82 FR 43715 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 180 (September 19, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 180 (September 19, 2017)
| Page Range | 43715-43720 | |
| FR Document | 2017-19760 |
[Federal Register Volume 82, Number 180 (Tuesday, September 19, 2017)] [Proposed Rules] [Pages 43715-43720] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-19760] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0812; Product Identifier 2016-NM-198-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage structures are subject to widespread fatigue damage (WFD). This proposed AD would require reinforcement modifications of various structural parts of the fuselage, and related investigative and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0812; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. [[Page 43716]] FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227- 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0812; Product Identifier 2016-NM-198-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0207, dated October 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. The MCAI states: An analysis conducted on A330 aeroplanes identified structural areas which are susceptible to widespread fatigue damage (WFD). This condition, if not corrected, could lead to crack initiation and undetected propagation, leading to reduced structural integrity of the aeroplane, possibly resulting in rapid depressurisation and consequent injury to occupants. To address this potential unsafe condition, Airbus developed a number of modifications (Mod) and published associated Service Bulletins (SB) for embodiment in service, to provide instructions to reinforce the various structural parts of the fuselage. For the reasons described above, this [EASA] AD requires accomplishment of these modifications and reinforcements [and related investigative and corrective actions]. Related investigative actions include a rotating probe hole inspection for cracking. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0812. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. This service information describes procedures for modifications and reinforcement of various structural parts of the fuselage. These documents are distinct since they apply to different airplane models in different configurations. Airbus Service Bulletin A330-53-3144, Revision 01, dated July 25, 2006. Airbus Service Bulletin A330-53-3144, Revision 04, dated November 23, 2015. Airbus Service Bulletin A330-53-3222, Revision 01, dated March 31, 2016. Airbus Service Bulletin A330-53-3223, Revision 00, dated January 19, 2015. Airbus Service Bulletin A330-53-3224, Revision 01, excluding Appendix 01 and including Appendix 02, dated April 14, 2016. Airbus Service Bulletin A330-53-3225, Revision 02, excluding Appendix 01 and including Appendix 02, dated June 8, 2016. Airbus Service Bulletin A330-53-3226, Revision 02, excluding Appendix 01 and including Appendices 02, 03, and 04, dated October 27, 2016. Airbus Service Bulletin A330-53-3236, Revision 02, excluding Appendix 01 and including Appendices 02 and 03, dated March 23, 2016. Airbus Service Bulletin A330-53-3237, Revision 01, dated February 8, 2016. Airbus Service Bulletin A330-53-3238, Revision 01, dated October 19, 2015. Airbus Service Bulletin A330-53-3239, Revision 01, dated July 4, 2016. Airbus Service Bulletin A330-53-3244, Revision 01, dated August 2, 2016. Airbus Service Bulletin A330-53-3248, Revision 02, dated July 27, 2016. Airbus Service Bulletin A330-53-3251, Revision 01, dated June 23, 2016. Airbus Service Bulletin A330-53-3252, Revision 01, dated June 30, 2016. Airbus Service Bulletin A330-53-3257, Revision 01, dated March 15, 2016. Airbus Service Bulletin A330-53-3258, Revision 00, dated April 20, 2015. Airbus Service Bulletin A330-53-3259, Revision 02, dated July 18, 2016. Airbus Service Bulletin A330-53-3263, Revision 01, excluding Appendix 01 and including Appendix 02, dated December 1, 2015. [[Page 43717]] Airbus Service Bulletin A330-53-3273, Revision 00, dated September 28, 2016. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Explanation of Compliance Time The compliance time for the reinforcement modifications specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is addressed before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 99 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Reinforcement modifications........ Up to 317 work-hours x Up to $41,050................ Up to $67,995................ Up to $6,731,505. $85 per hour = $26,945. -------------------------------------------------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2017-0812; Product Identifier 2016-NM-198-AD. (a) Comments Due Date We must receive comments by November 3, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A330-201, -202, -203, -223, and -243 airplanes. (2) Model A330-223F and -243F airplanes. (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage structures are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent crack initiation and undetected propagation in the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modifications Except as specified in paragraphs (i)(1) and (i)(2) of this AD, before exceeding the applicable total flight cycles or total flight [[Page 43718]] hours structural modification point (SMP) for each action, as specified in table 1 to paragraph (g) of this AD: Modify the airplane, including all applicable related investigative actions and corrective actions, based on the weight variant (WV) group designations specified in table 2 to paragraph (h) of this AD, and as specified in table 1 to paragraph (g) of this AD, except as specified in paragraph (i)(3) of this AD. Do all applicable related investigative actions and corrective actions before further flight. For the purposes of this AD, the short range (SR) and long range (LR) SMPs specified in table 1 to paragraph (g) of this AD must be used. Table 1 to Paragraph (g) of This AD--Modification ---------------------------------------------------------------------------------------------------------------- Description of action Applicability