Airworthiness Directive · Amendment 39-21425 · Tail rotor blades
Airbus Helicopters
This AD applies to Airbus Helicopters Model SA330J helicopters, certificated in any category, with a tail rotor (T/R) blade part number (P/N) 330A12-0005-(all dash numbers) (without a de-icing system) or 330A12-0006-(all dash numbers) (with a de-icing system), installed.
The FAA is superseding Airworthiness Directive (AD) 2020-19- 02, which applied to certain Airbus Helicopters (previously Eurocopter France) Model SA330J helicopters. AD 2020-19-02 required repetitively inspecting affected tail rotor (T/R) blades and depending on the inspection results, repairing or replacing the T/R blade. AD 2020-19-02 also prohibited installing an affected T/R blade unless it passed the inspections. This AD retains the requirements of AD 2020-19-02 and also clarifies the applicability, clarifies the affected T/R blades in the required actions, reduces a compliance time, and corrects the prohibition requirement. This AD was prompted by the determination that these corrections are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For T/R blade P/N 330A12-0006-(all dash numbers) (with a de-icing system), within 15 hours time-in-service (TIS) after the effective date of this AD or within 15 hours TIS after last inspecting the T/R blade as required by paragraph (f)(1) of AD 2020-19-02, whichever occurs first, and thereafter at intervals not to exceed 15 hours TIS; and for T/R blade P/N 330A12-0005-(all dash numbers) (without a de-icing system), within 30 hours TIS after the effective date of this AD, or within 30 hours TIS after last inspecting the T/R blade as required by paragraph (f)(1) of AD 2020-19-02, whichever occurs first, and thereafter at intervals not to exceed 30 hours TIS:
(i) Inspect each T/R blade for debonding by following the visual and in-depth inspection procedures in the Accomplishment Instructions, paragraph 3.B.2., of Airbus Helicopters Emergency Alert Service Bulletin No. 05.101, Revision 0, dated March 21, 2016 (EASB 05.101). If there is debonding within allowable limits, before further flight, repair or replace the T/R blade. If there is debonding that exceeds allowable limits, before further flight, replace the T/R blade.
(ii) Eddy current inspect each T/R blade for a crack by following the Accomplishment Instructions, paragraph 3.B.3.a. of EASB 05.101, then either paragraph 3.B.3.b.1. or 3.B.3.b.2. of EASB 05.101 depending on your crack detector, and paragraph 3.B.3.c. of EASB 05.101 except the “if there are no cracks” and “if there are one or several cracks” steps. Instead of the “if there are no cracks” and “if there are one or several cracks” steps, if there is a crack, before further flight, replace the T/R blade.
(2) As of the effective date of this AD, do not install a T/R blade identified in paragraph (c) of this AD on any helicopter unless the actions of paragraphs (g)(1)(i) and (ii) of this AD have been accomplished.
