway. The nose landing gear collapsed and the fuselage buckled. In the enclosed Pilot/Operator Aircraft Accident Report (NTSB Form 6120.1/2), the pilot stated that the airplane climbed to 12,500 feet with "no problems." He reported that he had the left fuel tank selected with 15 gallons of fuel in the tank. He added that he reduced the manifold pressure to 17 inches for the descent, deployed the speed brakes and closed the cowl flaps. While descending through 6,000 feet msl, the pilot "heard a loss of power." The pilot stated that he switched the fuel selector to the right fuel tank, and then returned the selector to the left fuel tank. He applied full rich mixture and regained power. He left the mixture at full rich for the rest of the descent; however, at 600 feet, while turning from downwind to base, the engine again lost power. The pilot turned the airplane toward the runway, and applied back elevator pressure to clear a ditch at the approach end of the runway. He stated that the airspeed was indicating "65-70 knots", but he "[did not have any] elevator control," and the airplane "nosed in and bounced about 50 feet," coming to rest nose down. According to the FAA inspector, who visited the accident site, fuel was found in the lines to the engine. There was an undetermined "small quantity" of fuel in the wing tanks. Engine control continuity was confirmed from the cockpit to the engine. The throttle, propeller, and mixture controls were found in the full forward position. According to a mechanic, who test ran the engine following the accident, the left fuel tank contained 10 gallons of fuel and the right fuel tank contained 13 gallons of fuel. The mechanic stated that he started and test ran the engine on the airplane. He ran the engine through all parameters for 25 minutes and found no anomalies. The pilot stated that while descending through 6,000 feet msl, the engine lost power. The pilot reported that when he enriched the mixture, the engine regained power. He stated that he left the mixture full rich; however, when the airplane was at 600 feet and turning to base, the engine lost power again. He stated that he attempted to clear a ditch on the approach end of the runway with back elevator pressure. The airplane then 'nosed in and bounced about 50 feet,' coming to rest nose down. A mechanic, who test ran the engine following the accident, stated that he started the engine and ran it on the airplane for 25 minutes through all its parameters with no anomalies noted. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1999_FTW00LA019.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 (stall). Sourced from NASA NTRS, NTSB Safety Studies, FAA CAMI, AOPA Air Safety Institute, Embry-Riddle Scholarly Commons, arXiv, and the Semantic Scholar academic graph.
- NASA NTRS 2026 · Conference Paper
Computational Analysis of Steady State Aerodynamics of Transonic Truss-Braced Wing Configuration in Deep Stall
This study presents a computational investigation of steady state aerodynamics of the Subsonic Ultra-Green Aircraft Research (SUGAR) Transonic Truss-Braced Wing (TTBW) configuration over a wide range …
- arXiv 2023 · arXiv preprint
Automating Bird Diverter Installation through Multi-Aerial Robots and Signal Temporal Logic Specifications
This paper tackles the task assignment and trajectory generation problem for bird diverter installation using a fleet of multi-rotors.
- arXiv 2023 · arXiv preprint
Variation of Critical Crystallization Pressure for the Formation of Square Ice in Graphene Nanocapillaries
Two-dimensional square ice in graphene nanocapillaries at room temperature is a fascinating phenomenon and has been confirmed experimentally.
- arXiv 2023 · arXiv preprint
Polycrystallinity enhances stress build-up around ice
Damage caused by freezing wet, porous materials is a widespread problem, but is hard to predict or control. Here, we show that polycrystallinity makes a great difference to the stress build-up process…
- arXiv 2022 · arXiv preprint
Enhanced Prediction of Three-dimensional Finite Iced Wing Separated Flow Near Stall
Icing on three-dimensional wings causes severe flow separation near stall. Standard improved delayed detached eddy simulation (IDDES) is unable to correctly predict the separating reattaching flow due…
- Embry-Riddle Scholarly Commons 2021 · Journal article (JAAER)
Analysis on the Negative Emotional, Physiological, and Cognitive Responses Elicited from of the Activation of a Stall Alarm
Failing to identify an aerodynamic stall can lead to the inability of an aircraft to sustain flight. To warn pilots of an impending or fully-developed stall, many aircraft have safety devices installe…
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