2020-19-02: Tail Rotor Blades

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by: 0 a. Removing Airworthiness Directive (AD) 2000-22-19, Amendment 39-11967 (65 FR 68071, November 14, 2000); and 0 b. Adding the following new AD: \n\n2020-19-02 Airbus Helicopters: Amendment 39-21243; Docket No. FAA- 2020-0793; Project Identifier MCAI-2020-00976-R. \n\n(a) Applicability \n\n\n\tThis AD applies to Airbus Helicopters (previously Eurocopter France) Model SA330J helicopters, certificated in any category, with a tail rotor (T/R) blade part number 330A12-0005-(all dash numbers) or 330A12-0006-(all dash numbers) installed. \n\n(b) Unsafe Condition \n\n\n\tThis AD defines the unsafe condition as fatigue cracking of a T/ R blade. This condition could result in failure of a T/R blade and subsequent loss of control of the helicopter. \n\n(c) Affected ADs \n\n\n\tThis AD replaces AD 2000-22-19, Amendment 39-11967 (65 FR 68071, November 14, 2000) (''AD 2000-22-19''). \n\n(d) Effective Date \n\n\n\tThis AD becomes effective October 7, 2020. \n\n(e) Compliance \n\n\n\tYou are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. \n\n(f) Required Actions \n\n\n\t(1) Within 30 hours time-in-service (TIS) after the effective date of this AD or within 30 hours TIS after last inspecting the T/R blades as required by paragraph (a) of AD 2000-22-19, whichever occurs first, and thereafter at intervals not to exceed 15 hours TIS for T/R blades with deicing systems installed or 30 hours TIS for T/ R blades without deicing systems installed: \n\t(i) Inspect each T/R blade for debonding by following the visualand 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. \n\t(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. \n\t(2) As of the effective date of this AD, do not install a T/R blade identified in paragraph (a) of this AD on any helicopter unless the actions of paragraph (f)(1) of this AD have been accomplished. \n\n(g) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Rotorcraft Standards Branch, FAA, may approve AMOCs for this \n\n((Page 59419)) \n\nAD. Send your proposal to: Matt Fuller, AD Program Manager, Continued Operational Safety Branch, Airworthiness Products Section, General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email [email protected]. \n\t(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. \n\n(h) Additional Information \n\n\n\tThe subject of this AD is addressed in European Aviation Safety Agency (EASA) (now European Union Aviation Safety Agency) No. 2016- 0059-E, dated March 22, 2016. You may view the EASA AD on the internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-2020-0793. \n\n(i) Subject \n\n\n\tJoint Aircraft Service Component (JASC) Code: 6410, Tail Rotor Blades. \n\n(j) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Airbus Helicopters Emergency Alert Service Bulletin No. 05.101, Revision 0, dated March 21, 2016. \n\t(ii) (Reserved) \n\t(3) For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 972-641-0000 or800-232-0323; fax 972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. \n\t(4) You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 817-222-5110. \n\t(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on August 31, 2020. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-20751 Filed 9-21-20; 8:45 am) BILLING CODE P