Airworthiness Directive · Amendment 39-21437 · Vertical stabilizer, spar/rib
Airbus Helicopters
Superseded. A later AD replaced this one: AD 2021-20-16. Comply with the one in force.
This AD applies to Airbus Helicopters specified in paragraph (c)(1) and (2) of this AD, certificated in any category.
(1) Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, all serial numbers.
(2) Model AS350B3 helicopters, all serial numbers except those that have embodied Modification 07.3148 in production, or Eurocopter AS350 Service Bulletin 55.00.14 (any revision) in service.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, AS355N and AS355NP helicopters; and certain Model AS350B3 helicopters. This AD was prompted by a report that, during an unscheduled post-flight inspection of the tail cone area, a crack was found in the spar of the upper part of the vertical fin and fractures were found in the two front attachment screws. This AD requires repetitive visual inspections of the right-hand side of the vertical fin spar for discrepancies (cracking), and corrective action if necessary, 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, EASA AD 2020-0186, dated August 20, 2020 (EASA AD 2020-0186).
(1) Where EASA AD 2020-0186 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2020-0186 does not apply to this AD.
(3) The actions specified in paragraph (2) of EASA AD 2020-0186 are not required by this AD.
(4) Where paragraph (3) of EASA AD 2020-0186 specifies to contact the manufacturer for approved repair instructions, for this AD, if any cracking is detected during any inspection, repair before further flight using a method approved by the Manager, International Validation Branch, FAA. For a repair method to be approved by the Manager, International Validation Branch, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
(5) Where EASA AD 2020-0186 refers to flight hours (FH), this AD requires using hours time-in-service.
(6) Where the service information referred to in EASA AD 2020-0186 specifies to perform a visual inspection and “if in doubt” remove the rear and the tail rotor gear box (TGB) fairings to perform a detailed inspection and “carry out” a dye-penetrant inspection, those actions are required by this AD if any crack indication (e.g., paint chips, dents, or swelling) is found during any inspection done without removing the rear and the TGB fairings.
(7) Although the service information referenced in EASA AD 2020-0186 specifies to scrap certain parts, this AD requires removing those parts from service instead.
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.
