- Location: Holly Springs, MS
- Accident Number: CEN26FA093
- Date & Time: January 18, 2026, 16:40 Local
- Registration: N6711J
- Aircraft: Piper PA-28-140
- Injuries: 2 Fatal
- Flight Conducted Under: Part 91: General aviation - Instructional
https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/202312/pdf
https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N6711J
On January 18, 2026, about 1640 central standard time, a Piper PA28-140 airplane, N6711J, was destroyed when it was involved in an accident near Holly Springs, Mississippi. The flight instructor and student pilot were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.
According to the airport manager, the airplane had departed Holly Springs-Marshall County Airport (M41), Holly Springs, Mississippi, after doing several touch and go landings. There was no ADS-B data available for the accident flight.
The airplane impacted terrain in a wooded area about 693 ft east of the departure end of runway 18 at M41. The first identified impact point was a pine tree about 185 ft south of the main wreckage. The airplane struck numerous pine trees along the impact path. Five branches were located at the site varying from .75 to 2 in diameter with clean cut marks and black paint transfer consistent with the airplane’s propeller. No ground impact marks were found at the accident site. A post-impact fire consumed a large portion of the airframe. The flight instruments and flight controls were thermally damaged or destroyed. The manual flap selector was thermally damaged and was found in the full flap (40 degree) position. The fuel selector valve was selected to the right fuel tank position and functioned normally when tested with low-pressure air.
Flight control continuity was confirmed for the flight controls. The stabilator trim cables were continuous from the empennage to the forward cabin location. The stabilator trim actuator control rod was extended 1.6 in on the top side of the actuator, which was consistent with a partial nose up trim position.
The airplane was equipped with a Lycoming O-320-E3D reciprocating engine. The engine remained attached to the engine mount. The propeller assembly was partially embedded in soft dirt. Engine control cable continuity was confirmed from the firewall forward to both the mixture and throttle arms of the engine’s carburetor. The mixture was found halfway between lean and rich while the throttle arm was found at a partial power setting. The engine primer control was found within the wreckage in the forward and locked position.
The spark plugs were removed from their respective cylinders. The spark plugs had normal wear patterns, and the coloration was consistent with normal engine operation. The lower plugs on cylinder Nos. 1 and 2 were oil soaked consistent with the oil drained from each cylinder upon removal. The lower spark plug for cylinder No. 3 was found impact fractured below the ignition harness nut. Examination of each cylinder was completed with a borescope with no anomalies found. Thumb suction and compression was confirmed on all cylinders by rotating the propeller in the direction of engine rotation. With all rocker box covers removed, all rocker arms moved freely and through their full range of motion with no anomalies found.
The oil lines to the oil cooler were found attached. The oil filter was found attached to the accessory section and safety wired but thermally damaged. The filter was removed, cut open, and inspected. The filter element had burned, but no metallic particles were noted between the remains of the filter pleats. The oil suction screen plug was found tight and secured to the oil sump with safety wire. Once removed, the screen was found free and clear of any debris. The oil filler neck was consumed by fire with only the metal dipstick remaining within the engine case. Oil was present in the oil sump, but total quantity was not determined.
Both magnetos were present, secure, and exhibited varying degrees of thermal damage to their aluminum housing. The magnetos were removed and an attempt to rotate them by hand was made. During the attempt, friction was present and both magnetos would bind during rotation. The left-hand magneto was disassembled, and thermal damage was noted internally. The right-hand magneto suffered a higher degree of thermal damage to its aluminum housing and was not disassembled.
The engine driven fuel pump was found attached to the rear accessory section of the engine and exhibited thermal damage. All fuel lines were found attached, but the aluminum housing showed signs of melting and deformation. During disassembly of the engine driven fuel pump, the gaskets and diaphragms were found thermally damaged. The fuel pump activation rod was found present within the accessory case and moved freely with rotation of the engine’s crankshaft.
The airplane was equipped with a Power Flow Systems Exhaust. The exhaust system was cut free from the engine at each cylinder and checked for blockage. The exhaust system was found free of any blockages or anomalies. All intake pipes were removed and found free and clear of blockage or debris.
The carburetor remained attached to the lower side of the engine. The airbox and air duct hoses were found impact or thermally separated. The carburetor was removed from the engine and examined. The float bowl was removed from the carburetor, and no fuel or fluid was found in the bowl. No sediment was present and the brass floats were free of damage or deformation. The needle and seat were present. The seat was free and clear of any damage but showed discoloration consistent with thermal damage. The needle tip was deformed consistent with exposure to the post impact fire.
The propeller assembly was found partially embedded in the ground. Both blades remained attached to the propeller hub and the propeller was largely intact. The propellor exhibited slight thermal discoloration to one blade on the cambered side. No observable bending or deformation was noted to either blade. Slight chordwise scratches and smears were noted and consistent with cut pine branches found at the accident site.
The wreckage was retained for further examination.