SMP SR SMP LR ---------------------------------------------------------------------------------------------------------------- Improve circumferential joints at Group 32A............. 32,500 total flight cycles 26,600 flight cycles. frames (FR) 45 and 54 of the Group 33A............. 23,700 total flight cycles 20,400 total flight fuselage, in accordance with the ...................... or 71,300 total flight cycles Accomplishment Instructions of Group 33B............. hours, whichever occurs 23,700 total flight Airbus Service Bulletin first. cycles. A330[dash]53[dash]3144, Revision 04, 27,600 total flight cycles dated November 23, 2015 (``A330-53- or 83,000 total flight 3144, R4''). hours, whichever occurs first. Group 33C............. 23,300 total flight cycles 20,000 total flight or 70,000 total flight cycles. hours, whichever occurs first. Group 33D............. 22,700 total flight cycles 19,500 total flight or 68,300 flight hours, cycles. whichever occurs first. Improve splicing area from FR48 to Groups 32A and 32E.... 23,100 total flight cycles 20,900 total flight FR53-2 between stringers (STRG) 23 ...................... or 80,900 total flight cycles. and 26 left hand (LH)/right hand Group 33A............. hours, whichever occurs 21,800 total flight (RH) of the fuselage, in accordance ...................... first. cycles. with the Accomplishment Instructions Group 33B............. 24,200 total flight cycles 17,700 total flight of Airbus Service Bulletin A330-53- or 79,100 total flight cycles. 3222, Revision 01, dated March 31, hours, whichever occurs 2016 (``A330-53-3222, R1'') (Airbus first. Modification 204315). 19,700 total flight cycles or 64,300 total flight hours, whichever occurs first. Groups 33C, 33D, and 21,600 total flight cycles 19,400 total flight 33E. or 70,600 flight hours, cycles. whichever occurs first. A330-200F............. 27,400 total flight cycles 27,400 total flight or 82,200 total flight cycles or 82,200 hours, whichever occurs total flight hours, first. whichever occurs first. Reinforce couplings in area FR20-- Groups 32A, 32E, 33B, 30,900 total flight cycles 30,900 total flight FR25/STRG20 RH--STRG22 RH of the 33C, 33D and 33E. cycles. forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330[dash]53[dash]3223, Revision 00, dated January 19, 2015 (``A330[dash]53[dash]3223, R0''). Reinforce circumferential joint at Group 33A............. 29,700 total flight cycles 25,500 total flight FR72 of the fuselage, in accordance or 89,600 total flight cycles. with the Accomplishment Instructions hours, whichever occurs of Airbus Service Bulletin first. A330[dash]53-3224, Revision 01, excluding Appendix 01 and including Appendix 02, dated April 14, 2016 (``A330[dash]53-3224, R1''). Reinforce circumferential joint at Group 33A............. 16,300 total flight cycles 13,300 total flight FR58 of the fuselage, in accordance or 49,300 total flight cycles or 90,700 with the Accomplishment Instructions hours, whichever occurs total flight hours, of Airbus Service Bulletin first. whichever occurs A330[dash]53-3225, Revision 02, first. excluding Appendix 01 and including Appendix 02, dated June 8, 2016 (``A330[dash]53-3225, R2''). Reinforce circumferential joint Group 32A............. .......................... 21,000 total flight between FR53.6--FR53.7 for emergency ...................... 26,100 total flight cycles cycles. door TYPE 1 area of the center Groups 33C, 33D and or 91,600 total flight 12,600 total flight fuselage, in accordance with the 33E. hours, whichever occurs cycles or 84,800 Accomplishment Instructions of first. total flight hours, Airbus Service Bulletin A330[dash]53- 15,600 total flight cycles whichever occurs 3226, Revision 02, excluding or 46,800 total flight first. Appendix 01 and including Appendices hours, whichever occurs 02, 03, and 04, dated October 27, first. 2016 (``A330-53-3226, R2''); or Airbus Service Bulletin A330[dash]53[dash]3273, Revision 00, dated September 28, 2016 (``A330[dash]53[dash]3273, R0''). Group 33A............. 34,400 total flight cycles 27,800 total flight .......................... cycles. Group 33B............. 19,900 total flight cycles 16,100 total flight or 59,800 total flight cycles. hours, whichever occurs first. Group 32E............. 19,900 total flight cycles 16,200 total flight or 69,900 total flight cycles. hours, whichever occurs first. Reinforce circumferential joint Group 33A............. 30,900 total flight cycles 25,400 total flight between FR53.6--FR53.7 LH/RH of or 93,200 total flight cycles. option emergency door TYPE A area of hours, whichever occurs the center fuselage, in accordance first. with the Accomplishment Instructions of Airbus Service Bulletin A330-53- 3236, Revision 02, excluding Appendix 01 and including Appendices 02 and 03, dated March 23, 2016 (``A330-53-3236, R2''). Improve fatigue life of internal Groups 32A, 33A, 33B, 27,300 total flight cycles 27,300 total flight center fuselage structure on 33C, and 33D. .......................... cycles. longitudinal beams above the center Group 32A............. 38,400 total flight cycles 38,400 total flight wing box, in accordance with the cycles. Accomplishment Instructions of Airbus Service Bulletin A330[dash]53- 3237, Revision 01, dated February 8, 2016 (``A330[dash]53-3237, R1''). Update lower/lateral frame splicing Group 33A............. 28,800 total flight cycles 28,800 total flight with corner fitting between FR53.3 Group 33B............. 36,200 total flight cycles cycles. and FR54 of the center fuselage, in Groups 33C and 33D.... 34,700 total flight cycles 36,200 total flight accordance with the Accomplishment cycles. Instructions of Airbus Service 34,700 total flight Bulletin A330[dash]53-3238, Revision cycles. 