2026-19890: Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters

Federal Register, Volume 91 Issue 187 (Tuesday, September 29, 2026) [Federal Register Volume 91, Number 187 (Tuesday, September 29, 2026)] [Proposed Rules] [Pages 61361-61364] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 2026-19890] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2026-11790; Project Identifier MCAI-2025-01757-R] RIN 2120-AA64 Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters

Agency

Federal Aviation Administration (FAA), DOT.

Action

Notice of proposed rulemaking (NPRM). -----------------------------------------------------------------------

Summary

The FAA proposes to supersede Airworthiness Directive (AD) 2025-13-06, which applies to certain Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2025-13-06 requires inspections of the ball pivot, control rod, and yaw actuator assembly and, depending on the results of these inspections, corrective actions. AD 2025-13-06 also prohibits installing an affected part unless it is a serviceable part and certain requirements are met. Since the FAA issued AD 2025-13-06, the manufacturer developed a repetitive inspection of the ball pivot. This proposed AD would retain some of the actions of AD 2025-13-06 and would require repetitive inspection of the ball pivot and, depending on the results of those inspections, corrective actions. This proposed AD would also prohibit installing an affected part unless it is a serviceable part and certain requirements are met. Additionally, this proposed AD would require reporting the results of the inspections. The FAA is proposing this AD to address the unsafe condition on these products.

Dates

The FAA must receive comments on this NPRM by November 13, 2026.

Addresses

You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. AD Docket: You may examine the AD docket at regulations.gov under Docket No. FAA-2026-11790; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the mandatory continuing airworthiness information (MCAI) any comments received, and other information. The street address for Docket Operations is listed above. Material Incorporated by Reference: For European Union Aviation Safety Agency (EASA) material identified in this proposed AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone +49 221 8999 000; email: [email protected]; website: easa.europa.eu. You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 10101 Hillwood Parkway, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110.

For Further Information Contact

Mahmood Shah, Aviation Safety [[Page 61362]] Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (817) 222-5538; email: [email protected].

Supplementary Information

Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments using a method listed under ADDRESSES. Include ``Docket No. FAA-2026-11790; Project Identifier MCAI-2025-01757-R'' at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend the proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ``PROPIN.'' The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Mahmood Shah, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background The FAA issued AD 2025-13-06, Amendment 39-23072 (90 FR 28879, July 2, 2025) (AD 2025-13-06), for certain AHD Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. AD 2025-13-06 was prompted by an MCAI originated by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued AD 2025-0108, dated May 8, 2025, (EASA AD 2025-0108) to correct an unsafe condition identified as damage to the ball bearing control system. AD 2025-13-06 requires a one-time visual inspection of the ball pivot, fluorescent penetrant inspection of the control rod, visual inspection and measurement of certain parts of the yaw actuator assembly, and depending on the results of these inspections, corrective actions. AD 2025-13-06 also prohibits installing an affected part unless it is a serviceable part and certain requirements are met. The FAA issued AD 2025-13-06 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 loss of control of the helicopter. Actions Since AD 2025-13-06 Was Issued Since the FAA issued AD 2025-13-06, EASA superseded EASA AD 2025- 0108 and issued EASA AD 2025-0260, dated November 25, 2025 (EASA AD 2025-0260) (also referred to as the MCAI). The MCAI states the manufacturer developed a repetitive inspection of the ball pivot. You may examine the MCAI in the AD docket at regulations.gov under Docket No. FAA-2026-11790. Material Incorporated by Reference Under 1 CFR Part 51 The FAA reviewed EASA AD 2025-0260, which specifies procedures for a one-time visual inspection of the ball pivot, a fluorescent penetrant inspection of the control rod of the yaw actuator, inspection of the yaw actuator interface connections, and a check (inspection) of the freedom of movement of the tail rotor control. Depending on the inspection results, EASA AD 2025-0260 specifies procedures for corrective actions to include further inspections and the replacement of affected parts. In addition, EASA AD 2025-0260 specifies procedures for repetitive inspection of the ball pivot, and depending on the results of the inspections, corrective actions, which include further inspections and the replacement of affected parts. EASA AD 2025-0260 requires reporting the inspection results (including no findings) to AHD and prohibits installing ball pivot part number (P/N) 92-201-00 and P/N 92-207-00; yaw actuator assembly P/N L672M2005104, P/N L672M2005105, and P/N L672M2005106; and control rod P/N L672M2006101 and P/N L672M2006102 on any helicopter unless certain requirements are met. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination These products have been approved by the civil aviation authority (CAA) of another country and are approved for operation in the United States. Pursuant to the FAA's bilateral agreement with this State of Design Authority, that authority has notified the FAA of the unsafe condition described in the MCAI referenced above. The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed AD Requirements in This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2025-0260, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. See ``Differences Between this Proposed AD and the MCAI'' for a discussion of the general differences included in this proposed AD. Differences Between This Proposed AD and the MCAI The MCAI applies to Model EC635 P2+, EC635 P3, EC635 T1, and EC635 T3 helicopters, whereas this AD does not because those models do not have an FAA type certificate. Explanation of Required Compliance Information In the FAA's ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use some CAA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with manufacturers and CAAs. As a result, the FAA proposes to incorporate EASA AD 2025-0260 by reference in the FAA final rule. This proposed AD would, therefore, require compliance with EASA AD 2025-0260 in its entirety through that incorporation, except for any differences identified as exceptions in the regulatory text of this proposed AD. Using common terms that are the same as the heading of a particular [[Page 61363]] section in EASA AD 2025-0260 does not mean that operators need comply only with that section. For example, where the AD requirement refers to ``all required actions and compliance times,'' compliance with this AD requirement is not limited to the section titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2025-0260. Material required by EASA AD 2025-0260 for compliance will be available at regulations.gov under Docket No. FAA-2026-11790 after the FAA final rule is published. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 377 helicopters of U.S. registry. The FAA estimates the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspect ball pivot............... 2 work-hours x $85 $0 $170 per inspection. $64,090 per per hour = $170. inspection. Perform fluorescent penetrant 2 work-hours x $85 0 $170................ $64,090. inspection. per hour = $170. Inspect yaw actuator interface 2 work-hours x $85 0 $170................ $64,090. connections. per hour = $170. Inspect control rod.............. 1 work-hour x $85 0 $85................. $32,045. per hour= $85. Report inspection results........ 1 work-hour x $85 0 $85................. $32,045. per hour = $85. Inspect freedom of movement...... 1 work-hour x $85 0 $85 per inspection.. $32,045 per per hour = $85. inspection. ---------------------------------------------------------------------------------------------------------------- The FAA estimates the following costs to do any replacements that would be required based on the results of the inspection. The agency has no way of determining the number of helicopters that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replace adapter............................... 1 work-hour x $85 per hour = $85 $803 $888 Replace ball pivot............................ 1 work-hour x $85 per hour = $85 2,846 2,931 Replace close tolerance bolt.................. 1 work-hour x $85 per hour = $85 42 127 Replace connector cover....................... 1 work-hour x $85 per hour = $85 571 656 Replace control rod........................... 1 work-hour x $85 per hour = $85 6,835 6,920 Replace input lever........................... 2 work-hours x $85 per hour = 9,755 9,925 $170. Replace rod end............................... 1 work-hour x $85 per hour = $85 643 728 ---------------------------------------------------------------------------------------------------------------- Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are mandatory. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings The FAA determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. [[Page 61364]] The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0