Stall / Spin · NTSB CEN22FA214
CESSNA 152 — Wauwatosa, WI
| Date | May 26, 2022 |
| Location | Wauwatosa, WI |
| Aircraft | CESSNA 152 |
| Purpose of flight | Personal |
| Conditions | Day · Visual Meteorological Cond |
| Phase / occurrence | Takeoff Aerodynamic stall/spin |
| Pilot age | 18 |
| Pilot total time | 54 hrs · Student / very low time |
| Time in type | 54 hrs |
| Fatalities | 1 |
Probable cause
NTSB findings
- Personnel issues-Task performance-Use of equip/info-Use of equip/system-Student/instructed pilot
- Aircraft-Aircraft systems-Flight control system-(general)-Incorrect use/operation
- Personnel issues-Task performance-Use of equip/info-Aircraft control-Student/instructed pilot
- Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Angle of attack-Not attained/maintained
What happened
The student pilot was performing a solo flight and practicing takeoffs and landings. A witness reported, and ADS-B data confirmed, that the student pilot performed a touch-and-go. According to the witness, the airplane touched down long and then took off again. When the airplane lifted off the ground, the flaps remained down. The airplane climbed just above tree height in a nose-high attitude. Shortly thereafter, the left wing dropped, and the airplane descended “straight down.”
During the climb, the student pilot reported to air traffic control (ATC) that he had an engine failure. Subsequently, he reported that he did not have his flaps up.
A performance study was conducted to estimate the drag characteristics of the airplane and the engine power developed during the initial takeoff, subsequent landing, and accident takeoff. Before telling ATC that the flaps were not up, the pilot reported an engine failure; however, according to the study, the energy state of the airplane and the computed power required during the accident climb at flaps 30° are inconsistent with a loss of power.
Instead, performance calculations indicate that the engine was producing power consistent with the power levels achieved during the previous (initial) takeoff and climb, which was performed with the flaps up. The airplane’s lift coefficient, computed using ADS-B data and wind speeds consistent with the reported weather, indicate that the flaps 30° maximum lift coefficient was reached about 13 seconds after the pilot reported an engine failure, and nearly coincident with the time that the pilot reported that the flaps were not up. The increase of the airplane’s lift coefficient to the maximum lift, and the rapid drop in pitch angle, angle of attack, and flight path angle that followed, are consistent with an aerodynamic stall and subsequent loss of control.
Physical examination of the airframe, engine, and propeller did not reveal any preimpact failures or malfunctions that would have precluded normal operation of the airplane.