Airport (less than 10 km from airport)

After takeoff while over the departure end of the runway, deep gray colored smoke was observed by the tower controller trailing the right engine. The pilot was alerted of this and advised the controller the flight was returning. Witnesses reported seeing smoke trailing the right engine and that the airplane rolled to the left, pitched nose down, impacted trees, and then the ground. A fatigue crack was detected in the exhaust aft of the No. 6 cylinder of the right engine; and incomplete fusion of a weld repair was also noted. Heat damaged components from the right engine were replaced and the engine was started and found to operate normally. A foreign object of undetermined origin was found in the intake area of the No. 3 cylinder. Analysis of the voice tape revealed both engines/propellers were operating near full rated rpm when the pilot acknowledged the transmission that smoke was trailing the right engine, one engine/propeller rpm then decreased to about 2,160 rpm. Examination of the flight controls revealed no evidence of preimpact failure or malfunction. Flap positions at impact could not be determined. Calculations indicate that the airplane was approximately 55 pounds over the maximum certificated takeoff weight at takeoff.

On September 16, 1998, at 2253 central daylight time, a Boeing 737-524 transport airplane, N20643, operating as Continental Airlines flight 475, was substantially damaged following a loss of control during the landing roll at the Don Miguel Hidalgo International Airport near Guadalajara, Mexico. The 2 airline transport rated pilots, the 4 flight attendants, and the 102 passengers were not injured. The airplane was owned and operated by Continental Airlines of Houston, Texas, under Title 14 CFR Part 121. Night visual meteorological conditions prevailed for the scheduled international passenger-cargo flight for which an IFR flight plan was filed. The flight was dispatched from the George Bush International Airport near Houston, Texas, at 2056, for the two hour flight to Guadalajara, State of Jalisco, Mexico. The flight's scheduled arrival time was 2254. After executing a missed approach on their first ILS approach to runway 28, the flight was vectored for a second approach to runway 28. The second approach was reported by both pilots to be uneventful; however, after touchdown, the aircraft drifted to the left side of the runway. The left main landing gear exited the hard surface of the runway approximately 2,700 feet from the landing threshold and eventually all 3 landing gears exited the 197 foot wide asphalt runway. The first officer, who was flying the airplane, stated that he never felt any anti-skid cycling during the landing roll and did not feel any "radical braking" which was expected with the auto-brake in the number 3 setting. The airplane's nose landing gear collapsed resulting in structural damage to the avionics bay, the forward baggage compartment, the engine cowlings and pylons. Both engines incurred FOD. A total of 15 runway lights on the southern edge of runway 28 were found either sheared or knocked down. The tower operator reported that intermittent heavy rain showers accompanied with downdrafts and strong winds associated with a thunderstorm northeast of the airport prevailed throughout the area at the time of the accident. The two transport category airplanes that landed prior to Continental flight 475 reported windshear on final approach. The winds issued to Continental 475 by the tower while on short final were from 360 degrees at 20 knots, gusting to 40 knots. Prior to the arrival of Continental flight 475, an Aeromexico MD-82, drifted to the left side of the runway to the point where the left main gear exited the hard surface of the runway. The pilot of that flight stated that he used differential power to regain control and bring the aircraft back on the runway. The flight taxied to the gate without further incident.

Shortly after takeoff, while in initial climb, the aircraft collided with a flock of birds. Both engines suffered a loss of power and the aircraft lost height and crash landed. It went out of control, overran and came to rest, bursting into flames. All four crew members escaped with minor injuries while the aircraft was destroyed by fire. At the time of the accident, wind was gusting up to 14 knots and several birds were sighted in the vicinity of the airport.

While parked at Chaklala AFB, the aircraft was destroyed by fire after being struck by another Pakistan Air Force Hercules C-130. The aircraft was empty at the time of the accident.

The crew was engaged in a local post maintenance test flight. While taxiing, the crew lost control of the airplane that collided with a parked Pakistan Air Force C-130. A major fire occurred, destroying both aircraft. All five crew members were killed while the second aircraft was empty.

The airplane departed at night after maintenance was performed on the left engine. The pilot attempted to return to the airport and while on base leg struck the ground inverted and nose down. The left engine propeller was found feathered. On the left engine, the # 5 cylinder was off the engine and the # 5 piston with the connecting rod still attached were found nearby. Interviews revealed that during maintenance, the # 1,3,5,and 6 cylinders had been removed and reinstalled; however, the # 5 cylinder had not been tightened. Several people had worked on the airplane at various stages of the work. The maintenance facility did not have a system to pass down what had been accomplished, and the FAA did not require the tracking of work accomplished in other than 14 CFR Part 121, or 14 CFR Part 145 facilities.

