EASA AD 2014-0162R2

Revises an AD to introduce a modification to the 9-deg frame as a terminating action for required repetitive inspections for cracks. The AD originally was prompted by the finding of a crack on the 9-deg frame. The affected helicopter had accumulated 10,786 flight hours (FH) at the time of the inspection. The crack was located 230 mm above the cabin floor and had grown over a large section of the frame on the right-hand (RH) side. To address this potential unsafe condition, EASA issued an emergency AD to require repetitive detailed visual inspections on the RH and left-hand (LH) side of the affected frame to detect any crack and of applicable corrective action, if necessary. After that AD was issued, the results of analyses demonstrated that the flight time leading to crack initiation in the affected area varied significantly depending on the weight and balance data of the affected helicopter models. EASA issued subsequent ADs modifying compliance times and inspection thresholds. Since then, Airbus Helicopters developed the modification to provide structural reinforcement and a terminating action for the inspections.