01, dated October 19, 2015 (``A330[dash]53-3238, R1''). Reinforce longitudinal butt joints in A330-200F............. 15,100 total flight cycles 15,100 total flight section 13, in accordance with the cycles. Accomplishment Instructions of Airbus Service Bulletin A330[dash]53- 3239, Revision 01, dated July 4, 2016 (``A330[dash]53-3239, R1''). Reinforce circumferential joint at A330-200F............. 15,500 total flight cycles 15,500 total flight FR31 between STRG 7LH and STRG 8RH or 46,500 total flight cycles or 46,500 of forward fuselage, in accordance hours, whichever occurs total flight hours, with the Accomplishment Instructions first. whichever occurs of Airbus Service Bulletin first. A330[dash]53-3244, Revision 01, dated August 2, 2016 (``A330[dash]53- 3244, R1''). Reinforce frame couplings in section Group 33A............. 32,000 total flight cycles 32,000 total flight 13, 14, and 14A of the forward cycles. fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330[dash]53- 3248, Revision 02, dated July 27, 2016 (``A330[dash]53-3248, R2''). [[Page 43719]] Reinforce circumferential joint/ Group 33C 38,200 total flight cycles 32,000 total flight stringer coupling in area of FR37.1 Pre[dash]Modification .......................... cycles. of the forward fuselage, in 46636. .......................... ..................... accordance with the Accomplishment Groups 33C and 33D 30,600 total flight cycles ..................... Instructions of Airbus Service Post-Modification or 99,500 total flight 27,600 total flight Bulletin A330[dash]53-3251, Revision 46636. hours, whichever occurs cycles. 01, dated June 23, 2016 first. (``A330[dash]53-3251, R1''). Group 33E............. 32,200 total flight cycles 29,100 total flight cycles. Reinforce circumferential joint/ Groups 33C and 33D, 30,600 total flight cycles 27,600 total flight stringer coupling in area of FR37.1 Post-Modification or 99,500 total flight cycles. of the forward fuselage, in 46636. hours, whichever occurs ..................... accordance with the Accomplishment ...................... first. 29,100 total flight Instructions of Airbus Service Group 33E............. 32,200 total flight cycles cycles. Bulletin A330[dash]53-3252, Revision 01, dated June 30, 2016 (``A330[dash]53-3252, R1''). Reinforce frame couplings in rear Groups 33A and 33B.... 24,000 total flight cycles 24,000 total flight area of the fuselage, in accordance cycles. with the Accomplishment Instructions of Airbus Service Bulletin A330-53- 3257, Revision 01, dated March 15, 2016 (``A330[dash]53-3257, R1''). Reinforce corner fittings in section Group 32A............. 31,800 total flight cycles 31,800 total flight 13 of the forward fuselage, in cycles. accordance with the Accomplishment Instructions of Airbus Service Bulletin A330[dash]53[dash]3258, Revision 00, dated April 20, 2015 (``A330[dash]53[dash]3258, R0''). Reinforce circumferential joint at Group 32E............. 18,500 total flight cycles 14,600 total flight FR58 (aeroplane Post-Modification or 65,400 total flight cycles or 95,700 40556/D18255) of the rear fuselage, hours, whichever occurs total flight hours, in accordance with the first. whichever occurs Accomplishment Instructions of first. Airbus Service Bulletin A330[dash]53- 3259, Revision 02, dated July 18, 2016 (``A330[dash]53-3259, R2''). Group 33A............. 34,800 total flight cycles 28,400 total flight cycles. Group 33B............. 33,500 total flight cycles 27,400 total flight cycles. Reinforce frames in rear area of the Groups 32A, 32E, 33B, 23,300 total flight cycles 20,800 total flight fuselage, in accordance with the 33C, 33D, and 33E. or 69,700 total flight cycles. Accomplishment Instructions of hours, whichever occurs Airbus Service Bulletin A330[dash]53- first. 3263, Revision 01, excluding Appendix 01 and including Appendix 02, dated December 1, 2015 (``A330[dash]53-3263, R1''). ---------------------------------------------------------------------------------------------------------------- (h) Weight Variant (WV) Group Designations For the purposes of this AD, table 2 to paragraph (h) of this AD identifies the WV group designations specified in the ``Applicability'' column of Table 1 to paragraph (g) and Table 3 to paragraph (i) of this AD: Table 2 to Paragraph (h) of This AD--WV Group Designations ------------------------------------------------------------------------ Airplane model WV group Weight variants ------------------------------------------------------------------------ A330-200...................... Group 32A........ 020, 021, 022, 023, 024, 025, 026, and 027. Group 32E........ 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 061, 062, 063, 064, 080, 081, 082, and 083. A330-200F..................... N/A.............. 000, 001, and 002. A330-300...................... Group 33A........ 000, 001, 002, 003, and 004. Group 33B........ 010, 011, 012, 013, and 014. Group 33C........ 020, 024, 025, 026, and 027. Group 33D........ 022. Group 33E........ 030, 031, 032, 033, 034, 035, 039, 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 080, 081, 082, and 083. ------------------------------------------------------------------------ (i) Exceptions to Service Information and Compliance Times (1) Do not do the applicable modifications required by paragraph (g) of this AD before the applicable times specified in table 3 to paragraph (i) of this AD. Where two limits (total flight cycles and total flight hours) within the same sub-row of the table are specified, both times must be exceeded before accomplishment of the modification. For airplanes already modified before the threshold specified in table 3 to paragraph (i) of this AD is reached, within 6 months after the effective date of this AD, obtain instructions for additional maintenance tasks (modifications/inspections) from and approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), and accomplish those tasks within the compliance time specified therein. (2) For airplanes that have already reached or exceeded the SMP threshold(s), as specified for each action in table 1 to paragraph (g) of this AD, as applicable, accomplishment of the modification can be deferred for a period not exceeding 12 months after the effective of this AD; except for accomplishment of the modifications specified in A330-53-3237, R1, which can be deferred for a period not exceeding 15 months after the effective date of this AD. (3) If any service information specified in paragraph (g) or (j) of this AD specifies to contact Airbus for appropriate action: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (l)(2) of this AD. [[Page 43720]] Table 3 to Paragraph (i) of This AD --Compliance Time Lower Threshold ------------------------------------------------------------------------ Airbus Service Bulletin Modification not (modification) Applicability before: ------------------------------------------------------------------------ A330-53-3222, R1.............. Groups 32A, 32E, 10,000 total flight 33A, 33C, 33D cycles. and 33E. Group 33B........ 12,000 total flight cycles. A330-200F........ 8,900 total flight cycles and 26,600 total flight hours. A330-53-3224, R1.............. Group 33A........ 10,000 total flight cycles and 6,600 total flight hours. A330-53-3225, R2.............. Group 33A........ 3,900 total flight cycles and 10,200 total flight hours. A330-53-3237, R1.............. Groups 32A, 33A, 3,900 total flight 33B, 33C, and cycles. 