Airworthiness Directive · Amendment 39-23275 · Horizontal stabilizer structure
Airbus Helicopters
This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD was prompted by a report of the loss of the horizontal stabilizer during flight. This AD requires initially inspecting the removed horizontal stabilizer, inspecting the tightening torque, and measuring the attachment holes, bracket, and tube assembly and if necessary performing corrective actions. This AD also requires repetitively inspecting the horizontal stabilizer while not removed, and if necessary performing corrective actions. This AD also prohibits installing an affected horizontal stabilizer unless certain requirements are met. 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) Emergency AD 2026-0015-E, dated January 22, 2026 (EASA Emergency AD 2026-0015-E).
(1) Where EASA Emergency AD 2026-0015-E refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA Emergency AD 2026-0015-E requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where the material referenced in EASA Emergency AD 2026-0015-E specifies “check”, this AD requires replacing that text with “inspection”.
(4) Where paragraph (3) of EASA Emergency AD 2026-0015-E and the material referenced in EASA Emergency AD 2026-0015-E states “contact AH [Airbus Helicopters] for approved repair instructions and within the compliance time specified therein”, this AD requires replacing that text with “repair any discrepancy before further flight, using a 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.
(5) Where the material referenced in EASA Emergency AD 2026-0015-E specifies “cracks”, this AD requires replacing that text with “cracks, nicks or corrosion”.
(6) This AD does not adopt the “Remarks” section of EASA Emergency AD 2026-0015-E.
Although the material referenced in EASA Emergency AD 2026-0015-E specifies to submit certain information to the manufacturer, this AD does not include that requirement.
