2025-13-06: Tail Rotor Control System

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: 2025-13-06 Airbus Helicopters Deutschland GmbH: Amendment 39-23072; Docket No. FAA-2025-1117; Project Identifier MCAI-2025-00845-R. (a) Effective Date This airworthiness directive (AD) is effective July 18, 2025. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters, serial numbers 0001 through 1999 inclusive, certificated in any category. Note 1 to paragraph (c): Helicopters with an EC135P3H designation are Model EC135P3 helicopters, and helicopters with an EC135T3H designation are Model EC135T3 helicopters. (d) Subject Joint Aircraft System Component (JASC) Code 6720, Tail Rotor Control System. (e) Unsafe Condition This AD was prompted by a report of a loss of tail rotor controls due to a broken control rod of the yaw actuator. The root cause of this damage is unknown, and investigation is ongoing. The FAA is issuing this AD to detect and address damage to the ball bearing control system. The unsafe condition, if not addressed, could result in loss of tail rotor controls 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 paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency AD 2025-0108, dated May 8, 2025 (EASA AD 2025-0108). (h) Exceptions to EASA AD 2025-0108 (1) Where EASA AD 2025-0108 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (2) Where EASA AD 2025-0108 refers to its effective date, this AD requires using the effective date of this AD. (3) Where paragraph (2) of EASA AD 2025-0108 specifies "any discrepancy, as defined in the ASB", this AD requires replacing that text with "any wear or damage." (4) Where the material referenced in EASA AD 2025-0108 specifies to examine the close-tolerance bolt, the input lever, the rod end, the adapter, and the connector cover for wear and damage, for the purposes of this AD damage is defined as specified in paragraphs (h)(4)(i) through (iv) of this AD, as applicable. (i) Damage for the close-tolerance bolt is defined as deformed or stripped, rounded head; bent, stripped, or missing threads; bent shank; grooves in the shank, corrosion or rust; and gouges. (ii) Damage for the input lever is defined as deformation or elongated attachment hole; bent flange; gouges; corrosion; and cracks. (iii) Damage for the rod end is defined as corrosion, gouges, bending, and seizing. (iv) Damage for the adapter or connector is defined as deformation, elongated attachment holes, gouges, cracks, corrosion, and missing surface coating on the adapter or connector. (5) Where the material referenced in EASA AD 2025-0108 specifies if the ball pivot shows rough stiffness, hard stops, corrosion, or damage, for the purposes of this AD damage is defined as deformation (bent flanges), gouges, areas of bare metal, or missing finish. (6) Where paragraph (4) of EASA AD 2025-0108 specifies to report inspection results to Airbus Helicopters Deutschland within certain compliance times, for this AD, report inspection results at the applicable times specified in paragraphs (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 15 days after the inspection. (ii) For an inspection done before the effective date of this AD: Submit the report within 15 days after the effective date of this AD. (7) Where the material referenced in EASA AD 2025-0108 specifies actions for non-installed equipment or parts, this AD does not require those actions. (8) Where the material referenced in EASA AD 2025-0108 specifies to replace an affected part, this AD requires removing an affected part from service and replacing it with a serviceable part. (9) This AD does not adopt the Remarks section of EASA AD 2025-0108. (i) No Returning Parts Requirement Although the material referenced in EASA AD 2025-0108 specifies to return parts to the manufacturer, this AD does not require that action. (j) Special Flight Permits Special flight permits are prohibited. (k) 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 (l) 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. (l) Additional information For more information about this AD, contact Steven Warwick, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY; phone: (817) 222-5225; email: steven.r.warwick@faa.gov. (m) 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 2025-0108, dated May 8, 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: 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 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 fr.inspection@nara.gov . Issued on June 18, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-12388 Filed 6-30-25; 4:15 pm]BILLING CODE 4910-13-P