33D. A330-53-3238, R1.............. Groups 32A, 33A, 9,000 total flight 33B, 33C, and cycles. 33D. ------------------------------------------------------------------------ (j) Additional Work for Certain Airplanes For airplanes that have been modified before the effective date of this AD, in accordance with Airbus Service Bulletin A330-53-3144, Revision 00, dated August 23, 2005; Airbus Service Bulletin A330-53- 3222, Revision 00, dated January 15, 2015; or Airbus Service Bulletin A330-53-3237, Revision 00, dated January 15, 2015, as applicable: Within 12 months after the effective date of this AD, accomplish the additional work specified in the Accomplishment Instructions of Airbus Service Bulletin A330-53-3144, Revision 01, dated July 25, 2006; A330-53-3222, R1; and A330-53-3237, R1; as applicable. (k) Credit for Previous Actions This paragraph provides credit for applicable actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (k)(1) through (k)(19) of this AD. (1) Airbus Service Bulletin A330-53-3144, Revision 01, dated July 25, 2006. (2) Airbus Service Bulletin A330-53-3144, Revision 02, dated April 20, 2011. (3) Airbus Service Bulletin A330-53-3144, Revision 03, dated January 15, 2015. (4) Airbus Service Bulletin A330-53-3224, Revision 00, dated January 16, 2015. (5) Airbus Service Bulletin A330-53-3225, Revision 00, dated January 16, 2015. (6) Airbus Service Bulletin A330-53-3225, Revision 01, dated February 26, 2016. (7) Airbus Service Bulletin A330-53-3226, Revision 00, dated January 15, 2015. (8) Airbus Service Bulletin A330-53-3226, Revision 01, dated March 3, 2016. (9) Airbus Service Bulletin A330-53-3236, Revision 00, dated January 15, 2015. (10) Airbus Service Bulletin A330-53-3236, Revision 01, dated August 24, 2015. (11) Airbus Service Bulletin A330-53-3238, Revision 00, dated January 15, 2015. (12) Airbus Service Bulletin A330-53-3239, Revision 00, dated April 20, 2015. (13) Airbus Service Bulletin A330-53-3244, Revision 00, dated April 7, 2015. (14) Airbus Service Bulletin A330-53-3251, Revision 00, dated May 13, 2015. (15) Airbus Service Bulletin A330-53-3252, Revision 00, dated April 10, 2015. (16) Airbus Service Bulletin A330-53-3257, Revision 00, dated July 21, 2015. (17) Airbus Service Bulletin A330-53-3259, Revision 00, dated May 11, 2015. (18) Airbus Service Bulletin A330-53-3259, Revision 01, dated February 26, 2016. (19) Airbus Service Bulletin A330-53-3263, Revision 00, dated July 21, 2015. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0207, dated October 19, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0812. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on September 7, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-19760 Filed 9-18-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43715
persons were invited to attend the assessment rate actions issued in past SUMMARY: We propose to adopt a new
meeting and participate in Committee years. airworthiness directive (AD) for all
deliberations on all issues. Like all Airbus Model A330–200 series
List of Subjects in 7 CFR Part 959
Committee meetings, the June 7, 2017, airplanes, Model A330–200 Freighter
meeting was a public meeting, and all Marketing agreements, Onions, series airplanes, and Model A330–300
entities, both large and small, were able Reporting and recordkeeping series airplanes. This proposed AD was
to express views on this issue. Finally, requirements. prompted by an evaluation by the
interested persons are invited to submit For the reasons set forth in the design approval holder (DAH)
comments on this proposed rule, preamble, 7 CFR part 959 is proposed to indicating that certain fuselage
including the regulatory and be amended as follows: structures are subject to widespread
informational impacts of this action on fatigue damage (WFD). This proposed
small businesses. PART 959—ONIONS GROWN IN AD would require reinforcement
In accordance with the Paperwork SOUTH TEXAS modifications of various structural parts
Reduction Act of 1995 (44 U.S.C. of the fuselage, and related investigative
chapter 35), the order’s information ■ 1. The authority citation for 7 CFR
part 959 continues to read as follows: and corrective actions if necessary. We
collection requirements have been are proposing this AD to address the
previously approved by OMB and Authority: 7 U.S.C. 601–674. unsafe condition on these products.
assigned OMB No. 0581–0178 DATES: We must receive comments on
(Vegetable and Specialty Crops). No Subpart A—[Amended]
this proposed AD by November 3, 2017.
changes in those requirements as a ■ 2. Designate the subpart labeled
result of this action are necessary. ADDRESSES: You may send comments,
‘‘Order Regulating Handling’’ as subpart using the procedures found in 14 CFR
Should any changes become necessary, A.
they would be submitted to OMB for 11.43 and 11.45, by any of the following
approval. Subpart B—Administrative Provisions methods:
This proposed rule would impose no • Federal eRulemaking Portal: Go to
additional reporting or recordkeeping ■ 3. Designate the subpart labeled http://www.regulations.gov. Follow the
requirements on either small or large ‘‘Rules and Regulations’’ as subpart B instructions for submitting comments.
South Texas onion handlers. As with all and revise the heading as shown above. • Fax: 202–493–2251.