Shortly after takeoff, the No. 2 engine failed and shutdown procedures for the No. 2 engine were accomplished. The flight crew declared an emergency and requested to return to the airport. On approach, an engine out go-around was required as ATC had instructed the flight crew of a B-747 to "position and hold" on the end of the runway. The first officer was the pilot flying. Following an uneventful touchdown, as the airplane slowed to about 80 knots, the captain took control of the airplane. Shortly thereafter, the right main landing gear (MLG) collapsed and the airplane slid to a stop on the runway. Examination of the No. 2 engine revealed that 80 percent of the main fuel pump main drive shaft was worn to the spline root. The examination also revealed that the grease used to lubricate the main drive shaft output splines was not the authorized grease specified per OHM 73-11-1 or MIL-G-81322. Additionally, the magnetic seal compression O-ring that rides on the drive gear journal outer diameter was hardened and exhibited inner diameter axial cracks. The component manufacturer indicated that the failure of the magnetic seal was the first such reported incident in 30 years; however, it agreed to review operational data from airlines to reevaluate the mean time between overhaul intervals for the seal and to recommend an inspection interval, as necessary. Examination of the right MLG revealed a fracture failure of the trunnion bearing support fitting that was caused by fatigue cracking and stress corrosion cracking.

While parked on the apron at Quito-Mariscal Sucre Airport, the crew started the engine when a pneumatic valve blocked. The problem was resolved and two engines were started with ground power unit while the third engine was started during taxi. During the takeoff roll on runway 17, at Vr speed, the pilot-in-command started the rotation but the aircraft failed to respond. For unknown reasons, the crew took 10 seconds to decide to abort the takeoff. The captain initiated an emergency braking procedure but the remaining distance of 800 metres was insufficient. Unable to stop, the aircraft overran, struck a concrete wall, an auto spare parts building and crashed near a soccer field, bursting into flames. Seventy people in the aircraft was well as 10 people on the ground were killed while 21 people in the airplane and 15 on the ground were injured, some seriously. At the time of the accident, the total weight of the aircraft was 73,309 kilos, within limits.

The airplane was dispatched as a cargo flight to pick up a load of 118 boxes of automotive seatbelts. After refueling and loading the cargo on board, the flight crew taxied to runway 22 for a no-flap takeoff, which called for a V1 speed of 141 knots. The first officer was the flying pilot for this leg of the flight. The crew reported that the initial takeoff roll from the 11,009 foot runway was normal. At approximately 120 knots, the flight crew reported hearing a loud bang followed by a vibration. The captain called for the first officer to abort the takeoff. The captain later stated that he believed he saw the #2 engine "roll back." The flight crew reported that the brakes were not effective in slowing the airplane. A witness stated that the airplane was going west on the runway at a high rate of speed when it "went up to two feet, then came back down." Another witness stated that he saw the airplane "exit off the end of the runway" and after about "seventy-five to one hundred feet, the front wheels lifted off the ground about ten feet." The airplane overran the departure end of the runway, went through the airport's chain link perimeter fence, across a 4-lane highway, collided with 3 vehicles on the roadway, and went through a second chain link fence, before coming to rest. The airplane came to rest on its belly, 2,010 feet from the departure threshold of runway 22. The investigation revealed that the flight crew was provided an inaccurate weight for the cargo, and the airplane was found to be 942 pounds over the maximum takeoff weight at the time of the accident. The density altitude was calculated to be 5,614 feet at the time of the accident. Both crewmembers were current and properly certified; however, the captain had upgraded to his present position two months prior to the accident, and the first officer had accumulated a total of 123.8 hours in the Falcon 20 at the time of the accident. Both engines were operated in a test cell and performed within limits. About 90% of the right outboard main landing gear tire's retread was found on the runway approximately 7,200 feet from where the aircraft had commenced its takeoff roll. The operator stated that since the aircraft was over maximum gross weight, the long taxi to the runway could have resulted in the brakes and tires heating more than normal.

Final power assurance checks were carried out on the aircraft’s engines on the morning of the accident. The AME (Aircraft Maintenance Engineer) trimmed the elevator-trim tab to the Full Nose UP position in order to reduce the stick forces required to hold the tail down during the engine power checks, but he did not set the elevator trim back to the neutral position on completion of the checks. The AME was requested by the pilot(s) to remove the aileron and elevator external gust locks and the landing gear down lock pins. He left the rudder lock in place, which was later removed by one of the pilots. The pilot(s) did not carry out a pre-flight inspection. At approximately 1646 on 24 August 1998 the DC3TP, registration number ZS-NKK, crashed during take-off from runway 11 at Wonderboom Airport. The PIC (Pilot-in-Command), who did not wear a shoulder harness, sustained fatal injuries and the co-pilot, who did wear a shoulder harness, serious injures. The accident occurred on the first flight after the aircraft had undergone a maintenance inspection, which included power assurance checks of the engines. The co-pilot sat in the left-hand seat and while he started the engines, the PIC attended to the cockpit checklist.