Takeoff (climb)

The airplane took off from the airport on a left downwind departure and after reaching an altitude of approximately 300 feet, banked steeply and dove into the ground. Witness statements indicated that the takeoff ground roll extended to midfield of the runway, a distance of 4,850 feet before the airplane lifted off. According to the Airplane Flight Manual performance charts, the normal ground roll should have been about 2,100 feet. While turning crosswind, the airplane steepened its bank and continued toward the downwind. As the angle of bank approached 90 degrees, the nose dropped and the airplane descended to impact with trees and the ground. Several trees were struck before the airplane came to rest on the underlying terrain in the backyard of a residence. The airplane was thermally destroyed in the impact sequence and post crash fire. Calculations of the airplane weight and balance data put it at least 251 pounds over maximum allowable gross takeoff weight. Remaining wreckage not consumed in the ground fire was examined and the engine was sent to the manufacturer for inspection. No discrepancies were found. Cockpit instrumentation and all autopilot components were thermally destroyed. Flaps and landing gear were found in the retracted position and the elevator trim surface was slightly nose up from the takeoff setting. The autopilot had a reported history of malfunction and the electric elevator trim system was scheduled for repair a week before the accident, but the owner took the airplane prior to the work being performed. The airplane had been modified with the addition of several Supplemental Type Certificates, one of which was a wing spoiler system. The controls and
many of the actuating linkages for the spoiler system were destroyed in the fire.

The crew departed Freetown-Lungi Intl Airport on a short positioning flight to Freetown-Hastings Airport. After takeoff, during initial climb, the twin engine aircraft entered clouds at an altitude of about 500 feet. While exiting the clouds, the crew noticed a Mil Mi-8 helicopter flying nearby. His crew was completing a local flight on behalf of the UNO. The crew of the Let attempted an evasive manoeuvre but the rotor of the helicopter struck the base of the aircraft's tail. The crew managed to return for an emergency landing but the undercarriage partially failed upon landing. Both pilots escaped uninjured while the aircraft was damaged beyond repair. The crew of the helicopter was able to land safely.

A Cessna 208 Caravan I on amphibious floats, C-GMPB, serial number 20800082, was ferrying members of the Royal Canadian Mounted Police (RCMP) Emergency Response Team from Teslin, Yukon, to a site on the south end of Teslin Lake, British Columbia. At about 1645 Pacific daylight time, three team members, two dogs, and gear were unloaded on a gravel bar across from the mouth of the Jennings River. The aircraft departed for the Teslin airport at about 2355 with the pilot and one RCMP engineer on board. Shortly after take-off, the aircraft was seen to pitch up into a steep climb, stall, then descend at a steep angle into the water. The aircraft was destroyed, and the pilot and the passenger were fatally injured.

A Piper PA-31-350 Navajo Chieftain, N27944, operated by Patuxent Airways, Inc., Hollywood, Maryland, and a Piper PA-44-180 Seminole, N2225G, operated by Hortman Aviation Services, Inc., Philadelphia, Pennsylvania, were destroyed when they collided in flight over Burlington Township, New Jersey. The airline transport pilot, commercial pilot, and seven passengers aboard the Navajo Chieftain were killed, as were the flight instructor and the private pilot aboard the Seminole. Day visual meteorological conditions existed at the time of the accident, and both airplanes were operating under visual flight rules when the collision occurred. The flight crews of both airplanes were properly certificated and qualified in accordance with applicable Federal regulations. None of these individuals was experiencing any personal problems or rest anomalies that would have affected their performance. The airplanes had undergone the required inspections. Examination of their maintenance documents revealed that both airplanes complied with all appropriate airworthiness directives. Evidence gathered from the wreckage indicated that neither airplane had experienced an in-flight fire, bird strike, or structural or mechanical failure. Tissue samples revealed that the pilot of the Seminole had taken doxylamine sometime before the accident. (Doxylamine is a sedating antihistamine that has substantial adverse effects on performance.) However, the amount of blood available for analysis was insufficient for determining exactly when the pilot may have ingested the medication or whether his performance was impaired by the effects of doxylamine. A partial cockpit visibility study revealed that the Seminole would have been visible to the pilots in the Chieftain for at least the 60 seconds before the collision. No stereo photographs from a Seminole cockpit were available to determine precise obstruction angles. However, because of the relative viewing angle, the Chieftain would have been visible to the pilots in the Seminole for most of the last 60 seconds. The study further revealed that about 4 seconds before impact, or about .11 nm separation, the angular width of each airplane in each pilot's field of vision would have been approximately 0.5 to 0.6 degrees or about 1/4 inch apparent size at the windscreen.

