N575BCPiper PA-31P · 1977

On May 21, 2021, at 1814 eastern daylight time, a Piper PA-31P, N575BC, was destroyed when it was involved in an accident near Myrtle Beach, South Carolina. The airline transport pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The accident flight was the airplane’s first flight following completion of an annual inspection. Before the flight, the airplane was fueled with 167.5 gallons of 100 low lead aviation fuel.

The airplane departed Myrtle Beach International Airport (MYR), Myrtle Beach, South Carolina, at 1812, with the intended destination of Grand Strand Airport (CRE), North Myrtle Beach, South Carolina. According to automatic dependent surveillance-broadcast and air traffic control (ATC) communications information, the pilot established contact with ATC and reported that he was ready for departure from runway 18. He was instructed to fly runway heading, climb to 1,700 ft mean sea level (msl), and was cleared for takeoff. Once airborne, the controller instructed the pilot to turn left; however, the pilot stated that he needed to return to runway 18. The controller instructed the pilot to enter a right closed traffic pattern at 1,500 ft msl.

As the airplane continued to turn to the downwind leg of the traffic pattern, it reached an altitude of about 1,000 ft mean sea level (msl). While on the downwind leg of the traffic pattern, the airplane descended to 450 ft msl, climbed to 700 ft msl, and then again descended to 475 ft msl before radar contact was lost. About 1 minute after the pilot requested to return to the runway, the controller asked if any assistance was required, to which the pilot replied, “yes, we’re in trouble.” There were no further radio communications from the pilot.

The airplane’s most recent annual inspection was completed on May 19, 2021. Maintenance performed at that time included removing, repainting, and reinstalling the primary and secondary flight control surfaces.

The airplane’s most recent annual inspection was completed on May 19, 2021. Maintenance performed at that time included removing, repainting, and reinstalling the primary and secondary flight control surfaces.

The airplane impacted in a field about 0.1 mile from the last radar return, at an elevation of 20 ft. A postimpact fire ensued, and the debris field was about 400 ft long by 150 ft wide. All major components of the airplane were in the vicinity of the main wreckage. Each engine came to rest in about a 5-ft crater and remained attached to the fuselage.

The left engine crankcase was impact damaged in multiple locations. The gearbox was impact separated. All valve covers remained intact and attached to the cylinders. The valve covers were removed, and no anomalies were noted. Examination with a lighted borescope revealed crankshaft and camshaft continuity and no anomalies of the cylinders. All engine accessories were impact separated and fragmented. The left engine turbocharger was impact separated and would bind when rotated by hand; scoring was noted on the casing.

The right engine crankcase was impact damaged in multiple locations. All valve covers remained intact and attached to the cylinders. The valve covers were removed and no anomalies were noted. Examination with a lighted borescope revealed crankshaft and camshaft continuity and no anomalies of the cylinders. All engine accessories were impact separated and fragmented. The oil suction screen was removed and was not occluded. The right engine turbocharger was impact separated and would bind when rotated by hand.

The left propeller was impact separated from the engine. Two of the three blades were separated from the hub. All blades exhibited polishing. One blade was bent forward, one exhibited tip curling, and the last blade was bent aft. The blade that was bent aft remained attached to the propeller hub.

The right propeller was impact separated from the right engine. Two of the three blades were impact separated from the hub. All blades exhibited polishing. One blade was bent forward, one blade was bent aft, and one blade remained straight. The straight blade remained attached to the propeller hub.

Flight control cable continuity was established from all flight control surfaces to the cockpit through multiple overload breaks in the cables. The wings and fuselage were largely consumed by fire. The remaining skin and structure exhibited accordion-like impact damage that was symmetrical on both wings. The landing gear was in the extended position. The flaps were in the retracted position. The empennage was separated from the fuselage and located about 50 ft from the main wreckage. The top section of the vertical stabilizer and the rudder were impact-crushed downward. The elevator remained attached to the right horizontal stabilizer. The right trim tab remained attached to the right elevator, was deflected trailing edge up, but was impact separated from the control rod. The left trim tab remained attached to the left elevator, the connecting rod remained attached to the flight controls, and it was deflected trailing edge up.

Further examination of the elevator trim tabs revealed that both were installed upside-down and reversed (the left tab was installed on the right elevator and the right tab on the left elevator). As a result, the control horns on both trim tabs and their respective control rods, which should have been located on the top side of the trim tabs above the tab’s hinge line, were instead located on the bottom side of the tabs below the tab’s hinge line. This installation resulted in a reversal of the direction of the trim tabs’ movements; a command of nose-up trim from the cockpit controls would incorrectly move the trim tabs in the nose-down direction, and vice versa.

Maintenance Facility

According to the director of maintenance, during the annual inspection, corrosion was noted on the flight control surfaces, and the surfaces were removed from the airplane for corrosion removal, repair, and repainting. When the primary and secondary flight control surfaces were removed, they were tagged; however, during the process of repainting, because of the corrosive solutions the tag was separated from the control surface.

After the maintenance was performed on the airplane, the director of maintenance had another mechanic sit in the airplane and exercise the controls while he verified the primary flight control movement to ensure that they were installed properly. He did not check the elevator trim tab movement for proper installation. The director of maintenance, who was a mechanic with inspection authorization, approved the airplane for return to service.

The director of maintenance further stated that he also maintained a non-pressurized Piper PA-31 (the accident airplane was the pressurized version). The non-pressurized PA-31 was equipped with only one elevator trim tab located on the right side of the elevator, and the control horn and control rod were located on the bottom side of the trim tab.

PA-31P Illustrated Parts Catalog

According to the Piper PA-31P illustrated parts catalog, the Elevator Assembly figure incorrectly depicted the control horn on the bottom of the trim tab. (see Figure 1.) The illustrated parts catalog also noted in the Introduction section that, “UNDER NO CIRCUMSTANCES SHALL THIS CATALOG BE USED FOR RIGGING AND INSTALLATION PURPOSES.”

Figure 1. Excerpt from Illustrated Parts Catalog showing the control horn located on the bottom side of the elevator trim tab.

PA-31P Maintenance Manual

According to the Piper PA-31P maintenance manual, the elevator and elevator trim control figures correctly depicted that the control rod attached to the control horn as located on the top of the elevator trim tab. The instructions to install the elevator trim tab indicated to, “refer to figure 4-5.” Figure 2 is an excerpt from Figure 4-5 in the maintenance manual.

Figure 2. Excerpt from Airplane Maintenance Manual showing the trim tab hinge, with the control horn, and control rod located on the top side of the elevator trim tab.

Toxicology testing performed for the Department of Pathology and Laboratory Medicine’s office detected ethanol at 0.225 milligrams per hectogram (mg/hg) and isopropanol in the pilot’s liver tissue. Caffeine was also detected in his liver tissue. Toxicology testing performed by the FAA Forensic Sciences Laboratory detected ethanol in the pilot’s liver tissue at 0.078 gm/hg and in his muscle tissue at 0.144 gm/hg; n-propanol was detected in muscle tissue. The non-sedating fever and pain medication acetaminophen was detected in his liver and muscle tissue.

Ethanol is a social drug commonly consumed by drinking beer, wine, or liquor. It acts as a central nervous system depressant; it impairs judgment, psychomotor functioning, and vigilance. Ethanol is water soluble, and after absorption it quickly and uniformly distributes throughout the body’s tissues and fluids. The distribution pattern parallels water content and blood supply of the tissue. Ethanol can be produced after death by microbial activity; sometimes in conjunction with other alcohols, such as propanol. Extensive trauma increases the spread of bacteria and raises the risk of ethanol production after death.