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2026-05-06: Tail rotor system

FAA order 2026-05-06 is an airworthiness directive in force since April 17, 2026. The FAA's subject line: Tail rotor system. It names Airbus Helicopters AS332: about 8 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: rotorcraft systems.

What it applies to as the FAA lists it

Kind of product
Aircraft
Makes
Airbus Helicopters
Models
AS332C, AS332C1, AS332L, AS332L1, SA330J
On this site
Airbus Helicopters AS332 8 registered

Dates and paperwork

In force since
April 17, 2026
Published
March 13, 2026 (signed February 26, 2026)
Docket
FAA-2025-5043
Status
Current
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and SA330J helicopters. This AD was prompted by reports of fatigue cracks found on arms of the tail rotor (TR) pitch change spider due to a load increase originating from degraded bearing stacks. This AD requires reduced life limit intervals for the affected bearing stack and requires replacing the affected bearing stack before exceeding these intervals. This AD also prohibits the installation of the affected bearing stack on a helicopter, unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.

The order itself the regulatory text, as published

Show the full text (4,492 characters)
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: 2026-05-06 Airbus Helicopters: Amendment 39-23279; Docket No. FAA-2025-5043; Project Identifier MCAI-2024-00780-R. (a) Effective Date This airworthiness directive (AD) is effective April 17, 2026. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS 332L1, and SA330J helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 6400, Tail rotor system. (e) Unsafe Condition This AD was prompted by reports of fatigue cracks found on arms of the tail rotor pitch change spider due to a load increase originating from degraded bearing stacks. The FAA is issuing this AD to prevent degradation of bearing stacks. The unsafe condition, if not addressed, could lead to structural failure of the tail rotor assembly, which could result in 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 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 AD 2024-0250, dated December 20, 2024 (EASA AD 2024-0250). (h) Exceptions to EASA AD 2024-0250 (1) Where EASA AD 2024-0250 refers to its effective date, this AD requires using the effective date of this AD. (2) Where EASA AD 2024-0250 requires compliance in terms of flight hours, this AD requires using hours time-in-service. (3) Where the material referenced in EASA AD 2024-0250 specifies "check", for this AD replace that text with "inspection". (4) This AD does not adopt the "Remarks" section of EASA AD 2024-0250. (i) No Reporting or Return of Parts Requirement Although the material referenced in EASA AD 2024-0250 specifies to submit certain information and to return parts to the manufacturer, this AD does not require those actions. (j) Special Flight Permit 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 responsible Flight Standards 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 responsible Flight Standards Office. (l) Additional Information For more information about this AD, contact Michael Yeshiambel, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (316) 946-4133; email: michael.m.yeshiambel@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 2024-0250, dated December 20, 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 this 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 February 26, 2026. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2026-04919 Filed 3-12-26; 8:45 am]BILLING CODE 4910-13-P

Related safety bulletins advice on the same designs, not orders

2008-07-01SW-08-30R2 · Inadvertent Deployment of Crash Position Indicator (CPI) Beacon
2008-06-30SW-08-30R1 · Inadvertent Deployment of Crash Position Indicator (CPI) Beacon

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 5, 2026. Connections as data: /graph/directive/2026-05-06.json · aircraft systems.