Airworthiness Directive · Amendment 39-22689 · Tail rotor blades
Airbus Helicopters Deutschland GmbH (AHD) Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T2, EC135T3, and EC635T2+ helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T2, EC135T3, and EC635T2+ helicopters. This AD was prompted by a report of a separated tail rotor (T/R) blade due to a crack which was caused by intergranular corrosion. This AD requires repetitively inspecting certain part- numbered T/R blades for a crack and, depending on the results, removing any cracked T/R blade from service. This AD also prohibits installing certain T/R blades on any helicopter unless certain requirements are met. These actions are specified in a European Union Aviation Safety Agency (EASA) emergency AD, which is incorporated by reference. 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 2024-0028-E, dated January 25, 2024 (EASA AD 2024-0028-E).
(1) Where EASA AD 2024-0028-E states “flight hours (FH)” and “FH;” for this AD, replace that text with “hours time-in-service (TIS).”
(2) Where EASA AD 2024-0028-E refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0028-E states “Before an affected part exceeds 685 FH since first installation on a helicopter, or within 10 FH after the effective date of this AD, whichever occurs later;” for this AD, replace that text with “Before an affected part, as defined in EASA AD 2024-0028-E, accumulates 685 total hours TIS, or within 10 hours TIS after the effective date of this AD, whichever occurs later, and if the total hours TIS accumulated on an affected part, as defined in EASA AD 2024-0028-E, is unknown, before further flight after the effective date of this AD.”
(4) Where paragraph (2) of EASA AD 2024-0028-E states “following the installation of an affected part, having accumulated 685 FH or more since first installation on a helicopter, inspect that affected part in accordance with the instructions of the ASB within the interval as defined in Table 2 of this AD, as applicable. Thereafter, that affected part must be inspected as required by paragraph (1) of this AD;” for this AD, replace that text with “do not install an affected part, as defined in EASA AD 2024-0028-E, unless that affected part has been inspected in accordance with the instructions of the ASB as specified in paragraph (h)(4)(i) or (ii) of this AD, as applicable.
(i) For an affected part that has accumulated 685 or more total hours TIS since first installation on any helicopter, before further flight after the effective date of this AD, inspect that affected part unless already done within the interval as defined in Table 2 of EASA AD 2024-0028-E, as applicable, and thereafter inspect that affected part within the interval as defined in Table 1 of EASA AD 2024-0028-E, as applicable.
(ii) For an affected part that has accumulated an unknown number of total hours TIS, before further flight after the effective date of this AD, inspect that affected part and thereafter inspect that affected part within the interval as defined in Table 1 of EASA AD 2024-0028-E, as applicable.”
(5) Instead of complying with paragraph (3) of EASA AD 2024-0028-E, for this AD, comply with the following: “As a result of an inspection required by paragraphs (1) or (2) of EASA AD 2024-0028-E, if there is a crack, before further flight, remove the affected part, as defined in EASA AD 2024-0028-E, from service and replace it with a serviceable part, as defined in EASA AD 2024-0028-E, by following the instructions of the ASB.”
(6) Where the service information referenced in EASA AD 2024-0028-E specifies “Examine the TRB (1) within the AFFECTED AREA (2) for cracks with one of the following methods;” for this AD, replace that text with “Examine the TRB (1) within the AFFECTED AREA (2) for any crack by following Method C or Method D.”
Note 1 to paragraph (h)(6): This note applies to paragraphs (h)(6) and (7) of this AD. Advisory Circular 65-31B contains examples of FAA-acceptable Level II and Level III qualification standards criteria for inspection personnel doing nondestructive test inspections.
(7) Where the service information referenced in EASA AD 2024-0028-E specifies performing an eddy current inspection or a fluorescent penetrant inspection (FPI), this AD requires an eddy current inspection or FPI performed by a Level II or Level III inspector certified in the FAA-acceptable standards for nondestructive inspection personnel.
(8) This AD does not adopt the “Remarks” section of EASA AD 2024-0028-E.
Although the service information referenced in EASA AD 2024-0028-E specifies to submit certain information and send removed parts to the manufacturer, this AD does not include those actions.
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.