Witness's reported that the airplane took off from runway 05, which has an up slope of 1.2 degrees. The airplane was observed at approximately 10 feet above ground level, in a nose high attitude traveling parallel to the ground and not climbing. The airplane narrowly cleared a 6- foot fence off the departure end of runway 05. Shortly thereafter, the airplane impacted a utility pole, the roof of a bus stop, which was followed by a brick wall. At the time of the accident runway 23, which has a 1.2-degree down slope and has a clear-cut area on the departure end, was available for use. The basic empty weight for this airplane is 3,097 pounds; the useful load is 1,201.7 pounds. The actual load at the time of the accident was in excess of the useful load. There is no record of the pilot completing a weight and balance computation prior to take-off. The toxicology examinations were negative for carbon monoxide, cyanide, drugs and alcohol. The toxicology examination revealed that 1175(mg/dl) glucose was detected in the urine. Examination of the airplane and subsystems failed to disclose any mechanical or component failures.

A DHC-3 and a Cessna 185 (both float equipped aircraft) had been chartered to move equipment from an outpost camp which was being threatened by forest fires in the Tadoule Lake (Lac Brochet, MB) area. Takeoff was conducted in a westerly direction into light winds estimated to be 5 to 8 knots. Besides the pilot there were two passengers (the camp owner and his son), two 45 gallon drums of #2 gas, a propane cylinder, battery chargers plus other sundry items. It was reported that once the aircraft was airborne, a windshift occurred which may have resulted in rollover and a downdraft situation. The aircraft began to descend, despite the application of full engine power, and settled into the trees with little forward speed and the wings in a near level attitude. The aircraft was then consumed by fire, the pilot and his two passengers were able to escape with minor scrapes and bruises. The pilot of the Cessna 185 witnessed the accident while airborne and he then returned and landed and rendered assistance to the three occupants. The local temperature was 27 degrees C, and the aircraft was near its maximum gross weight. It was reported that the aircraft had a headwind in proximity to the forest fire on takeoff, and that it flew into the area of a tailwind during initial climb.

