Airport (less than 10 km from airport)

The airplane was on a VFR charter flight from Kiunga Airport, Western Province to Tekin Airstrip, Sandaun Province, Papua New Guinea. During the landing roll aircraft sustained a left main landing gear assembly collapse and subsequent runway excursion. There were seven persons onboard: one pilot and six passengers. At 09:06, P2-BWC departed Kiunga Airport and arrived at Tekin circuit area at 09:40. The pilot established the aircraft on the final approach profile, he configured the aircraft for landing by fully extending the flaps and maintained an airspeed of about 80 knots (kts). The pilot also stated that he experienced a downdraft prior to touch down. The aircraft landed at 09:43 with an airspeed of 75 knots as recalled by the pilot. The aircraft touched down about 3m short of the airstrip edge boundary. The investigation determined that due to reduced damping effect of the oleo and/or the tyre of the left main landing gear, the landing gear attachment bolts sustained significant impact stress from the landing impact force and snapped, causing the gear assembly to collapse and separate from the aircraft. Subsequently, the left wing abruptly dropped, and the aircraft began veering to the left, towards the eastern edge of the airstrip. The aircraft continued veering to the left and subsequently the left wingtip struck the outer edge of the extended right-hand flap of P2-BWE, a wreckage of the same aircraft type owned and operated by NASL that was involved in a similar accident on 18 January 2022, causing P2-BWC to abruptly veer further left and skid across the airstrip boundary as the nose-wheel and right main wheel bogged into the ground. The pilot immediately shut down the engine and evacuated the passengers with the assistance of one of the Operator’s personnel who was also a passenger on board. There were no reported injuries and the aircraft sustained significant damage.

The airplane was conducting a single pilot VFR charter flight from Kiunga Airport, Western Province to Tekin Airstrip, Sandaun Province, Papua New Guinea when during the landing roll, the aircraft sustained a left Main Landing Gear (MLG) assembly collapse and subsequent runway excursion. There were eight persons onboard: one pilot and seven passengers. At 08:43, P2-BWE departed Kiunga Airport and arrived at Tekin Airstrip circuit at 09:18. The pilot then tracked towards the Northwest of the airstrip and made a left base turn for approach. The pilot stated that he established the aircraft on final approach with an airspeed of 120 kts. He subsequently configured the aircraft for landing; propeller pitch set to full fine, power set to maintain nominated approach speed, and full flap. The pilot indicated that he reduced airspeed while on approach and maintained an airspeed between 85 and 90 kts. As he flared the aircraft to land, the airspeed was between 75 to 80 kts. The touchdown speed, as he recalled, was 75 kts. The aircraft touched down two metres short of the designated landing threshold of runway18, which had an elevation of 15cm. Reviewing the flight records of the pilot, and from his interview, the AIC deduced that the pilot was not adequately familiar with Tekin Airstrip. The aircraft sustained substantial damaged. All the passengers and pilot evacuated the aircraft without injuries.

Parked on the apron at Hangzhou-Xiaoshan Airport, the airplane was prepared for a cargo service to Novosibirsk with 8 crew members and a load of 20 tons of various goods on board. A fire erupted in the cargo compartment. The crew evacuated the aircraft and was uninjured while the aircraft was partially destroyed by fire and broke in two.

The aircraft departed La Isabela-Dr. Joaquín Balaguer Airport on a charter flight to Orlando, carrying six passengers and three crew members. Shortly after takeoff, the crew informed ATC about technical problems and was cleared to divert to Santo Domingo-Las Américas Airport for an emergency landing. On approach, the aircraft went out of control and crashed, bursting into flames. The aircraft disintegrated on impact and all nine occupants were killed, among them the Portorican music artist José Angel Hernández aka Flow La Movie. According to a preliminary report, the crew encountered technical problems with the spoilers and maintenance was performed to change the ground spoiler actuators. After maintenance, the crew completed a ground check and while all spoilers properly deployed on both wings, only the spoilers on the left wing retracted as the spoilers on the right wing remained deployed. The crew failed to notice this asymetry. Immediately after takeoff, the crew reported controllability problems and elected to return but finally decided to divert to Las Américas Airport. The aircraft eventually went out of control and crashed 16 minutes after takeoff.

During an instrument approach at night in a twin-engine turboprop airplane, the pilot reported an engine failure, but did not specify which engine. About 9 seconds later, the airplane impacted terrain about ¼-mile short of the runway and a postcrash fire consumed a majority of the wreckage. During that last 9-second period of the flight, the airplane’s groundspeed slowed from 99 kts to 88 kts, as it descended about 400 ft in a slight left turn to impact (the airplane’s minimum controllable airspeed was 92 kts). The slowing left turn, in conjunction with left wing low impact signatures observed at the accident site were consistent with a loss of control just prior to impact. Postaccident teardown examination of the left engine revealed that the 1st stage turbine rotor had one blade separated at the midspan. The blade fracture surface had varying levels of oxidation and the investigation could not determine if the 1st stage turbine blade separation occurred during the accident flight or a prior flight. The 2nd stage turbine was operating at temperatures higher than the 1st stage turbine, which was consistent with engine degradation over a period of time. Additionally, the 2nd stage turbine stator assembly was missing vane material from the 6 to 12 o’clock positions, consistent with thermal damage. All of these findings would have resulted in reduced performance of the left engine, but not a total loss of left engine power. The teardown examination of the right engine did not reveal evidence of any preimpact anomalies that would have precluded normal operation. Examination of both propellers revealed that all blade angles were mid-range and exhibited evidence of little to no powered rotation. Neither propeller was in a feathered position, as instructed by the pilot operating handbook for an engine failure. If the pilot had perceived that the left engine had failed, and had he secured the engine and feathered its propeller (both being accomplished by pulling the red Engine Stop and Feather Control handle) and increased power on the right engine, the airplane’s performance should have been sufficient for the pilot to complete the landing on the runway.

