Landing (descent or approach)

A HS-748 suffered landing gear problems, causing the airplane to end up on its belly, blocking Lokichoggio's single 1800-metre runway 09/27. Three other light aircraft, a Dornier 228, an Antonov 28 and a Cessna 208, landed safely at the airfield on runway 27 after the HS-748 accident. Two Antonov 12 aircraft inbound to Lokichoggio from Torit, Southern Sudan, diverted to Juba upon getting information of the runway obstruction. Transafrik Hercules S9-BAS, flying for the United Nations World Food Programme, contacted Lokichoggio Tower at 14:30 hours. The aircraft was returning from a food air drop at Motot, Southern Sudan. The pilot was advised to divert to Eldoret International Airport but he opted to land at Lokichoggio. The Tower cleared the Hercules to land on runway 27 at the pilot’s discretion. The aircraft made a very heavy landing short of the runway and the top centre fuselage broke. The aircraft came to a stop about one kilometre from the touchdown point. Shortly before coming to a halt, the aircraft impacted the HS 748 with its right wing tip. The captain, the first officer, the flight engineer and the two loadmasters evacuated themselves safely. A repair crew started to work on S9-BAS on site at Lokichoggio in May 2006. The fuselage was repaired but the contractor left before repairs were completed. The airplane was seen in November 2008 parked at Lokichoggio without landing gear, engines and vertical stabilizer.

A 748 Air Services Hawker Siddeley Andover aircraft departed Lokichoggio Airport (LKG) at 08:40 hours for Boma, Southern Sudan. After Boma, the aircraft landed at Torit (HSTR) then Natinga, all in Southern Sudan, before proceeding back to Lokichoggio. The aircraft joined long final from the west of the airfield and was given instructions to land on runway 09. As soon as the aircraft touched down, the propellers struck the runway surface for some distance then the aircraft veered off the centerline to the left and came to a stop. The captain, the first officer and the loadmaster evacuated themselves. They were not injured. The aircraft sustained substantial damage, blocking Lokichoggio's single 1800-metre runway 09/27. Three other light aircraft, a Dornier 228, an Antonov 28 and a Cessna 208, landed safely at the airfield on runway 27 after the HS-748 accident. Two Antonov 12 aircraft inbound to Lokichoggio from Torit, Southern Sudan, diverted to Juba upon getting information of the runway obstruction. Transafrik Hercules S9-BAS, flying for the United Nations World Food Programme, contacted Lokichoggio Tower at 14:30 hours. The aircraft was returning from a food air drop at Motot, Southern Sudan. The pilot was advised to divert to Eldoret International Airport but he opted to land at Lokichoggio. The Tower cleared the Hercules to land on runway 27 at the pilot’s discretion. The aircraft made a very heavy landing short of the runway and the top centre fuselage broke. The aircraft came to a stop about one kilometre from the touchdown point. Shortly before coming to a halt, the aircraft impacted the HS 748 with its right wing tip. The captain, the first officer, the flight engineer and the two loadmasters evacuated themselves safely.

During the approach, the flightcrew was unable to get the right main landing gear extended and locked. After several attempts, while conferring with the checklist and company personnel, the flightcrew performed an emergency landing with the unsafe landing gear indication. During the landing, the right main landing gear slowly collapsed, and the airplane came to rest off the right side of the runway. Examination of the right main landing gear revealed that the retract actuator fitting was secured with two fasteners, a smaller bolt, and a larger bolt. The nut and cotter key were not recovered with the smaller bolt, and 8 of the 12 threads on the smaller bolt were stripped consistent with an overstress pulling of the nut away from the bolt. The larger bolt was bent and separated near the head, consistent with a tension and overstress separation as a result of the smaller bolt failure. The overstress failures were consistent with the right main landing gear not being locked in the extended position when aircraft weight was applied; however, examination of the right main landing gear down lock system could not determine any pre-impact mechanical malfunctions. Further, the right main landing gear retract actuator was tomography scanned, and no anomalies were noted. The unit was then functionally tested at the manufacturer's facility, under the supervision of an FAA inspector. The unit tested successfully, with no anomalies noted.

The purpose of the flight was for the second pilot to perform an evaluation of the first pilot, who was recently designated by the operator as a backup pilot. Following several successful flights with and without passengers, the pilots discussed single engine operations, and the first pilot reduced the right engine's power to flight idle and feathered the propeller. During the final leg of the approach to landing, the airplane crossed over a fence near the runway threshold, and the first pilot pitched the airplane downward. The nose landing gear contacted the runway "hard," and the airplane began to bounce. After several bounces, the first pilot elected to abort the landing, increased power on the left engine to "full." As the first pilot pitched the airplane upward, it yawed to the right, "stalled," and impacted the ground.

