Airworthiness Directive · Amendment 39-23241 · Fuselage structure
Leonardo S.p.A. Helicopters
This AD applies to Leonardo S.p.A. Model AB412 and AB412 EP helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.A. Model AB412 and AB412 EP helicopters. This AD was prompted by a report of a cracked left upper cap angle (cap angle) having a certain part-number. This AD requires repetitively inspecting the cap angle and, depending on the results, performing corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
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 2024-0104, dated May 24, 2024 (EASA AD 2024-0104).
(1) Where EASA AD 2024-0104 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2024-0104 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (1) of EASA AD 2024-0104 specifies “Within 25 FH [flight hours] since last inspection accomplished in accordance with the instructions of Agusta MBT 412-128 (as required by EASA AD 2009-0185), or within 5 FH after the effective date of this AD, whichever occurs later”, this AD requires replacing that text with “Within 5 hours time-in-service after the effective date of this AD”.
(4) Where the material referenced in paragraph (1) of EASA AD 2024-0104 specifies “if no cracks are revealed”, this AD requires replacing that text with “If there are no cracks in the area inspected”.
(5) This AD does not adopt paragraph (2) of EASA AD 2024-0104.
(6) Where paragraph (3) of EASA AD 2024-0104 specifies contacting Leonardo for approved instructions if there is a crack or damage, and where the material referenced in EASA AD 2024-0104 specifies to contact Leonardo Helicopters for further instruction if there is a crack, this AD requires, before further flight, actions done in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Leonardo S.p.A.'s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(7) Where paragraph (3) of EASA AD 2024-0104 specifies “any crack or damage”, this AD requires replacing that text with “any crack or damage (smoking of the fitting attachment and crazing of sealant bead around the fitting as crack indications)”.
(8) This AD does not adopt the “Remarks” section of EASA AD 2024-0104.
Although the material referenced in EASA AD 2024-0104 specifies to submit certain information to the manufacturer, this AD does not require that action.