Federal marketing order programs, • Mail: U.S. Department of
Subparts ‘‘Assessment Rates’’ and Transportation, Docket Operations, M–
reports and forms are periodically
‘‘Handling Regulations’’—[Amended] 30, West Building Ground Floor, Room
reviewed to reduce information
requirements and duplication by ■ 4. Remove the subpart headings W12–140, 1200 New Jersey Avenue SE.,
industry and public sector agencies. ‘‘Assessment Rates’’ and ‘‘Handling Washington, DC 20590.
AMS is committed to complying with Regulations’’. • Hand Delivery: Deliver to Mail
the E-Government Act, to promote the ■ 5. Transfer §§ 959.237 and 959.322 to address above between 9 a.m. and 5
use of the internet and other subpart B. p.m., Monday through Friday, except
information technologies to provide ■ 6. Section 959.237 is revised to read Federal holidays.
increased opportunities for citizen as follows: For service information identified in
access to Government information and this NPRM, contact Airbus SAS,
§ 959.237 Assessment rate. Airworthiness Office—EAL, 1 Rond
services, and for other purposes.
USDA has not identified any relevant On and after August 1, 2017, an Point Maurice Bellonte, 31707 Blagnac
Federal rules that duplicate, overlap, or assessment rate of $0.065 per 50-pound Cedex, France; telephone +33 5 61 93 36
conflict with this action. equivalent is established for South 96; fax +33 5 61 93 45 80; email
A small business guide on complying Texas onions. airworthiness.A330–A340@airbus.com;
with fruit, vegetable, and specialty crop Dated: September 12, 2017. Internet http://www.airbus.com. You
marketing agreements and orders may Bruce Summers, may view this referenced service
be viewed at: http://www.ams.usda.gov/ Acting Administrator, Agricultural Marketing information at the FAA, Transport
rules-regulations/moa/small-businesses. Service. Standards Branch, 1601 Lind Avenue
Any questions about the compliance [FR Doc. 2017–19690 Filed 9–18–17; 8:45 am] SW., Renton, WA. For information on
guide should be sent to Richard Lower BILLING CODE 3410–02–P
the availability of this material at the
at the previously mentioned address in FAA, call 425–227–1221.
the FOR FURTHER INFORMATION CONTACT
Examining the AD Docket
section.
DEPARTMENT OF TRANSPORTATION
A 30-day comment period is provided You may examine the AD docket on
to allow interested persons to respond Federal Aviation Administration the Internet at http://
to this proposed rule. Thirty days is www.regulations.gov by searching for
deemed appropriate because: (1) The 14 CFR Part 39 and locating Docket No. FAA–2017–
2017–18 fiscal period begins on August 0812; or in person at the Docket
1, 2017, and the marketing order [Docket No. FAA–2017–0812; Product Management Facility between 9 a.m.
requires that the rate of assessment for Identifier 2016–NM–198–AD] and 5 p.m., Monday through Friday,
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
each fiscal period apply to all assessable RIN 2120–AA64 except Federal holidays. The AD docket
onions handled during such fiscal contains this proposed AD, the
period; (2) the Committee needs to have Airworthiness Directives; Airbus regulatory evaluation, any comments
sufficient funds to pay its expenses, Airplanes received, and other information. The
which are incurred on a continuous AGENCY: Federal Aviation street address for the Docket Operations
basis; and (3) handlers are aware of this Administration (FAA), DOT. office (telephone 800–647–5527) is in
action, which was unanimously the ADDRESSES section. Comments will
ACTION: Notice of proposed rulemaking
recommended by the Committee at a be available in the AD docket shortly
(NPRM).
public meeting and is similar to other after receipt.
VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\19SEP1.SGM 19SEP1](https://thefederalregister.org/doc/82_FR_43895/page/1.svg)
![43716 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules
FOR FURTHER INFORMATION CONTACT: the WFD rule, the rule requires that www.regulations.gov by searching for
Vladimir Ulyanov, Aerospace Engineer, DAHs establish a limit of validity (LOV) and locating Docket No. FAA–2017–
International Section, Transport of the engineering data that support the 0812.
Standards Branch, FAA, 1601 Lind structural maintenance program.
Related Service Information Under 1
Avenue SW., Renton, WA 98057–3356; Operators affected by the WFD rule may
CFR Part 51
telephone 425–227–1138; fax 425–227– not fly an airplane beyond its LOV,
1149. unless an extended LOV is approved. Airbus has issued the following
SUPPLEMENTARY INFORMATION: The WFD rule (75 FR 69746, service information. This service
November 15, 2010) does not require information describes procedures for
Comments Invited identifying and developing maintenance modifications and reinforcement of
We invite you to send any written actions if the DAHs can show that such various structural parts of the fuselage.
relevant data, views, or arguments about actions are not necessary to prevent These documents are distinct since they
this proposal. Send your comments to WFD before the airplane reaches the apply to different airplane models in
an address listed under the ADDRESSES LOV. Many LOVs, however, do depend different configurations.
section. Include ‘‘Docket No. FAA– on accomplishment of future • Airbus Service Bulletin A330–53–
2017–0812; Product Identifier 2016– maintenance actions. As stated in the 3144, Revision 01, dated July 25, 2006.
NM–198–AD’’ at the beginning of your WFD rule, any maintenance actions • Airbus Service Bulletin A330–53–
comments. We specifically invite necessary to reach the LOV will be 3144, Revision 04, dated November 23,
comments on the overall regulatory, mandated by airworthiness directives 2015.
economic, environmental, and energy through separate rulemaking actions. • Airbus Service Bulletin A330–53–
aspects of this proposed AD. We will In the context of WFD, this action is 3222, Revision 01, dated March 31,
consider all comments received by the necessary to enable DAHs to propose 2016.
closing date and may amend this LOVs that allow operators the longest • Airbus Service Bulletin A330–53–
proposed AD based on those comments. operational lives for their airplanes, and 3223, Revision 00, dated January 19,
We will post all comments we still ensure that WFD will not occur. 2015.
receive, without change, to http:// This approach allows for an • Airbus Service Bulletin A330–53–
www.regulations.gov, including any implementation strategy that provides 3224, Revision 01, excluding Appendix
personal information you provide. We flexibility to DAHs in determining the 01 and including Appendix 02, dated
will also post a report summarizing each timing of service information April 14, 2016.
substantive verbal contact we receive development (with FAA approval), • Airbus Service Bulletin A330–53–
about this proposed AD. while providing operators with certainty 3225, Revision 02, excluding Appendix
regarding the LOV applicable to their 01 and including Appendix 02, dated
Discussion
airplanes. June 8, 2016.
