Airworthiness Directives; Airbus Airplanes, 58772-58777 [2017-26362]

Download as PDF 58772 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules amount and percent of capital measure is designed to limit the filing exemption to institutions that create only low-dollar risks to the Reserve Banks and that incur small overdrafts relative to their capital measure. * * * * * * * * * * 3. Capital Measure * * * b. U.S. Branches and Agencies for Foreign Banks For U.S. branches and agencies of foreign banks, net debit caps on daylight overdrafts in Federal Reserve accounts are calculated by applying the cap multiples for each cap category to the FBO’s U.S. capital equivalency measure.69 U.S. capital equivalency is equal to 10 percent of worldwide capital for FBOs.70 An FBO that is well capitalized (calculated as if the FBO were subject to the Board’s Regulation H 71) may be eligible for a streamlined procedure (see section II.E.) for obtaining additional collateralized intraday credit under the maximum daylight overdraft capacity provision. * * * * * Revisions to Section II.E of the PSR Policy The Board proposes to revise Section II.E of the ‘‘Federal Reserve Policy on Payment System Risk’’ as follows: E. Maximum Daylight Overdraft Capacity * * * * * directors resolution indicating its board’s approval of that level. * * * * * * * * 2. Streamlined Procedure for Certain FBOs An FBO that is well capitalized (calculated as if the FBO were subject to the Board’s Regulation H 75) and has a self-assessed net debit cap may request from its Reserve Bank a streamlined procedure to obtain a maximum daylight overdraft capacity. These FBOs are not required to provide documentation of the business need or obtain the board of directors’ resolution for collateralized capacity in an amount that exceeds its current net debit cap (which is based on 10 percent worldwide capital times its cap multiple), as long as the requested total capacity is 100 percent or less of worldwide capital times a self-assessed cap multiple.76 In order to ensure that intraday liquidity risk is managed appropriately and that the FBO will be able to repay daylight overdrafts, eligible FBOs under the streamlined procedure will be subject to initial and periodic reviews of liquidity plans that are analogous to the liquidity reviews undergone by U.S. institutions.77 If an eligible FBO requests capacity in excess of 100 percent of worldwide capital times the self-assessed cap multiple, it would be subject to the general procedure. * * * * * By order of the Board of Governors of the Federal Reserve System, December 8, 2017. Ann E. Misback, Secretary of the Board. [FR Doc. 2017–26923 Filed 12–13–17; 8:45 am] 1. General Procedure An institution with a self-assessed net debit cap that wishes to expand its daylight overdraft capacity by pledging collateral should consult with its administrative Reserve Bank. The Reserve Bank will work with an institution that requests additional daylight overdraft capacity to determine the appropriate maximum daylight overdraft capacity level. In considering the institution’s request, the Reserve Bank will evaluate the institution’s rationale for requesting additional daylight overdraft capacity as well as its financial and supervisory information. The financial and supervisory information considered may include, but is not limited to, capital and liquidity ratios, the composition of balance sheet assets, and CAMELS or other supervisory ratings and assessments. An institution approved for a maximum daylight overdraft capacity level must submit at least once in each twelve-month period a board of BILLING CODE 6210–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1100; Product Identifier 2017–NM–077–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 75 See sradovich on DSK3GMQ082PROD with PROPOSALS 69 The term ‘‘U.S. capital equivalency’’ is used in this context to refer the particular measure calculate net debit caps and does not necessarily represent an appropriate for supervisory or other purposes. 70 FBOs that wish to establish a non-zero net debit cap must report their worldwide capital on the Annual Daylight Overdraft Capital Report for U.S. Branches and Agencies of Foreign Banks (FR 2225). The instructions for FR explain how FBOs should calculate their worldwide capital. See https:// www.federalreserve.gov/apps/reportforms/ reportdetail.aspx?sOoYJ+5BzDZ1kLYTc+ZpEQ==. 71 See 12 CFR 208.43(b). VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 12 CFR 208.43(b). example, an FBO that is well capitalized is eligible for uncollateralized capacity of 10 percent of worldwide capital times the cap multiple. The streamlined max cap procedure would provide such an institution with additional collateralized capacity of 90 percent of worldwide capital times the cap multiple. As noted above, FBOs report their worldwide capital on the Annual Daylight Overdraft Capital Report for U.S. Branches and Agencies of Foreign Banks (FR 2225). 77 The liquidity reviews will be conducted by the administrative Reserve Bank, in consultation with each FBO’s home country supervisor. 76 For PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 We propose to supersede Airworthiness Directive (AD) 2015–15– 13, which applies to certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. AD 2015–15–13 requires modification of the potable water service panel and waste water service panel, including doing applicable related investigative and corrective actions. Since we issued AD 2015–15– 13, further investigations linked to widespread fatigue damage (WFD) analysis highlighted that, to meet the WFD requirements, it is necessary that the affected modification not be accomplished before reaching a certain threshold. This proposed AD would require modification of the waste water and potable water service panels with new compliance times. This proposed AD would also remove certain airplanes from the applicability and add Model A320–216 airplanes to the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by January 29, 2018. 