Tuesday, November 03, 2026

Bombardier BD-100-1A10 Challenger 350, N272BQ, incident occurred on October 29, 2026, at Sedona Airport (SEZ/KSEZ), Sedona, Arizona

This is preliminary information, subject to change, and may contain errors. Any errors in this writing will be corrected when/if the NTSB preliminary report is released.

https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N272BQ

- History of Flight:
On October 29, 2026, at about 1422 local time, a Bombardier BD-100-1A10 Challenger 350, N272BQ, registered to JSV Aviation Ventures 272 LLC and being operated by Exclusive Jets on a Part 135 on-demand flight, sustained unknown damage when it struck a light pole with the right wing while taxiing after landing at Sedona. The two pilots were not injured. The flight originated from Phoenix-Sky Harbor International Airport (PHX/KPHX), Phoenix, Arizona. 

The airplane remained on the ground at Sedona and departed on a flight to a Dallas on November 3rd.

Piper PA-28-140 Cherokee, N4154J, incident occurred on October 28, 2026, at Fulton County Airport (NY0), Johnstown, New York

This is preliminary information, subject to change, and may contain errors. Any errors in this writing will be corrected when/if the NTSB preliminary report is released.

https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N4154J

- History of Flight:
On October 28, 2026, at about 1032 local time, a privately-registered Piper PA-28-140 Cherokee, N4154J, sustained unknown damage when it suffered a propeller strike upon landing on runway 10 due to a loose landing light. The pilot was not injured. The local flight originated from NY0.

Van’s RV-7A, N425DG, fatal accident occurred on October 7, 2026, near Petaluma Municipal Airport (O69), Petaluma, California

  • Location: Petaluma, CA
  • Accident Number: WPR27FA012 
  • Date & Time: October 7, 2026, 10:38 Local 
  • Registration: N425DG
  • Aircraft: Vans RV7A 
  • Injuries: 2 Fatal
  • Fatal Flight Conducted Under: Part 91: General aviation - Instructional 

https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/203963/pdf

https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N425DG

On October 7, 2026, about 1038 Pacific daylight time, an experimental amateur built Vans RV-7A, N425DG, was destroyed when it was involved in an accident near Petaluma, California. The pilot and flight instructor were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

According to a family member, the flight instructor was conducting a flight review with the pilot. Preliminary ADS-B flight track data showed that the airplane departed from runway 29 at Petaluma Municipal Airport (O69), Petaluma, California, about 1037:29.  The airplane  climbed to about 300 ft above ground level (agl) and accelerated to a ground speed of about 89 knots. The airplane crossed the departure end of runway 29 about 1037:55, at about 300 ft agl and a ground speed of 84 knots. About 1037:58, the airplane entered a turn to the right and maintained an approximate altitude of 300 ft agl, with brief altitude oscillations. The airplane's ground speed continued to decelerate until the end of the ADS-B data.  At 1038:10, the data showed the airplane in a descent at about 200 ft agl and a ground speed of 63 knots. (See figure 1.)

A review of security camera footage located at O69 showed the airplane on upwind for runway 29 in a climb attitude, until it leveled off and subsequently began a turn to the right. The airplane remained at about the same altitude in the right turn.  About 9 seconds after the start of the turn, the airplane's angle of bank increased and it descended in a nose down attitude into terrain.

According to a witness located near the departure end of runway 29, he heard the airplane departing and did not look up, initially. He then heard what sounded to him like an engine “backfire” and walked out of his hangar to look. He observed the accident airplane in a right bank and stated that the bank angle continued to increase. Subsequently, the airplane rolled to the left and “fell straight down” until it impacted the ground where a postcrash fire ensued.


Examination of the accident site revealed that the airplane impacted an open field at an elevation of about 118 ft mean sea level (msl) about 1,300 ft north of the departure end of runway 29. The wreckage debris path was about 63 ft in length, about 60 ft wide and oriented on a magnetic heading of about 154° from the first identified point of contact (FIPC) to the main wreckage. The FIPC was a depression in the ground about 6 ft wide, 8 ft long, and about 2 ft deep. The propeller was separated from the engine slightly aft of the propeller flange and located about 57 ft northwest of the main wreckage. All 6 propeller bolts remained attached to the propeller flange. The airplane's canopy was observed about 59 ft southwest of the main wreckage. The main wreckage came to rest upright on a magnetic heading of about 299°and displayed extensive thermal damage. All major structural components of the airplane were located throughout the debris path.

The wreckage was recovered to a secure location for further examination.