Fatigue damage can occur locally, in The European Aviation Safety Agency • Airbus Service Bulletin A330–53–
small areas or structural design details, (EASA), which is the Technical Agent 3226, Revision 02, excluding Appendix
or globally, in widespread areas. for the Member States of the European 01 and including Appendices 02, 03,
Multiple-site damage is widespread Union, has issued EASA Airworthiness and 04, dated October 27, 2016.
damage that occurs in a large structural Directive 2016–0207, dated October 19, • Airbus Service Bulletin A330–53–
element such as a single rivet line of a 2016 (referred to after this as the 3236, Revision 02, excluding Appendix
lap splice joining two large skin panels. Mandatory Continuing Airworthiness 01 and including Appendices 02 and 03,
Widespread damage can also occur in Information, or ‘‘the MCAI’’), to correct dated March 23, 2016.
multiple elements such as adjacent an unsafe condition for all Airbus • Airbus Service Bulletin A330–53–
frames or stringers. Multiple-site 3237, Revision 01, dated February 8,
Model A330–200 series airplanes,
damage and multiple-element damage 2016.
Model A330–200 Freighter series
cracks are typically too small initially to
airplanes, and Model A330–300 series • Airbus Service Bulletin A330–53–
be reliably detected with normal 3238, Revision 01, dated October 19,
airplanes. The MCAI states:
inspection methods. Without 2015.
intervention, these cracks will grow, An analysis conducted on A330 aeroplanes • Airbus Service Bulletin A330–53–
and eventually compromise the identified structural areas which are
susceptible to widespread fatigue damage 3239, Revision 01, dated July 4, 2016.
structural integrity of the airplane. This (WFD). • Airbus Service Bulletin A330–53–
condition is known as widespread This condition, if not corrected, could lead 3244, Revision 01, dated August 2,
fatigue damage. It is associated with to crack initiation and undetected 2016.
general degradation of large areas of propagation, leading to reduced structural • Airbus Service Bulletin A330–53–
structure with similar structural details integrity of the aeroplane, possibly resulting 3248, Revision 02, dated July 27, 2016.
and stress levels. As an airplane ages, in rapid depressurisation and consequent • Airbus Service Bulletin A330–53–
WFD will likely occur, and will injury to occupants. 3251, Revision 01, dated June 23, 2016.
To address this potential unsafe condition,
certainly occur if the airplane is
Airbus developed a number of modifications
• Airbus Service Bulletin A330–53–
operated long enough without any (Mod) and published associated Service 3252, Revision 01, dated June 30, 2016.
intervention. Bulletins (SB) for embodiment in service, to • Airbus Service Bulletin A330–53–
The FAA’s WFD final rule (75 FR 3257, Revision 01, dated March 15,
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
provide instructions to reinforce the various
69746, November 15, 2010) became structural parts of the fuselage. 2016.
effective on January 14, 2011. The WFD For the reasons described above, this • Airbus Service Bulletin A330–53–
rule requires certain actions to prevent [EASA] AD requires accomplishment of these 3258, Revision 00, dated April 20, 2015.
structural failure due to WFD modifications and reinforcements [and • Airbus Service Bulletin A330–53–
throughout the operational life of related investigative and corrective actions]. 3259, Revision 02, dated July 18, 2016.
certain existing transport category Related investigative actions include a • Airbus Service Bulletin A330–53–
airplanes and all of these airplanes that rotating probe hole inspection for 3263, Revision 01, excluding Appendix
will be certificated in the future. For cracking. You may examine the MCAI in 01 and including Appendix 02, dated
existing and future airplanes subject to the AD docket on the Internet at http:// December 1, 2015.
VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\19SEP1.SGM 19SEP1](https://thefederalregister.org/doc/82_FR_43895/page/2.svg)
![Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43717
• Airbus Service Bulletin A330–53– Design Authority, we have been notified WFD develops in airplanes. Standard
3273, Revision 00, dated September 28, of the unsafe condition described in the inspection techniques cannot be relied
2016. MCAI and service information on to detect WFD before it becomes a
This service information is reasonably referenced above. We are proposing this hazard to flight. We will not grant any
available because the interested parties AD because we evaluated all pertinent extensions of the compliance time to
have access to it through their normal information and determined an unsafe complete any AD-mandated service
course of business or by the means condition exists and is likely to exist or bulletin related to WFD without
identified in the ADDRESSES section. develop on other products of these same extensive new data that would
type designs. substantiate and clearly warrant such an
FAA’s Determination and Requirements
extension.
of This Proposed AD Explanation of Compliance Time
This product has been approved by The compliance time for the Costs of Compliance
the aviation authority of another reinforcement modifications specified We estimate that this proposed AD
country, and is approved for operation in this proposed AD for addressing WFD affects 99 airplanes of U.S. registry.
in the United States. Pursuant to our was established to ensure that We estimate the following costs to
bilateral agreement with the State of discrepant structure is addressed before comply with this proposed AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Reinforcement modifications ............... Up to 317 work-hours × $85 per hour Up to $41,050 ....... Up to $67,995 ....... Up to $6,731,505.
