Airworthiness Directive · Amendment 39-23199 · Vertical stabilizer, spar/rib structure
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS 350B3, AS355E, AS 355-F, AS 355-F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, as identified in European Union Aviation Safety Agency AD 2024-0139, dated July 12, 2024 (EASA AD 2024-0139).
The FAA is superseding Airworthiness Directive (AD) 2021-20- 16, which applied to all Airbus Helicopters Model AS355E, AS 355-F, AS 355-F1, AS355F2, AS355N, and AS355NP helicopters and certain Model AS 350B3 helicopters. AD 2021-20-16 required repetitive cleaning and visual and detailed inspections of the right-hand side of the vertical fin spar and vertical fin upper attachments for discrepancies (cracking) with corrective action, if necessary. Since the FAA issued AD 2021-20-16, Airbus Helicopters developed a modification of the upper fin assembly. This AD requires the same actions as AD 2021-20-16 and replacement of the upper fin assembly with a modified upper fin assembly, which constitutes a terminating action for the repetitive inspections. 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, EASA AD 2024-0139.
(1) Where EASA AD 2024-0139 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2024-0139 refers to its effective date or to any of the dates listed in paragraphs (h)(2)(i) through (iv) of this AD, this AD requires using the effective date of this AD.
(i) July 12, 2017 (the effective date of EASA AD 2017-0114, dated June 28, 2017).
(ii) April 23, 2021 (the effective date of EASA AD 2021-0099, dated April 9, 2021).
(iii) April 14, 2023 (the effective date of EASA AD 2023-0075, dated April 7, 2023).
(iv) May 18, 2023 (the effective date of EASA AD 2023-0089, dated May 4, 2023).
(3) Where paragraph (1) of EASA AD 2024-0139 specifies to inform all flight crew and operate the helicopter accordingly, this AD does not require those actions as those actions are already required by existing FAA operating regulations (see 14 CFR 91.505 and 14 CFR 135.21).
(4) Although the material referenced in EASA AD 2024-0139 allows some actions to be performed by a pilot, this AD does not.
(5) Where the material referenced in EASA AD 2024-0139 states “if you are not sure”, this AD requires replacing that text with “to confirm suspected cracks (scratch, line, misalignment, etc.)”.
(6) Where the material referenced in EASA AD 2024-0139 states to do a dye-penetrant inspection (DPI), this AD requires the actions in paragraph (h)(6)(i), (ii), or (iii) of this AD, as applicable:
(i) If the right-hand (RH) side of the spar (a) has previously been inspected by a DPI method, accomplish a DPI of the RH side of the spar (a).
(ii) If the RH side of the spar (a) has not previously been inspected by a DPI, accomplish a fluorescent penetrant inspection (FPI) of the RH-hand side of the spar (a), instead of a DPI.
(iii) If you cannot determine whether the RH side of the spar (a) has previously been inspected by a DPI, clean all surfaces to be inspected and accomplish an FPI of the RH side of the spar (a) instead of a DPI.
Note 1 to paragraph (h)(6)(iii): Work Card 20-02-09-101 (MTC) contains DPI information related to this AD.
Note 2 to paragraph (h)(6)(iii): When entering compliance with the applicable paragraph of the AD into the helicopter maintenance records, explicitly documenting that a dye penetrant inspection was performed improves the accuracy of maintenance records regarding use of dye penetrant inspection dye.
(7) Where the material referenced in EASA AD 2024-0139 refers to damage, for this AD, damage is defined as looseness, corrosion, broken or missing lockwire, loss of protective surface finish, deformation, fracture, crack, or nick.
(8) Where paragraph (8) of EASA AD 2024-0139 states “maintenance flight”, this AD requires replacing that text with “flight to perform an operational check as specified in 14 CFR 91.407”.
(9) Where paragraph (10) of EASA AD 2024-0139 and the material referenced in EASA AD 2024-0139 specify contacting Airbus Helicopters for repair instructions, this AD requires using a repair method approved by the FAA, EASA, or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(10) Where the material referenced in EASA AD 2024-0139 specifies to discard parts, this AD requires removing those parts from service.
(11) Where paragraph (16) of EASA AD 2024-0139 only allows credit for the initial actions in paragraphs (4) through (9) of EASA AD 2024-0139, this AD allows credit for any action in paragraphs (4) through (9) of EASA AD 2024-0139.
(12) This AD does not adopt the “Remarks” section of EASA AD 2024-0139.
Although the material referenced in EASA AD 2024-0139 specifies to submit certain information to the manufacturer, this AD does not require that action.
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.
