Airport (less than 10 km from airport)

The aircraft, a Piper PA46-500TP Malibu Meridian, should carry out a private flight from Västeras airport to Prague. On board were a pilot and two passengers. Shortly after take-off an engine failure occurred and the pilot decided to make an emergency landing on Björnö Island, situated slightly to the right in the flight direction. The aircraft hit the ground with the left wing first and then rolled a number of times before it came to a final stop. During the accident both wings and parts of the tail separated from the aircraft. The fuselage remained relatively undamaged during the crash course. All three occupants escaped with minor injuries. A special study of the sequence of events shows that the impact, with the left wing first, caused the airplane's wings to act as shock absorbers, which greatly contributed to that the occupants only received minor injuries. During the accident - which occurred next to a secondary protection zone for water supply to the city of Västerås – a significant amount of fuel leaked out from the wreckage. The accident site was decontaminated after the accident. Examination undertaken in the area after the accident has not showed any trace of residual contamination in the soil.

The accident flight was a repositioning flight being operated by two airline transport pilots, and it was the multiengine turboprop airplane's first flight after an aviation maintenance technician (AMT) had replaced the left engine propeller with an overhauled propeller. The AMT subsequently performed an engine run, which included verifying correct power settings and corresponding blade angles. A review of flight data recorder (FDR) data revealed that, about 2 seconds after rotation, the left engine propeller rpm decreased to 60 percent, and the left engine torque increased off-scale (beyond 5,000 ft lbs), which is consistent with the left propeller traveling to the feathered position and the engine torque increasing in an attempt to maintain propeller rpm. About 30 seconds later, the flight crew shut down the left engine and attempted to return to the departure airport. Postaccident examination of the rudder trim actuator revealed that the rudder trim was at its full-right limit, which would have occurred to counteract the left engine drag before its shutdown. Based on this evidence, it is likely that the flight crew did not readjust the trim when the drag was alleviated, which resulted in the airplane being operated in a crosscontrolled attitude for about 50 seconds with a left bank and full-right rudder trim. Although the airplane should have been able to climb about 500 ft per minute with one engine operating, it slowed and descended from 300 ft in the cross-controlled attitude until it stalled, as indicated by a stall warning recorded by the cockpit voice recorder, and subsequently impacted terrain. Examination of the wreckage, including teardown examination of the left engine and propeller, did not reveal any preimpact mechanical anomalies. Review of the airplane maintenance manual revealed instructions to check the propeller reversing linkage on the front end of the engine, which controlled the beta valve, for proper rigging during propeller installation. The manual also contained a warning that misadjustment of the beta valve can cause unplanned feathering of the propeller and result in a possible hazard to airplane operation and over torque damage to the engine; however, the beta valve rigging could not be verified postaccident due to impact damage. Additionally, the ground/flight idle solenoid energizes when weight becomes off wheels and further opens the beta valve, which could exacerbate an existing misrigged condition as soon as the airplane becomes airborne, which is when the airplane experienced the uncommanded propeller feathering. The FDR data were consistent with the flight crew not performing the Before Takeoff (Runup) checklist. One of the items on that checklist was a low-pitch solenoid test, which would have energized the solenoid and possibly driven the left propeller uncommanded to feather during ground operations rather than in flight. A similar test during the post maintenance engine-run would have had the same results.

After landing at Roseau-Canefield, the pilot encountered difficulties to stop the aircraft that overran. It collided with a fence and came to rest against various obstacles. All seven occupants evacuated safely and the aircraft was damaged beyond repair.

The instrument-rated commercial pilot was approaching the destination airport after a cross country flight in night instrument meteorological conditions. According to radar track data and air traffic control communications, while receiving radar vectors to the final approach course, the pilot did not always immediately comply with assigned headings and, on several occasions, allowed the airplane to descend below assigned altitudes. According to airplane performance calculations based on radar track and GPS data, the pilot made an engine power reduction about 2.5 minutes before the accident as he maneuvered toward the final approach fix. Following the engine power reduction, the airplane's airspeed decreased from 162 to 75 knots calibrated airspeed, and the angle of attack increased from 2.7° to 14°. About 4 miles from the final approach fix, the airplane descended below the specified minimum altitude for that segment of the instrument approach. The tower controller subsequently alerted the pilot of the airplane's low altitude, and the pilot replied that he would climb. At the time of the altitude alert, the airplane was 500 ft below the specified minimum altitude of 2,000 ft mean sea level. According to airplane performance calculations, 5 seconds after the tower controller told the pilot to check his altitude, the pilot made an abrupt elevator-up input that further decreased airspeed, and the airplane entered an aerodynamic stall. A witness saw the airplane abruptly transition from a straight-and-level flight attitude to a nose-down, steep left bank, vertical descent toward the ground, consistent with the stall. Additionally, a review of security camera footage established that the airplane had transitioned from a wings-level descent to a near vertical spiraling descent. A post accident examination of the airplane did not reveal any anomalies that would have precluded normal operation during the accident flight. Although the pilot had monocular vision following a childhood injury that resulted in very limited vision in his left eye, he had passed a medical flight test and received a Statement of Demonstrated Ability. The pilot had flown for several decades with monocular vision and, as such, his lack of binocular depth perception likely did not impede his ability to monitor the cockpit instrumentation during the accident flight. The pilot had recently purchased the airplane, and records indicated that he had obtained make and model specific training about 1 month before the accident and had flown the airplane about 10 hours before the accident flight. The pilot's instrument proficiency and night currency could not be determined from the available records; therefore, it could not be determined whether a lack of recent instrument or night experience contributed to the pilot's difficulty in maintaining control of the airplane.