= $26,945.
We have received no definitive data Regulatory Findings § 39.13 [Amended]
that would enable us to provide cost We determined that this proposed AD ■ 2. The FAA amends § 39.13 by adding
estimates for the on-condition actions would not have federalism implications the following new airworthiness
specified in this proposed AD. under Executive Order 13132. This directive (AD):
Authority for This Rulemaking proposed AD would not have a Airbus: Docket No. FAA–2017–0812; Product
substantial direct effect on the States, on Identifier 2016–NM–198–AD.
Title 49 of the United States Code the relationship between the national (a) Comments Due Date
specifies the FAA’s authority to issue Government and the States, or on the We must receive comments by November
rules on aviation safety. Subtitle I, distribution of power and 3, 2017.
section 106, describes the authority of responsibilities among the various
the FAA Administrator. ‘‘Subtitle VII: levels of government. (b) Affected ADs
Aviation Programs,’’ describes in more For the reasons discussed above, I None.
detail the scope of the Agency’s certify this proposed regulation: (c) Applicability
authority. 1. Is not a ‘‘significant regulatory
This AD applies to the Airbus airplanes
We are issuing this rulemaking under action’’ under Executive Order 12866; identified in paragraphs (c)(1), (c)(2), and
the authority described in ‘‘Subtitle VII, 2. Is not a ‘‘significant rule’’ under the (c)(3) of this AD, certificated in any category,
Part A, Subpart III, Section 44701: DOT Regulatory Policies and Procedures all manufacturer serial numbers.
General requirements.’’ Under that (44 FR 11034, February 26, 1979); (1) Model A330–201, –202, –203, –223, and
section, Congress charges the FAA with 3. Will not affect intrastate aviation in –243 airplanes.
Alaska; and (2) Model A330–223F and –243F airplanes.
promoting safe flight of civil aircraft in (3) Model A330–301, –302, –303, –321,
air commerce by prescribing regulations 4. Will not have a significant
economic impact, positive or negative, –322, –323, –341, –342, and –343 airplanes.
for practices, methods, and procedures
the Administrator finds necessary for on a substantial number of small entities (d) Subject
safety in air commerce. This regulation under the criteria of the Regulatory Air Transport Association (ATA) of
is within the scope of that authority Flexibility Act. America Code 53, Fuselage.
because it addresses an unsafe condition List of Subjects in 14 CFR Part 39 (e) Reason
that is likely to exist or develop on This AD was prompted by an evaluation by
products identified in this rulemaking Air transportation, Aircraft, Aviation
safety, Incorporation by reference, the design approval holder (DAH) indicating
action. that certain fuselage structures are subject to
Safety.
This proposed AD is issued in widespread fatigue damage (WFD). We are
accordance with authority delegated by The Proposed Amendment issuing this AD to prevent crack initiation
and undetected propagation in the fuselage,
the Executive Director, Aircraft Accordingly, under the authority which could result in reduced structural
Certification Service, as authorized by
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
delegated to me by the Administrator, integrity of the airplane.
FAA Order 8000.51C. In accordance the FAA proposes to amend 14 CFR part
with that order, issuance of ADs is (f) Compliance
39 as follows:
normally a function of the Compliance Comply with this AD within the
and Airworthiness Division, but during PART 39—AIRWORTHINESS compliance times specified, unless already
this transition period, the Executive DIRECTIVES done.
Director has delegated the authority to (g) Modifications
issue ADs applicable to transport ■ 1. The authority citation for part 39
Except as specified in paragraphs (i)(1) and
category airplanes to the Director of the continues to read as follows: (i)(2) of this AD, before exceeding the
System Oversight Division. Authority: 49 U.S.C. 106(g), 40113, 44701. applicable total flight cycles or total flight
VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\19SEP1.SGM 19SEP1](https://thefederalregister.org/doc/82_FR_43895/page/3.svg)
![43720 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules
TABLE 3 TO PARAGRAPH (i) OF THIS AD —COMPLIANCE TIME LOWER THRESHOLD
Airbus Service Bulletin Applicability Modification not before:
(modification)
A330–53–3222, R1 ......................... Groups 32A, 32E, 33A, 33C, 33D 10,000 total flight cycles.
and 33E.
Group 33B ..................................... 12,000 total flight cycles.
A330–200F .................................... 8,900 total flight cycles and 26,600 total flight hours.
A330–53–3224, R1 ......................... Group 33A ..................................... 10,000 total flight cycles and 6,600 total flight hours.
A330–53–3225, R2 ......................... Group 33A ..................................... 3,900 total flight cycles and 10,200 total flight hours.
A330–53–3237, R1 ......................... Groups 32A, 33A, 33B, 33C, and 3,900 total flight cycles.
33D.
A330–53–3238, R1 ......................... Groups 32A, 33A, 33B, 33C, and 9,000 total flight cycles.
33D.
(j) Additional Work for Certain Airplanes (18) Airbus Service Bulletin A330–53– 2016–0207, dated October 19, 2016, for
For airplanes that have been modified 3259, Revision 01, dated February 26, 2016. related information. This MCAI may be
before the effective date of this AD, in (19) Airbus Service Bulletin A330–53– found in the AD docket on the Internet at
accordance with Airbus Service Bulletin 3263, Revision 00, dated July 21, 2015. http://www.regulations.gov by searching for
A330–53–3144, Revision 00, dated August and locating Docket No. FAA–2017–0812.