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, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@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. SUMMARY: 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– 1100; or in person at the Docket E:\FR\FM\14DEP1.SGM 14DEP1 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules 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. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: sradovich on DSK3GMQ082PROD 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– 2017–1100; Product Identifier 2017– NM–077–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 WFD. 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. VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 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. We issued AD 2015–15–13, Amendment 39–18223 (80 FR 45857, August 3, 2015) (‘‘AD 2015–15–13’’), for certain Airbus Model A319 series airplanes; Model A320–211, –212, –214, –231,–232, and –233 airplanes; and Model A321 series airplanes. AD 2015– 15–13 was prompted by reports of cracks that could be initiated at the waste water service panel area and the potable water service panel area. AD 2015–15–13 requires modification of the potable water service panel and waste water service panel, including doing applicable related investigative and corrective actions. We issued AD 2015– 15–13 to prevent any cracking at the waste water service panel area and the potable water service panel area, which could affect the structural integrity of the airplane. Since we issued AD 2015–15–13, further investigations linked to WFD analysis highlighted that, to meet the WFD requirements, it is necessary that the affected modification is not PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 58773 accomplished before reaching a certain threshold by imposing a ‘‘window of embodiment.’’ The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0098, dated June 7, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Airbus Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: During the full scale fatigue test on A320– 200, it was noticed that, due to fatigue, cracks could initiate at the potable water and waste water service panel areas. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. Prompted by these findings, Airworthiness Limitation Section (ALS) Part 2 tasks were introduced for the affected aeroplanes. Since those actions were taken, Airbus developed production mod 160055 and mod 160056 to embody reinforcements (cold working on certain rivet rows) of the potable water and waste water service panels, and published associated Airbus Service Bulletin (SB) A320–53–1272 and Airbus SB A320–53–1267 for in-service embodiment. Complementary design office studies highlighted that the ‘‘Sharklets’’ installation on certain aeroplanes has a significant impact on the aeroplane structure (particularly, A319 and A320 postmod 160001, A320 post-SB A320–57–1193 (mod 160080), and A321 post-mod 160021), leading to different compliance times, depending on aeroplane configuration. Consequently, EASA issued AD 2014–0081 [which corresponds to FAA AD 2015–15–13] to require reinforcement of the potable water and waste water service panels. Accomplishment of these modifications cancelled the need for the related ALS Part 2 Tasks. Since that AD was issued, further investigations linked to the Widespread Fatigue Damage (WFD) analysis highlighted that, to meet the WFD requirements, it is necessary that the affected modification is not accomplished before reaching a certain threshold, by imposing a so-called ‘‘window of embodiment’’. Consequently, Airbus revised SB A320–53–1272 (now at revision (Rev.) 04) and SB A320–53–1267 (now at Rev. 05). For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014–0081, which is superseded, and introduces additional compliance times for those actions. This proposed AD would also remove Model A319 series airplanes on which modification 28162, 28238, and 28342 have been embodied (‘‘Corporate Jet’’ modifications) from the applicability because production modifications E:\FR\FM\14DEP1.SGM 14DEP1 58774 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules mitigated the risk associated with the unsafe condition. This proposed AD would also add Model A320–216 airplanes to the applicability because those airplanes are affected by the identified unsafe condition. 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– 1100. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–53–1267, Revision 05, dated November 29, 2016, which describes procedures for modifying the waste water service panel. Airbus has also issued Service Bulletin A320–53–1272, Revision 04, dated November 29, 2016, which describes procedures for modifying the potable water service panel. Both modifications include a check of the diameter of the holes of removed fasteners, a related investigative action (rotating probe inspection for cracking on the holes of the removed fasteners) and a corrective action (repair). 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 the same type design. sradovich on DSK3GMQ082PROD with PROPOSALS Explanation of Compliance Time The compliance time for the replacement specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is replaced 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. VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 Costs of Compliance We estimate that this proposed AD affects 851 airplanes of U.S. registry. We also estimate that it would take about 27 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $700 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $2,548,745, or $2,995 per product. 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 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: PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–15–13, Amendment 39–18223 (80 FR 45857, August 3, 2015), and adding the following new AD: ■ Airbus: Docket No. FAA–2017–1100; Product Identifier 2017–NM–077–AD. (a) Comments Due Date We must receive comments by January 29, 2018. (b) Affected ADs This AD replaces AD 2015–15–13, Amendment 39–18223 (80 FR 45857, August 3, 2015) (‘‘AD 2015–15–13’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, except for those airplanes on which Airbus modification 160055 or modification 160056 has been embodied in production, and except for Model A319 series airplanes on which modification 28162, 28238, and 28342 have been embodied (‘‘Corporate Jet’’). (1) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Airbus Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. (3) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 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 E:\FR\FM\14DEP1.SGM 14DEP1 58775 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules that the potable water and waste water service panel areas are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent cracking of the potable water and waste water service panel areas, 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) Modification of the Potable Water Service Panel (1) Within the compliance times specified in Table 1 to paragraphs (g)(1) and (i) of this AD, as applicable, modify the potable water service panel, including doing a check of the diameter of the holes of removed fasteners, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1272, Revision 04, dated November 29, 2016, except as required by paragraph (g)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. TABLE 1 TO PARAGRAPHS (g)(1) AND (i) OF THIS AD—COMPLIANCE TIMES FOR THE PORTABLE WATER SERVICE PANEL REINFORCEMENT Compliance time maximum (before the accumulation of the specified total flight cycles since the airplane’s first flight) Affected airplanes * Compliance time minimum ** A319, pre-modification 160001 and pre-service bulletin A320–57–1193 A319, post-modification 160001 or post-service bulletin A320–57–1193 A320, pre-modification 160001 and pre-service bulletin A320–57–1193 A320, post-modification 160001 or post-service bulletin A320–57–1193 A321–100 ................................................................................................. A321–200 pre-modification 160021 ......................................................... A321–200 post-modification 160021 ....................................................... 33,100 total flight cycles ............... None .............................................. 25,100 total flight cycles ............... None .............................................. 25,100 total flight cycles ............... 22,100 total flight cycles ............... None .............................................. 48,500 46,000 54,200 48,300 60,000 60,000 60,000 total total total total total total total flight flight flight flight flight flight flight cycles. cycles. cycles. cycles. cycles. cycles. cycles. * A321–111, A321–112 and A321-131 airplanes are collectively referred to as ‘‘A321–100.’’ Similarly, A321–211, A321–212, A321–213, A321– 231 and A321–232 airplanes are collectively referred to as ‘‘A321-200’’. ** Not before accumulating the specified total flight cycles since the airplane’s first flight. (2) Where Airbus Service Bulletin A320– 53–1272, Revision 04, dated November 29, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (m)(2) of this AD. (h) Modification of the Waste Water Service Panel (1) Within the compliance times specified in Table 2 to paragraphs (h)(1) and (i) of this AD, as applicable, modify the waste water service panel, including doing a check of the diameter of the holes of removed fasteners, and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1267, Revision 05, dated November 29, 2016, except as required by paragraph (h)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. TABLE 2 TO PARAGRAPHS (h)(1) AND (i) OF THIS AD—COMPLIANCE TIMES FOR THE WASTE WATER SERVICE PANEL REINFORCEMENT Compliance time minimum ** Compliance time maximum A319, pre-modification 160001 and pre-service bulletin A320–57–1193. A319, post-modification 160001 or post-service bulletin A320–57–1193. A320, pre-modification 160001 and pre-service bulletin A320–57–1193. 28,600 total flight cycles .................... Before the accumulation of 44,400 total flight cycles since the airplane’s first flight. None ................................................... Before the accumulation of 43,600 total flight cycles since the airplane’s first flight. 35,800 total flight cycles .................... A320, post-modification 160001 or post-service bulletin A320–57–1193. A321–100 ........................ 5,400 total flight cycles ...................... Before the accumulation of 46,000 total flight cycles since the airplane’s first flight; or within 2,300 flight cycles since the last accomplishment of Airworthiness Limitation Section (ALS) Part 2 Task 534126–01–3 without exceeding 48,000 total flight cycles since the airplane’s first flight; whichever occurs later. Before the accumulation of 39,200 total flight cycles since the airplane’s first flight. A321–200 pre-modification 160021. A321–200 post-modification 160021. sradovich on DSK3GMQ082PROD with PROPOSALS Affected airplanes * 35,700 total flight cycles .................... 36,900 total flight cycles .................... None ................................................... Before the accumulation of 52,500 total flight cycles since the airplane’s first flight. Before the accumulation of 53,500 total flight cycles since the airplane’s first flight. Before the accumulation of 51,200 total flight cycles since the airplane’s first flight. * A321–111, A321–112 and A321–131 airplanes are collectively referred to as ‘‘A321–100.’’ Similarly, A321–211, A321–212, A321–213, A321– 231 and A321–232 airplanes are collectively referred to as ‘‘A321–200’’. ** Not before accumulating the specified total flight cycles since the airplane’s first flight. (2) Where Airbus Service Bulletin A320– 53–1267, Revision 05, dated November 29, 2016, specifies to contact Airbus for appropriate action, and specifies that action VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (m)(2) of this AD. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (i) Corrective Action for Airplanes With Certain Modifications For airplanes on which the modification, as required by paragraph (g) or (h) of this AD, E:\FR\FM\14DEP1.SGM 14DEP1 58776 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules as applicable, was accomplished before reaching the applicable minimum compliance time as defined in Table 1 to paragraphs (g)(1) and (i) of this AD or Table 2 to paragraphs (h)(1) and (i) of this AD: Before exceeding 60,000 flight cycles since the airplane’s first flight, contact the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA) for approved corrective action instructions and accomplish those instructions accordingly. (j) Terminating Action for Airplanes on Which the Potable Water Service Panel Modification Is Done Modification of an airplane as required by paragraph (g) of this AD terminates the requirement for accomplishing the ALS Part 2 task for that airplane as specified in Table 3 to paragraph (j) of this AD, as applicable. TABLE 3 TO PARAGRAPH (j) OF THIS AD—ALS PART 2 TASK TERMINATED AFTER POTABLE WATER SERVICE PANEL MODIFICATION ALS Part 2 task No. Affected airplanes A319, pre-modification 160001 and pre-service bulletin A320–57–1193 ........................................................................................... A319, post-modification 160001 or post-service bulletin A320–57–1193 ........................................................................................... A320, pre-modification 160001 and pre-service bulletin A320–57–1193 ........................................................................................... A320, post-modification 160001 or post-service bulletin A320–57–1193 ........................................................................................... A321 pre-modification 160021 ............................................................................................................................................................. A321 post-modification 160021 ........................................................................................................................................................... (k) Terminating Action for Airplanes on Which the Waste Water Service Panel Modification Is Done Modification of an airplane as required by paragraph (h) of this AD terminates the 534125–01–2 534125–01–5 534125–01–3 534125–01–6 534125–01–4 534125–01–7 requirement for accomplishing the ALS Part 2 task for that airplane as specified in Table 4 to paragraph (k) of this AD, as applicable. TABLE 4 TO PARAGRAPH (k) OF THIS AD—ALS PART 2 TASK TERMINATED AFTER WASTE WATER SERVICE PANEL MODIFICATION ALS Part 2 task No. Affected airplanes A319, pre-modification 160001 and pre-service bulletin A320-57–1193 ............................................................................................ A319, post-modification 160001 or post-service bulletin A320-57–1193 ............................................................................................ A320, pre-modification 160001 and pre-service bulletin A320-57–1193 ............................................................................................ A320, post-modification 160001 or post-service bulletin A320-57–1193 ............................................................................................ A321 pre-modification 160021 ............................................................................................................................................................. A321 post-modification 160021 ........................................................................................................................................................... sradovich on DSK3GMQ082PROD with PROPOSALS (l) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD if those actions were performed before the effective date of this AD using the service information in paragraphs (l)(1)(i) through (l)(1)(iv) of this AD. (i) Airbus Service Bulletin A320–53–1272, Revision 00, dated January 10, 2013, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A320–53–1272, Revision 01, dated August 6, 2013, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A320–53– 1272, Revision 02, dated May 19, 2014, which was incorporated by reference in AD 2015–15–13. (iv) Airbus Service Bulletin A320–53– 1272, Revision 03, dated November 26, 2015, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD if those actions were performed before the effective date of this AD using the service information in paragraphs (l)(2)(i) through (l)(2)(v) of this AD. (i) Airbus Service Bulletin A320–53–1267, Revision 00, dated June 24, 2013, which is not incorporated by reference in this AD. VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 (ii) Airbus Service Bulletin A320–53–1267, Revision 01, dated October 2, 2013, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A320–53– 1267, Revision 02, dated May 19, 2014, which was incorporated by reference in AD 2015–15–13. (iv) Airbus Service Bulletin A320–53– 1267, Revision 03, dated November 26, 2015, which is not incorporated by reference in this AD. (v) Airbus Service Bulletin A320–53–1267, Revision 04, dated February 1, 2016, which is not incorporated by reference in this AD. (m) Other FAA AD Provisions (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 (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 534126–01–2 534126–01–5 534126–01–3 534126–01–6 534126–01–4 534126–01–7 principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (g)(2) and (h)(2) 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 E:\FR\FM\14DEP1.SGM 14DEP1 Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Proposed Rules changes to procedures or tests identified as RC require approval of an AMOC. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0098, dated June 7, 2017, 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– 2017–1100. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone 425– 227–1405; fax 425–227–1149. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ 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 November 29, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–26362 Filed 12–13–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Office of the Secretary 14 CFR Part 241 Amendatory instructions 3 through 6 of the proposed rule published July 15, 2011 (76 FR 41726), are withdrawn as of December 14, 2017. ADDRESSES: Electronic Access: You can view and download related documents and public comments by going to the website http://www.regulations.gov. Enter the docket number DOT–RITA– 2011–0001 in the search field. FOR FURTHER INFORMATION CONTACT: Zeenat Iqbal and Blane A. Workie, Office of Aviation Enforcement and Proceedings, 1200 New Jersey SE, Room W96–414, Washington, DC 20590, (202) 366–9893, zeenat.iqbal@dot.gov (email). SUPPLEMENTARY INFORMATION: DATES: Background On July 7, 2011, the Office of the Secretary issued a notice of proposed rulemaking (NPRM) proposing to collect detailed information about ancillary fees paid by airline consumers to determine the total amount of fees carriers collect through the a la carte pricing approach for optional services related to air transportation. The Department also proposed to alter its matrix for collecting and publishing data on mishandled baggage and to collect information regarding damage, delay or loss of wheelchairs and scooters transported in the aircraft cargo compartment. The final rule relating to reporting of data for mishandled baggage and wheelchairs (2104–AE41) was issued on November 2, 2016 (81 FR 76300). We are withdrawing the other topic covered in the proposed rule, the reporting of airline fee revenue. [Docket No. RITA–2011–0001] The NPRM RIN 2105–AE31 In the NPRM, the Department proposed to create two stand-alone reporting forms, designated P–9 and P– 9.1, to capture ancillary revenues. Specifically, air carriers with annual reporting revenue of $20 million or more would be required to submit the P–9 form quarterly and air carriers with annual reporting revenue below $20 million would be required to submit the form P–9.1 on a semiannual basis. The information required by the two proposed schedules was identical; they differed only in the required reporting frequency. The NPRM also proposed to define ancillary revenues as those charges paid by airline passengers that are not included in the standard ticket fare. The Department solicited comments on which items should be specifically identified as ancillary revenues, and proposed to collect data on 19 separate charges for optional services. The categories included: (1) Booking fees, (2) priority check-in and Ancillary Airline Passenger Revenues Office of the Secretary, Department of Transportation. ACTION: Proposed rule; withdrawal. AGENCY: The Department of Transportation (the Department) is withdrawing a notice of proposed rulemaking (NPRM) published on July 15, 2011 that proposed to collect detailed revenue information regarding airline imposed fees from those air carriers meeting the definition of a large certificated air carrier. We are withdrawing this rulemaking in light of the comments we received. The withdrawal of this rulemaking corresponds with the Department’s and Administration’s priorities and is consistent with the Executive Order 13771, Reducing Regulation and Controlling Regulatory Costs, January 30, 2017. sradovich on DSK3GMQ082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:01 Dec 13, 2017 Jkt 244001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 58777 security screening, (3) baggage, (4) inflight medical equipment, (5) in-flight entertainment/internet access, (6) sleep sets, (7) in-flight food/non-alcoholic drinks, (8) alcoholic drinks, (9) pets, (10) seating assignments, (11) reservation cancellation and change fees; (12) charges for lost ticket; (13) unaccompanied minor/passenger assistance fee; (14) frequent flyer points/ points acceleration; (15) commissions on travel packages; (16) travel insurance; (17) duty-free and retail sales; (18) one-time access to lounges and (19) other. Comments Received In response to the 2011 NPRM, the Department received approximately 280 comments from airlines, airports, trade associations, unions, consumer groups and private citizens who use this data. There was wide support among consumers and consumer rights groups for the proposed rule’s reporting requirements. Consumers and consumer rights groups, as well as ACI–NA and Southwest Airlines, commented that the reporting requirement would bring the benefits of both increased transparency and improved data corroboration regarding the impact of ancillary fees on the Airport and Airway Trust Fund. On the other hand, most airlines and industry organizations commented that the proposed rule will not benefit the public because the Department has not demonstrated a need for this information. They asserted that the rule will not increase the transparency of pricing for airline revenues. Airlines also commented that if the justification for this rule is to tax ancillary revenues, the Department must state that justification. In addition, several airlines and industry groups suggested that the Department underestimated the proposed rule’s economic burden on industry. With regard to the proposed 19 categories, industry groups, consumer groups and airlines commented that the Department failed to justify the proposed categories and suggested various changes to the list of 19 charges for which air carriers would have to report revenues under the proposed rule. Carriers also expressed concern that the proposed reporting requirements would require carriers to reveal proprietary information to their competitors. Some carriers suggested that there is no correlation between a carrier’s disclosure of itemized aggregate revenue data and consumer concerns regarding fare transparency. Southwest Airlines, which supported the Department’s stated goal of making ticket pricing more transparent for E:\FR\FM\14DEP1.SGM 14DEP1

Agencies

[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Proposed Rules]
[Pages 58772-58777]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26362]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-15-
13, which applies to certain Airbus Model A319 series airplanes; Model 
A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015-
15-13 requires modification of the potable water service panel and 
waste water service panel, including doing applicable related 
investigative and corrective actions. Since we issued AD 2015-15-13, 
further investigations linked to widespread fatigue damage (WFD) 
analysis highlighted that, to meet the WFD requirements, it is 
necessary that the affected modification not be accomplished before 
reaching a certain threshold. This proposed AD would require 
modification of the waste water and potable water service panels with 
new compliance times. This proposed AD would also remove certain 
airplanes from the applicability and add Model A320-216 airplanes to 
the applicability. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by January 29, 
2018.

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, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; 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-
1100; or in person at the Docket

[[Page 58773]]

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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone 425-227-1405; 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-2017-1100; 
Product Identifier 2017-NM-077-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 WFD. 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.
    We issued AD 2015-15-13, Amendment 39-18223 (80 FR 45857, August 3, 
2015) (``AD 2015-15-13''), for certain Airbus Model A319 series 
airplanes; Model A320-211, -212, -214, -231,-232, and -233 airplanes; 
and Model A321 series airplanes. AD 2015-15-13 was prompted by reports 
of cracks that could be initiated at the waste water service panel area 
and the potable water service panel area. AD 2015-15-13 requires 
modification of the potable water service panel and waste water service 
panel, including doing applicable related investigative and corrective 
actions. We issued AD 2015-15-13 to prevent any cracking at the waste 
water service panel area and the potable water service panel area, 
which could affect the structural integrity of the airplane.
    Since we issued AD 2015-15-13, further investigations linked to WFD 
analysis highlighted that, to meet the WFD requirements, it is 
necessary that the affected modification is not accomplished before 
reaching a certain threshold by imposing a ``window of embodiment.''
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0098, dated June 7, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319 series airplanes; Airbus Model A320-211, -212, -214, -216, -231, -
232, and -233 airplanes; and Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. The MCAI states:

    During the full scale fatigue test on A320-200, it was noticed 
that, due to fatigue, cracks could initiate at the potable water and 
waste water service panel areas.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Prompted by these findings, Airworthiness Limitation Section 
(ALS) Part 2 tasks were introduced for the affected aeroplanes. 
Since those actions were taken, Airbus developed production mod 
160055 and mod 160056 to embody reinforcements (cold working on 
certain rivet rows) of the potable water and waste water service 
panels, and published associated Airbus Service Bulletin (SB) A320-
53-1272 and Airbus SB A320-53-1267 for in-service embodiment. 
Complementary design office studies highlighted that the 
``Sharklets'' installation on certain aeroplanes has a significant 
impact on the aeroplane structure (particularly, A319 and A320 post-
mod 160001, A320 post-SB A320-57-1193 (mod 160080), and A321 post-
mod 160021), leading to different compliance times, depending on 
aeroplane configuration.
    Consequently, EASA issued AD 2014-0081 [which corresponds to FAA 
AD 2015-15-13] to require reinforcement of the potable water and 
waste water service panels. Accomplishment of these modifications 
cancelled the need for the related ALS Part 2 Tasks.
    Since that AD was issued, further investigations linked to the 
Widespread Fatigue Damage (WFD) analysis highlighted that, to meet 
the WFD requirements, it is necessary that the affected modification 
is not accomplished before reaching a certain threshold, by imposing 
a so-called ``window of embodiment''. Consequently, Airbus revised 
SB A320-53-1272 (now at revision (Rev.) 04) and SB A320-53-1267 (now 
at Rev. 05).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0081, which is superseded, and 
introduces additional compliance times for those actions.

    This proposed AD would also remove Model A319 series airplanes on 
which modification 28162, 28238, and 28342 have been embodied 
(``Corporate Jet'' modifications) from the applicability because 
production modifications

[[Page 58774]]

mitigated the risk associated with the unsafe condition. This proposed 
AD would also add Model A320-216 airplanes to the applicability because 
those airplanes are affected by the identified unsafe condition.
    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-
1100.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1267, Revision 05, dated 
November 29, 2016, which describes procedures for modifying the waste 
water service panel. Airbus has also issued Service Bulletin A320-53-
1272, Revision 04, dated November 29, 2016, which describes procedures 
for modifying the potable water service panel. Both modifications 
include a check of the diameter of the holes of removed fasteners, a 
related investigative action (rotating probe inspection for cracking on 
the holes of the removed fasteners) and a corrective action (repair). 
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 the same 
type design.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced 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 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 27 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $700 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $2,548,745, or $2,995 per product.
    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 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 removing Airworthiness Directive (AD) 
2015-15-13, Amendment 39-18223 (80 FR 45857, August 3, 2015), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-1100; Product Identifier 2017-NM-077-AD.

(a) Comments Due Date

    We must receive comments by January 29, 2018.

(b) Affected ADs

    This AD replaces AD 2015-15-13, Amendment 39-18223 (80 FR 45857, 
August 3, 2015) (``AD 2015-15-13'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
except for those airplanes on which Airbus modification 160055 or 
modification 160056 has been embodied in production, and except for 
Model A319 series airplanes on which modification 28162, 28238, and 
28342 have been embodied (``Corporate Jet'').
    (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (2) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.
    (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 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

[[Page 58775]]

that the potable water and waste water service panel areas are 
subject to widespread fatigue damage (WFD). We are issuing this AD 
to prevent cracking of the potable water and waste water service 
panel areas, 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) Modification of the Potable Water Service Panel

    (1) Within the compliance times specified in Table 1 to 
paragraphs (g)(1) and (i) of this AD, as applicable, modify the 
potable water service panel, including doing a check of the diameter 
of the holes of removed fasteners, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1272, 
Revision 04, dated November 29, 2016, except as required by 
paragraph (g)(2) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

     Table 1 to Paragraphs (g)(1) and (i) of This AD--Compliance Times for the Portable Water Service Panel
                                                  Reinforcement
----------------------------------------------------------------------------------------------------------------
                                                                                      Compliance time maximum
                                                                                    (before the accumulation of
               Affected airplanes *                   Compliance time minimum **     the specified total flight
                                                                                    cycles since the airplane's
                                                                                           first flight)
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service       33,100 total flight cycles...  48,500 total flight cycles.
 bulletin A320-57-1193.
A319, post-modification 160001 or post-service      None.........................  46,000 total flight cycles.
 bulletin A320-57-1193.
A320, pre-modification 160001 and pre-service       25,100 total flight cycles...  54,200 total flight cycles.
 bulletin A320-57-1193.
A320, post-modification 160001 or post-service      None.........................  48,300 total flight cycles.
 bulletin A320-57-1193.
A321-100..........................................  25,100 total flight cycles...  60,000 total flight cycles.
A321-200 pre[dash]modification 160021.............  22,100 total flight cycles...  60,000 total flight cycles.
A321-200 post[dash]modification 160021............  None.........................  60,000 total flight cycles.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321[dash]131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-
  211, A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321[dash]200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.

    (2) Where Airbus Service Bulletin A320-53-1272, Revision 04, 
dated November 29, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (m)(2) of this 
AD.

(h) Modification of the Waste Water Service Panel

    (1) Within the compliance times specified in Table 2 to 
paragraphs (h)(1) and (i) of this AD, as applicable, modify the 
waste water service panel, including doing a check of the diameter 
of the holes of removed fasteners, and do all applicable related 
investigative and corrective actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1267, 
Revision 05, dated November 29, 2016, except as required by 
paragraph (h)(2) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

       Table 2 to Paragraphs (h)(1) and (i) of This AD--Compliance Times for the Waste Water Service Panel
                                                  Reinforcement
----------------------------------------------------------------------------------------------------------------
     Affected airplanes *                  Compliance time minimum **                Compliance time maximum
----------------------------------------------------------------------------------------------------------------
A319, pre-modification 160001   28,600 total flight cycles.....................  Before the accumulation of
 and pre-service bulletin A320-                                                   44,400 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A319, post-modification 160001  None...........................................  Before the accumulation of
 or post-service bulletin A320-                                                   43,600 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A320, pre-modification 160001   35,800 total flight cycles.....................  Before the accumulation of
 and pre-service bulletin A320-                                                   46,000 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight; or within 2,300 flight
                                                                                  cycles since the last
                                                                                  accomplishment of
                                                                                  Airworthiness Limitation
                                                                                  Section (ALS) Part 2 Task
                                                                                  534126-01-3 without exceeding
                                                                                  48,000 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight; whichever occurs
                                                                                  later.
A320, post-modification 160001  5,400 total flight cycles......................  Before the accumulation of
 or post-service bulletin A320-                                                   39,200 total flight cycles
 57-1193.                                                                         since the airplane's first
                                                                                  flight.
A321-100......................  36,900 total flight cycles.....................  Before the accumulation of
                                                                                  52,500 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
A321-200 pre-modification       35,700 total flight cycles.....................  Before the accumulation of
 160021.                                                                          53,500 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
A321-200 post-modification      None...........................................  Before the accumulation of
 160021.                                                                          51,200 total flight cycles
                                                                                  since the airplane's first
                                                                                  flight.
----------------------------------------------------------------------------------------------------------------
* A321-111, A321-112 and A321-131 airplanes are collectively referred to as ``A321-100.'' Similarly, A321-211,
  A321-212, A321-213, A321-231 and A321-232 airplanes are collectively referred to as ``A321-200''.
** Not before accumulating the specified total flight cycles since the airplane's first flight.

    (2) Where Airbus Service Bulletin A320-53-1267, Revision 05, 
dated November 29, 2016, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (m)(2) of this 
AD.

(i) Corrective Action for Airplanes With Certain Modifications

    For airplanes on which the modification, as required by 
paragraph (g) or (h) of this AD,

[[Page 58776]]

as applicable, was accomplished before reaching the applicable 
minimum compliance time as defined in Table 1 to paragraphs (g)(1) 
and (i) of this AD or Table 2 to paragraphs (h)(1) and (i) of this 
AD: Before exceeding 60,000 flight cycles since the airplane's first 
flight, contact the Manager, International Section, Transport 
Standards Branch, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA) for 
approved corrective action instructions and accomplish those 
instructions accordingly.

(j) Terminating Action for Airplanes on Which the Potable Water Service 
Panel Modification Is Done

    Modification of an airplane as required by paragraph (g) of this 
AD terminates the requirement for accomplishing the ALS Part 2 task 
for that airplane as specified in Table 3 to paragraph (j) of this 
AD, as applicable.

  Table 3 to Paragraph (j) of This AD--ALS Part 2 Task Terminated After
                Potable Water Service Panel Modification
------------------------------------------------------------------------
                                                            ALS Part 2
                   Affected airplanes                        task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin       534125-01-2
 A320-57-1193...........................................
A319, post-modification 160001 or post-service bulletin      534125-01-5
 A320-57-1193...........................................
A320, pre-modification 160001 and pre-service bulletin       534125-01-3
 A320-57-1193...........................................
A320, post-modification 160001 or post-service bulletin      534125-01-6
 A320-57-1193...........................................
A321 pre-modification 160021............................     534125-01-4
A321 post-modification 160021...........................     534125-01-7
------------------------------------------------------------------------

(k) Terminating Action for Airplanes on Which the Waste Water Service 
Panel Modification Is Done

    Modification of an airplane as required by paragraph (h) of this 
AD terminates the requirement for accomplishing the ALS Part 2 task 
for that airplane as specified in Table 4 to paragraph (k) of this 
AD, as applicable.

  Table 4 to Paragraph (k) of This AD--ALS Part 2 Task Terminated After
                 Waste Water Service Panel Modification
------------------------------------------------------------------------
                                                            ALS Part 2
                   Affected airplanes                        task No.
------------------------------------------------------------------------
A319, pre-modification 160001 and pre-service bulletin       534126-01-2
 A320[dash]57-1193......................................
A319, post-modification 160001 or post-service bulletin      534126-01-5
 A320[dash]57-1193......................................
A320, pre-modification 160001 and pre-service bulletin       534126-01-3
 A320[dash]57-1193......................................
A320, post-modification 160001 or post-service bulletin      534126-01-6
 A320[dash]57-1193......................................
A321 pre-modification 160021............................     534126-01-4
A321 post-modification 160021...........................     534126-01-7
------------------------------------------------------------------------

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD if those actions were performed before the 
effective date of this AD using the service information in 
paragraphs (l)(1)(i) through (l)(1)(iv) of this AD.
    (i) Airbus Service Bulletin A320-53-1272, Revision 00, dated 
January 10, 2013, which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-53-1272, Revision 01, dated 
August 6, 2013, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A320-53-1272, Revision 02, dated 
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
    (iv) Airbus Service Bulletin A320-53-1272, Revision 03, dated 
November 26, 2015, which is not incorporated by reference in this 
AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD if those actions were performed before the 
effective date of this AD using the service information in 
paragraphs (l)(2)(i) through (l)(2)(v) of this AD.
    (i) Airbus Service Bulletin A320-53-1267, Revision 00, dated 
June 24, 2013, which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-53-1267, Revision 01, dated 
October 2, 2013, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A320-53-1267, Revision 02, dated 
May 19, 2014, which was incorporated by reference in AD 2015-15-13.
    (iv) Airbus Service Bulletin A320-53-1267, Revision 03, dated 
November 26, 2015, which is not incorporated by reference in this 
AD.
    (v) Airbus Service Bulletin A320-53-1267, Revision 04, dated 
February 1, 2016, which is not incorporated by reference in this AD.

(m) Other FAA AD Provisions

    (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 (n)(2) of this AD. Information 
may be emailed to: [email protected]. 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: As of the effective date of 
this AD, 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 EASA; or Airbus's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (g)(2) and (h)(2) 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

[[Page 58777]]

changes to procedures or tests identified as RC require approval of 
an AMOC.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0098, dated June 7, 2017, 
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-2017-1100.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; 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 November 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26362 Filed 12-13-17; 8:45 am]
BILLING CODE 4910-13-P