Airworthiness Directive · Amendment 39-16815 · Eurocopter France (Eurocopter) Model EC225LP Helicopters
Eurocopter France (Eurocopter) Model EC225LP Helicopters
Model EC225LP helicopters, certificated in any category, that have not been modified in accordance with Eurocopter Modification (MOD) 0743718.
This amendment adopts a new airworthiness directive (AD) for the Eurocopter Model EC225LP helicopters. This AD requires inspecting the dome fairing support for a crack at the dome fairing attachment point. If a crack is found, this AD requires replacing the dome fairing support and the associated coning stop support assembly before further flight. If no crack is found, this AD requires repetitive inspections and retorquing the screws at specified intervals. This AD is prompted by the discovery of two fatigue cracks in the dome fairing attachment on the dome fairing support. This condition, if not corrected, could lead to the loss of the dome fairing in flight, causing damage to the helicopter and injury to people on the ground.
To prevent loss of the dome fairing in flight, damage to the helicopter, and injury to people on the ground, accomplish the following:
(a) Within 15 hours time-in-service (TIS), unless accomplished previously, inspect for a crack in the dome fairing support at the dome fairing attachment points.
(1) If a crack is found in the dome fairing support or at a dome fairing attachment point, before further flight, replace the dome fairing support and the associated coning stop support assembly.
(2) If no crack is found, thereafter at intervals not exceeding 165 hours TIS, inspect for a crack in the dome fairing support, and re-torque the screws securing the dome fairing support to the dome fairing.
Note 1: Eurocopter Emergency Alert Service Bulletin No. 05A005, Revision 1, dated February 3, 2009, and Service Bulletin No. 62-007, Revision 1, dated July 10, 2009, which are not incorporated by reference, contain additional information about the subject of this AD.
(b) Accomplishing Eurocopter MOD 0743718 constitutes terminating action for the requirements of this AD.
(c) 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 Manager, Safety Management Group, FAA, Attn: Gary Roach, Aviation Safety Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-5130; fax: 817-222-5961, for information about previously approved alternative methods of compliance.
(d) A special flight permit will not be issued.
(e) The Joint Aircraft System/Component (JASC) Code is 6300: Main Rotor Drive System.