(l) Other FAA AD Provisions
23, 2005; Airbus Service Bulletin A330–53– (2) For more information about this AD,
The following provisions also apply to this contact Vladimir Ulyanov, Aerospace
3222, Revision 00, dated January 15, 2015; or
AD: Engineer, International Section, Transport
Airbus Service Bulletin A330–53–3237,
(1) Alternative Methods of Compliance Standards Branch, FAA, 1601 Lind Avenue
Revision 00, dated January 15, 2015, as
(AMOCs): The Manager, International SW., Renton, WA 98057–3356; telephone
applicable: Within 12 months after the
Section, Transport Standards Branch, FAA, 425–227–1138; fax 425–227–1149.
effective date of this AD, accomplish the
has the authority to approve AMOCs for this (3) For service information identified in
additional work specified in the
AD, if requested using the procedures found this AD, contact Airbus SAS, Airworthiness
Accomplishment Instructions of Airbus
in 14 CFR 39.19. In accordance with 14 CFR Office—EAL, 1 Rond Point Maurice Bellonte,
Service Bulletin A330–53–3144, Revision 01,
39.19, send your request to your principal 31707 Blagnac Cedex, France; telephone +33
dated July 25, 2006; A330–53–3222, R1; and
inspector or local Flight Standards District 5 61 93 36 96; fax +33 5 61 93 45 80; email
A330–53–3237, R1; as applicable.
Office, as appropriate. If sending information airworthiness.A330–A340@airbus.com;
(k) Credit for Previous Actions directly to the International Section, send it Internet http://www.airbus.com. You may
to the attention of the person identified in view this service information at the FAA,
This paragraph provides credit for
paragraph (m)(2) of this AD. Information may Transport Standards Branch, 1601 Lind
applicable actions required by paragraph (g)
be emailed to: 9-ANM-116-AMOC- Avenue SW., Renton, WA. For information
of this AD, if those actions were performed
REQUESTS@faa.gov. Before using any on the availability of this material at the
before the effective date of this AD using the
approved AMOC, notify your appropriate FAA, call 425–227–1221.
applicable service information specified in
principal inspector, or lacking a principal
paragraphs (k)(1) through (k)(19) of this AD. Issued in Renton, Washington, on
inspector, the manager of the local flight
(1) Airbus Service Bulletin A330–53–3144, September 7, 2017.
standards district office/certificate holding
Revision 01, dated July 25, 2006.
district office. Jeffrey E. Duven,
(2) Airbus Service Bulletin A330–53–3144, (2) Contacting the Manufacturer: For any
Revision 02, dated April 20, 2011. Director, System Oversight Division, Aircraft
requirement in this AD to obtain corrective Certification Service.
(3) Airbus Service Bulletin A330–53–3144, actions from a manufacturer, the action must
Revision 03, dated January 15, 2015. be accomplished using a method approved [FR Doc. 2017–19760 Filed 9–18–17; 8:45 am]
(4) Airbus Service Bulletin A330–53–3224, by the Manager, International Section, BILLING CODE 4910–13–P
Revision 00, dated January 16, 2015. Transport Standards Branch, FAA; or the
(5) Airbus Service Bulletin A330–53–3225, European Aviation Safety Agency (EASA); or
Revision 00, dated January 16, 2015. Airbus’s EASA Design Organization
(6) Airbus Service Bulletin A330–53–3225, DEPARTMENT OF THE TREASURY
Approval (DOA). If approved by the DOA,
Revision 01, dated February 26, 2016. the approval must include the DOA-
(7) Airbus Service Bulletin A330–53–3226, Internal Revenue Service
authorized signature.
Revision 00, dated January 15, 2015. (3) Required for Compliance (RC): Except
(8) Airbus Service Bulletin A330–53–3226, as required by paragraph (i) of this AD: If any 26 CFR Parts 1, 5f, and 46
Revision 01, dated March 3, 2016. service information contains procedures or [REG–125374–16]
(9) Airbus Service Bulletin A330–53–3236, tests that are identified as RC, those
Revision 00, dated January 15, 2015. procedures and tests must be done to comply RIN 1545–BN60
(10) Airbus Service Bulletin A330–53– with this AD; any procedures or tests that are
3236, Revision 01, dated August 24, 2015. not identified as RC are recommended. Those Guidance on the Definition of
(11) Airbus Service Bulletin A330–53– procedures and tests that are not identified Registered Form
3238, Revision 00, dated January 15, 2015. as RC may be deviated from using accepted
(12) Airbus Service Bulletin A330–53– methods in accordance with the operator’s AGENCY: Internal Revenue Service (IRS),
3239, Revision 00, dated April 20, 2015. Treasury.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
maintenance or inspection program without
(13) Airbus Service Bulletin A330–53– obtaining approval of an AMOC, provided ACTION: Partial withdrawal of notice of
3244, Revision 00, dated April 7, 2015. the procedures and tests identified as RC can
(14) Airbus Service Bulletin A330–53–
proposed rulemaking and notice of
be done and the airplane can be put back in
3251, Revision 00, dated May 13, 2015. proposed rulemaking.
an airworthy condition. Any substitutions or
(15) Airbus Service Bulletin A330–53– changes to procedures or tests identified as
3252, Revision 00, dated April 10, 2015. SUMMARY: This document contains
RC require approval of an AMOC.
(16) Airbus Service Bulletin A330–53– proposed regulations that provide
3257, Revision 00, dated July 21, 2015. (m) Related Information guidance on the definitions of
(17) Airbus Service Bulletin A330–53– (1) Refer to Mandatory Continuing registration-required obligation and
3259, Revision 00, dated May 11, 2015. Airworthiness Information (MCAI) EASA AD registered form, including guidance on
VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\19SEP1.SGM 19SEP1](https://thefederalregister.org/doc/82_FR_43895/page/6.svg)
Document Created: 2018-10-24 14:17:25
Document Modified: 2018-10-24 14:17:25
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 3, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227- 1149. | |
| FR Citation | 82 FR 43715 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR