Airworthiness Directive · Amendment 39-22582 · Stabilizers
ATR-GIE Avions de Transport Régional Airplanes
Superseded. A later AD replaced this one: AD 2026-16-07. Comply with the one in force.
This AD applies to ATR—GIE Avions de Transport Régional Model ATR42-500 and ATR72-212A airplanes, certificated in any category, as identified in ATR Service Bulletin ATR42-55-0020, dated March 2, 2023; or ATR Service Bulletin ATR72-55-1013, dated March 2, 2023; as applicable.
The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by reports of loose fasteners and cracks in the horizontal stabilizer (HS) left- and right- hand leading edge lateral ribs, the box in between, the center box upper panel, and HS forward back-up fitting. This AD requires an inspection of the HS affected areas for discrepancies and applicable corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2023-0125, dated June 22, 2023 (EASA AD 2023-0125).
(1) Where paragraph (1) of EASA AD 2023-0125 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2023-0125 specifies to “contact ATR for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly” if any discrepancy is detected, for this AD if any crack is detected, the crack must be repaired before further flight using a method approved by the Manager, International Validation Branch, FAA; or EASA; or ATR—GIE Avions de Transport Régional's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(3) This AD does not adopt the “Remarks” section of EASA AD 2023-0125.
Although the service information referenced in EASA AD 2023-0125 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Validation Branch, FAA; or EASA; or ATR—GIE Avions de Transport Régional's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
For more information about this AD, contact Shahram Daneshmandi, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-231-3220; email shahram.daneshmandi@faa.gov.
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.
