- Location: Albertville, AL
- Accident Number: ERA26FA338
- Date & Time: September 15, 2026, 06:20 Local
- Registration: N469TW
- Aircraft: REED JULIAN ESTILL RV-4
- Injuries: 1 Fatal
- Flight Conducted Under: Part 91: General aviation - Personal
https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/203819/pdf
https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N469TW
On September 15, 2026, about 0620 central daylight time, an experimental amateur-built RV-4, N469TW, was substantially damaged when it was involved in an accident near Albertville, Alabama. The pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.
The airplane was based at the pilot’s residence on a private airport. A witness near the airport reported that they saw the airplane being taxied to the south end of the runway before it departed to the northeast at about sunrise.
An additional witness near the accident site reported that the airplane overflew her residence in a steep left bank and its associated engine noise caused her windows to rattle. She stated that the airplane narrowly missed trees and utility lines along a roadway and that the airplane remained in the left bank as it descended and impacted the ground; a postimpact fire ensued.
The accident site was located about 75 ft east of the private airport’s runway in a wooded area that bordered an open field area near the base of a water tower. The wreckage path was about 382 ft-long and oriented on a magnetic heading of 024° at an elevation of 1,150 ft. The first identified point of impact was a linear ground scar about 27 ft-long that contained the left wingtip navigation light lens and fragments of the left wingtip. A soil depression observed at the end of the ground scar contained the fragmented engine cowlings and sections of the engine’s exhaust system.
The main wreckage came to rest in an upright position about 102 ft from the initial point of impact and was oriented on magnetic heading of 030°. The postimpact fire destroyed majority of the cockpit and fuel system. All the airplane’s primary components were located at the wreckage site. The left wing remained attached to the fuselage and exhibited thermal damage with upward deformation noted about mid-span. The right wing remained attached to the fuselage with impact damage noted to its leading edge skin. Both fuel tanks were breached from impact and thermal damage. Both ailerons were impact-separated and located near the main wreckage. The flaps were thermally damaged and partially separated from the wings. The rudder and vertical stabilizer remained intact with impact damage noted. The left horizontal stabilizer and elevator were displaced aft and partially separated from the fuselage. The right horizontal stabilizer and elevator remained attached to the fuselage with impact damage noted.
Rudder control continuity was established from the rudder pedals to the rudder control surface. Aileron and elevator control continuity was established from the cockpit controls through impact separations to the respective flight control surface.
The fuselage exhibited impact and thermal damage. The canopy was fragmented and separated from the fuselage. The instrument panel was fragmented. The seats and occupant restraint webbings were thermally destroyed. Two seatbelt receptacles were observed unlatched. The main landing gear was separated from the fuselage with aft deformation noted to the left gear.
The engine was separated from the fuselage, and the engine mount was fragmented. The oil sump and exhaust system was fragmented. Crankshaft continuity to the rear gears was established during hand rotation of the attached propeller. Valvetrain continuity was confirmed and compression and suction were attained from all four cylinders. The oil pump suction screen and pressure filter media were clear of debris. The sparkplugs electrodes were intact and exhibited normal wear and coloration when compared to the Champion Check-A-Plug chart. Both magnetos remained attached to the engine and produced spark from their ignition towers during hand rotation of their drive gears. The carburetor was separated from the engine, and its throttle plate was observed in the OPEN position. The ground adjustable, twoblade, composite propeller remained attached to the engine and both propeller blades were fragmented and separated from the hub.
The wreckage was retained for further examination.
