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2024-10-10: Tail Rotor Control System

FAA order 2024-10-10 is an airworthiness directive in force since July 23, 2024. The FAA's subject line: Tail Rotor Control System. It names Airbus Helicopters AS-365: about 20 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
SA-365N, SA-365N1, AS-365N2, AS-365N3
On this site
Airbus Helicopters AS-365 20 registered

Dates and paperwork

In force since
July 23, 2024
Published
June 18, 2024 (signed May 15, 2024)
Docket
FAA-2024-0038
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 SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted by a report of an obstructed tail rotor (TR) pedal control that was blocked during flight. This AD requires a one-time inspection for proper positioning of the TR actuator harness and cable ties installation and, depending on the results, accomplishing corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. 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 (4,471 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: 2024-10-10 Airbus Helicopters: Amendment 39-22756; Docket No. FAA-2024-0038; Project Identifier MCAI-2023-00645-R. (a) Effective Date This airworthiness directive (AD) is effective July 23, 2024. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code: 6720, Tail Rotor Control System. (e) Unsafe Condition This AD was prompted by a report of an obstructed tail rotor (TR) pedal control that was blocked during flight. The FAA is issuing this AD to detect and address interference of the tail rotor pedal control. The unsafe condition, if not addressed, could result in loss of yaw 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 (EASA) AD 2023-0090, dated May 4, 2023 (EASA AD 2023-0090). (h) Exceptions to EASA AD 2023-0090 (1) Where paragraph (1) of EASA AD 2023-0090 requires compliance within 165 flight hours, this AD requires accomplishing paragraph (1) of EASA AD 2023-0090 within 100 hours time-in-service. (2) Where EASA AD 2023-0090 refers to its effective date, this AD requires using the effective date of this AD. (3) Where the service information referenced in EASA AD 2023-0090 specifies discarding parts, this AD requires removing those parts from service. (4) This AD does not adopt the "Remarks" section of EASA AD 2023-0090. (i) No Reporting Requirement Although the service information referenced in EASA AD 2023-0090 specifies to submit certain information to the manufacturer, this AD does not include that requirement. (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. Information may be emailed 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) Related Information For more information about this AD, contact Dan McCully, Program Manager, International Validation Branch, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; phone: (404) 474-5548; email: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) European Union Aviation Safety Agency (EASA) AD 2023-0090, dated May 4, 2023. (ii) [Reserved] (3) For EASA AD 2023-0090, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email [email protected]; internet easa.europa.eu. You may find the EASA material on the EASA website at ad.easa.europa.eu. (4) You may view this service information 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 [email protected]. Issued on May 15, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-13348 Filed 6-17-24; 8:45 am]BILLING CODE 4910-13-P

Related safety bulletins advice on the same designs, not orders

2014-12-30SW-15-07 · Rotor Drive-Tail Rotor Drive Flange Shur-Lok Nut Inspection
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
2004-10-07SW-05-01 ·

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 November 6, 2026. Connections as data: /graph/directive/2024-10-10.json · aircraft systems.