Piper PA-46-350P Malibu Mirage JetPROP DLX, N931TT, fatal accident occurred on October 13, 2026, near Reedsburg, Wisconsin

  • Location: Reedsburg, WI
  • Accident Number: CEN27FA016
  • Date & Time: October 13, 2026, 21:30 Local
  • Registration: N931TT
  • Aircraft: PIPER AIRCRAFT INC PA 46-350P
  • Injuries: 6 Fatal
  • Flight Conducted Under: Part 91: General aviation - Personal

https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/204002/pdf

https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N931TT

On October 13, 2026, about 2130 central daylight time, a Piper Aircraft PA-46-350P JetProp DLX airplane, N931TT, was destroyed when it was involved in an accident near Reedsburg, Wisconsin. The pilot, the pilot-rated passenger, and the four passengers sustained fatal injuries. The airplane was operated as a Title 14 Code of Federal Regulations (CFR) Part 91 personal cross-country flight.

The pilot was the owner of the airplane, and the purpose of the flight was to transport friends to a sporting event and back home.

A preliminary review of flight track data showed that on the day of the accident, the airplane departed the Menomonie Municipal Airport (LUM), Menomonie, Wisconsin, about 1443. The airplane landed at the Kenosha Regional Airport (ENW), Kenosha, Wisconsin, about 1548.

The pilot filed an instrument flight rules flight plan, and the airplane departed from ENW about 2043, with a destination as LUM. The flight track data showed that the airplane departed from ENW and flew to the northwest, then turned to a west heading and climbed to a cruise altitude of flight level (FL) 240. The pilot was issued the weather conditions along the route of flight. At 2125, the pilot, who was in contact with the Chicago Air Route Traffic Control Center (ZAU ARTCC), reported the airplane had encountered icing conditions, and requested a lower altitude. The pilot was approved to descend the airplane to an altitude of 11,000 ft.

The ZAU ARTCC controller made several attempts to assist the pilot after the pilot stated the airplane was having issues with the radios, and the pilot was unsure of the airplane's heading, altitude, and airspeed. The controller lost communications with the airplane as it descended through 15,000 ft.

The flight track data showed the airplane initially continued in a west direction and entered into a right-hand descending turn, with upward pitch changes, and a rapid increase in airspeed reaching as high as 339 kts, before decreasing. The airplane briefly ended up on a track about 180° in the opposite direction, until the flight track data was lost about 2130.

A preliminary review of weather information revealed that the National Weather Service Aviation Weather Center Current Icing Product indicated an area of 50 percent probability of icing conditions existed at FL 240 in the vicinity of the accident site, near the time of the accident. The icing severity indicated pockets of light to moderate icing were possible in the vicinity of the accident site.

A preliminary review of archived information showed the pilot did not request weather information from Leidos Flight Service. The pilot did have an account through ForeFlight, and he did receive a weather briefing from ForeFlight.

The debris path was located throughout a rural residential area and the Mirror Lake Pine Oak Forest State Natural Area, owned and managed by the state of Wisconsin. Both areas consisted of large trees and heavy brush. There were no ground injuries or property damage.

Both wings were found separated from the fuselage. Both horizontal stabilizers and elevators were found separated from the empennage. The wreckage was documented at multiple locations, it was recovered from the accident site, and it was transported to a secure location for future examination. Multiple damaged avionics units were removed from the airplane and were transported to the NTSB Vehicle Recorders Laboratory.

The airplane, which was manufactured in 2008, was equipped with a Pratt & Whitney Canada PT6A-35 turboprop engine and a MT-Propeller MTV-16-1 four-blade, controllable pitch, wood and composite propeller. The airplane was originally manufactured and known as a Malibu Mirage, but was later converted in November 2019 to a JetProp DLX model through an FAA supplemental type certificate held by the Rocket Engineering Corporation. The airplane was also equipped with an autopilot system.

The pilot held an airline transport pilot certificate with ratings for airplane multi-engine land, airplane single engine land, and a type rating for the Embraer EMB-500 Phenom 100 airplanes. The pilot successfully completed a 14 CFR 61.58 pilot-in-command proficiency check on September 17, 2026, in an Embraer EMB-500 Phenom 100 airplane. The pilot-rated passenger held a commercial pilot certificate with ratings for airplane multi-engine land, airplane single engine land, and instrument airplane. He also held a flight instructor certificate with a rating for airplane single engine land.

A review of the airplane's maintenance records showed the airframe, the engine, and the propeller all had an annual inspection performed by a mechanic on November 13, 2025.

