Airworthiness Directive · Amendment 39-23136 · Main rotor transmission mount
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS 332L2 and EC 225LP helicopters, certificated in any category, as identified in European Union Aviation Safety Agency AD 2024-0142, dated July 17, 2024 (EASA AD 2024-0142).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS 332L2 and EC 225LP helicopters. This AD was prompted by reports of overlengthened and deformed attachment bolts installed on the link of the main gearbox (MGB) suspension bar attachment bracket. This AD requires replacing certain attachment bolts on the MGB suspension bar fittings, inspecting the removed bolts, and reporting the results of this inspection to Airbus Helicopters. 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, EASA AD 2024-0142.
Note 1 to paragraph (g): EASA AD 2024-0142 and Airbus Helicopters material that is referenced in EASA AD 2024-0142 refer to MGB suspension bar attachment “bolts” as “screws.”
(1) Where paragraph (1) of EASA AD 2024-0142 requires compliance within 2,500 flight hours since first installation, this AD requires compliance as specified in paragraphs (h)(1)(i) and (ii) of this AD.
(i) For each affected part that has accumulated 2,500 or more total hours time-in-service (TIS) or if the total hours TIS on the affected part cannot be determined: Before further flight, and thereafter at intervals not to exceed 2,500 total hours TIS on the affected part.
(ii) For each affected part that has accumulated less than 2,500 total hours TIS: Before the affected part accumulates 2,500 total hours TIS, and thereafter at intervals not to exceed 2,500 total hours TIS on the affected part.
(2) Where the material referenced in EASA AD 2024-0142 specifies discarding parts, this AD requires removing those parts from service.
(3) Instead of the reporting requirement in paragraph (3) of EASA AD 2024-0142, this AD requires reporting the results of each inspection to Airbus Helicopters at the compliance time specified in paragraph (h)(3)(i) or (ii) of this AD. The report must include the total hours TIS (if known) on each bolt, the batch number and serial number of the bolt, the length of the bolt, a detailed description of any findings, any previous maintenance, and any photos (if possible).
(i) For an inspection done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(ii) For an inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(4) This AD does not require paragraph (4) of EASA AD 2024-0142.
(5) Where the material referenced in EASA AD 2024-0142 specifies contacting Airbus Helicopters for repair instructions, this AD requires using a repair method approved by the Manager, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(6) This AD does not adopt the “Remarks” section of EASA AD 2024-0142.
