Piper PA-31 Cheyenne

Larry Ray Pruitt

On June 5, 2020, about 1520 eastern daylight time, a Piper PA-31T, N135VE, was destroyed when it was involved in an accident near Eatonton, Georgia. The two pilots and the three passengers were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot/owner, who was seated in the left front seat of the airplane, held a private pilot certificate for single and multiengine airplanes with an instrument rating. He had filed an instrument flight rules (IFR) flight plan and was in contact with air traffic control (ATC) shortly after he departed from Williston Municipal Airport (X60), Williston, Florida, at 1413. The other pilot, who was seated in the front right seat, held a private pilot certificate for single engine airplanes only and had no instrument rating. A review of preliminary ATC communications and radar data provided by the Federal Aviation Administration (FAA) revealed that the airplane was on a northerly heading en route to New Castle Henry County Marlatt Field (UWL) New Castle, Indiana, at an altitude of 25,000 ft mean sea level (msl). When the airplane was about 50 miles south of Eatonton, Georgia, one of the pilot's told ATC that he was deviating "to the right a little" to avoid weather. When the airplane passed over Eatonton, one of the pilot's advised ATC that they wanted to proceed direct to their destination on a 353° heading, and ATC approved. This was the last communication between ATC and the airplane. About a minute later, the airplane was observed on radar entering a right turn, followed by a rapid descent. Radar contact was lost about 1520. There were no distress calls made by either pilot. Several witnesses observed the airplane as it was descending and took video with their cell phones. A review of these videos revealed the airplane was spinning as it descended, was on fire and trailing black smoke. The main wreckage of the airplane impacted densely wooded terrain inverted. The airplane continued to burn and the cockpit, fuselage, empennage, inboard sections of both wings and the right engine sustained extensive fire damage. The outboard sections of both wings and the tail section had separated from the airplane as it descended and were located within 3 miles of the where the main wreckage came to rest. The left engine had also separated but has not yet been not located.

FMR Aviation

On April 20, 2020 about 0950 mountain daylight time, a Piper PA-31T1 airplane, N926K, was destroyed when it was involved in an accident about 1-1/2 miles west of Billings Logan International Airport (BIL), Billings, Montana. The airline transport pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 local flight. According to ATC information, the pilot requested to taxi to runway 28L for takeoff, and then perform pattern work, and land on runway 28R at BIL. After the pilot held short of runway 28L, the controller cleared the pilot for takeoff with instructions to extend the upwind leg. Shortly after takeoff, the pilot was instructed to enter the left traffic pattern for runway 28R twice, with no response. A subsequent attempt was made to establish communication, with no response. About a minute and a half after the airplane departed, a column of smoke was observed west of the airport. Radar data showed the airplane departing runway 28L and remaining on runway centerline heading for the length of the flight. The airplane's altitude climbed to about 100 ft above ground level and the airplane's groundspeed increased to 81 knots soon after departure, and then decreased to 70 knots before dropping off radar. Witnesses located near the departure end of runway 28L watched the airplane through a window, depart the runway with its gear not retracted. The airplane was lower than normal as it neared the end of the runway. All the witnesses moved outside to watch as the airplane flew away from their location. One of the witnesses stated that the airplane had a "slow descent trajectory and a slight-nose up attitude." The airplane passed over a hill and out of view. None of the witness reportedly saw the accident sequence but saw the column of smoke rising from the accident site. Another witness who was sitting in his vehicle near the accident site saw the airplane pass about 250 ft in front of his position. The airplane's wings were level and the landing gear was up when it struck the ground. He lost sight of the airplane as it flew into a nearby coulee. Ground scars found near the top of a coulee consisted of the airplane's fuselage impact mark and symmetrical propeller strikes consistent with the airplane impacting the ground in a shallow, nose-up, wings-level attitude. The airplane then continued over the coulee about 410 ft, and about 75 ft down before impacting the side of the coulee where a postimpact fire ensued. All major structural components of the airplane were located within the debris field.

Cheyenne Partners

On December 28, 2019, about 0921 central standard time, a Piper PA 31T airplane, N42CV, impacted terrain shortly after takeoff from the Lafayette Regional Airport/Paul Fournet Field (LFT), Lafayette, Louisiana. The commercial pilot and four passengers were fatally injured; one passenger sustained serious injuries. Two individuals inside a nearby building sustained minor injuries and one individual in a car sustained serious injuries. The airplane was destroyed by impact forces and a postimpact fire. The airplane was owned by Cheyenne Partners LLC and was piloted by an employee of Global Data Systems. The personal flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. Instrument meteorological conditions prevailed and a Federal Aviation Administration (FAA) instrument flight rules (IFR) flight plan was filed for the flight. The flight was originating at the time of the accident and was en route to the Dekalb-Peachtree Airport (PDK), Atlanta, Georgia. The pilot contacted the LFT ground controller and requested a clearance to PDK. The controller issued the IFR clearance to the pilot with an initial heading of 240° and an altitude of 2,000 ft mean sea level (msl). The controller then instructed the pilot to taxi the airplane to runway 22L. As the airplane approached the holdshort line for the runway, the pilot advised that the airplane was ready for takeoff and the controller cleared the airplane to depart from runway 22L. After takeoff the pilot was given a frequency change and successfully established communications with the next air traffic controller. The pilot was instructed to climb the airplane to 10,000 ft and to turn right to a heading of 330°. Automatic Dependent Surveillance – Broadcast (ADS-B) data provided by the FAA identified and depicted the accident flight. The ADS-B data started at 09:20:05 as the airplane climbed through 150 ft. msl, or 110 ft. above ground level (agl). The peak altitude recorded was 925 ft msl, from about 09:20:37 to 09:20:40, after which, the airplane entered a continuous descent to the ground. The last ADS-B data point was at 09:20:59, as the airplane descended through 175 ft msl in a steep dive. Preliminary analysis of this data indicates that after departing runway 22L, the airplane turned slightly to the right toward the assigned heading of 240° and climbed at a rate that varied between 1,000 and 1,900 feet per minute. At 09:20:13, the airplane started rolling back towards wings level. At 09:20:20, the airplane rolled through wings level in a continued roll towards the left. At this time, the airplane was tracking 232°, the altitude was 475 ft msl, and the speed accelerated through 165 kts. calibrated airspeed. The airplane continued to roll steadily to the left, at an average rate of about 2 degrees per second. At the peak altitude of 925 ft msl at 09:20:40, the roll angle was about 35° left, the track angle was about 200°, and the airspeed was about 172 knots. The airplane then started to descend while the left roll continued, and the airplane reached a roll angle of 70° left at 09:20:52, while it descended through 600 ft msl, between 2,000 and 3,000 feet per minute. According to the FAA, as the airplane descended through 700 ft msl, a low altitude alert was issued by the air traffic controller to the pilot; the pilot did not respond. No mayday or emergency transmission was recorded from the accident airplane. According to multiple witnesses on the ground, they first heard an airplane flying overhead, at a low altitude. Several witnesses stated that it sounded as if both engines were at a high rpm. Multiple witnesses observed the airplane appear out of the low cloud bank in a steep, left-bank turn. One witness stated that the airplane rolled wings level just before it struck the trees and transmission lines on the south edge of Verot School Road. The airplane then struck the road and continued across the United States Postal Service (USPS) parking lot. Two USPS employees received minor injuries from flying glass inside of the building. One individual was seriously injured after the airplane struck the car she was parked in. The car rolled several times before it came to rest inverted; a postimpact fire consumed the car. The wreckage path included fragmented and burned pieces of the airplane and tree debris, and extended from the trees and transmission line, along an approximate bearing of 315°, for 789 ft. The right wing, the outboard left wing, both engines, both elevator controls, the rudder, the instrument panel, and forward cabin separated from the main fuselage and pieces were located in the debris field. The main wreckage consisted of the main fuselage and the inboard left wing. Before the accident the Automated Surface Observing System at LFT reported at 0853, a wind from 120° at 5 knots, overcast clouds with a vertical visibility of 200 ft and ¾ statute mile ground visibility. The temperature was 19° C, the dewpoint was 19°C, and the altimeter was 29.97 inches of mercury.

