Airworthiness directives › 2021-04-04
AD 2021-04-04 Airworthiness Directives; Airbus Helicopters
Models named: SA330J. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(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.
Unsafe condition
This AD was prompted by two reports of cracked metal T/R blade skin. The FAA is issuing this AD to address fatigue cracking of a T/R blade. The unsafe condition, if not addressed, could result in failure of a T/R blade and subsequent loss of control of the helicopter.
Affected ADs
This AD replaces AD 2020-19-02, Amendment 39-21243 (85 FR 59416, September 22, 2020) (AD 2020-19-02).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1