During takeoff from the departure airport, as the pilot advanced the throttles, the aircraft made a "sudden turn to the right." The pilot successfully aborted the takeoff, performed an engine run-up, and then took off without incident. The pilot experienced no anomalies during the second takeoff or the flight to the destination airport. As he reduced the power while in the traffic pattern, at the destination airport, the left engine accelerated to 60 percent power. The pilot reported to the tower that he had "one engine surging and another engine that seems like I lost control or speed." The pilot advanced and retarded the throttles and the engines responded appropriately, so he continued the approach. As the pilot flared the airplane for landing, the left engine surged to 65 percent power with the throttle lever in the "idle" position. The airplane immediately turned to the right; the right wing dropped and impacted the ground. Disassembly of the engines revealed no anomalies to account for surging, or for an uncommanded increase in power or lack of throttle response. Functional testing of the fuel control units and fuel pumps revealed the flight idle fuel flow rate was 237 and 312 pounds per hour (pph), for the left and right engines, respectively. These figures were higher than the new production specification of 214 pph. According to the manufacturer, flight idle fuel flow impacts thrust produced when the power levers are set to the flight idle position and differences in fuel flow can result in an asymmetrical thrust condition.

Aircraft lost power on both engines while on approach to Moscow-Vnukovo airport. The crew decided to divert to Sheremetievo Airport when the undercarriage collapsed on landing. The aircraft veered off runway and slid in a grassy area before coming to rest. Nobody was injured but the aircraft was damaged beyond repair.

On May 16, 2005 about 1230EST (1845Z), a Britten Norman Islander aircraft, registration C6-ASA crashed approximately 3nm northeast of the Moss Town International Airport. The Pilot reported, “about 35 minutes south of Nassau International Airport [MYNN] I noticed that my ground speed was very low. I continued with my flight to MYEF because I should have had 1 hour and 30 minutes of fuel. About 10 miles from MYEF my right engine quit then 2 minutes later my left engine quit. I then look a suitable place to land three miles from the airport.” The one (1) pilot and two (2) passengers received no serious injuries. The aircraft was destroyed from impact sustained as it contacted the trees. The accident flight originated from Freeport, Grand Bahama, Bahamas to Moss Town, Exuma, Bahamas with an intermediate stop in South Bimini, Bahamas. Visual Flight Rules Conditions existed at the time of the accident. The aircraft was operated by Flamingo Air Limited, a Bahamian Air Operator Certificate holder. Flamingo Air Limited operated as a Commuter, Unscheduled / On Demand Operator in commercial air transport. Flamingo Air Limited operated under the provision of the Bahamas Aviation Safety Regulations (BASR 2001). Its aircraft are maintained under the provision of Bahamas Aviation Safety Regulations (BASR 2001). The aircraft had flown a total of 2 flights including the accident flight. The pilot flew both flights [the same pilot later flew the accident flight]. The pilot reported no problems with the aircraft prior to the accident. There were no open MEL items. There were no open (uncorrected) mechanical irregularities written in the Technical and Journey Log. On May 15, 2005 the pilot uplifted a total of 130 gallons of fuel, which is the maximum capacity for this aircraft. Prior to the accident flight, the aircraft completed two flights, MYAM to MYGF [flown on May 15, 2005] which lasted 45 minutes and MYGF to MYBS [flown on May 16, 2005] which lasted 30 minutes. No fuel was uplifted prior to the next flight which was MYBS to MYEF, the accident flight [flown on May 16, 2005]. During post accident interviews, the pilot confirmed that he had not noticed anything unusual about the airplane. The pilot later surmised that he had simply run out of fuel.

The single engine aircraft departed Valencia at 1400LT and was estimated to arrive at Pariaguán at 1518LT. While descending to Pariaguán Airport, the pilot informed ATC about his position, eight nautical miles from the airport. This was the last radio transmission. The wreckage was found the following day in an isolated area. All three occupants were killed. The accident occurred eight minutes prior to the ETA.

erimeter Aviation flight 914, a Metro II with 17 people on board, was on approach at Thompson, MB. The first officer flew the aircraft during the approach, and encountered turbulence and fluctuating airspeed. The captain took control at 200 feet agl. The aircraft was high and left of centreline. The captain added power, continued the approach and landed hard on runway 23 near the intersection with runway 32. After the aircraft arrived at the apron, a fuel leak was noted. The aircraft was inspected and damage was found in the wheel wells, wing leading edge, engine mounts and a wing-fuselage attachment point. No injuries were reported. Reported winds at 1400Z were 010 at 15-20 kts; 1500Z winds were 350 at 9 kts.

The twin engine aircraft was completing a charter flight from San Juan to Córdoba with seven passengers and two pilots on board. On approach to Córdoba-Ambrosio Taravella Airport by night, the crew encountered limited visibility due to poor weather conditions. The aircraft descended below the glide and collided with the inner marker antenna located about 700 metres short of runway 18 and crashed. Both pilots and four passengers were killed while three other passengers were seriously injured. Among those killed were the Argentinian racer Nicolas Vuyovich and Gustavo Ramonda, Director of the Toyota Corolla Racing Team who just won a race at the San Juan's autodrome.