2025-07-08: Tail Rotor Head

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: 2025-07-08 Airbus Helicopters: Amendment 39-23010; Docket No. FAA-2025-0614; Project Identifier MCAI-2025-00008-R. (a) Effective Date This airworthiness directive (AD) is effective April 25, 2025. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 6420 Tail Rotor Head. (e) Unsafe Condition This AD was prompted by a report of the loss of the tail rotor pitch control. The FAA is issuing this AD to detect and address any score, scratch, crack, or corrosion on the slide of the control plate of the tail rotor head assembly. The unsafe condition, if not addressed, could result in structural failure of the tail rotor head assembly and reduced or loss of 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 European Union Aviation Safety Agency (EASA) AD 2025-0001, dated January 6, 2025 (EASA AD 2025-0001). (h) Exceptions to EASA AD 2025-0001 (1) Where EASA AD 2025-0001 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (2) Where EASA AD 2025-0001 refers to its effective date, this AD requires using the effective date of this AD. (3) Where the material referenced in EASA AD 2025-0001 specifies discarding certain parts, this AD requires removing these parts from service. (4) Where paragraph (3.1) of EASA AD 2025-0001 specifies replacing the TRH assembly with an assembly repaired in accordance with AH instructions, this AD requires replacement in accordance with a method approved by the Manager, International Validation Branch, FAA, or EASA, or Airbus Helicopters Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA authorized signature. (5) Where the material referenced in EASA AD 2025-0001 specifies sending the TRH to Airbus Helicopters for replacement of the slide, this AD requires replacement in accordance with a method approved by the Manager, International Validation Branch, FAA, or EASA, or Airbus Helicopters DOA. If approved by the DOA, the approval must include the DOA authorized signature. (6) Where paragraph (4) of EASA AD 2025-0001 states to submit inspection results to AH within 30 days after that inspection, for this AD, report inspection results at the applicable times specified in paragraph (h)(6)(i) or (ii) of this AD. (i) For an inspection done on or after the effective date of this AD: Submit the report within 7 days after the inspection. (ii) For an inspection done before the effective date of this AD: Submit the report within 7 days after the effective date of this AD. (7) This AD does not adopt the "Remarks" section of EASA AD 2025-0001. (i) Special Flight Permits Special flight permits are prohibited. 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 local Flight Standards District 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 local Flight Standards District Office/certificate holding district office. (j) Additional Information For more information about this AD, contact Evan Weaver, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222-5134; 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 2025-0001, dated January 6, 2025. (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 the EASA 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 Pkwy., 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 April 4, 2025. Paul R. Bernado, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-06120 Filed 4-7-25; 11:15 am]BILLING CODE 4910-13-P