A review of the JetProp DLX Pilot's Operating Handbook and FAA-Approved Airplane Flight Manual states that the airplane may be operated in day or night visual flight rules, day or night instrument flight rules, and known icing when the appropriate equipment is installed and operable. This document states to monitor the ambient air temperate and that while severe icing may form at temperatures as cold as -18° Celsius (-0.4 Fahrenheit), increased vigilance is warranted at temperatures around freezing with visible moisture present. The document also contains a warning about operating in severe icing and states:

Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems and may seriously degrade the performance and controllability of the airplane.

Hughes 269B, N9390F, fatal accident occurred on October 6, 2026, near Lahmansville, West Virginia

  • Location: Lahmansville, WV
  • Accident Number: ERA27FA004
  • Date & Time: October 6, 2026, 16:53 Local
  • Registration: N9390F
  • Aircraft: Hughes 269B
  • Injuries: 1 Fatal
  • Flight Conducted Under: Part 91: General aviation - Personal

https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/203951/pdf

https://registry.faa.gov/aircraftinquiry/Search/NNumberResult?NNumberTxt=N9390F

On October 06, 2026, at about 1653 eastern daylight time, a Hughes 269B, N9390F, was substantially damaged when it was involved in an accident near Lahmansville, West Virginia. The pilot was fatally injured. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

A witness reported that the pilot performed an extensive preflight inspection and engine runup check. The helicopter lifted off at 1645 and departed from runway 06 of the private airstrip. The helicopter entered the right traffic pattern and completed two low approaches down the runway. During the third upwind climb, the witness observed that the helicopter appeared to ascend at a lower rate and entered a slight descent as it transitioned to downwind. Shortly afterward, the witness lost sight of the helicopter due to the terrain.

Another witness performing an agricultural operation about 1/2 mile southeast of the airport reported that helicopter overflew his property during the first two passes, as it transitioned from downwind to the base leg of the traffic pattern. During the third pass, the helicopter performed a 180° turn at an altitude of about 150 ft above ground level and maneuvered to a field about 1/4 mile northeast of his location. He observed the helicopter's tailboom make a “quick wag” as it appeared to enter a hover, followed by a high rate of descent in an upright position. The witness noted that he did not hear the engine or see the impact due to operating equipment and terrain.

One witness reported the helicopter's engine sound was “loud and of consistent tone.” Another witness reported the engine as having a “slight misfire” as it flew over his property.

The accident site was located about 1/2 mile east of the private airstrip in about a 9° sloped grass field adjacent to a roadway. The debris path was about 124 ft in length and oriented on a magnetic heading of 060°at an elevation of 1,050 ft. There was an odor of fuel present, and the grass surrounding the main wreckage exhibited fuel blight. 

Ground impressions consistent with the impact of the tailrotor and skids revealed the helicopter impacted the ground in about a 17° nose-up attitude and came to rest on its right side about 15 ft from the point of impact and oriented on a magnetic heading of 136°. A soil depression observed between the linear skid impressions contained residual engine oil and fragments of the engine oil sump. All components of the helicopter were accounted for at the accident site.

The tailboom was separated from the fuselage. The two tailrotor blades were undamaged and remained attached to the hub, with no anomalies noted to their pitch change links or swashplate. No anomalies were noted to the tailrotor gearbox during hand rotation of the rotor blades, and oil was visible in the sight glass. The tailrotor driveshaft was separated from impact forces about 19 inches from its drive pulley coupler and deformed upward about 3 inches from the tailrotor gearbox. The drive shaft exhibited torsional deformation between 37 to 50 inches from the tailrotor gearbox. The tailrotor pitch-change remained attached to its mounts and impact separated about 10 inches from the fuselage bellcrank.

The lower fuselage was crushed upward and the canopy was fragmented. The pilot's four-point restraint was latched, and its inertia real was locked with the webbing separated from impact forces. The restraint's lower outboard attached point was pulled from the fuselage. The pilot's seat frame was deformed downward and fractured. The fuel control was in the ON position, and the magneto switch was on BOTH. The electric fuel pump was ON, and the mixture control was partially leaned. The rotor clutch switch was engaged and in the locked position. The battery and generator switches were noted in the ON positions.

Continuity of the cyclic and collective controls were established from the cockpit controls to the main rotor head. Control continuity was established from the cockpit antitorque pedals to the bellcrank and through impact separated control tube to the tailrotor blades. Continuity of the throttle cable was confirmed from the collective to the impact fractured bellcrank assembly. The collective's throttle control friction was engaged and could not be released by hand. There was no impact damage noted to the collective control.

