2025-18-09: Main Rotor Transmission Mount

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2025-18-09 Airbus Helicopters: Amendment 39-23136; Docket No. FAA-2025-0914; Project Identifier MCAI-2024-00413-R. (a) Effective Date This airworthiness directive (AD) is effective October 21, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Helicopters Model AS 332L2 and EC 225LP helicopters, certificated in any category, as identified in European Union Aviation Safety Agency AD 2024-0142, dated July 17, 2024 (EASA AD 2024-0142). (d) Subject Joint Aircraft System Component (JASC) Code 6330, Main Rotor Transmission Mount. (e) Unsafe Condition This AD was prompted by reports of overlengthened and deformed attachment bolts installed on the new link of the main gearbox (MGB) suspension bar attachment bracket. The FAA is issuing this AD to prevent structural failure of the MGB suspension bar attachment bolts. The unsafe condition, if not addressed, could result in failure of an MGB attachment assembly, detachment of an MGB suspension bar, and consequent loss control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2024-0142. Note 1 to paragraph (g): EASA AD 2024-0142 and Airbus Helicopters material that is referenced in EASA AD 2024-0142 refer to MGB suspension bar attachment "bolts" as "screws." (h) Exceptions to EASA AD 2024-0142 (1) Where paragraph (1) of EASA AD 2024-0142 requires compliance within 2,500 flight hours since first installation, this AD requires compliance as specified in paragraphs (h)(1)(i) and (ii) of this AD. (i) For each affected part that has accumulated 2,500 or more total hours time-in-service (TIS) or if the total hours TIS on the affected part cannot be determined: Before further flight, and thereafter at intervals not to exceed 2,500 total hours TIS on the affected part. (ii) For each affected part that has accumulated less than 2,500 total hours TIS: Before the affected part accumulates 2,500 total hours TIS, and thereafter at intervals not to exceed 2,500 total hours TIS on the affected part. (2) Where the material referenced in EASA AD 2024-0142 specifies discarding parts, this AD requires removing those parts from service. (3) Instead of the reporting requirement in paragraph (3) of EASA AD 2024-0142, this AD requires reporting the results of each inspection to Airbus Helicopters at the compliance time specified in paragraph (h)(3)(i) or (ii) of this AD. The report must include the total hours TIS (if known) on each bolt, the batch number and serial number of the bolt, the length of the bolt, a detailed description of any findings, any previous maintenance, and any photos (if possible). (i) For an inspection done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) For an inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (4) This AD does not require paragraph (4) of EASA AD 2024-0142. (5) Where the material referenced in EASA AD 2024-0142 specifies contacting Airbus Helicopters for repair instructions, this AD requires using a repair method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (6) This AD does not adopt the "Remarks" section of EASA AD 2024-0142. (i) Alternative Methods of Compliance (AMOCs) (1) 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, send it to the attention of the person identified in paragraph (j) of this AD and email to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (j) Additional Information For more information about this AD, contact George Weir, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222-4045; email: [email protected]. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2024-0142, dated July 17, 2024. (ii) [Reserved] (3) For EASA material identified in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999 000; email: [email protected]; website: easa.europa.eu. You may find this material on the EASA website at ad.easa.europa.eu. (4) You may view this material at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Parkway, Room 6N-321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected]. Issued on September 3, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-17850 Filed 9-15-25; 8:45 am]BILLING CODE 4910-13-P