Bulldog Flying Club

The two pilots and three passengers were conducting a cross-country flight over the ocean from South Carolina to the Bahamas. About 30 minutes into the flight, while climbing through 24,300 ft to 25,000 ft about 95 miles beyond the coast, the pilot made a garbled radio transmission indicating an emergency and intent to return. At the time of the transmission the airplane had drifted slightly right of course. The airplane then began a descent and returned on course. After the controller requested several times for the pilot to repeat the radio transmission, the pilot replied, "we're descending." About 15 seconds later, at an altitude of about 23,500 ft, the airplane turned sharply toward the left, and the descent rate increased to greater than 4,000 ft per minute, consistent with a loss of control. Attempts by the air traffic controller to clarify the nature of the emergency and the pilot's intentions were unsuccessful. About 1 minute after the sharp left turn and increased descent, the pilot again declared an emergency. No further communications were received. Search efforts coordinated by the U.S. Coast Guard observed an oil slick and some debris on the water in the vicinity of where the airplane was last observed via radar, however the debris was not identified or recovered. According to recorded weather information, a shallow layer favorable for light rime icing was present at 23,000 ft. However, because the airplane was not recovered, the investigation could not determine whether airframe icing or any other more-specific issues contributed to the loss of control. One air traffic control communication audio recording intermittently captured the sound of an emergency locator transmitter (ELT) "homing" signal for about 45 minutes, beginning near the time of takeoff, and ending about 5 minutes after radar contact was lost. Due to the intermittent nature of the signal, and the duration of the recording, it could not be determined if the ELT signal had begun transmitting before or ceased transmitting after these times. Because ELT homing signals sound the same for all airplanes, the source could not be determined. However, the ELT sound was recorded by only the second of two geographic areas that the airplane flew through and began before the airplane arrived near either of those areas. Had the accident airplane's ELT been activated near the start of the flight, it is unlikely that it would be detected in the second area and not the first. Additionally, the intermittent nature of the ELT signal is more consistent with an ELT located on the ground, rather than an airborne activation. An airborne ELT is more likely to have a direct line-of-sight to one or more of the ground based receiving antennas, particularly at higher altitudes, resulting in more consistent reception. The pilot's initial emergency and subsequent radio transmissions contained notably louder background noise compared to the previous transmissions. The source or reason for the for the increase in noise could not be determined.

T-210 Holdings

The airline transport rated pilot and passenger departed on a cross-country business flight in a twin-engine, turbo-propeller-equipped airplane in day, visual meteorological conditions. Shortly after takeoff, the airplane banked left, descended, and impacted terrain about 1/2 mile from the end of the runway. There was not a post-crash fire and fuel was present on site. A postaccident airframe examination did not reveal any anomalies that would have precluded normal operation. Examination of the left engine found signatures consistent with the engine producing power at impact. Examination of the right engine revealed rotational scoring on the compressor turbine disc/blades, and rotational scoring on the upstream side of the power vane and baffle, which indicated that the compressor section was rotating at impact; however, the lack of rotational scoring on the power turbine disc assembly, indicated the engine was not producing power at impact. Testing of the right engine's fuel control unit, fuel pump, propeller governor, and overspeed governor did not reveal any abnormities that would have accounted for the loss of power. The reason for the loss of right engine power could not be determined based on the available information.

Symbios Orthopédie

On April 17th, at 11:04 UTC, the aircraft turboprop Piper PA-31 Cheyenne II, registration HBLTI, private property, took off from runway 17 of the Cascais aerodrome (LPCS) bound to Marseille airport (LFML), IFR private flight, with 1 pilot and 3 passengers on board. According to several eyewitness testimonies, after takeoff, the Swiss twin-engine started to put the left wing down and consequently to turn left while climbing slowly to about 300’ feet of altitude. The left bank1 increased and the speed decreased leading the aircraft to stall. The aircraft entered a steep dive and impacted the ground next to a logistics dock of a local supermarket, located southeast of the airfield. The crash occurred 700 m from the end of the departure runway. Following the impact, the aircraft exploded and caught fire affecting a logistic dock, a house and a truck. The aircraft was destroyed by impact force and the post-collision fire, all the four occupants were killed. The driver of the truck affected by the explosion of the plane was also killed. The fuselage, wings, the engines and propellers were severely damaged by the impact force and post-impact fuel-fed fire. The structural damage to the aircraft was consistent with the application of extensive structural loads during the impact sequence, and the effects of the subsequent fire. No pre-crash structural defects were found. All aircraft parts and control surfaces were located at the site. The flaps and the landing gear were found retracted at the time of impact.

