Landing (descent or approach)

The aircraft departed Hamilton, Ontario, on a cargo flight to Saltillo, Coahuila, with an intermediate stop in Shreveport, LA, carrying two pilots and a load consisting of 4 tons of auto parts. The aircraft arrived in Shreveport at 2319LT and departed at 2348LT. On approach to Saltillo-Plan de Guadalupe Airport, the crew encountered low visibility due to poor weather conditions and dark night. On final approach to runway 17, as the captain was unable to establish a visual contact with the runway, he decided to abandon the approach and initiated a go-around procedure. Nine seconds later, the aircraft stuck the ground and crashed 550 metres to the east of the runway 17 threshold, bursting into flames. The aircraft was totally destroyed, the captain was killed and the copilot was seriously injured.

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.

The Airbus 310 serial number 548 owned by Sudan Airways Was entered in Sudan Civil Register on 15/09/2007 , designated registration marks ST-ATN in accordance to registration certificate No. 0493 dated 15/09/2007 and issued with Certificate of airworthiness No AWP/COA/0203/2007 dated 19/09/2007. On the morning of 10th June at 8:30 hrs (local time 05:30 UTC) after arriving from Cairo with a deactivated no 1 engine reverse as being a carry forward defect and being labeled according to MEL, the captain accepted the aircraft to carry out its scheduled flight to Amman via Damascus. The trip en-route to Amman was uneventful. Same day in the afternoon, the Airbus A310, ST-ATN, was en-route flying from Damascus (Syria) to Khartoum (Sudan) with 203 passengers and 11 crew members on board. The Airbus approached Khartoum in the afternoon and due to bad weather conditions, the captain decided to divert to Port Sudan. The aircraft landed Port Sudan Airport normally and was refuelled with 20 tons of Jet A1. As mentioned by the Captain that he was in contact with Khartoum enquiring about the weather. After staying on ground at Port Sudan for about 1:15 hour, and being informed that the weather was getting better, the Captain decided to return back to Khartoum. A310, ST-ATN, took off to Khartoum where the captain initiated a night approach for the runway 36 as pilot flying. He got the clearance to land after the controller provided him with wind information (320° / 7 Kt) and runway condition (wet). The left engine thrust reverser was unserviceable and inhibited as per Minimum Equipment List (MEL) procedures. The aircraft landed smoothly about 17:26 UTC. R/W 36 landing and within 900 meters range from the threshold of R/W 36 as stated by the flying pilot. The captain reported that he experienced some difficulties in maintaining the aircraft on the centre line just after setting both thrust levers in the reverse position. Then he did not succeed in slowing down the aircraft nor could stop it before the end of the runway. The aircraft longitudinally overran the runway and came to a stop 215 meters after the runway end. Then it caught fire on its right side. The right hand slides could not be deployed, the crew and the passengers evacuated the aircraft from the left front slide, twenty nine passengers and one cabin crew were fatally injured.

On June 9, 2008, about 1401 eastern daylight time, an Aero Commander 500S, N501AP, registered to and operated by Gramar 500, Inc., experienced a loss of engine power in both engines and was ditched in the Atlantic Ocean about 1/2 mile south of North Bimini, Bahamas. Visual meteorological conditions prevailed in the area and a visual flight rules flight plan was filed for the 14 Code of Federal Regulations (CFR) Part 91 personal flight from Nassau International Airport (MYNN), Nassau, Bahamas, to Ft. Lauderdale Executive Airport (FXE), Ft. Lauderdale, Florida. The airplane was destroyed due to salt water immersion, and the airline transport rated pilot, the sole occupant, was not injured. The pilot stated that when the flight was past Bimini, the right engine started running rough and losing power. He turned southeast to enter a left base for runway 09 at South Bimini Airport, and the left engine also began to run rough and lost power. The pilot ditched the aircraft, evacuated into a life raft, and was rescued by a pleasure boater. The pilot also stated that 25 gallons of fuel were added while at MYNN, for a total fuel supply of 90 gallons. Both engines were test run 8 days after the accident using a test propeller. Both engines ran to near maximum RPM. One magneto from each engine was replaced prior to the test run.

The crew was completing a local training flight at Sidra Airport when the accident occurred in unknown circumstances. The aircraft came to rest in a sandy area with its undercarriage and left wing sheared off. Both pilots evacuated safely.

The twin engine aircraft departed Panama City-Marcos A. Gelabert Airport at 0734LT on a private flight to Contadora Island with five passengers and one pilot on board. Following an uneventful flight, the aircraft landed on wet runway 35. It skidded then veered off runway to the left and came to rest in bushes. All six occupants escaped uninjured while the aircraft was damaged beyond repair.

