Engine failure and subsequent loss of control during takeoff roll

No fatalities • Pushkin AFB, Russia • Takeoff (climb)

An aircraft experienced a sudden engine failure and propeller feathering during its takeoff roll, leading to a runway excursion and fire.

What happened

During the takeoff phase, the aircraft was traveling at a speed of 210 km/h after having covered a distance of 975 meters. At this point, engine n°4 experienced a failure, which triggered the automatic feathering of its propeller.

Following this mechanical issue, the crew did not identify the failure. Consequently, the pilot-in-command initiated rotation at a speed of 238 km/h, which was below the recommended speed of 250 km/h. The rotation was performed with an elevator setting of -26°.

Immediately after liftoff, the aircraft began to roll toward the right. Two seconds after the rotation phase, the right wing made contact with the ground. The aircraft subsequently lost control and its undercarriage was stripped away as it slid approximately 300 meters along the ground. The sequence ended when the aircraft burst into flames. All nine occupants managed to escape the wreckage, though they sustained various injuries.

Findings

  • The failure of engine n°4 was a primary factor in the loss of directional control.
  • The crew failed to recognize the status of the fourth engine during the critical takeoff period.

Frequently asked questions

What happened in the 1998-07-23 Antonov AN-12 accident near Pushkin AFB, Russia?

An aircraft experienced a sudden engine failure and propeller feathering during its takeoff roll, leading to a runway excursion and fire.

Were there any fatalities in the 1998-07-23 Antonov AN-12 accident?

No fatalities were recorded in this accident.

What aircraft was involved and where did it happen?

The accident on 1998-07-23 involved a Antonov AN-12, registration RA-11886, operated by Norilsk Avia, at Pushkin AFB, Russia.

What was the probable cause of the accident?

Failure of the engine n°4 due to an incorrect setting of the propeller speed control system.

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