American Medflight Air Ambulance

The airline transport pilot departed in the twin-engine, turbine-powered airplane on an air ambulance flight with two medical crew members and a patient on board in night visual meteorological conditions. According to a witness, during the initial climb, the airplane made a left turn of about 30° from the runway heading, then stopped climbing, made an abrupt left bank, and began to descend. The airplane impacted a parking lot and erupted into flames. In the 2 months before the accident, pilots had notified maintenance personnel three times that the left engine was not producing the same power as the right engine. In response, mechanics had replaced the left engine's bleed valve three times with the final replacement taking place three days before the accident. In addition, about 1 month before the accident, the left engine's fuel control unit was replaced during trouble shooting of an oil leak. Post accident examination revealed that the right engine and propeller displayed more pronounced rotational signatures than the left engine and propeller. This is consistent with the left engine not producing power or being at a low power setting at impact. Further, the abrupt left bank and descent observed by the witness are consistent with a loss of left engine power during initial climb. The extensive fire and impact damage to the airplane precluded determination of the reason for the loss of left engine power.

Cal-Ore Life Flight

About 13 minutes after takeoff for a medical transport flight, while climbing through about 14,900 ft mean sea level (msl), the pilot reported to air traffic control (ATC) that he was smelling smoke in the cockpit and would be returning to the originating airport. The flight was cleared to return with a descent at pilot's discretion to 9,000 ft msl. The pilot replied, "okay," and said that it looked like he was going to lose some power shortly. The pilot then stated that he had smoke in the cockpit, declared an emergency, and requested that ATC contact the fire department. About 1 minute 15 seconds after the initial report of smelling smoke, the pilot made the last radio transmission of the flight stating that he had three people on board. The wreckage was located about 9 hours later in an area of brush and heavily forested terrain. Portions of the burned and fragmented wreckage were scattered along a debris path that measured about 2,400 ft in length, which is consistent with an inflight breakup. The center fuselage and cockpit areas were largely intact and displayed no evidence of fire; however, there was an area of thermal damage to the forward fuselage consistent with an inflight fire. The thermal damage was primarily limited to the floor area between the two forward seats near the main bus tie circuit breaker panel and extended to the forward edge of the wing spar. All exposed surfaces were heavily sooted. Some localized melting and thermal-related tearing of the aluminum structure was present. The primer paint on the floor panels under the right aft corner of the pilot seat and the left aft corner of the co-pilot seat was discolored dark brown. An aluminum stringer in this location exhibited broomstrawing indicating that the stringer material was heated to near its melting point prior to impact. A single wire located in the area exhibited notching consistent with mechanical rubbing. The main bus tie circuit breakers were partially missing. The remaining breakers were heavily sooted on their aft ends, and one breaker was thermally discolored. Areas of charring were on the backside of the panel. Examination of the wiring in this area showed evidence of electrical arcing damage. Four hydraulic lines servicing the landing gear system were located in this area, and all the lines exhibited signs of thermal exposure with melting and missing sections of material. Six exemplar airplanes of the same make and model as the accident airplane were examined, and instances of unsafe conditions in which electrical lines and hydraulic lines in the area of the main bus tie circuit breaker panel were in direct contact were found on all six airplanes. Some of the wires in the exemplar airplanes showed chafing between hydraulic lines and the electrical wires, which, if left uncorrected, could have led to electrical arcing and subsequent fire. Based on the unsafe conditions found during examination of the exemplar airplanes and the thermal damage to the area near the main bus tie circuit breaker panel on the accident airplane, including broomstrawing of the aluminum structure, electrical arcing damage to the wiring, and melting of the hydraulic lines, it is likely that an electrical wire near the tie bus circuit breakers chafed on a hydraulic line and/or airplane structure, which resulted in arcing and a subsequent in-flight fire that was fed by the hydraulic fluid.

Inversiones PTT

Following an uneventful flight from Charallave, the pilot initiated the descent to Barcelona-Jose Antonio Anzoátegui Airport in poor weather conditions. On final, in a flat attitude, the twin engine aircraft impacted the water surface and came to rest some 3,7 km short of runway 15. All four occupants evacuated the cabin and took place in a lifeboat. Slightly injured, they were rescued two hours later. The aircraft sank and was lost.

Aircraft Guaranty Corporation Trustee

Following an uneventful personal flight, the pilot contacted the air traffic control tower controller and was immediately cleared to land. About 36 seconds later, the pilot reported "smoke in the cockpit." When asked to repeat, the pilot repeated "smoke in the cockpit." The tower controller cleared the pilot to land on any runway. About 47 seconds after the initial call of smoke, the pilot reported "mayday mayday mayday mayday mayday (unintelligible)." The airplane then crashed about ¼ mile short of the airport in a wooded area and burned. Security video showed the airplane pitch nose-down suddenly just before impact. The video revealed no visible smoke or fire trailing the airplane before ground impact. The pilot reported about 1,221 hours of total flight time on his Federal Aviation Administration first class medical certificate, issued about two months prior to the accident. He completed an initial training course for the airplane make and model 1 week before the accident. The airplane had recently undergone an annual inspection and extensive upgrades to its avionics. Both the left and right engines displayed contact signatures to their internal components characteristic of engines developing significant power at the time of impact, likely in the mid-to-high power range. The engines displayed no indications of any pre-impact anomalies or distress that would have precluded normal engine operation. Both propeller assemblies broke free from the engine during the crash sequence and the blades on both engines revealed signatures consistent with the development of power at impact. The center fuselage and cockpit areas were completely consumed in the postcrash fire. An examination of all remaining wires, wire bundles, switches, terminals, circuit breakers, electrical components, instruments, and avionics did not reveal evidence of precrash thermal distress. However, a small fire just before impact likely would not have had time to create thermal damage that would be discernable after an extensive postcrash fire.

Miami Aviation Specialist

The multiengine airplane had not been flown for about 4 months and was being prepared for export. The pilot was attempting a local test flight after avionics upgrades had been performed. Shortly after takeoff, the pilot transmitted that he was experiencing an "emergency"; however, he did not state the nature of the emergency. The airplane was observed experiencing difficulty climbing and entered a right turn back toward the airport. It subsequently stalled, rolled right about 90 degrees, and descended. The airplane impacted several parked vehicles and came to rest inverted. A postcrash fire destroyed the airframe. Both engines were destroyed by fire and impact damage. The left propeller assembly was fire damaged, and the right propeller assembly remained attached to the gearbox, which separated from the engine. Examination of wreckage did not reveal any preimpact malfunctions. It was noted that the left engine displayed more pronounced rotational signatures than the right engine, but this difference could be attributed to the impact sequence. The left propeller assembly displayed evidence of twisting and rotational damage, and the right propeller assembly did not display any significant evidence of twisting or rotational damage indicative of operation with a difference in power. The lack of flight recorders and the condition of the wreckage precluded the gathering of additional relevant information.

