Airworthiness Directive · Amendment 39-21643 · Fuselage main, frame
Airbus Helicopters (Type Certificate Previously Held by Eurocopter France)
This AD applies to all Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters (type certificate previously held by Eurocopter France) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD was prompted by a quality control check that revealed some stretcher attachment holes were improperly located on the frame where there was insufficient edge distance. This AD requires measuring the 9-degree frame flange (frame) for the correct edge distance of the four attachment holes for the stretcher support and inspecting for cracks, and repairing the frame, if necessary, and installation of a reinforcement plate (reinforcing angle), as specified in two Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with the applicable Direction Générale de l'Aviation Civile (DGAC) ADs specified in paragraphs (g)(1) and (2) of this AD.
(1) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters: DGAC AD 2001-061-053(A), dated February 21, 2001, (DGAC AD 2001-061-053(A)).
(2) For Model SA-366G1 helicopters: DGAC AD 2001-283-025(A), dated July 11, 2001 (DGAC AD 2001-283-025(A)).
(1) Where paragraph 3.1 of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies an initial compliance time to do the measurement, for this AD, do the measurement within 50 hours time-in-service (TIS) after the effective date of this AD.
(2) Where paragraph 3.1. of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies to do a measurement, for this AD, do an inspection of the area around the attachment holes for cracks concurrently with the measurement.
(3) Where paragraph 3.2.1.a) of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies “every 550 flight hours, check that there is no crack in the flange,” for this AD, inspect (check) the area around the attachment holes for cracks at intervals not to exceed 550 hours TIS.
(4) Where paragraph 3.2.1.b) of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) requires installation of a reinforcement plate (reinforcing angle) on the flange for certain helicopters, do the installation within 550 hours TIS after accomplishment of the measurement specified in paragraph 3.1. of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A).
(5) Where the service information referred to in DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies to perform a dye penetrant crack inspection “if in doubt,” this AD requires performing a dye penetrant inspection.
(6) Where paragraph 3.2.2. of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies to do various actions specified in paragraphs 3.2.2.a), b), and c) of those ADs, for this AD, if any frame is cracked, before further flight, repair the frame. Acceptable U.S. alternatives to the fasteners and materials needed to perform repairs or modifications are listed in American Eurocopter Engineering Report No. AEC/03R-E-005, “Addendum ASB 53.00.42 and 53.00.43 AS365”, dated January 29, 2003.
(7) Where the Note in paragraph 3.2.2. of DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) specifies the instructions are no longer applicable after a customized repair has been carried out, for this AD, modifying or repairing the frame constitutes terminating action for the requirements of this AD.
