GAA19CA570
2019-09-25 · Lexington, Nebraska, United States · Serious · 1 aircraft · Status: Completed
Airport LXN
Current FAA registration · N1216N
- Make / Model
- CIRRUS DESIGN SR22
- Year of manufacture
- 2003 · 16 years old at event
- Engine
- CONT MOTOR IO-550 SERIES (300 hp)
- Seats / Engines
- 4 seats · 1 engine
- Last airworthiness date
- 20030511
- ADS-B equipped
- Yes — Mode-S A05AA0
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
The pilot's exceedance of the airplane's critical angle of attack during a go around, which resulted in an aerodynamic stall and a hard landing.
Factual narrative
The pilot reported that, during approach to land will full flaps, he decided to perform a go around and applied full power. The airplane started turning left and he applied right rudder. The airplane was "low and slow" and was unable to gain altitude. The airplane continued to drift left then subsequently, landed hard in an adjacent field left of the runway. The pilot further reported that, during the go around, he did not adjust the flap setting to the takeoff setting. The airplane sustained substantial damage to the left wing. The pilot reported that there were no preaccident mechanical failures or malfunctions with the airplane that would have precluded normal operation. The pilot added that he did not remember if the stall warning horn was going off, but believed that the airplane aerodynamically stalled before impact. The pilot reported that the wind was from 040° at 20 knots, gusting to 30 knots. The airport's automated weather observation station reported that, about 5 minutes before the accident, the wind was from 050° at 12 knots, 10 statute mile visibility, sky clear, temperature 23°C (73°F), dew point 7°C (45°F), altimeter 29.98" Hg. The airport field elevation was 2412 ft. The pilot was departing on runway 32. The pilot operating handbook checklist titled "Balked Landing/Go-Around" stated in part: 1. Autopilot – DISENGAGE 2. Power Lever – FULL FORWARD 3. Flaps – 50% 4. Airspeed – 75-80 KIAS After clear of obstacles: 1. Flaps – UP The manufacturer published a performance chart titled "Balked Landing Rate of Climb." The calculated rate of climb with full flaps during the balked landing was about 1,168 ft per minute. The pilot reported that, during approach to land will full flaps, he decided to perform a go around and applied full power. The airplane started turning left and he applied right rudder. The airplane was "low and slow" and was unable to gain altitude. The airplane continued to drift left then subsequently, landed hard in an adjacent field left of the runway. The pilot further reported that, during the go around, he did not adjust the flap setting to the takeoff setting. The airplane sustained substantial damage to the left wing. The pilot reported that there were no preaccident mechanical failures or malfunctions with the airplane that would have precluded normal operation. The pilot added that he did not remember if the stall warning horn was going off, but believed that the airplane aerodynamically stalled before impact. The pilot reported that the wind was from 040° at 20 knots, gusting to 30 knots. The airport's automated weather observation station reported that, about 5 minutes before the accident, the wind was from 050° at 12 knots, 10 statute mile visibility, sky clear, temperature 23°C (73°F), dew point 7°C (45°F), altimeter 29.98" Hg. The airport field elevation was 2412 ft. The pilot was departing on runway 32. The pilot operating handbook checklist titled "Balked Landing/Go-Around" stated in part: 1. Autopilot – DISENGAGE 2. Power Lever – FULL FORWARD 3. Flaps – 50% 4. Airspeed – 75-80 KIAS After clear of obstacles: 1. Flaps – UP The manufacturer published a performance chart titled "Balked Landing Rate of Climb." The calculated rate of climb with full flaps during the balked landing was about 1,168 ft per minute. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12
NTSB Findings
FAA avdata. C = Cause, F = Factor.
- C Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Angle of attack-Capability exceeded - C
- C Personnel issues-Task performance-Use of equip/info-Aircraft control-Pilot - C
- — Environmental issues-Conditions/weather/phenomena-Wind-Crosswind-Effect on operation
- — Personnel issues-Task performance-Use of equip/info-Use of checklist-Pilot
Verbatim from NTSB's published report. Source file
NTSB_2019_GAA19CA570.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
Search this event elsewhere
External sources are reported, not agency: signal that something happened, not fact about what happened.
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Related research
Matched on aircraft type or causal vocabulary (stall, go-around, autopilot). All research papers
- 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 2025 · arXiv preprint ROSflight 2.0: Lean ROS 2-Based Autopilot for Unmanned Aerial Vehicles
ROSflight is a lean, open-source autopilot ecosystem for unmanned aerial vehicles (UAVs). Designed by researchers for researchers, it is built to lower the barrier to entry to UAV research and acceler…
- arXiv 2025 · arXiv preprint ROSplane 2.0: A Fixed-Wing Autopilot for Research
Unmanned aerial vehicle (UAV) research requires the integration of cutting-edge technology into existing autopilot frameworks.
- NASA NTRS 2025 · Conference Paper A Training Study to Improve Monitoring During A Go-Around
As part of an FAA program to improve go-around (GA) safety, we were asked to determine if we could improve the performance of the Pilot Monitoring (PM) during a GA maneuver.
- Flight Safety Foundation 2024 · FSF / AeroSafety World Go-Around Safety Forum Findings
Foundation Go-Around Safety Forum technical findings — examines why pilots fail to execute go-arounds when criteria are met (stabilized approach gate not met, energy state out of envelope, traffic con…
- arXiv 2024 · arXiv preprint A Data-Driven Autopilot for Fixed-Wing Aircraft Based on Model Predictive Control
Autopilots for fixed-wing aircraft are typically designed based on linearized aerodynamic models consisting of stability and control derivatives obtained from wind-tunnel testing.