Nothman Jerry Company Trustee

The private pilot and passenger departed on the 875-nautical-mile cross-country flight and leveled off at a cruise altitude of 24,000 feet mean seal level, which, based on the radar data, was accomplished with the use of the autopilot. About 1 hour 40 minutes after departure, the pilot contacted air traffic control personnel to request that he would “like to leave frequency for a couple of minutes.” No further radio transmissions were made. About 20 seconds after the last transmission, the airplane banked to the right, continued in a spiral while rapidly descending, and subsequently broke apart. At no time during the flight did the pilot indicate that he was experiencing difficulty or request assistance. Just prior to departing from the flight path, the pilot made an entry of the engine parameters in a flight log, which appeared to be consistent with his other entries indicating the airplane was not experiencing any difficulties. Portions of the wings, along with the horizontal stabilizers and elevators, separated during the breakup sequence. Analysis of the fracture surfaces, along with the debris field distribution and radar data, revealed that the rapid descent resulted in an exceedance of the design stress limits of the airplane and led to an in-flight structural failure. The airplane sustained extensive damage after ground impact, and examination of the engine components and surviving primary airframe components did not reveal any mechanical malfunctions or failures that would have precluded normal operation. The airplane was flying on a flight path that the pilot was familiar with over largely unpopulated hilly terrain at the time of the upset. The clouds were well below his cruising altitude, giving the pilot reliable external visual cues should the airplane have experienced a failure of either the flight instruments or autopilot. Further, no turbulence was reported in the area. The airplane was equipped with a supplemental oxygen system, which the pilot likely had his mask plugged into and available in the unstowed position behind his seat; the passenger’s mask was stowed under her seat. The airplane’s autopilot could be disengaged by the pilot by depressing the appropriate mode switch, pushing the autopilot disengage switch on the control wheel, or turning off the autopilot switch on the control head. All autopilot servos were also equipped with a clutch mechanism that allowed the servo to be manually overridden by the pilot at any time. It is likely that the reason the pilot requested to “leave the frequency” was to leave his seat and attend to something in the airplane. While leaving his seat, it is plausible he inadvertently disconnected the autopilot and was unable to recover by the time he realized the deviation had occurred.

Taxi Aéreo Hércules

The twin engine aircraft departed Dourados-Francisco de Matos Pereira Airport on an on-demand flight to Curitiba, carrying two passengers, two pilots and a load consisting of valuables. On final approach to Curitiba-Bacacheri Airport, both engines failed simultaneously. The crew attempted an emergency landing when the aircraft crashed in a field and came to rest near trees. A passenger was seriously injured while three other occupants were killed. The following day, the only survivor died from his injuries.

Private Brazilian

The twin engine aircraft was engaged in an illegal flight, carrying two pilots and a load consisting of 600 kilos of cocaine. After being tracked by the Honduran Police, the crew apparently attempted an emergency landing when the aircraft crashed. While the copilot was injured, the captain was killed.

Compañía Chilena de Fósforos

The twin engine aircraft departed Santiago-Eulogio Sánchez Errázuriz-Tobalaba Airport at 1815LT on a flight to Puerto Montt, carrying seven passengers and one pilot. On approach to Puerto Montt-Marcel Marchant Airport runway 19, his attention was focused on the GPS and he forgot to lower the landing gear. The aircraft belly landed and slid for few dozen metres before coming to rest on the main runway. All eight occupants escaped uninjured while the aircraft was damaged beyond repair.

Johannes Ruttinger Systemtechnik

The pilot, accompanied by three passengers who were family members, took off at 1835LT from Kassel-Calden Airport (Germany) for a private flight under IFR to Toulouse-Blagnac. After about three hours of flight, he was cleared for approach and received radar vectoring for the runway 14R ILS. During the last exchange with the controller, as the aeroplane was on final at 900 feet, the pilot stated that he had a problem without specifying what type, as the message was interrupted. Shortly afterwards, radar and radio contact was lost. The wreckage was found close to the threshold of runway 14R. Two passengers were rescued while the pilot and another passenger were killed. The occupants were four members of the same family : the parents and two children, a boy aged nine and a girl aged 13. While the parents were killed upon impact, the daughter died from her injuries a day later and the boy died three days later.

Línea de Aeroservicios - LASSA

The twin engine aircraft departed Robinson Crusoe Island on a cargo flight to Valparaiso, carrying one passenger, one pilot and a load consisting of 1,000 lbs of lobsters. Upon landing at Valparaiso Airport in good weather conditions, the airplane went out of control, veered off runway, crossed a road and came to rest in a wooded area located along the highway. The aircraft was damaged beyond repair and both occupants escaped with minor injuries.

Rajet Aeroservicios

The twin engine aircraft was chartered by the State of Coahuila to conduct a survey flight of the area around Piedras Negras following recent floods and damages caused by hurricane Alex. The aircraft departed Piedras Negras Airport at 0930LT bound to the northwest. En route, while performing an aerial inspection of the area around the La Fragua Lake, the aircraft went out of control and crashed in a field, bursting into flames. The wreckage was found 600 metres south of the La Fragua Dam, about 35 km northwest of Piedras Negras Airport. The aircraft was destroyed by a post crash fire and all 8 occupants were killed. Crew: Juan Roberto Rendón, pilot, Guillermo Ainsle Ibarra, copilot. Passengers: Horacio del Bosque Dávila, Coahuila's Secretary of Public works, José Manuel Maldonado Maldonado, Mayor of Piedras Negras, Ricardo Garza Bermea, Director of the Piedras Negras Civil Protection, David Rey Chavira Jiménez, Guillermo Ainsle Montemayor, Alfonso Ainsle Montemayor.

