Airworthiness Directives; Airbus Airplanes, 34453-34456 [2017-15481]

Download as PDF Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules with the requirements of paragraphs (l)(1) and (l)(2) of this AD. (1) For all fastener holes where no damage or cracks were detected (i.e., those not repaired), accomplish the actions required by paragraph (g) of this AD, unless the terminating action specified in paragraph (m) of this AD has been done. (2) For all repaired fastener holes: Within 30 days after the effective date of this AD, or within a compliance time approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the EASA; or Airbus’s EASA DOA, whichever occurs later, contact the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the EASA; or Airbus’s EASA DOA; for inspection instructions and applicable corrective actions, and do the inspections and applicable corrective actions accordingly. (m) Terminating Action for Certain Airplanes For airplanes that have been inspected, as specified in ALI task 534129 or task 534130, and repaired before the effective date of this AD, as specified in the applicable structural repair manual, or as specified in an Airbus RDAS: Modification of the four fastener holes at door stop locations where no damage or crack was detected (i.e., door stop locations not repaired) by cold working holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1290, Revision 01, dated October 3, 2016, constitutes terminating action for the repetitive inspections of those four fastener holes at those door stop locations as required by paragraph (g) or (l)(1) of this AD for that airplane. asabaliauskas on DSKBBY8HB2PROD with PROPOSALS (n) Actions for Airplanes With Certain Repairs For an airplane that has been repaired before the effective date of this AD in the areas described in this AD using an Airbus RDAS unrelated to ALI task 534129 or task 534130: Before exceeding the compliance times specified in paragraph (g) of this AD, contact the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the EASA; or Airbus’s EASA DOA; for corrective action instructions and accomplish those instructions accordingly. Accomplishment of corrective action(s) on an airplane, as required by this paragraph, does not constitute terminating action for the repetitive inspections as required by paragraph (g) or (j) of this AD for that airplane, as applicable, unless specified otherwise in the instructions. (o) Terminating Action for ALI Tasks (1) Accomplishment of inspections on an airplane, as required by paragraph (g), (j), or (l) of this AD, as applicable, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for that airplane. (2) Modification of the four fastener holes at a door stop location of an airplane as specified in paragraph (i) or (m) of this AD, as applicable, and subsequent initial inspection required by paragraph (j) of this AD, constitutes terminating action for the VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 inspection requirements of ALI task 534129 or task 534130, as applicable, for those holes for that airplane. Subsequent repetitive inspections are required by paragraph (j) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1288, including Appendixes 01 and 02, dated October 10, 2014. (2) This paragraph provides credit for actions required by paragraphs (i) and (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1290, dated October 10, 2014. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 manager of the International Branch, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-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 Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0238, dated December 2, 2016, corrected January 4, 2017, for related information. This MCAI may be found in the AD docket on the Internet at PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 34453 http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0707. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 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 Airplane Directorate, 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 July 13, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–15485 Filed 7–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0709; Directorate Identifier 2016–NM–200–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. This proposed AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. This proposed AD would require repetitive inspections for cracking of the external bottom skin in certain areas on the left and right wings, and corrective actions if necessary. This proposed AD also provides an optional terminating modification for the repetitive inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 8, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: E:\FR\FM\25JYP1.SGM 25JYP1 34454 Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. asabaliauskas on DSKBBY8HB2PROD with PROPOSALS 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– 0709; 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. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 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– 2017–0709; Directorate Identifier 2016– NM–200–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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0222, dated November 7, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318 and A319 series airplanes; and Model A320– 211, –212, –214, –216, –231, –232, and –233 airplanes. The MCAI states: During installation in production of new wing box ribs on post-mod 39729 aeroplanes, it was discovered that the centre wing lower rib foot angle was not matching with the bottom skin panel inner surface. This condition, if not detected and corrected, could induce fatigue cracking of the skin panel at the rib foot attachment, with possible detrimental effect on wing structural integrity. This condition was initially addressed by Airbus on the production line through adaptation mod 152155, then through mod 152200. For affected aeroplanes in service, Airbus issued Service Bulletin (SB) A320– 57–1205, providing instructions for repetitive detailed inspections (DET) or special detailed inspections (SDI), and SB A320–57–1207, providing modification instructions. For the reasons described above, this [EASA] AD requires repetitive inspections (DET or SDI) of the wing bottom skin lower surface for crack detection and, depending on findings, the accomplishment of applicable corrective action(s). This [EASA] AD also includes reference to an optional modification (Airbus SB A320–57–1207), providing terminating action for the repetitive inspections required by this [EASA] AD. The corrective action for cracking is to repair using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; EASA; or Airbus’s EASA Design Organization Approval. 