Event WPR17LA183

Factual narrative

On August 11, 2017, about 1755 mountain daylight time, a Piper PA28-200, N33732, was substantially damaged when it was involved in an accident near West Jordan, Utah. The pilot and one passenger sustained minor injuries. Two other passengers were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that in preparation for the cross-country flight from South Valley Regional (U42), Salt Lake City, UT to Casper, Wyoming, he performed a weight and balance calculation and determined that the weight was just below maximum gross weight. Before takeoff he accomplished run-up checks, which included leaning the mixture; no anomalies were noted. The 1730 weather advisory reported the wind from 130o at 3 knots, the altimeter setting was 30.03 inches of mercury and the density altitude was 7,400 ft. The pilot stated that after takeoff from runway 16, when the airplane attained an airspeed of 80 mph, the landing gear was retracted, and he retracted one notch of flaps. The airplane climbed to about 350 ft to 400 ft above ground level then stopped climbing and the airplane was not gaining airspeed above 80 mph. The pilot also noted that the stall indication light was on. The pilot lowered the nose of the airplane a little to gain additional airspeed. The airspeed did not increase, and the pilot reported that he feared that they were in trouble and decided to try and return to the airport. About 30° into a right turn, the airplane began to lose altitude, and by the time he had completed the turn, he knew he was not going to make it to the runway. With power lines now in his path and having determined that he would not be able to clear them, the pilot lowered the airplane's nose and flew under the wires. The pilot subsequently landed in an uneven open field, which resulted in substantial damage to the airplane's left wing. The pilot reported that he did not believe that there was a loss of engine power. An engine examination and subsequent successful engine run revealed no evidence of a mechanical malfunction or failure that would have precluded normal operation. At 1755, the local automated weather from U42 indicated wind from 120° at 6 knots, visibility 10 miles, sky clear, temperature 32° C, dew point 12° C, and an altimeter setting of 30.03 inches of mercury. The calculated density altitude at the time of the accident was 7,600 ft. The airplane's climb performance chart indicated that with the airplane at gross weight of 2,650 lbs, full throttle, the mixture leaned, the landing gear and flaps retracted, an airspeed of 100 mph, and a density altitude of 7,600 ft, the rate of climb was about 490 ft per minute. The pilot reported that in preparation for the cross-country flight, he performed a weight and balance calculation and determined that the weight was just below maximum gross weight. The weather advisory from 25 minutes before the accident, the density altitude was 7,400 ft. Before takeoff, he performed run-up checks and leaned the mixture. The pilot stated that after the airplane lifted off, the airplane climbed about 80 mph to about 350 ft to 400 ft above ground level then stopped climbing; the airspeed would not increase above 80 mph and the stall indication light was on. The pilot lowered the nose of the airplane a little to gain additional airspeed, but the airspeed did not increase above 80 mph. The pilot attempted to return to the airport, but about 30° into a right downwind turn, the airplane began to lose altitude, and to the airplane would not reach the runway. The pilot flew under power lines and subsequently landed the airplane in an uneven open field, which resulted in substantial damage to the airplane's left wing. An examination and successful engine run revealed no evidence of a mechanical failure or malfunction that would have precluded normal operation. It is likely that with the airplane at or near gross weight and was taking off at a high density altitude, which would degrade engine performance; thus, the airplane was not able to attain an airspeed sufficient to maintain a positive climb rate.     Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

Hierarchical cause / factor breakdown from the FAA bulk avdata database. Each finding tagged C (Cause) or F (Factor).

• C Personnel issues-Task performance-Planning/preparation-Performance calculations-Pilot - C
• C Environmental issues-Conditions/weather/phenomena-Temp/humidity/pressure-High density altitude-Effect on equipment - C
• C Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Airspeed-Not attained/maintained - C
• — Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Climb rate-Attain/maintain not possible
• — Aircraft-Aircraft oper/perf/capability-Aircraft capability-Maximum weight-Related operating info
• — Aircraft-Aircraft oper/perf/capability-Performance/control parameters-Airspeed-Not attained/maintained