Takeoff (climb)

Shortly after takeoff from Bangalore-Jakkur Airport runway 08, while in initial climb, the aircraft suffered an engine failure. It stalled and crashed in shallow water in Jakkur Lake, about one km northeast of the aerodrome. Both pilots were rescued and the aircraft was damaged beyond repair.

After takeoff from Malabo Airport, the airplane encountered difficulties to gain sufficient height. It continued in a flat attitude until it impacted a hillside located about 19 km east of the airport, near Baney. The aircraft was totally destroyed and all 60 occupants were killed, among them several students flying to the continent for holidays.

The airplane was destroyed on impact with terrain during a forced landing following an observed in-flight loss of engine power after takeoff. A witness observed the takeoff and stated that the airplane took off from the end of runway 34. About halfway down the runway the airplane emitted a sound like a rapid misfire, a pop, and then no more audible engine sounds. The airplane was about 300 to 400 feet above ground level at that point. He said that the airplane turned right then turned left to a bank where the wing was straight down. The airplane's wings then leveled, the airplane descended, and it impacted terrain. He stated that the time from the sounds to the impact was about two to three seconds. An on-scene examination revealed no airframe pre-impact anomalies. An engine examination revealed a cracked crankshaft propeller flange. The engine without the turbochargers and with the original crankshaft was test run up to 2,100 RPM. A propeller and governor inspection revealed no anomalies. Examination of the turbocharger system's exhaust bypass valve assembly revealed its butterfly valve was stuck (bound) in the extended closed position. The engine's cracked crankshaft was removed and a serviceable crankshaft was installed. The engine was test run again with a serviceable exhaust bypass valve assembly. The engine produced rated power. The original exhaust bypass valve assembly was reinstalled. The exhaust bypass valve assembly's wastegate bound again during an engine run and a loss of engine power was observed. Sectioning of the bypass valve assembly revealed a bent wastegate shaft. The valve assembly lever arm was bent and exhibited pre-impact tool marks consistent with pliers loosening a bound wastegate shaft. The airplane's pilot operating handbook and Federal Aviation Administration (FAA) approved airplane flight manual (POH), in part, stated, "ENGINE POWER LOSS DURING TAKEOFF If sufficient runway remains for a normal landing, leave gear down and land straight ahead." The engine manufacturer's maintenance and operator's manual stated that the wastegate is required to be checked for operation and condition during 100 hour inspections. The manual did not specify a procedure for maintenance personnel on how to check the wastegate's operation and its acceptable condition. National Transportation Safety Board Recommendation A-94-081, issued to the FAA in 1994, stated, "Require the amendment of pilot operating handbooks and airplane flight manuals applicable to aircraft equipped with engine turbochargers by including in the 'Emergency Procedures' section information regarding turbocharger failure. The information should include procedures to minimize potential hazards relating to fire in flight and/or loss of engine power." The airplane's POH latest revision was dated October 14, 2002 and review of the emergency procedures section showed that the POH did not contain information, procedures, or amplified procedures on turbocharger failures. The airplane accumulated 8.7 hours of operation since the last annual inspection.

Shortly after liftoff, about 20 feet above the ground, the pilot noticed a drop in the right engine manifold pressure. As the airplane began a right roll, efforts by the pilot to arrest the roll failed. When the pilot decided to put the airplane back on the ground, the right wing collided with the ground, the airplane cart wheeled and came to rest on its belly and burst into flames. Examination of the wreckage site revealed the aircraft located approximately 200 feet on the northwest side of the runway 22 centerline. The left fuel tank was ruptured and the left side of the airplane was fire damaged. Both occupants were slightly injured and the aircraft was damaged beyond repair.

After takeoff from Kapoeta Airport, one of the engine failed. The crew elected to return but eventually made an emergency landing near the airport. There were no injuries and the aircraft was damaged beyond repair. The exact date of the mishap remains unknown, somewhere in June 2005.

