Airworthiness Directive · Amendment 39-14075 · Agusta S.p.A. Model A109E Helicopters
Agusta S.p.A. Model A109E Helicopters
Model A109E helicopters, certificated in any category.
This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that requires visually inspecting each main transmission support fitting (fitting) attachment bolt (bolt) for a fracture, a crack, or looseness, and verifying the torque on each fitting bolt. This amendment is prompted by two incidents of fatigue failure of the bolts that secure the transmission rear support fittings to the helicopter. The actions specified by this AD are intended to detect a fracture, a crack, or looseness of a fitting bolt, and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter.
To detect a fracture, a crack, or looseness of a main transmission support fitting (fitting) attachment bolt (bolt), and prevent fatigue failure of a fitting bolt and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 5 hours time-in-service (TIS), and then at intervals not to exceed 10 hours TIS until a torque inspection of each fitting bolt is accomplished in accordance with paragraph (b) of this AD, inspect each fitting bolt, part number NAS625-14, for a fracture, a crack, or looseness using a light and a mirror in accordance with Part I, steps 1. through 4., of Agusta Bollettino Tecnico No. 109EP-43, dated March 25, 2004 (BT).
(1) On each of the 4 fittings, if a fracture or a crack is found in any bolt, replace all 4 bolts in the fitting with airworthy fitting bolts before further flight.
(2) If looseness is found in any bolt in any fitting, inspect each of the 4 bolts on each of the 4 fittings (16 bolts total) to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt in a fitting, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 5.1 through 9. of the BT.
(b) Within 25 hours TIS, inspect each bolt in each fitting to determine if the torque is between 11.3-15.8 Nm (100-140 inch-pounds). If the indicated torque is not within the acceptable range on any bolt, before further flight, remove all 4 bolts in the fitting and replace them with airworthy fitting bolts in accordance with Part II, steps 5.1 through 9., of the BT.
(c) Accomplishing the inspections specified in paragraphs (a) and (b) constitute terminating actions for the requirements of this AD.
(d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
