Airworthiness Directive · Amendment 39-22598 · Tail rotor gearbox
Airbus Helicopters
This AD applies to Airbus Helicopters Model SA-365C1, SA-365C2, and SA-365N helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365C1, SA-365C2, and SA-365N helicopters. This AD was prompted by reports of damaged control rod dual bearings (dual bearings) that are installed on the tail rotor gearbox (TGB). This AD requires repetitively inspecting the TGB magnetic plug for particles, analyzing any particles collected, taking corrective actions if necessary, and reporting certain information. Finally, this AD allows an affected dual bearing to be installed on a helicopter if certain actions are accomplished, 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.
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 (EASA) AD 2023-0001, dated January 4, 2023 (EASA AD 2023-0001).
(1) Where EASA AD 2023-0001 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2023-0001 refers to the effective dates specified in paragraphs (h)(2)(i) and (ii) of this AD, this AD requires using the effective date of this AD.
(i) March 21, 2022 (the effective date of EASA AD 2022-0038, dated March 7, 2022).
(ii) The effective date of EASA AD 2023-0001.
(3) Where EASA AD 2023-0001 defines Groups, for Group 2, replace the text “SA 365 N helicopters with an affected part installed that has accumulated 500 flight hours (FH) or more since first installation on a helicopter,” with “SA-365N helicopters with an affected part installed that has accumulated 500 or more total hours time-in-service on the affected part or the total hours time-in-service on the affected part cannot be determined.”
(4) Where the service information referenced in EASA AD 2023-0001 permits a pilot to perform a check of the magnetic plug, this AD requires that action be performed by a person authorized under 14 CFR 43.3.
(5) Where Note 1 of EASA AD 2023-0001 specifies, “Helicopters that were under close monitoring on March 21 2022 (the effective date of EASA AD 2022-0038) must continue the close monitoring procedure up to the first inspection accomplished in accordance with the instructions of ASB 1;” for this AD, replace that text with, “Helicopters that are under close monitoring as of the effective date of this AD must continue close monitoring until the first instance of the requirements in paragraph (1) of EASA AD 2023-0001 are completed.”
(6) Where EASA AD 2023-0001 requires replacing the TGB and the service information referenced in EASA AD 2023-0001 specifies replacing the TGB, for this AD, before further flight, remove the TGB from service and replace it with an airworthy part, or repair the TGB in accordance with a method approved by the Manager, Europe Middle East & Africa Section, International Validation Branch, FAA; EASA; or Airbus Helicopters' Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(7) Where paragraphs (5) and (6) of EASA AD 2023-0001 require replacing an affected part, as defined in EASA AD 2023-0001, with a serviceable part, as defined in EASA AD 2023-0001; for this AD, remove the affected part, as defined in EASA AD 2023-0001, from service and replace it with a serviceable part, as defined in EASA AD 2023-0001.
(8) Where paragraph (5) of EASA AD 2023-0001 does not specify a compliance time; for this AD, the compliance time for those actions is before further flight.
(9) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies to do the actions identified in paragraphs (h)(9)(i) and (ii) of this AD, this AD does not include those requirements.
(i) Comply with paragraph 2.D., except this AD requires reporting information, including the information in Appendix 4. of the service information, in accordance with paragraph (h)(18) of this AD.
(ii) Send parts and particles to Airbus Helicopters.
(10) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies replacing the chip detector or conical housing chip detector if there is an anomaly; for this AD, an anomaly may be indicated by the magnetic component of the TGB chip detector or the conical housing chip detector not being magnetized. If there is an anomaly, this AD requires before further flight, removing from service the TGB chip detector or the conical housing chip detector, as applicable to your model helicopter.
(11) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies making sure that the chip detector or conical housing chip detector is in good condition; for this AD, good condition for the chip detector is indicated when there are no signs of wear on the locking systems (including wear on the bayonets and slotted tubes). If there are any signs of wear on the locking systems, this AD requires, before further flight, removing the TGB chip detector from service. Good condition for the conical housing chip detector is when the conical housing chip detector is magnetized. If the conical housing chip detector is not magnetized, this AD requires, before further flight, removing the conical housing chip detector from service.
(12) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies replacing the O-rings if necessary; this AD requires, before further flight, removing any affected O-ring from service and replacing it with an airworthy O-ring.
(13) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies removing an affected TGB, returning it to an approved workshop, including sending all the particles found in the affected part; this AD requires, before further flight, removing an affected TGB from service and replacing it with an airworthy part, or repairing the TGB in accordance with a method approved by the Manager, Europe Middle East & Africa Section, International Validation Branch, FAA; EASA; or Airbus Helicopters' DOA. If approved by the DOA, the approval must include the DOA-authorized signature. You are not required to send the particles found in the TGB to Airbus Helicopters or send an affected TGB to an approved workshop.
(14) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies to use tooling, this AD allows the use of equivalent tooling.
(15) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies discarding certain parts, this AD requires removing those parts from service.
(16) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies performing a metallurgical analysis of particles if there is a doubt concerning the type, size, or classification of any collected particle, this AD requires, before further flight, performing a metallurgical analysis if the type, size, or classification of any collected particle cannot be determined.
(17) Where the service information (including any work card) referenced in EASA AD 2023-0001 specifies if there is any doubt remaining (pertaining to particle classification) after performing a metallurgical analysis, contact Airbus, this AD requires, if the type, size, or classification of any collected particle cannot be determined after performing a metallurgical analysis, before further flight, removing an affected TGB from service and replacing it with an airworthy part, or repairing the TGB in accordance with a method approved by the Manager, Europe Middle East & Africa Section, International Validation Branch, FAA; EASA; or Airbus Helicopters' DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(18) Where the service information referenced in EASA AD 2023-0001 requires reporting inspection results, including Appendix 4.A., to Airbus Helicopters, if any M50 particles are found, this AD requires reporting those inspection results along with a detailed description of any information and findings, and if possible, provide photos, at the applicable time in paragraph (h)(18)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after accomplishing the metallurgical analysis.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
(19) This AD does not adopt the “Remarks” section of EASA AD 2023-0001.
