On July 2, 2022, about 0829 central daylight time, a Piper PA-28-140 airplane, N270SA, sustained substantial damage when it was involved in an accident near Oklahoma City, Oklahoma. The pilot sustained serious injuries and the passenger was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that, after takeoff from runway 18 at the Sundance Airport (HSD), Oklahoma City, Oklahoma, the airplane did not perform as it normally would. He stated that, as the airplane climbed above the height of the nearby houses, the airspeed and altitude began to decrease. Unable to climb, he allowed the airplane to drift west to avoid “putting anything in danger.” As he began a right turn, he lowered the nose to remain under transmission lines, but the airplane seemed to immediately “fall out of the sky.” The airplane subsequently impacted the ground and slid to a stop, which resulted in substantial damage to both wings and the fuselage. Several witnesses described seeing the airplane low to the ground, not climbing, and in a right turn before it impacted the ground. A review of weight and balance documentation revealed that the airplane had a basic empty weight of 1,263.04 lbs. The pilot stated that he weighed 180 lbs and the passenger weighed about 300 lbs. He stated that the airplane was filled to the tabs with fuel, which equated to about 36 gallons. With no reported cargo, the airplane’s weight totaled 1,959.04 and the center of gravity (CG) was 86.24 inches aft of datum. The maximum gross weight of the airplane was 2,150 lbs and the forward CG limit was 84 inches and the aft CG limit was 95.9 inches. When the weight and balance envelope is viewed in a graphical format in the Type Certificate Data Sheet, it becomes evident that the forward CG limit changes with weight. When the airplane was 1,650 lbs or less, the CG forward limit was 84 inches and the aft limit was 95.9 inches. At 1,975 lbs, the forward limit was 85.9 inches and the aft limit was 95.9 inches. (See Figure). Weight and Balance Envelope from the Type Certificate Data Sheet for Serial Number 28-21576 A postaccident examination of the airframe and engine did not reveal any preimpact mechanical malfunctions or failures that would have precluded normal operation. The computed density altitude based upon the field elevation of 1,192 ft, an altimeter setting of 29.97 and a temperature of 26° C was 2,729 ft.