No fatalities

2020-10-14: Antonov AN-32 (OB-2120-P) — AerCaribe Peru — Iquitos-Coronel Francisco Secada Vignetta, Peru

Iquitos-Coronel Francisco Secada Vignetta, PeruLanding (descent or approach)

On October 14, 2020, an Antonov AN-32 (registration OB-2120-P) operated by AerCaribe Peru was involved in an aviation accident near Iquitos-Coronel Francisco Secada Vignetta, Peru during landing or approach. No fatalities were reported. Investigators recorded the probable cause as: Runway Excursion due to loss of directional control of the aircraft after landing by disengaging the propeller stops for aerodynamic braking at a higher than established speed, which generated an uncontrollable leftward turning moment of the trajectory, due… This summary draws on records from the Bureau of Aircraft Accidents Archives (B3A).

Sourcesthe Bureau of Aircraft Accidents Archives (B3A)Primary reportUpdated 1781190277Data APIEditorial standards

After landing on runway 06 at Iquitos Airport, the aircraft lost directional control, veered left, struck trees and bushes, lost its right wing, and broke in two. A fire erupted but was extinguished. All four crew members sustained minor injuries; the aircraft was destroyed.

Accident Summary

On approach to Iquitos-Coronel Francisco Secada Vignetta Airport, the aircraft touched down on runway 06. Immediately after touchdown, it lost directional control and veered to the left side of the runway. The aircraft struck trees and bushes, resulting in the loss of its right wing. It came to rest approximately 100 meters left of the runway, broken into two sections. A fire erupted but was quickly extinguished by emergency personnel.

Injuries and Damage

All four crew members aboard the aircraft sustained minor injuries. The aircraft was destroyed in the accident.

Probable Cause

According to the official investigation, the probable cause was a runway excursion due to loss of directional control after landing. This occurred when the propeller stops were disengaged for aerodynamic braking at a speed higher than established, which generated an uncontrollable leftward turning moment caused by asymmetric thrust from the propellers.

Contributing Factors

The investigation identified several contributing factors:

  • The landing was performed on an unstabilised approach, and the established go-around procedure was not executed.
  • The failed landing due to asymmetric thrust was not handled by applying the operator's Quick Reference Handbook (QRH) procedure to shut down the failed engine.
  • A probable failure of the KTA Fuel Regulator of the Automatic Engine Rotation Frequency and Power Regulation System, which blocked the reduction of power on the No. 2 engine to the regimes required for approach and landing.