Skymaster Air Services

The twin engine aircraft, with a pilot and a flight nurse on board, was being operated by Skymaster Air Services under the instrument flight rules (IFR) on a flight from Bankstown Airport, New South Wales (NSW) to Archerfield Airport, Queensland. The aircraft was being positioned to Archerfield for a medical patient transfer flight from Archerfield to Albury, NSW. The aircraft departed Bankstown at 0740 Eastern Standard Time. At 0752, the pilot reported to air traffic control (ATC) that he was turning the aircraft around as he was having ‘a few problems. At about 0806, the aircraft collided with a powerline support pole located on the eastern side of the intersection of Sackville Street and Canley Vale Road, Canley Vale, NSW. The pilot and flight nurse sustained fatal injuries and the aircraft was destroyed by impact damage and a post-impact fire.

Mayes Aviation

A witness reported that the multi-engine turboprop airplane was on final approach to land when it suddenly veered to the left and entered a rapid descent. The witness stated that he heard the "whine of the engines" before the airplane impacted terrain about 1/2 mile south of the runway threshold. In the days preceding the accident flight, the airplane had been at a maintenance facility to resolve a vibration in the rudder system while the autopilot system was engaged. There were no anomalies reported with the autopilot system during a test flight completed immediately before the accident flight. However, anomalies with the rate gyro were noted by a mechanic who recommended replacing it, but the pilot departed on the accident flight without the recommended repair having been completed. Further, examination of the autopilot annunciator panel indicated that the autopilot was likely not engaged at the time of impact, likely because the airplane was on a short final approach for landing. Accordingly, any existing autopilot faults would not have affected the flight as the autopilot system was likely not in use. There were no failures identified with the primary flight controls, engines, or propellers that would have prevented the pilot from maintaining control of the airplane manually. Toxicological testing revealed the presence of Zolpidem in the pilot's blood (Zolpidem, the trade name for Ambien, is used for short-term treatment of insomnia); however, the reported levels would likely not have resulted in any impairment.

Cheyenne Sales %26 Leasing

Shortly after takeoff in the pressurized twin-engine airplane, the pilot was cleared to climb and maintain 16,000 feet. The pilot reported passing through instrument conditions with heavy snow and that he cleared the tops of the clouds at 7,000 feet. The pilot was then cleared to climb and maintain flight level (FL) 230. Radar data showed the airplane's altitude and course varied throughout the flight after having reached FL 230. Several times during the flight the air traffic controller questioned the pilot regarding his altitude and/or course. Each time the pilot responded that he was at the correct altitude and/or course. The radar data showed that after each of these conversations, the airplane would return to the assigned altitude and/or course. The controller then informed the pilot that, because radar showed the airplane’s altitude fluctuating between FL 224 and FL 237, he was going to have to descend out of positive controller airspace. The pilot acknowledged this transmission. The controller instructed the pilot to descend to 17,000 feet. The last transmission from the pilot was when he acknowledged the descent. Radar data showed that one minute later the airplane was at FL 234. During the last minute and 12 seconds of radar data, the airplane reversed its course and descended from FL 233 to FL 214, at which time radar data was lost. Witnesses reported hearing loud engine sounds and seeing the airplane in a spiraling descent until ground impact. Post accident inspection of the engines did not identify any anomalies that would have precluded normal operation. Most of the fuselage was consumed by fire; however, flight control continuity was established. Given the pilot’s experience and the flight’s altitude and course variations the investigation considered that the pilot may have suffered from hypoxia; however, due to the post impact fire the functionality of the airplane’s pressurization system could not be observed and no conclusive determination could be made that the pilot as impaired.

Avia Center

Shortly after a night takeoff from runway 05 at Buenos Aires-San Fernando Airport, the pilot initiated a left turn at low altitude when the twin engine aircraft collided with two poles and two parked trucks then crashed on the ground, bursting into flames. The aircraft was totally destroyed and both occupants were killed.

Dovler Mangelli Fonialli

The twin engine aircraft departed San Cristóbal-Paramillo Airport on a private flight to Charallave with two passengers and one pilot on board. At 2319LT, he was cleared for a VOR-DME approach to runway 10. It was dark but the visibility was about 10 km. Shortly later, another aircraft on approach declared an emergency and became priority. The pilot was instructed to follow a holding pattern when two minutes later, the aircraft struck trees and crashed in a wooded and hilly terrain, bursting into flames. The wreckage was found the following morning 5,5 km northeast of the airport. The aircraft was totally destroyed and all three occupants were killed.

Westair Aviation

The twin engine aircraft made a wheels-up landing at Foremost Airport. The pilot, sole on board, was uninjured while the aircraft was damaged beyond repair. For unknown reasons, the landing gear had not been extended on approach.

We-Lease

On approach to Madison-Dane County-Truax Field, the pilot encountered technical problems with the right main gear that remained stuck in its wheel well. He decided to retract the gear and to complete a wheels-up landing. The twin engine aircraft belly landed and slid for few dozen metres before coming to rest. Both occupants escaped uninjured and the aircraft was damaged beyond repair.

BHS Direct

The pilot departed Zweibrücken Airport on a flight to Athens with an intermediate stop in Split as the aircraft should be delivered to its new owner based in Greece. After takeoff from runway 21 at Zweibrücken Airport, while in initial climb, the aircraft deviated to the left while the standard departure route was a straight climb until 7 nm. The pilot was contacted by ATC and reported problems. Shortly later, the altitude of the aircraft fluctuated from 1,500 to 3,200 feet and again, the pilot was contacted by ATC to check the situation. Few seconds later, the aircraft entered an uncontrolled descent and crashed in an open field located in Rieschweiler, about 6 km northeast of the airport. The aircraft was totally destroyed upon impact and the pilot, sole on board, was killed. It was reported that, prior to departure, the pilot encountered difficulties to close the main cabin door and had to be shown how to operate it. A member of the FBO staff then asked the pilot if he should explain the aircraft's avionics and, after the pilot replied yes, went on to describe how to operate the RNAV system. The pilot then had difficulty in starting the right engine and was directed to the 'ignition switch' on the overhead panel.

Private Guatemalan

On final approach to Quetzaltenango-Los Altos Airport, the pilot encountered engine problems. He completed a belly landing in a wheatfield located few km from the airport. The pilot escaped uninjured while the aircraft was damaged beyond repair.

Air Loop

The twin engine aircraft departed Valetta Airport, Malta, on a night flight to Milan-Linate Airport, carrying one passenger and one pilot. After passing Elba Island at an altitude of 21,000 feet, over the Gulf of Genoa, the aircraft deviated from the prescribed route to the east while it was supposed to pass over Genoa before descending to Milan. Few minutes later, the aircraft entered an uncontrolled descent and crashed in a wooded and hilly terrain located in Cassano di Centenaro, about 43 km southwest of Piacenza. The aircraft disintegrated on impact and both occupants were killed.