The Air Tindi Ltd. de Havilland DHC-3T (Turbo) Otter (registration C-FXUY, serial number 142) water taxied from the Air Tindi dock at Yellowknife, Northwest Territories, for a charter flight to Blachford Lake. The aircraft was loaded with two crew members, seven passengers, and 840 pounds of cargo. Before the flight, the pilot conducted a preflight passenger briefing, which included information about the location of life preservers and emergency exits. During the take-off run, at about 1912 mountain daylight time, the aircraft performed normally. It became airborne at about 55 mph, which is lower than the normal take-off speed of 60 mph. The pilot applied forward control column to counter the pitch-up tendency, but there was no response. He then trimmed the nose forward, but the aircraft continued to pitch up until it stalled at about 50 feet above the water and the left wing dropped. The aircraft struck the water in the East Bay in a nose-down, 45/ left bank attitude. On impact, the left wing and left float detached from the aircraft, and the aircraft came to rest on its left side. The crew was able to evacuate the passengers before the aircraft submerged, and local boaters assisted in the rescue. There were no serious injuries to the crew or passengers. The aircraft suffered substantial damage.

The crew stated the airplane was hire by a private individual and had 220 gallons of fuel onboard, and was carrying 6 pieces of granite, weighing 3,200 lbs. The passenger was responsible for the granite during the flight. During takeoff, about 400 feet above the ground, a discrepancy with the left engine manifold pressure was noted, followed by a slight hesitation and mild backfire. Oil was seen leaking from the front nose section of the engine followed by an engine manifold pressure and rpm decrease. Smoke coming from the left engine was observed and reported by the airport controllers. The left engine's propeller failed to feather and the airplane wouldn't maintain altitude. The airplane impacted trees, vehicles, and the right wing struck a home before coming to a stop on the road. A fire ensued immediately after ground impact, all onboard exited without assistance. The fuselage from the cockpit to the tail section melted from the fire. The right wing was damaged by impact and fire, and the right engine remained intact on the wing. The left wing was separated 12 feet from the outboard and the engine separated from the firewall. Both engine's propellers were in the low pitch position. The flaps were full up and the landing gear were retracted. A weight and balance sheet was never furnished. The pieces of granite and limited cargo recovered from the wreckage weighed 3,140 lb. Examination of the airplane revealed all flight controls surface were present and flight control continuity was accounted for and established. No evidence of any pre-impact mechanical discrepancies with the airframe or its systems was found that wound have prevented normal operation of airplane. On December 09, 2004, the left engine's nose section assembly was found with six out of the ten retaining bolts broken. The section was inspected and all ten bolts were replaced with serviceable ones. The assembly of the dose dome section and installation to the engine was performed by the repair station mechanic. The remaining assembling of the engine was completed by the operator's mechanic/pilot. During the left engine post accident examination, the ten bolts securing the nose dome section flange to the stationary reduction gear were fractured with their respective safety wire still intact. The chamber for the propeller feathering oil system was not secured to the plate sections, producing a bypass of the oil for the propeller feathering process. Metal flakes and pieces were observed deposited in the oil breather screen, consistent with the master rod bearing in an advance stage of deterioration. The silver plated master rod bearing had a catastrophic failure. Silver like metal flakes and particles were observed throughout the nose section, reduction gear section, main oil screen, and oil filter housing of the engine. An indication of propeller shaft housing movement was evident. Metal flakes with carbon build up were observed in the propeller shaft support and sleeve assembly. A metallurgical examination of the ten bolts securing the nose dome assembly indicated all were fractured though the threaded section of the shanks. The fatigue zones propagated from the opposite sides toward the center of the bolts consistent with reversed bending of the bolt.

The aircraft, chartered by the Colombian Army, was completing a special flight from Miraflores to Villavicencio with an intermediate stop in San José del Guaviare, carrying three crew members and a certain number of soldiers (around 25 but the exact number could not be confirmed). Shortly after takeoff from runway 20, while in initial climb, the left engine caught fire. The crew elected to return for an emergency landing and initiated a right turn when smoke entered the cabin. Shortly later, the left main gear detached and as the speed dropped, the crew attempted an emergency landing when the aircraft crashed in a wooded area located 2 km from the airport. All occupants were rescued, some were injured. The aircraft was destroyed.

Shortly after takeoff from Zacapa Airport, the crew encountered technical problems when the aircraft stalled and crashed on a small hill. All 17 occupants were rescued and the aircraft was destroyed.

During the takeoff roll at Khartoum-Haj Yusuf Airport, the left engine caught fire and exploded. The captain rejected takeoff and initiated an emergency braking procedure. Unable to stop within the remaining distance, the aircraft overran and came to rest few dozen metres past the runway end, bursting into flames. Three passengers were killed while all other occupants were rescued. The following day, four survivors including a stewardess, died from their injuries.