The airplane was departing into instrument meteorological conditions using a standard instrument departure. The takeoff instructions consisted of making a climbing right turn direct to a nondirectional beacon. After departing, the pilot made a radio communication to an air traffic controller asking if he will tell him when to turn. The controller replied that he would not be calling his turn and that the pilot should fly the departure as published making a climbing right turn to overfly the approach end of the runway. The pilot acknowledged the communication, which was his last transmission. The airplane made a 360° turn and descended below the cloud layer. The airplane then climbed back into the cloud layer and made an inverted loop, descending into the ground in a near-vertical attitude. A postaccident examination of the airplane revealed no evidence of preimpact mechanical malfunctions or failures. Recorded audio of the airplane before the accident was consistent with the engines operating. The signatures on both propellers were consistent with one another and consistent with the engines operating at a similar rpm. The pilot was qualified and recently underwent recurrent training. The reasons the pilot became spatially disoriented could not definitely determined. The pilot left the anti-collision lights on while in the clouds, which may have resulted in him having flicker vertigo.

The pilot was conducting a scheduled air taxi flight with five passengers onboard. Shortly after departure, the pilot began to smell an electrical burn odor, and he elected to return to the airport. About 1 minute later, the electrical burn smell intensified, which was followed by visible smoke in the cockpit, and the pilot declared an emergency to the tower. After landing and all the passengers had safely departed the airplane, heavy smoke filled the cockpit and passenger compartment, and the pilot saw a candle-like flame just behind the pilot and co-pilot seats, just beneath the floorboards of the airplane. Moments later, the airplane was engulfed in flames. Postaccident examination of the airframe revealed the origin of the fire to be centered behind the pilot’s row of seats, where a wire harness was found improperly installed on top of the aft fuel line from the left tank. Examination of the wire harness found a range of thermal and electrical damage consistent with chafing from the fuel line. It is likely that the installation of the wire harness permitted contact with the fuel line, which resulted in chafing, arcing, and the subsequent fire.

While on final approach, the airplane gradually slowed to near its stall speed. About 600 ft beyond the last recorded data, the airplane impacted the ground in a nose-down attitude that was consistent with a stall. Postaccident examination revealed no preaccident mechanical failures or malfunctions that would have contributed to the accident. Witnesses near the accident site reported very heavy sleet with low visibility conditions, whereas a witness located near the final approach flightpath, about 2 miles before the accident site observed the airplane fly by below an overcast cloud layer with no precipitation present. Based on the witness accounts and weather data, the airplane likely entered a lake effect band of heavy sleet during the final portion of the flight. The airplane was modified with 5-bladed propellers, and other pilots reported it would decelerate rapidly, especially when the speed/propeller levers were moved to the high rpm (forward) position. The pilot usually flew a larger corporate jet and had not flown the accident airplane for 8 months. The passenger was a student pilot with an interest in becoming a professional pilot. The pilot’s poor airspeed control on final approach was likely influenced by a lack of recency in the turboprop airplane. The workload of inflight deicing tasks may have also contributed to the poor airspeed control. The aerodynamic effects of the heavy sleet that was encountered near the accident site likely contributed to the stall to some degree.

A pilot-rated witness observed the airplane during the final approach to the destination airport and stated that the airplane was flying slowly, with a high pitch attitude, and was “wallowing” as if nobody was flying. The airplane stalled and impacted the ground about 300 ft from the runway. GPS and automatic dependent surveillance-broadcast (ADS-B) data captured the accident flight, but the ADS-B data ended about 0.24 miles before the accident. GPS data showed that the airplane’s speed was at or near the published stall speed for the airplane’s given loading condition. The airplane sustained substantial damage to the fuselage and both wings. Examination of the airplane verified flight and engine control continuity. No preimpact anomalies were found with respect to the airplane, engines, or systems. The pilot allowed the airspeed to decrease during the approach, increased pitch attitude, and exceeded critical angle of attack, which resulted in an aerodynamic stall and spin into terrain.

The twin engine airplane departed Goiânia-Santa Genoveva Airport on a taxi flight to Caratinga, carrying three passengers and two pilots. On final approach to Caratinga-Ubaporanga Airport in VFR conditions, the airplane collided with a lightning rod located on the top of a high-voltage pylon. Upon impact, the left engine was torn off and the airplane stalled before crashing in a river bed located about 4,1 km short of runway 02. The airplane was destroyed by impact forces and all five occupants were killed, among them the Brazilian singer Marília Mendonça aged 26.