D %26 R Henderson

At 0906 Eastern Standard Time on 28 July 2004, a Piper Aircraft Corporation PA31T Cheyenne aircraft, registered VH-TNP, with one pilot and five passengers, departed Bankstown, New South Wales on a private, instrument flight rules (IFR) flight to Benalla, Victoria. Instrument meteorological conditions at the destination necessitated an instrument approach and the pilot reported commencing a Global Positioning System (GPS) non-precision approach (NPA) to Benalla. When the pilot had not reported landing at Benalla as expected, a search for the aircraft was commenced. Late that afternoon the crew of a search helicopter located the burning wreckage on the eastern slope of a tree covered ridge, approximately 34 km southeast of Benalla. All occupants were fatally injured and the aircraft was destroyed by impact forces and a post-impact fire.

Oracam

The twin engine aircraft departed Tel Aviv on a flight to Toussus-le-Noble with an intermediate stop in Corfu, carrying two passengers and one pilot. On approach at 3,000 feet, the aircraft' speed and height dropped. It entered an uncontrolled descent and crashed in a wooded area located in Dampierre-en-Yvelines, about 10 km from the runway 07L threshold. All three occupants were killed.

Lee Larson Aircraft Sales

A Piper PA-31T "Cheyenne" and a Cessna 172P "Skyhawk" collided in midair during cruise flight at dusk and in visual meteorological conditions. The Cheyenne departed under visual flight rules (VFR) from a local airport northwest of Denver, and was proceeding direct at 7,800 feet to another local airport south of Denver. Radar indicated its ground speed was 230 knots. Its altitude encoder was transmitting intermittently. The Skyhawk departed VFR from the south airport and was en route to Cheyenne, Wyoming, at 7,300 feet. The pilot requested and was cleared to climb to 8,500 feet and penetrate class B airspace. Radar indicated its ground speed was 110 knots. The Skyhawk was flying in the suggested "VFR flyway"; the Cheyenne was not. When the controller observed the two airplanes converging, he asked the pilot of the Cheyenne for his altitude. He replied he was at 7,600 feet. The controller immediately issued a traffic advisory, but the pilot did not acknowledge. Both airplanes departed controlled flight: the Skyhawk struck a house, and the Cheyenne fell inverted into the backyard of a residence. Wreckage was scattered over a 24 square block area in west Denver. At the time of the accident, the controller was handling low altitude en route, arrival and departure traffic for both airports. Wreckage examination disclosed four slashes, consistent with propeller strikes, on top of the Cheyenne's right engine nacelle, the cabin above the right wing trailing edge, the empennage at the root of the dorsal fin, and at the tail cone. The Cheyenne was on a similar flight three days before the collision when the pilot was informed by air traffic control that the transponder was operating intermittently. According to recorded radar and voice communications from that flight, the transponder/encoder operated intermittently and the pilot was so advised. Examination of the Cheyenne's altimeter/encoder revealed a cold solder connection on pin 8 of the 15-pin altimeter connector. When the wire was resoldered to the pin, the information from the altimeters, encoder, and altitude serializer was normal.

Robert D. Calhoon

The pilot of the twin turbo-prop airplane lost control of the aircraft during the initial takeoff climb phase while in instrument meteorological conditions. An instrument flight rules flight plan was filed for the planned 169-nautical mile cross-country flight. The aircraft impacted terrain approximately 1.7 miles northwest of the departure airport. The 2,893-hour instrument rated private pilot, who had accumulated over 765 flight hours in the same make and model, had been cleared to his destination "as filed," and told to maintain 7,000 feet, and to expect 17,000 feet in 10 minutes. After becoming airborne, the flight was cleared for a left turn. The tower controller then cleared the flight to contact air route traffic control center. The pilot did not acknowledge the frequency change; however, he did establish radio contact with center on 133.1, and reported "climbing through 4,900 feet for assigned 7,000." The weather reported at the time of flight was winds from 010 degrees at 15 knots with 700 feet overcast and 3 miles visibility in mist. The radar controller observed the aircraft climbing through 5,500 feet and subsequently observed the airplane starting a descent. No distress calls were received from the flight. Signatures at the initial point of impact were consistent with a nose-low ground impact in a slight right bank. A post-impact fire consumed the airplane. No discrepancies or anomalies were found at the accident site that could have prevented normal operation of the airplane.

Alibrixia Nord

Crashed upon takeoff for unknown reasons. There were no casualties.

Robert D. Calhoon

At the conclusion of a dark night IMC cross-country flight, the pilot was being vectored onto the ILS approach. After stabilizing, the approach "was normal." At decision altitude, the pilot indicated that he could see the approach lights and the runway, but was not in a position to land so he executed a missed approach. After being vectored around for another approach, he stated that he was on the localizer but was "high" on the glide slope. After giving "a little" nose down pitch, he became distracted when the autopilot became "accidentally disengaged." The pilot stated that he "inadvertently descended through the glide slope and impacted the ground short of the runway." He further stated that the "first indication" that he was low was when the aircraft "struck the ground." The aircraft was destroyed on impact. A facility check conducted by the FAA of the ILS found all parameters within normal specifications.

Cage Acquisitions

At 2144, the pilot contacted air traffic control and requested visual flight rules (VFR) flight following to his destination. The flight was the final leg of a four-leg trip, which the pilot had begun approximately 1120 that morning. At 2220, the flight began a slow descent toward the destination airport. Radar data confirmed that the airplane executed a steady descent, and flew a straight line course toward Graham. The final radar return occurred 37 minutes later at an altitude of 3,000 feet (radar coverage is not available below 3,000 feet), 8 miles southeast of the Graham Municipal Airport. Two minutes after the final radar return, the pilot reported to air traffic control that the flight was two miles out, and he canceled VFR flight following. No further communications or distress calls were received from the airplane. The pilot did not request or receive updated weather from the air traffic controllers during the flight. According to witnesses who lived near the accident site, they heard an airplane flying low, observed dense fog and heard the sounds of an airplane crashing. According to the nearest weather reporting station, near the time of the accident, the temperature- dew point spread was within 2 degrees, visibilities were reduced to between 3 and 4 miles in fog, and the ceiling was decreasing from 600 feet broken to 400 feet overcast. At the time of the accident, the pilot's duty day exceeded 12 hours. Examination of the airframe revealed no preimpact anomalies and that the gear was extended and the flaps were retracted. Examination of both engines revealed evidence of power at the time of impact.