The instrument-rated private pilot was conducting a personal cross-country flight in the airplane. A review of the air traffic control transcripts and radar data revealed that the pilot was executing the RNAV GPS Y instrument approach to the runway. The air traffic controller then canceled the pilot's approach clearance and issued a heading change off of the approach course to provide spacing between a preceding aircraft. The pilot acknowledged the heading assignment. Radar data indicated that, after the controller cancelled the approach, the airplane began a left climbing turn from 5,600 to 5,800 ft, continued the left turn through the assigned 270 heading, and then descended rapidly. At that point, the airplane was no longer visible on the controller's radar display, and contact with the pilot was lost. The final recorded radar return showed the airplane at 5,100 ft. The airplane impacted a television tower guy wire, several power lines, and terrain, and then came to rest in an open field about 800 ft from the tower. A postaccident examination of the airplane and engine revealed no anomalies that would have precluded normal operation. A postaccident examination of the engine revealed rotational signatures on the first stage compressor blades and light rotational signatures in the compressor and power turbines, and debris was found in the engine's gas path, all of which are consistent with engine rotation at impact. A witness in the parking lot next to the television tower stated that he heard the accident airplane overhead, saw a large flash of light that filled his field of view, and then observed the television tower collapse on top of itself. Surveillance videos located 1.5 miles north-northeast and 0.3 mile north-northwest of the accident site showed the airplane in a left descending turn near the television tower. After it passed the television tower, multiple bright flashes of light were observed, which were consistent with the airplane impacting the television tower guy wire and then the power lines. Further, the radar track and accident wreckage were consistent with a rapid, descending left turn to impact. Weather conditions were conducive to the accumulation of ice at the destination airport about the time that the pilot initiated the left turn. It is likely that the airplane accumulated at least light structural icing during the descent and that this affected the airplane's controllability. Also, the airplane likely encountered wind gusting up to 31 knots as it was turning; this also could have affected the airplane's controllability. The night, instrument meteorological conditions at the time of the accident were conducive to the development of spatial disorientation, and the airplane's rapid, descending left turn to impact is consistent with the pilot's loss of airplane control due to spatial disorientation. Therefore, based on the available evidence, it is likely that, while initiating the climbing left turn, the pilot became spatially disoriented, which resulted in his loss of airplane control and his failure to see and avoid the tower guy wire, and that light ice accumulation on the airplane and the gusting wind negatively affected the airplane's controllability.

The Jetstream 41 aircraft, with registration number SX-DIA, operated by “SKY EXPRESS”, took off on 2nd February 2015 at 07:00 hrs. local time from the Airport of Heraklion ‘N. Kazantzakis’, performing the scheduled flight No. ‘SEH100’, the first in the day, destined for the Airport of Rhodes ‘Diagoras’. Pre-flight checks were completed with no findings and in this flight the Captain was designated as the Pilot Flying. A 3-member crew and 16 passengers were onboard. The flight crew reported for duty one hour prior to the time of flight and proceeded with all actions as laid down in the Company manual. The flight crew was also briefed that in the area of the Airport of Rhodes the winds were S-SE at 17 kt with Wind Gust 36 kt. At 07:23:54 hrs., approximately 12 min prior to landing, in the first contact of the flight crew with the Control Tower of the Airport of Rhodes, the flight crew was briefed by the Air Traffic Controller (ATC) with respect to the weather conditions at the area of the airport, variable winds prevailing with a direction from 20° to 160°, average wind direction from 110°, wind velocity 20 kt gusting 38 kt. As laid down in the airport procedures, ATC, given the weather conditions, alerted the fire service vehicles to be stationed in readiness at their designated positions on the taxiways. At 07:24:43 hrs. Rhodes ATC contacted the flight crew wishing to remind that as a result of the strong wind shear and turbulence, landing at the airport is not recommended under the circumstances. At 07:29:34 hrs. Rhodes ATC contacted again the flight crew informing that the wind is shifting from 40° to 260°, average wind direction from 120°, mean wind velocity 20 kt and wind gust 32 kt. At 07:32:36 hrs., at about 8nm to the airport, the ATC contacting again the flight crew informed that wind in the last ten minutes is shifting in all directions, with mean wind velocity 16 kt and wind gust 37 kt; ATC also reminded that under these conditions landing is not recommended. At 07:34:04 hrs., at about 4 nm to the airport, Rhodes ATC contacted again the flight crew informing that wind is shifting from 60° to 200°, mean wind velocity 15 kt, wind gust 32 kt and that runway 07 is free for landing. At 07:35:08 hrs. ATC again reports wind direction from 110°, 17kt. Communication between ATC and the flight crew was smooth without any problem, with the flight crew each time acknowledging the information provided by ATC. Given the prevailing winds, landing with 9° flaps and an airspeed of about 129 kt was selected. With the flight crew having performed all pre-landing checks prescribed in the manual and with the indicator lights for the ‘Down and Lock’ landing system being illuminated green, at about 07:36 hrs. the aircraft landed, with the right main landing gear touching down first. During deceleration immediately after touchdown, with the flight crew having performed all checks specified in the a/c manual and after ATC directed the aircraft to vacate the runway via taxiway ‘C’, the aircraft veered to the left and came to rest at the left edge of the runway without exiting the runway, with an eastward direction. With the fire service vehicle approaching the aircraft, the flight crew contacted the Control Tower of the airport stating that everything is ok, and then reporting inability to taxi when asked whether the aircraft is able to taxi; when asked whether a tire was burst, the flight crew confirmed that this is the case. At 07:37:49 hrs. the Fire Service advises the Control Tower of the airport that the fire truck sprays foam due to fuel leakage. At 07:41:08 hrs. the Control Tower, when so asked by the ‘follow me’ vehicle, inquired of the flight crew whether passengers could be disembarked and the answer was that getting off from the passenger door (forward left) would not be feasible given the presence of the fire-fighting foam on the runway, and that the rear right door (Emergency Exit) would be used instead. As reported by the Air Traffic Controller passengers were disembarked 15 minutes after the incident, and the process lasted approximately 10 minutes. Upon a first visual inspection at the accident site and before the left wing of the aircraft was raised on jacks, it appeared that the left main landing gear folded back resulting in the aircraft’s left side dragging the runway (the left main landing gear and its housing into contact with the runway) and stopping at the left edge of the runway facing to the east.

