2025-24-04: Vertical Stabilizer, Spar/Rib Structure

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: a. Removing Airworthiness Directive 2021-20-16, Amendment 39-21754 (86 FR 57550, dated October 18, 2021); and b. Adding the following new airworthiness directive: 2025-24-04 AIRBUS HELICOPTERS: Amendment 39-23199; Docket No. FAA-2025-1735; Project Identifier MCAI-2024-00408-R. (a) Effective Date This airworthiness directive (AD) is effective January 12, 2026. (b) Affected ADs This AD replaces AD 2021-20-16, Amendment 39-21754 (86 FR 57550, dated October 18, 2021). (c) Applicability This AD applies to Airbus Helicopters Model AS 350B3, AS355E, AS 355-F, AS 355-F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, as identified in European Union Aviation Safety Agency AD 2024-0139, dated July 12, 2024 (EASA AD 2024-0139). (d) Subject Joint Aircraft System Component (JASC) Code 5531, Vertical Stabilizer, Spar/Rib Structure. (e) Unsafe Condition This AD was prompted by a report of a structural crack in the vertical attachment spar of the upper tail fin and fractures in its two front attachment screws. The FAA is issuing this AD to address cracking in the upper fin spar and fracturing of the front attachment screws. The unsafe condition, if not addressed, could result in in-flight separation of the upper part of the vertical fin and consequent 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2024-0139. (h) Exceptions to EASA AD 2024-0139 (1) Where EASA AD 2024-0139 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (2) Where EASA AD 2024-0139 refers to its effective date or to any of the dates listed in paragraphs (h)(2)(i) through (iv) of this AD, this AD requires using the effective date of this AD. (i) July 12, 2017 (the effective date of EASA AD 2017-0114, dated June 28, 2017). (ii) April 23, 2021 (the effective date of EASA AD 2021-0099, dated April 9, 2021). (iii) April 14, 2023 (the effective date of EASA AD 2023-0075, dated April 7, 2023). (iv) May 18, 2023 (the effective date of EASA AD 2023-0089, dated May 4, 2023). (3) Where paragraph (1) of EASA AD 2024-0139 specifies to inform all flight crew and operate the helicopter accordingly, this AD does not require those actions as those actions are already required by existing FAA operating regulations (see 14 CFR 91.505 and 14 CFR 135.21). (4) Although the material referenced in EASA AD 2024-0139 allows some actions to be performed by a pilot, this AD does not. (5) Where the material referenced in EASA AD 2024-0139 states "if you are not sure", this AD requires replacing that text with "to confirm suspected cracks (scratch, line, misalignment, etc.)". (6) Where the material referenced in EASA AD 2024-0139 states to do a dye-penetrant inspection (DPI), this AD requires the actions in paragraph (h)(6)(i), (ii), or (iii) of this AD, as applicable: (i) If the right-hand (RH) side of the spar (a) has previously been inspected by a DPI method, accomplish a DPI of the RH side of the spar (a). (ii) If the RH side of the spar (a) has not previously been inspected by a DPI, accomplish a fluorescent penetrant inspection (FPI) of the RH-hand side of the spar (a), instead of a DPI. (iii) If you cannot determine whether the RH side of the spar (a) has previously been inspected by a DPI, clean all surfaces to be inspected and accomplish an FPI of the RH side of the spar (a) instead of a DPI. Note 1 to paragraph (h)(6)(iii): Work Card 20-02-09-101 (MTC) contains DPI information related to this AD. Note 2 to paragraph (h)(6)(iii): When entering compliance with the applicable paragraph of the AD into the helicopter maintenance records, explicitly documenting that a dye penetrant inspection was performed improves the accuracy of maintenance records regarding use of dye penetrant inspection dye. (7) Where the material referenced in EASA AD 2024-0139 refers to damage, for this AD, damage is defined as looseness, corrosion, broken or missing lockwire, loss of protective surface finish, deformation, fracture, crack, or nick. (8) Where paragraph (8) of EASA AD 2024-0139 states "maintenance flight", this AD requires replacing that text with "flight to perform an operational check as specified in 14 CFR 91.407". (9) Where paragraph (10) of EASA AD 2024-0139 and the material referenced in EASA AD 2024-0139 specify contacting Airbus Helicopters for repair instructions, this AD requires using a repair method approved by the FAA, EASA, or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (10) Where the material referenced in EASA AD 2024-0139 specifies to discard parts, this AD requires removing those parts from service. (11) Where paragraph (16) of EASA AD 2024-0139 only allows credit for the initial actions in paragraphs (4) through (9) of EASA AD 2024-0139, this AD allows credit for any action in paragraphs (4) through (9) of EASA AD 2024-0139. (12) This AD does not adopt the "Remarks" section of EASA AD 2024-0139. (i) No Reporting Requirement Although the material referenced in EASA AD 2024-0139 specifies to submit certain information to the manufacturer, this AD does not require that action. (j) 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 (k) of this AD and email to: AMOC@faa.gov. (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. (k) Additional Information For more information about this AD, contact Steven Warwick, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; phone: (817) 222-5225; email: steven.r.warwick@faa.gov. (l) 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 2024-0139, dated July 12, 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: ADs@easa.europa.eu; 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 fr.inspection@nara.gov. Issued on November 19, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-22234 Filed 12-5-25; 8:45 am]BILLING CODE 4910-13-P