Falcon Communications

About 20 minutes before the accident, the pilot reported to the air traffic controller that he had a problem with an engine and needed to shut the engine down. The flight had just leveled at 23,000 feet. The controller told the pilot that he was near Jackson, Tennessee, and that he could descend to 7,000 feet. About 10 minutes later, the pilot reported he was at 8,000 feet and requested radar vectors for the instrument landing system approach to runway 2 at the McKellar-Sipes Regional Airport, at Jackson. The pilot told the controller he had the left engine shut down. About 5 minutes later, the pilot reported he had a propeller runaway. About 1 minute later, the pilot reported he was in visual conditions and requested radar vectors direct to the airport. About 2 minutes later, the pilot reported he had a cloud layer under him and that he had the localizer frequency for runway 2 set. About 1 minute later, the pilot was told to contact the McKellar Airport control tower. The pilot acknowledged this instruction. No further transmissions were received from the flight. Examination of the left engine at the accident site showed the left propeller control was found disconnected at the point the propeller control extension bracket attaches to the propeller governor. The propeller control cable had also pulled loose from a swaged point at the control rod and was also separated further aft due to overstress. The housing for the propeller control rod was found securely attached to the engine and the control rod was securely attached to the extension bracket. The propeller governor control arm, which was disconnected from the propeller control cable and rod, was found spring loaded into the high RPM position. Examination of the fractured left propeller bracket assembly was performed by the NTSB Materials Laboratory, Washington, D.C. The bracket assembly was fractured in the area of the outermost eyehole, at the point a bolt passes through the bracket assembly and the propeller governor arm. The fracture surface contained small amounts of dirt, grease, and minor corrosion. The fracture surface features include flat areas that lie on multiple planes separated by ratchet marks, features typically left behind by the propagation of a fatigue crack. The fatigue crack emanated from multiple origins on opposite sides of the bracket. The total area of the fatigue crack occupied approximately 85 percent of the fracture surfaces. The fatigue fractures initiated on the outer edges of the surface and propagated inward toward the center. The remaining 15% of the fracture surface had features consistent with overstress separation. Near the middle of each fatigue region were microfissures suggesting that the crack propagated under high-stress conditions. The NTSB Materials Laboratory also examined the separation point between the left propeller control flexible cable and the rigid rod that connects to the bracket assembly. The cable and the swaged part of the rigid rod were in good condition with no fractures or damage. The Piper PA-31-T2 Pilot Operating Handbook, Section 3, Emergency Procedures, does not contain a procedure for loss of propeller control. Section 3 did contain a procedure for "Over speeding Propeller", which stated that if a propellers speed should exceed 1,976 rpm, to place the power lever of the engine with the over speeding propeller to idle, feather the propeller, place the engine condition lever in the stop position, and complete the engine shutdown procedures. Pilot logbook records show the pilot completed a simulator training course for the accident model airplane about 9 days before the accident and had about 13 flight hours in the Piper PA-31-T2.

Unifly

The twin engine aircraft departed Douala on a charter flight to N'Djamena, carrying one pilot, one steward and two members of the Chadian Government. While approaching N'Djamena Airport, weather conditions deteriorated and the visibility was limited due to a sand storm. Probably to establish a visual contact with the ground, the pilot reduced his altitude when the aircraft struck a tree and crashed about 3 km from the runway 05 threshold, near Kousséri, Cameroon. The steward was seriously injured while all three other occupants were killed, among them the pilot, a Spanish citizen and both passengers who were Amderamane Dadi, General Secretary of the Presidency, and Ali Ahmed Lanine, Chadian Minister for Economic Promotion and Development.

Udélio Scodro

The twin engine aircraft departed Goiânia on a private flight to Ribeirão Preto, carrying four passengers and two pilots, the aircraft's owner and a friend. Three minutes after being cleared by Brasilía Control Center, at an altitude of 18,000 feet, the pilot informed ATC about poor weather conditions and severe turbulences. Shortly later, the aircraft entered an uncontrolled descent and crashed in a sugarcane field located near Água Comprida. The aircraft was destroyed by impact forces and a post crash fire and all six occupants were killed.

Cape Smythe Air Service

The airline transport certificated pilot was landing at a remote village on a scheduled domestic commuter flight with nine passengers. The accident airplane, a twin-engine turboprop certified for single-pilot operations, was equipped with a fuselage-mounted belly cargo pod. Witnesses saw the airplane touch down on the gravel runway with the landing gear retracted. The belly pod lightly scraped the runway for about 40 feet before the airplane transitioned to a climb. The propeller tips did not contact the runway. As the airplane began climbing away from the runway, the landing gear was extended. The airplane climbed to about 100 to 150 feet above the ground, and then began a descending left turn, colliding with tundra-covered terrain. A postcrash fire destroyed the fuselage, right wing, and the right engine. The flaps were found extended to 40 degrees. The balked landing procedure for the airplane states, in part: "power levers to maximum, flaps to 15 degrees, landing gear up, and then retract the flaps." Five passengers seated in the rear of the airplane survived the crash. The survivors did not recall hearing a gear warning horn before ground contact. The airplane was landed gear-up eight months before the accident. The airplane was nearly landed gear-up four months before the accident. Each time, a landing gear warning horn was not heard by the pilot or passengers. A postcrash examination of the airplane and engines did not locate any preimpact mechanical malfunction. The FAA's Fairbanks, Alaska, FSDO conducted an inspection of the operator six months before the accident, and recommended the operator utilize two pilots in the accident airplane. Following the accident, the Fairbanks FSDO required the operator to utilize two pilots for passenger flights in the accident airplane make and model.

Rougier

The twin engine aircraft departed Douala on a flight to Abong Mbang with an intermediate stop in Djoum, carrying five passengers and one pilot. On final approach to Abong Mbang, the pilot encountered poor weather conditions with limited visibility due to heavy rain falls. On short final, the aircraft struck the ground about 60 metres short of runway threshold. Upon impact, the undercarriage were torn off and the aircraft came to rest on its belly. All six occupants escaped uninjured while the aircraft was damaged beyond repair.

