Airworthiness Directives; Airbus Airplanes, 43715-43720 [2017-19760]

Download as PDF asabaliauskas on DSKBBXCHB2PROD with PROPOSALS Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules persons were invited to attend the meeting and participate in Committee deliberations on all issues. Like all Committee meetings, the June 7, 2017, meeting was a public meeting, and all entities, both large and small, were able to express views on this issue. Finally, interested persons are invited to submit comments on this proposed rule, including the regulatory and informational impacts of this action on small businesses. In accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. chapter 35), the order’s information collection requirements have been previously approved by OMB and assigned OMB No. 0581–0178 (Vegetable and Specialty Crops). No changes in those requirements as a result of this action are necessary. Should any changes become necessary, they would be submitted to OMB for approval. This proposed rule would impose no additional reporting or recordkeeping requirements on either small or large South Texas onion handlers. As with all Federal marketing order programs, reports and forms are periodically reviewed to reduce information requirements and duplication by industry and public sector agencies. AMS is committed to complying with the E-Government Act, to promote the use of the internet and other information technologies to provide increased opportunities for citizen access to Government information and services, and for other purposes. USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this action. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: https://www.ams.usda.gov/ rules-regulations/moa/small-businesses. Any questions about the compliance guide should be sent to Richard Lower at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. A 30-day comment period is provided to allow interested persons to respond to this proposed rule. Thirty days is deemed appropriate because: (1) The 2017–18 fiscal period begins on August 1, 2017, and the marketing order requires that the rate of assessment for each fiscal period apply to all assessable onions handled during such fiscal period; (2) the Committee needs to have sufficient funds to pay its expenses, which are incurred on a continuous basis; and (3) handlers are aware of this action, which was unanimously recommended by the Committee at a public meeting and is similar to other VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 assessment rate actions issued in past years. List of Subjects in 7 CFR Part 959 Marketing agreements, Onions, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, 7 CFR part 959 is proposed to be amended as follows: PART 959—ONIONS GROWN IN SOUTH TEXAS 1. The authority citation for 7 CFR part 959 continues to read as follows: ■ Authority: 7 U.S.C. 601–674. Subpart A—[Amended] 2. Designate the subpart labeled ‘‘Order Regulating Handling’’ as subpart A. ■ Subpart B—Administrative Provisions 3. Designate the subpart labeled ‘‘Rules and Regulations’’ as subpart B and revise the heading as shown above. ■ Subparts ‘‘Assessment Rates’’ and ‘‘Handling Regulations’’—[Amended] 4. Remove the subpart headings ‘‘Assessment Rates’’ and ‘‘Handling Regulations’’. ■ 5. Transfer §§ 959.237 and 959.322 to subpart B. ■ 6. Section 959.237 is revised to read as follows: ■ § 959.237 Assessment rate. On and after August 1, 2017, an assessment rate of $0.065 per 50-pound equivalent is established for South Texas onions. Dated: September 12, 2017. Bruce Summers, Acting Administrator, Agricultural Marketing Service. [FR Doc. 2017–19690 Filed 9–18–17; 8:45 am] BILLING CODE 3410–02–P 43715 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 https://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 https://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. SUMMARY: Examining the AD Docket 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at https:// 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. E:\FR\FM\19SEP1.SGM 19SEP1 43716 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 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: asabaliauskas on DSKBBXCHB2PROD with PROPOSALS 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 https:// 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 VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 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 https:// PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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. E:\FR\FM\19SEP1.SGM 19SEP1 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules • 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 43717 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 Reinforcement modifications ............... Up to 317 work-hours × $85 per hour = $26,945. Up to $41,050 ....... Up to $67,995 ....... asabaliauskas on DSKBBXCHB2PROD with PROPOSALS 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. 16:33 Sep 18, 2017 Jkt 241001 Up to $6,731,505. Regulatory Findings We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. VerDate Sep<11>2014 Cost on U.S. operators § 39.13 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 (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. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 [Amended] 2. The FAA amends § 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. (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 E:\FR\FM\19SEP1.SGM 19SEP1 43718 Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 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 Improve circumferential joints at frames (FR) 45 and 54 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3144, Revision 04, dated November 23, 2015 (‘‘A330–53–3144, R4’’). Group 32A ................. Group 33A ................. 32,500 total flight cycles ................................. 23,700 total flight cycles or 71,300 total flight hours, whichever occurs first. 27,600 total flight cycles or 83,000 total flight hours, whichever occurs first. 23,300 total flight cycles or 70,000 total flight hours, whichever occurs first. 22,700 total flight cycles or 68,300 flight hours, whichever occurs first. 23,100 total flight cycles or 80,900 total flight hours, whichever occurs first. 24,200 total flight cycles or 79,100 total flight hours, whichever occurs first. 19,700 total flight cycles or 64,300 total flight hours, whichever occurs first. 21,600 total flight cycles or 70,600 flight hours, whichever occurs first. 27,400 total flight cycles or 82,200 total flight hours, whichever occurs first. Group 33B ................. Group 33C ................. Group 33D ................. Improve splicing area from FR48 to FR53–2 between stringers (STRG) 23 and 26 left hand (LH)/right hand (RH) of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3222, Revision 01, dated March 31, 2016 (‘‘A330–53–3222, R1’’) (Airbus Modification 204315). Groups 32A and 32E Group 33A ................. Group 33B ................. Groups 33C, 33D, and 33E. A330–200F ................ Reinforce couplings in area FR20—FR25/STRG20 RH—STRG22 RH of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3223, Revision 00, dated January 19, 2015 (‘‘A330-53-3223, R0’’). Reinforce circumferential joint at FR72 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3224, Revision 01, excluding Appendix 01 and including Appendix 02, dated April 14, 2016 (‘‘A330-53–3224, R1’’). Reinforce circumferential joint at FR58 of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3225, Revision 02, excluding Appendix 01 and including Appendix 02, dated June 8, 2016 (‘‘A330-53–3225, R2’’). Reinforce circumferential joint between FR53.6—FR53.7 for emergency door TYPE 1 area of the center fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3226, Revision 02, excluding Appendix 01 and including Appendices 02, 03, and 04, dated October 27, 2016 (‘‘A330–53– 3226, R2’’); or Airbus Service Bulletin A330-53-3273, Revision 00, dated September 28, 2016 (‘‘A330-53-3273, R0’’). SMP LR 26,600 flight cycles. 20,400 total flight cycles 23,700 total flight cycles. 20,000 total flight cycles. 19,500 total flight cycles. 20,900 total flight cycles. 21,800 total flight cycles. 17,700 total flight cycles. 19,400 total flight cycles. 27,400 total flight cycles or 82,200 total flight hours, whichever occurs first. 30,900 total flight cycles. Groups 32A, 32E, 33B, 33C, 33D and 33E. 30,900 total flight cycles ................................. Group 33A ................. 29,700 total flight cycles or 89,600 total flight hours, whichever occurs first. 25,500 total flight cycles. Group 33A ................. 16,300 total flight cycles or 49,300 total flight hours, whichever occurs first. Group 32A ................. ............................... Groups 33C, 33D and 33E. ......................................................................... 26,100 total flight cycles or 91,600 total flight hours, whichever occurs first. 15,600 total flight cycles or 46,800 total flight hours, whichever occurs first. 13,300 total flight cycles or 90,700 total flight hours, whichever occurs first. 21,000 total flight cycles. 12,600 total flight cycles or 84,800 total flight hours, whichever occurs first. Group 33A ................. 34,400 total flight cycles ................................. .................................................................... 19,900 total flight cycles or 59,800 total flight hours, whichever occurs first. 19,900 total flight cycles or 69,900 total flight hours, whichever occurs first. 30,900 total flight cycles or 93,200 total flight hours, whichever occurs first. 27,800 cles. 16,100 cles. 16,200 cles. 25,400 cles. Groups 32A, 33A, 33B, 33C, and 33D. Group 32A ................. 27,300 total flight cycles ................................. Group 33A ................. Group 33B ................. Groups 33C and 33D 28,800 total flight cycles ................................. 36,200 total flight cycles ................................. 34,700 total flight cycles ................................. 27,300 cles. 38,400 cles. 28,800 cles. 36,200 cles. 34,700 cles. 15,100 cles. Group 33B ................. Group 32E ................. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS Reinforce circumferential joint between FR53.6—FR53.7 LH/RH of option emergency door TYPE A area of the center fuselage, in accordance 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 center fuselage structure on longitudinal beams above the center wing box, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53– 3237, Revision 01, dated February 8, 2016 (‘‘A330-53–3237, R1’’). Update lower/lateral frame splicing with corner fitting between FR53.3 and FR54 of the center fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53– 3238, Revision 01, dated October 19, 2015 (‘‘A330-53–3238, R1’’). Group 33A ................. Reinforce longitudinal butt joints in section 13, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3239, Revision 01, dated July 4, 2016 (‘‘A330-53–3239, R1’’). Reinforce circumferential joint at FR31 between STRG 7LH and STRG 8RH of forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3244, Revision 01, dated August 2, 2016 (‘‘A330-53–3244, R1’’). Reinforce frame couplings in section 13, 14, and 14A of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3248, Revision 02, dated July 27, 2016 (‘‘A330-53–3248, R2’’). A330–200F ................ 15,100 total flight cycles ................................. A330–200F ................ 15,500 total flight cycles or 46,500 total flight hours, whichever occurs first. Group 33A ................. 32,000 total flight cycles ................................. VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 38,400 total flight cycles ................................. E:\FR\FM\19SEP1.SGM 19SEP1 total flight cytotal flight cytotal flight cytotal flight cy- total flight cytotal flight cytotal flight cytotal flight cytotal flight cytotal flight cy- 15,500 total flight cycles or 46,500 total flight hours, whichever occurs first. 32,000 total flight cycles. Federal Register / Vol. 82, No. 180 / Tuesday, September 19, 2017 / Proposed Rules 43719 TABLE 1 TO PARAGRAPH (g) OF THIS AD—MODIFICATION—Continued Description of action Applicability SMP SR Reinforce circumferential joint/stringer coupling in area of FR37.1 of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3251, Revision 01, dated June 23, 2016 (‘‘A330-53–3251, R1’’). Group 33C Pre-Modification 46636. Groups 33C and 33D Post-Modification 46636. Group 33E ................. 38,200 total flight cycles ................................. Groups 33C and 33D, Post-Modification 46636. 