What happened
On 22nd January 2014, an Airbus Helicopter EC130B4, registration A6-DYR, was performing a routine positioning flight from the Atlantis Palm Heliport to Dubai International Airport. The flight, operated by Helidubai, was being conducted without passengers; the occupants included the pilot and a helicopter landing officer.
Shortly after departing the helipad at 15:32 GST, the aircraft began a climb while simultaneously initiating a counter-clockwise turn. This turn accelerated rapidly, reaching a rate of approximately 180 degrees per second. The climb was interrupted at an altitude of roughly 22 meters as the helicopter entered a rapid descent. The aircraft pitched forward and struck the helipad with a high rate of descent and minimal forward speed. The impact was severe, generating vertical loads exceeding 20g.
Following the initial impact, the helicopter underwent an uncontrolled ground rotation along the heliport centerline. During this phase, the Fenestron tail rotor assembly separated from the tail boom after colliding with nearby structures. The aircraft eventually came to a stop after striking a retaining wall. Both the pilot and the passenger sustained serious injuries and required medical evacuation.
The investigation
The GCAA AAIS investigation examined the aircraft's flight data, including records from the Digital Engine Control Unit and the Vehicle and Engine Management Display. Investigators analyzed the wreckage, the impact site, and CCTV footage of the event. The investigation also reviewed the aircraft's airworthiness documentation and the meteorological conditions at the time of the accident, which were noted as light and variable winds.
Findings
- The primary cause of the accident was a loss of control during the takeoff phase, characterized by an accelerating counter-clockwise turn and a subsequent rapid descent.
- The vertical deceleration during the impact was extreme, exceeding 20g, which caused the seat restraint systems to trigger and resulted in the incapacitation of both occupants.
- The heavy landing caused extensive structural damage to the primary and secondary airframe components, including the failure of the skids under static load.
- During the subsequent ground rotation, the loss of tail rotor effectiveness and collisions with curb structures led to the separation of the tail rotor assembly.
- There was no evidence of pre-existing engine faults or loss of tail rotor effectiveness prior to the heavy landing.