Cape Smythe Air Service

The airplane collided with frozen pack ice, three miles from the airport, during a GPS instrument approach. Instrument conditions of 3/4 mile visibility in snow and fog were reported at the time of the accident. The pilot stated that he began a steep descent with the autopilot engaged. He indicated that as the airplane crossed the final approach course, the autopilot turned the airplane inbound toward the airport. He continued the steep descent, noted the airplane had overshot the course, and the autopilot was not correcting very well. He disengaged the autopilot and manually increased the correction heading to intercept the final approach course. During the descent he completed the landing checklist, extended the landing gear and flaps, and was tuning both the communications and navigation radios. The pilot said he looked up from tuning the radios to see the sea ice coming up too quickly to react, and impacted terrain. The pilot relayed there were no pre accident anomalies with the airplane, and that he 'did not stay ahead of the airplane.'

Cape Smythe Air Service

The airline transport certificated pilot was landing a twin-engine turboprop airplane at a remote airport on a scheduled air taxi flight. Rising hilly terrain is located east of the airport. The pilot said that during the approach for landing, he noticed the airport wind sock indicating a wind from the east about 25 knots. When the pilot descended to 500 feet, about mid-base, the airplane encountered moderate turbulence and an increased rate of descent. He added engine power to arrest the descent. As he turned toward the runway, the airplane encountered 3 to 4 rolling oscillations with a bank angle up to 90 degrees while descending toward the runway. According to a company mechanic who traveled to the scene, it appeared that the airplane struck the runway about 1,200 feet from the approach end with the left wing and left elevator, while yawed about 45 degrees to the left of the runway centerline. The airplane then slid off the left side of the runway. After the collision, the pilot evacuated the passengers, and noticed the airport wind sock was indicating a tailwind. The Airport/Facility Directory contains the following in the airport remarks: 'Unattended. Easterly winds may cause severe turbulence in vicinity of runway.'

Robert J. Denison

On takeoff during the initiation of a cross-country flight, the pilot raised the landing gear following liftoff and the aircraft settled back onto the ground off the end of the runway. According to the pilot and the FAA inspector who examined the aircraft, both engines were producing normal power. The elevator trim was set at 12 degrees nose up vice 3-6 degrees required, and the aircraft was within weight and balance limits. The pilot lowered the landing gear prior to impact. According to information provided by the aircraft manufacturer, induced drag increases during landing gear retraction and extension due to the landing gear doors being extended into the air stream as the landing gear cycles.

Brian Hawley

The pilot was descending the airplane from 23,000 feet for an instrument approach. All communications were normal until after he acknowledged an instruction to contact approach control, when radio contact was lost. Radar contact ceased at 11,300 feet due to radar signal reception difficulties. Contact was lost almost directly over the eventual impact site, which was on the eastern side of a small valley. Witnesses on the western side of the valley had seen the airplane flying near them, at treetop level, eastbound, and clear of clouds. About the same time, on the eastern side of the valley where the airplane would impact trees, then terrain, there was heavy rain. The commercial pilot had about 1,850 total flight hours, and had completed a 'Wings III' flight proficiency program and an instrument proficiency program about two months earlier. The airplane had been on a continuous maintenance program. At the accident site, all of the airplane's control surfaces were found, and the engines and propellers displayed signatures consistent with being under power at impact. There were insufficient remains to conduct an autopsy or toxicological testing. Previously, the pilot's father, two uncles, and a male cousin had suffered fatal heart attacks.

Busscar

Following an uneventful flight from Rio de Janeiro-Santos Dumont Airport, the pilot started the descent to Joinville Airport by night and marginal weather conditions. He was informed about the visibility at destination being 2 km with ceiling at 650 feet. At 2032LT, he initiated the approach and reported to ATC that if it was raining, he would divert to Curitiba. Four minutes later, on final approach, the twin engine aircraft struck trees and crashed about 15 km southeast of runway 33 threshold. The aircraft was destroyed by impact forces and a post crash fire and all three occupants were killed.

Gray Leasing

The pilot had filed an instrument flight rules (IFR) flight plan for 25,000 feet mean sea level (MSL), and he amended it to 27,000 feet MSL en route. About 36 minutes after the altitude change to 27,000 feet, the pilot advised air traffic control (ATC) that he had lost cabin pressurization and needed an immediate descent. About 20 seconds later he was cleared to 25,000 feet, then 15 seconds later to 15,000 feet. Shortly after the pilot acknowledged the lower altitudes, the radio communications deteriorated to microphone clicks with no carrier. The aircraft started a shallow descent with slight heading changes, then was observed to make a rapid descent into desert terrain. About 10 months prior to the accident the aircraft had been inspected in accordance with the Piper Cheyenne Progressive Inspection 100-hour Cycle, event No. 1. According to the servicing agency, the aircraft inspection was completed and the aircraft was returned to service with a 12,500 feet MSL altitude restriction due to unresolved oxygen system issues. The last oxygen bottle hydrostatic check noted on the bottle was October 1989. The oxygen system was in need of required maintenance and the masks were in a rotted condition. The pilot failed to report his severe coronary artery disease condition, medications, and other conditions to his FAA medical examiner for the required flight physical.

Bruce L. Erickson

The flight was on a practice nondirectional beacon (NDB) approach to Great Falls runway 34 in visual conditions. Abeam the final approach fix, the aircraft was 4 miles right of course. Upon being advised of this by ATC, the pilot corrected back to final with a 60-degree intercept angle, rolling out on course 3 miles from the runway. When the pilot called missed approach, the local controller (a trainee) instructed the pilot to make a 360-degree right turn to enter right downwind for runway 3, and the pilot acknowledged. The controller trainee then amended this instruction to a 180-degree right turn to enter right downwind for runway 21, then to a 180- degree right turn to enter right downwind for runway 3. The crew did not acknowledge the amended instruction. Controllers then observed the airplane had crashed. Witnesses reported the airplane entered a steep descent from a right turn and impacted the ground at a steep angle. The flight was described as recurrent training required by the owner's insurance; however, the second aircraft occupant's airline transport pilot and flight instructor certificates had been revoked, and he held only a private pilot certificate. Investigators found no evidence of aircraft malfunctions.

Société Soon

The pilot, sole on board, was descending to Paris-Orly in poor weather conditions when he informed ATC about control problems. The twin engine aircraft entered an uncontrolled descent and crashed in a field. The pilot was killed.