Bellanca 17-30A N8869V accident near Ash Flat, Arkansas

Probable cause

The partial loss of engine power during a go-around resulting in an inadvertent entry into an aerodynamic stall. Contributing to the accident was the inexperience of the low-time pilot.

NTSB analysis

The 80-hour pilot reported that, while attempting to land in gusty wind conditions, the wind suddenly became “super gusty” as the airplane flew over the runway numbers. The pilot performed a go-around; however, when he added throttle, the engine lost all power and due to the low altitude, he was unable to perform an engine restart. He performed a forced landing near the runway but lost control of the airplane and impacted terrain.

The engine was examined, and no anomalies were detected. The left magneto could not be tested due to being waterlogged due to outside storage of the engine before the examination. The National Transportation Safety Board (NTSB) sound spectrum analysis determined that the engine was operating around 1,700 rpm at the time of impact.

The airplane’s EDM-900 was downloaded, and the information plotted. The data was not time coded but did show a sharp reduction of horsepower, exhaust gas temperatures, fuel flow, and RPM, that restored briefly before dropping off, likely due to the accident.

The video recovered from the accident airplane showed the airplane approaching the runway; after crossing the runway threshold, the airplane floated. There was a slight increase in engine power, and the stall warning horn sounded briefly. The airplane continued to float, and the nose of the airplane pitched up and the stall warning horn was briefly heard again. As the pitch angle continued to increase, the stall warning horn was heard. The engine rpm decreased and popping sounds consistent with a rough running engine were noted. A few seconds later the popping noises ceased, and the engine rpm returned to a higher power setting. The pitch angle continued to increase, and the stall warning was audible. The pilot lost control of the airplane as it entered a stall and impacted terrain.

The sound spectrum analysis indicated that the engine ran rough for about 6 seconds, and then the engine rpm was heard increasing to about 2,100 rpm about 9 seconds before it gradually decreased to 1,700 rpm at impact.

The reason for the partial loss of engine power could not be determined.

Text from the NTSB. Open the NTSB docket for CEN22LA152 for the full record.