On Tuesday 25 July 2000 the Concorde registered F-BTSC, operated by Air France, took off from Paris Charles de Gaulle to undertake charter flight AF4590 to New York with nine crew members (3 FC, 6 CC) and 100 passengers on board. The Captain was Pilot Flying (PF), the First Officer was Pilot Not Flying (PNF). The total weights of the aircraft and of the fuel on board stated by the Flight Engineer (FE) at the time the aircraft started out were 186.9 t and 95 t respectively. The speeds selected by the crew were V1: 150 kt, VR: 198 kt, V2: 220 kt. At 13 h 58 min 27 s, the crew contacted ATC on the Flight data frequency and requested the whole length of runway 26 right for a takeoff at 14 h 30. At 14 h 07 min 22 s, the controller gave start-up clearance and confirmed runway 26 right for takeoff. At 14 h 34 min 38 s, the Ground controller cleared the aircraft to taxi towards the runway 26 right holding point via the Romeo taxiway. At 14 h 40 min 02 s, the Loc Sud controller cleared 4590 to line up. At 14 h 42 min 17 s, he gave it takeoff clearance, and announced a wind from 090° at 8kt. The crew read back the takeoff clearance. The FE stated that the aircraft had used eight hundred kilos of fuel during taxiing. At 14 h 42 min 31 s, the PF commenced takeoff. At 14 h 42 min 54.6 s, the PNF called one hundred knots, then V1 nine seconds later. A few seconds after that, tyre No 2 (right front) on the left main landing gear was destroyed after having run over a piece of metal lost by an aircraft that had taken off five minutes before. The destruction of the tyre in all probability resulted in large pieces of rubber being thrown against the underside of the left wing and the rupture of a part of tank 5. A severe fire broke out under the left wing and around the same time engines 1 and 2 suffered a loss of thrust, severe for engine 2, slight for engine 1. By 14 h 43 min 13 s, as the PF commenced the rotation, the controller informed the crew the presence of flames behind the aircraft. The PNF acknowledged this transmission and the FE announced the failure of engine 2. The recorded parameters show a transient loss of power on engine 1 that was not mentioned by the crew. At around 14 h 43 min 22 s the engine fire alarm sounded and the FE announced "shut down engine 2" then the Captain called for the "engine fire" procedure. A few seconds later, the engine 2 fire handle was pulled and the fire alarm stopped. The PNF drew the PF’s attention to the airspeed, which was 200 kt. At 14 h 43 min 30 s, the PF called for landing gear retraction. The controller confirmed the presence of large flames behind the aircraft. At 14 h 43 min 42 s the engine fire alarm sounded again for around 12 seconds. It sounded for the third time at about 14 h 43 58 s and continued until the end of the flight. At 14 h 43 min 56 s, the PNF commented that the landing gear had not retracted and made several callouts in relation to the airspeed. At 14 h 43 min 59 s, the GPWS alarm sounded several times. The FO informed ATC that they were trying for Le Bourget aerodrome. The recorded parameters then indicate a loss of power on engine 1. A few seconds later, the aircraft crashed onto a hotel at “La Patte d’Oie” in Gonesse at the intersection of the N17 and D902 roads. The aircraft was totally destroyed by impact forces and a post crash fire and all 109 occupants were killed as well as four people working in the hotel. Five other employees were injured. The aircraft was chartered by the German Operator Deilmann to carry German tourists to New York. On board were nine French citizens (all crew members), 96 Germans, two Danish, one American and one Austrian.

On July 20, 2000, about 1312 eastern daylight time, a Douglas DC-3, N54AA, registered to Allied Air Freight, Inc., operating as a Title 14 CFR Part 135 cargo charter flight, crashed after takeoff from Nassau International Airport, New Providence Island, Bahamas. Visual meteorological conditions prevailed and a VFR flight plan was filed. The airplane was destroyed by post crash fire and the ATP-rated pilot and commercially-rated copilot were fatally injured. The flight originated about 6 minutes before the accident. According to initial reports, after takeoff from runway 14, the pilot advised the tower that he would have to shut down the right engine and return for an emergency landing on runway 14. The airplane was observed to lose altitude and crash about 2 miles from the airport, east of the extended centerline of runway 14.

At liftoff, the engine failed. The aircraft stalled and crashed along the runway. There were no casualties but the aircraft was damaged beyond repair.

The aircraft, registered to a private individual, departed Villavicencio-La Vanguardia Airport on a charter flight to Mitú, carrying 17 passengers and two pilots while the aircraft was certified to carry 13 passengers maximum. The crew filed an flight plan with only six people on board. Shortly after takeoff, while in initial climb, the right engine caught fire. The crew activated the fire extinguishing system but as both bottles were empty, the fire could not be contained. The captain initiated a right hand turn to return to the airport when the aircraft stalled and crashed, bursting into flames, two minutes after takeoff. Both pilots and eight passengers were killed while nine other people were injured. The aircraft was totally destroyed by impact forces and a post crash fire.