Airworthiness Directive · Amendment 39-21889 · Main rotor system
Airbus Helicopters
This AD applies to the Airbus Helicopters helicopters, certificated in any category, identified in paragraphs (c)(1) through (3) of this AD, all serial numbers.
(1) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters.
(2) Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters.
(3) Model SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters; AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters; and Model SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted a report of increased vibration during flight. This AD requires the application of alignment markings on, and repetitive inspections of, the main rotor (MR) pitch rod upper links and, depending on findings, the accomplishment of applicable corrective actions, 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 2021-0048, dated February 16, 2021 (EASA AD 2021-0048).
(1) Where EASA AD 2021-0048 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2021-0048 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where the service information referenced in EASA AD 2021-0048 specifies discarding parts, this AD requires removing those parts from service.
(4) This AD does not mandate compliance with the “Remarks” section of EASA AD 2021-0048.
(5) Where a work card in the service information referenced in EASA AD 2021-0048 specifies returning a part to the manufacturer, this AD does not include that requirement.
(6) For Model AS350 helicopters: For the visual inspection of the pitch rod upper link, where a work card in the service information referenced in EASA AD 2021-0048 specifies to do an inspection of a pitch rod body for any dent, impact, scratch, or corrosion, and any dent, impact, scratch, or corrosion is found, this AD requires replacing the pitch rod before further flight.
(7) For Model AS355 helicopters: For the visual inspection of the pitch rod upper link, where a work card in the service information referenced in EASA AD 2021-0048 specifies to do an inspection of a pitch rod body for any impact, scratch, strike, or corrosion, and any impact, scratch, strike, or corrosion is found, this AD requires replacing the pitch rod before further flight.
(8) For Model SA365 helicopters: For the visual inspection of the pitch rod upper link, where a work card in the service information referenced in EASA AD 2021-0048 specifies to “check bonding and state retaining ring on the pitch rods,” and any discrepancy (e.g., disbonding) is found and no corrective action is specified, before further flight, contact the Manager, General Aviation & Rotorcraft Section, International Validation Branch FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA); for approved corrective actions, and accomplish those actions before further flight. If approved by the DOA, the approval must include the DOA-authorized signature.
(9) For Model SA365 helicopters: For the visual inspection of the pitch horn, if any discrepancy (corrosion, scratch, impact, crack, or debonded retaining ring) is found during the inspection of the pitch horn and there is no corrective action specified in the work card in the service information referenced in EASA AD 2021-0048, before further flight, contact the Manager, General Aviation & Rotorcraft Section, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA DOA; for approved corrective actions, and accomplish those actions before further flight. If approved by the DOA, the approval must include the DOA-authorized signature.
(10) For Model AS365 helicopters: For the visual inspection of the pitch horn, where a work card in the service information referenced in EASA AD 2021-0048 specifies to do a dye penetrant inspection “if in doubt,” this AD requires doing a dye penetrant inspection.
(11) For Model AS350 and EC130 helicopters: Where a work card in the service information referenced in EASA AD 2021-0048 refers to “the pitch change lever,” for this AD, that term is equivalent to “pitch horn.”
Although the service information referenced in EASA AD 2021-0048 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