The main rotor gearbox housing remained attached to the bottom of the main rotor mast and to the center frame. The gearbox lower housing was fractured from impact forces and oil was present in the assembly. The main gearbox rotated freely, and continuity was established from the drive pulley to the rotor head. The lower drive pulley was partially separated from its support structure, and its input shaft remained engaged in the pulley and attached to the engine. The drive belts were intact and partially separated from the pulleys. The freewheeling (one-way) sprag clutch operated correctly and its supporting structure was fractured from impact forces. The sprag clutch actuator cable remained attached to the sprag clutch and the linear actuator.

The three main rotor blades were secured to their respective grips, which remained attached to the main rotor head and mast. The red rotor blade was relatively straight with slight skin buckling observed, and its trim attach point pulled inward. The blue rotor blade was bent downward about 9 inches from its attach point and downward deformation about mid-span with light chord-wise abrasion noted to its outboard area. The yellow rotor blade was bent downward about 9 inches from its attached point and exhibited skin buckling and chord-wise abrasion at its outboard area. A material consistent to that of a body filler was observed on the lower blade skin's outboard area. Sections of the filler were separated and were not located at the accident site. The damage noted to the rotor blades were consistent with low rotor rpm at ground contact.

The fuel tank was breached at its outboard manufactured seam and a semicircle impression with linear transfer marks consistent with impact from the main rotor drive pulley and belts was observed to its inboard area. The fuel cap remained attached to its receptacle, and vent and pick-up screen were clear of debris. Fuel line continuity was established from the fuel servo to the fuel tank through impact fractured fuel lines. Fuel was observed in the gascolator, and its filter was clear of debris. The electric fuel pump was determined to be functional during field test with a power source.

The engine remained attached to its mounts and exhibited impact damage to upper crankcase area. The oil sump was fragmented, and the induction air filter was crushed. The oil pump suction screen and pressure filter media were clear of debris. The exhaust and induction tubes were crushed. The fuel and oil lines remained attached to their respective attachments. The engine driven fuel pump exhibited impact damage and fuel was observed within the pump. The fuel servo was impacted separated from the engine. The throttle was observed in the closed/idle position, and the control cable rod end was fractured from the servo. The mixture was observed in the rich position, and its control cable was pulled from its fuel servo attachment. Fuel was observed in the servo, and its fuel inlet screen was clear of debris. Impact damage was noted to the fuel injector lines, and the injectors were clear of debris.

Both magnetos remained attached to the engine and produced spark from their ignition towers during rotation of their drive gears. The sparkplug electrodes were intact and exhibited normal wear and coloration.  

Initial rotation of the crankshaft beyond about 90° was unsuccessful. Disassembly of the engine revealed impact deformation noted to the crankcase precluded camshaft rotation. There were no preaccident anomalies noted to the crankshaft, main bearings, or oil system. The connecting rods remained attached to their respective crank pins and rotated freely. The interior of the cylinders, pistons, rings, and valves were unremarkable.

The wreckage was retained for further examination.

Beechcraft G36 Bonanza, N646MM, accident occurred on August 30, 2026, French Valley Airport (F70), Murrieta, California

  • Location: Murrieta, CA 
  • Accident Number: WPR26LA367
  • Date & Time: August 30, 2026, 10:40 Local 
  • Registration: N646MM 
  • Aircraft: HAWKER BEECHCRAFT CORP G36
  • Injuries: 6 None 
  • Flight Conducted Under: Part 91: General aviation - Personal

https://data.ntsb.gov/carol-repgen/api/Aviation/ReportMain/GenerateNewestReport/204008/pdf

https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=N646MM

On August 30, 2026, at 1040 Pacific daylight time, a Hawker Beechcraft G36, N646MM, was substantially damaged when it was involved in an accident near Murrieta, California. The student pilot, flight instructor, and 4 passengers were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

The flight instructor reported that they were conducting a cross-country flight from French Valley Airport (F70), Murrieta/Temecula, California, to Blythe Airport (BLH), Blythe, California. During the takeoff roll on runway 18, at about rotation speed, the left side of the airplane dropped abruptly, and the airplane veered to the left. The flight instructor directed the student pilot to apply right aileron input to level the wings and return the airplane to the center of the runway. According to the student pilot, after leveling the wings, the nose landing gear lifted off the runway surface, the airplane veered aggressively to the right and became unresponsive to flight control inputs. The flight instructor assumed control and reduced the throttle to idle. The airplane exited the runway surface and the left wing collided with an airport sign, which resulted in substantial damage to the left wing.

The wreckage was retained for further examination.