2026-02-05: Fuselage Structure (General)

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: 2026-02-05 Leonardo S.p.A.: Amendment 39-23241; Docket No. FAA-2026-0014; Project Identifier MCAI-2024-00309-R. (a) Effective Date This airworthiness directive (AD) is effective February 6, 2026. (b) Affected ADs None. (c) Applicability This AD applies to Leonardo S.p.A. Model AB412 and AB412 EP helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 5300, Fuselage Structure (General). (e) Unsafe Condition This AD was prompted by a report of a cracked left upper cap angle (cap angle) part number 212-030-191-1. The FAA is issuing this AD to detect and correct cracking or damage of the cap angle which, if not addressed, could result in reduced structural integrity of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions 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 2024-0104, dated May 24, 2024 (EASA AD 2024-0104). (h) Exceptions to EASA AD 2024-0104 (1) Where EASA AD 2024-0104 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2024-0104 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (3) Where paragraph (1) of EASA AD 2024-0104 specifies "Within 25 FH [flight hours] since last inspection accomplished in accordance with the instructions of Agusta MBT 412-128 (as required by EASA AD 2009-0185), or within 5 FH after the effective date of this AD, whichever occurs later", this AD requires replacing that text with "Within 5 hours time-in-service after the effective date of this AD". (4) Where the material referenced in paragraph (1) of EASA AD 2024-0104 specifies "if no cracks are revealed", this AD requires replacing that text with "If there are no cracks in the area inspected". (5) This AD does not adopt paragraph (2) of EASA AD 2024-0104. (6) Where paragraph (3) of EASA AD 2024-0104 specifies contacting Leonardo for approved instructions if there is a crack or damage, and where the material referenced in EASA AD 2024-0104 specifies to contact Leonardo Helicopters for further instruction if there is a crack, this AD requires, before further flight, actions done in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Leonardo S.p.A.'s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (7) Where paragraph (3) of EASA AD 2024-0104 specifies "any crack or damage", this AD requires replacing that text with "any crack or damage (smoking of the fitting attachment and crazing of sealant bead around the fitting as crack indications)". (8) This AD does not adopt the "Remarks" section of EASA AD 2024-0104. (i) No Reporting Requirement Although the material referenced in EASA AD 2024-0104 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: [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. (k) Additional Information For more information about this AD, contact Deep Gaurav, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 228-3731; email: [email protected]. (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 2024-0104, dated May 24, 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 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 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 January 13, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026-01183 Filed 1-21-26; 8:45 am]BILLING CODE 4910-13-P