30,600 total flight cycles or 99,500 total flight hours, whichever occurs first. 32,200 total flight cycles ................................. Reinforce circumferential joint/stringer coupling in area of FR37.1 of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3252, Revision 01, dated June 30, 2016 (‘‘A330-53–3252, R1’’). 30,600 total flight cycles or 99,500 total flight hours, whichever occurs first. 32,200 total flight cycles ................................. SMP LR 32,000 total flight cycles. 27,600 total flight cycles. 29,100 total flight cycles. 27,600 total flight cycles. 29,100 total flight cycles. 24,000 total flight cycles. (h) Weight Variant (WV) Group Designations For the purposes of this AD, table 2 to paragraph (h) of this AD identifies the WV Group 32A ................. 31,800 total flight cycles ................................. 31,800 total flight cycles. Group 32E ................. 18,500 total flight cycles or 65,400 total flight hours, whichever occurs first. 34,800 total flight cycles ................................. Group 33B ................. Reinforce frames in rear area of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53–3263, Revision 01, excluding Appendix 01 and including Appendix 02, dated December 1, 2015 (‘‘A330-53–3263, R1’’). 24,000 total flight cycles ................................. Group 33A ................. Reinforce frame couplings in rear area of the fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3257, Revision 01, dated March 15, 2016 (‘‘A330-53–3257, R1’’). Reinforce corner fittings in section 13 of the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3258, Revision 00, dated April 20, 2015 (‘‘A330-53-3258, R0’’). Reinforce circumferential joint at FR58 (aeroplane Post-Modification 40556/D18255) of the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53– 3259, Revision 02, dated July 18, 2016 (‘‘A330-53–3259, R2’’). Group 33E ................. Groups 33A and 33B 33,500 total flight cycles ................................. Groups 32A, 32E, 33B, 33C, 33D, and 33E. 23,300 total flight cycles or 69,700 total flight hours, whichever occurs first. 14,600 total flight cycles or 95,700 total flight hours, whichever occurs first. 28,400 total flight cycles. 27,400 total flight cycles. 20,800 total flight cycles. 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 ........................................................ Group 32E ........................................................ A330–200F ................................ A330–300 .................................. N/A ................................................................... Group 33A ........................................................ Group 33B ........................................................ Group 33C ........................................................ Group 33D ........................................................ Group 33E ........................................................ 020, 021, 022, 023, 024, 025, 026, and 027. 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 061, 062, 063, 064, 080, 081, 082, and 083. 000, 001, and 002. 000, 001, 002, 003, and 004. 010, 011, 012, 013, and 014. 020, 024, 025, 026, and 027. 022. 030, 031, 032, 033, 034, 035, 039, 050, 051, 052, 053, 054, 055, 056, 057, 058, 059, 060, 080, 081, 082, and 083. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (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 VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 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, PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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. E:\FR\FM\19SEP1.SGM 19SEP1 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 (modification) Applicability A330–53–3222, R1 ......................... Groups 32A, 32E, 33A, 33C, 33D and 33E. Group 33B ..................................... A330–200F .................................... Group 33A ..................................... Group 33A ..................................... Groups 32A, 33A, 33B, 33C, and 33D. Groups 32A, 33A, 33B, 33C, and 33D. A330–53–3224, R1 ......................... A330–53–3225, R2 ......................... A330–53–3237, R1 ......................... A330–53–3238, R1 ......................... asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (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. VerDate Sep<11>2014 16:33 Sep 18, 2017 Jkt 241001 Modification not before: 10,000 total flight cycles. 12,000 total flight cycles. 8,900 total flight cycles and 26,600 total flight hours. 10,000 total flight cycles and 6,600 total flight hours. 3,900 total flight cycles and 10,200 total flight hours. 3,900 total flight cycles. 9,000 total flight cycles. (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-AMOCREQUESTS@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 DOAauthorized 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 2016–0207, dated October 19, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://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 https://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 DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Parts 1, 5f, and 46 [REG–125374–16] RIN 1545–BN60 Guidance on the Definition of Registered Form Internal Revenue Service (IRS), Treasury. ACTION: Partial withdrawal of notice of proposed rulemaking and notice of proposed rulemaking. AGENCY: This document contains proposed regulations that provide guidance on the definitions of registration-required obligation and registered form, including guidance on SUMMARY: E:\FR\FM\19SEP1.SGM 19SEP1

Agencies

[Federal Register Volume 82, Number 180 (Tuesday, September 19, 2017)]
[Proposed Rules]
[Pages 43715-43720]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[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 https://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 https://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 https://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 https://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 https://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.

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 https://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 https://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

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