A TACA Airlines Airbus A320, flight TA390, with Irish Registry EI-TAF, with 135 passengers and crew on board, overran at the end of the runway during landing at Tegucigalpa caused the deaths of three people on board and two on the ground. The government of Honduras delegated the conduct of investigation to the Salvadoran Civil Aviation Authorities, as provided for in Annex 13 to the Chicago Convention. In accordance with international agreements, France sent two investigators from the BEA (Bureau d'Enquêtes et d'Analyses), accompanied by five technical advisors from Airbus; United States sent two investigators from the NTSB (National Transportation Safety Board), accompanied by one advisor from FAA (Federal Aviation Administration) and one technical Advisor from IAE (International Aero Engine); and Ireland sent one investigator. Both flight recorders (CVR and DFDR) were recovered and taken to the NTSB in order to perform the read out. The following data result from the analysis done by the BEA and Airbus of the accident recorders, which have been processed within the NTSB facilities under the leadership of the in-charge Authorities. It is confirmed that the aircraft was dispatched without any deferred MEL item. Prior to landing, the wind information given by the ATC to the crew was 190°/10kt and ATC also confirmed that the runway was wet. The Captain was the Pilot Flying (PF). Landing configuration was established with Slats/Flaps fully extended, gear down, ground spoilers armed, autobrake selected to MED. The aircraft landing weight was 63.5t (max landing weight 64.5t), Vapp 137kt. The aircraft was cleared to land on runway 02 and landed with Autopilot and Flight Directors OFF, and autothrust engaged in managed speed mode. At time of touch down, IAS was 139kt and Ground Speed (GS) was 159kt (estimated tailwind was 12kt from DFDR data analysis). The aircraft landed on runway 02 (Runway 02 is 3297 feet high and has a displaced threshold of 213m). The Landing Distance Available (LDA) for runway 02 is of 1649m. The touch down occurred at approximately 400m from the runway 02 displaced threshold. Immediately after touchdown, the crew selected MAX REV, and both engine reversers and the Ground Spoilers (G/S) deployed normally. The nosewheel touch down occurred 7s after the Main Landing Gear (MLG) following PF inputs. The crew applied manual braking 4s after MLG touch down and commanded maximum pedal braking in 10s (14s after MLG touch down). At 70 knots Indicated Airspeed Speed (IAS), upon Pilot Non Flying (PNF) call-out, the PF selected IDLE REV. The remaining distance to the runway end was approximately 190m. The aircraft overran the runway at 54kt and dropped down the 20 m embankment sustaining severe damage on impact with the ground. The landing performance analysis confirms that the landing performances are consistent with runway condition and crew actions.

Few minutes after takeoff from Goma Airport, en route to Kalima, the crew reported engine problems and was cleared to return for an emergency landing. After touchdown, control was lost. The aircraft veered off runway to the right and collided with lava blocs. The aircraft was destroyed and all five occupants were injured.

The crew was completing a night training flight on behalf of the U.S. Air Force 86th Flying Training Squadron, 47th Flying Training Wing, Laughlin Air Force Base, Texas. After several manoeuvres in the vicinity of the Lubbock-Preston Smith Airport, the crew started an non precision approach to runway 17R. At that time, weather conditions were not so good with rain showers and winds up to 40 knots. On final approach, the aircraft seems to sink and pitched down. The captain increased both engines power but the aircraft hit the ground 1,1 mile short of runway 17R threshold. On impact, the nose gear was sheared off and the aircraft came to rest in a field. Both pilots were slightly injured while the aircraft was damaged beyond repair.

The amphibious-float-equipped airplane departed from a paved runway for the 40-nautical mile flight to its destination, where a water landing on a lake was to be made. The pilot did not raise the landing gear after takeoff. During the flight, the air was bumpy and turbulent, and this resulted in the gear advisory system activating numerous times. The purpose of the system is to alert the pilot of the landing gear position--up for a water landing or down for a runway landing--when the airspeed decreased below a set threshold value. The pilot disabled the system by pulling its circuit breaker because the alerts were becoming a nuisance; he intended to reset the breaker during descent, but did not do so. Upon reaching the destination, the pilot set up a 150- to 200-feet-per-minute rate of descent for a glassy water landing on the lake. With the landing gear in the down position, the airplane contacted the water and abruptly nosed over. The airplane came to rest floating inverted, suspended by the floats. The pilot reported that the day of the accident was his nineteenth consecutive duty day, including office duty and flight duty. He stated that he feels the lack of days off during the previous 19 days was a contributing factor to this accident. When asked what would have prevented the accident, the pilot suggested consistency in using the checklist. On two flights earlier in the day he had used a written checklist; on the accident flight he did not.