The single engine aircraft was approaching Shatyrkul in foggy conditions when it crashed in a snow covered field located 1,2 km south of the landing zone area, some 20 km north of Shatyrkul. SAR arrived on scene at 1701LT. A female passenger was seriously injured and was evacuated to a local hospital while six other occupants were killed. The four passengers were employees of the Kazakhmys Mining Company. At the time of the accident, the visibility was poor due to fog.

The aircraft was performing a military cargo flight from Damascus, carrying food, potable water and ammunition for the Syrian soldiers fighting against the Islamic State. On final approach to Abu Adh Dhuhur AFB by night and foggy conditions, the aircraft descended too low and collided with high tension cables. It stalled and crashed in an open field located near the airport. All 24 passengers and six crew members were killed and the aircraft was totally destroyed by impact forces.

On or about 1000H January 17, 2015, the Holy Father “Pope Francis” visited the typhoon-devastated province of Leyte and utilized an Airbus 320 aircraft for Tacloban airport, and Bombardier Global 5000 RP-C9363 aircraft was part of the Papal entourage with passengers on board. The weather condition was worsening and the visit of the Pope had to cut short due to approaching tropical storm code named “AMANG”, with strong winds of up to 130km/h(80mph) according to PAGASA and moderate rain as signal n°2 was already forecasted at the province of Leyte. At 1304H, the Global 5000 RP-C9363 was given start up clearance by tower controller and subsequently a taxi clearance at 1308H to exit via south taxiway next to the departing Airbus320 PAL8010. At 1306H, the First Airbus 320 PAL8010 aircraft carrying the Papal entourage took-off utilizing RWY 36 with prevailing wind condition of 290̊/18 knots crosswind and temperature of 24°. At 1311H, RP-C 9363 was not allowed to move from present position to proceed to the active runway via south taxiway by the military ground marshaller. At 1322H, the 2nd Airbus 320 PAL8191 took-off with prevailing wind conditions of 290°/23 kts crosswind. The separation time between the Global 5000 to the first and second aircraft were 29 minutes and 13 minutes respectively. At 1335H, finally RP-C9363 Global 5000 was cleared for take-off at runway 36 bound for Ninoy Aquino International Airport (RPLL) with two (2) pilots and 14 passengers on board. The wind condition at that time was 300°/18 kts with gustiness and temperature of 24°. The aircrew performed rolling take-off and the acceleration was normal, the pilot nonflying (NPF) called for air speed alive, 80 knots, V1 and Rotate. Before approaching south taxiway abeam the terminal building, the aircraft started to veer to the left side of the runway centerline. The aircraft continued to roll veering to the left side of the runway and the left hand main landing gear was already out of the runway after the north taxiway. The aircraft underwent runway excursion and sustained substantial damage after simultaneous collision with the concrete bases of runway edge lights and to the concrete culvert before it came to a complete stop at approximately 1500 meters from the take-off point. Immediate evacuation was performed to all passengers. The crash and fire rescue personnel arrived at the area and assisted the passengers and aircrew.

For unknown reasons, the aircraft landed hard on runway 07 at Los Roques Airport. Upon impact, the right main gear collapsed and punctured the right wing. Out of control, the twin engine aircraft cartwheeled and came to rest near the runway shoulder. All 10 occupants escaped uninjured and the aircraft was damaged beyond repair.