Airworthiness Directive · Amendment 39-22745 · Flight controls
ATR-GIE Avions de Transport Régional Airplanes
This AD applies to all ATR—GIE Avions de Transport Régional Model ATR42-500 and Model ATR72-101, -102, -201, -202, -211, -212, and -212A airplanes.
The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and Model ATR72 airplanes. This AD was prompted by reports of heavy corrosion on one of the two lugs of the travel limiting unit (TLU) lever assembly. This AD requires repetitive inspections of the TLU lever assembly for corrosion and, depending on findings, a conductivity test and applicable corrective actions, and prohibits the installation of affected parts, 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 paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2024-0096, dated May 2, 2024 (EASA AD 2024-0096).
(1) Where EASA AD 2024-0096 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (4) of EASA AD 2024-0096 specifies “to contact ATR for repair instructions and to accomplish those instructions accordingly,” this AD requires replacing that text with “repair of any corrosion 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) The service information referenced in EASA AD 2024-0096 specifies replacement of the TLU lever “before further flight” or “within 6 months,” as applicable depending on the results of the inspection and conductivity test. For this AD, the compliance time to replace the TLU lever starts from the conductivity test.
(4) Replace paragraph (8) of EASA AD 2024-0096 with “Accomplishment of the applicable actions for affected parts in accordance with ATR AOM 2024/04 Issue 1 is acceptable to comply with the requirements of paragraphs (1), (2), (3), and (4) of this AD, as applicable, for those affected parts only.”
(5) Paragraph (9) of EASA AD 2024-0096 specifies to report inspection results to ATR within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(5)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
(6) This AD does not adopt the “Remarks” section of EASA AD 2024-0096.
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 manager of the International Validation Branch, mail it to the address identified in paragraph (j) 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 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.
Aircraft