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– 0709. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–57–1205, dated May 26, 2016. This service information describes procedures for inspecting the external bottom skin for cracking in the area of the rib 2 attachment between stringer 8 and stringer 11 on both wings, and repairing any cracks. Airbus has also issued Service Bulletin A320–57–1207, including Appendix 01 and Appendix 02, dated May 26, 2016. This service information describes procedures for inspecting the lower rib feet (rib 2) and the bottom skin upper surface on both wings for cracking, modifying the wings by installing shims between the lower rib foot (rib 2) and the bottom skin upper surface, and repairing any cracks. 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. Costs of Compliance We estimate that this proposed AD affects 10 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection .......... 5 work-hours × $85 per hour = $425 per inspection cycle. VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Parts cost Frm 00028 Fmt 4702 Cost per product $0 Sfmt 4702 $425 per inspection cycle ..... E:\FR\FM\25JYP1.SGM 25JYP1 Cost on U.S. operators $4,250 per inspection cycle. Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules 34455 ESTIMATED COSTS FOR OPTIONAL ACTIONS Action Labor cost Modification ................................................. 32 work-hours × $85 per hour = $2,720 ....................................... We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. According to the manufacturer, some of the costs of the optional modification of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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. Regulatory Findings asabaliauskas on DSKBBY8HB2PROD with PROPOSALS 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. Parts cost Cost per product $5,750 $8,470 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. Airbus Modification 39729 was embodied in production, except those airplanes on which Airbus Modification 152155 or Modification 152200 was embodied in production. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. This AD was prompted by a report indicating that the lower rib foot angle of the center wing box did not match with the bottom skin panel inner surface. Misalignment of the lower rib foot angle of the center wing box with the bottom skin panel inner surface could induce fatigue cracking of the skin panel at the rib foot attachment. We are issuing this AD to detect and correct cracking of the external bottom skin in the area of the rib 2 attachment of the wings, which could result in reduced structural integrity of the wing. 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 Air Transport Association (ATA) of America Code 57, wings. (e) Reason (f) Compliance 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (d) Subject [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2017–0709; Directorate Identifier 2016–NM–200–AD. (a) Comments Due Date We must receive comments by September 8, 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 on which Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before exceeding the applicable compliance time specified in table 1 to paragraph (g) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Do a detailed inspection or a special detailed inspection for cracking of the external bottom skin in the area of the rib 2 attachment between stringer 8 and stringer 11 of the left and right wings, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1205, dated May 26, 2016. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable intervals, based on the method used for the most recent inspection, as specified in table 2 to paragraph (g) of this AD. TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES Airplane model and configuration Compliance time—whichever occurs first since first flight of the airplane Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; preAirbus Modification 155374; not used as VIP or Elite. Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; postAirbus Modification 155374; not used as VIP or Elite. Before the accumulation of 14,500 total flight cycles or 29,000 total flight hours. VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 PO 00000 Frm 00029 Fmt 4702 Before the accumulation of 13,600 total flight cycles or 27,300 total flight hours. Sfmt 4702 E:\FR\FM\25JYP1.SGM 25JYP1 34456 Federal Register / Vol. 82, No. 141 / Tuesday, July 25, 2017 / Proposed Rules TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION TIMES—Continued Airplane model and configuration Compliance time—whichever occurs first since first flight of the airplane Model A319 series airplanes; post-Airbus Modifications 28162, 28238, and 28342; used as VIP or CJ. Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite. Before the accumulation of 7,400 total flight cycles or 32,000 total flight hours. Before the accumulation of 14,500 total flight cycles or 43,500 total flight hours. TABLE 2 TO PARAGRAPH (g) OF THIS AD—REPETITIVE INSPECTION INTERVALS Airplane model and configuration Detailed inspection—whichever occurs first Special detailed inspection—whichever occurs first Model A318 series airplanes; Model A319 series airplanes; and Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; not used as VIP or Elite. Model A319 series airplanes; post-Airbus Modifications 28162, 28238, and 28342; used as VIP or CJ. Model A318 series airplanes; post-Airbus Modification 39195; used as VIP or Elite. 4,000 flight cycles or 8,000 flight hours ... 5,000 flight cycles or 10,000 flight hours. 2,000 flight cycles or 8,600 flight hours ... 2,500 flight cycles or 11,000 flight hours. 4,000 flight cycles or 12,000 flight hours 5,000 flight cycles or 15,000 flight hours. Note 1 to paragraph (g) of this AD: Airbus Modification 155374 defines the minimum airplane configuration for operation on Commonwealth of Independent States runway profiles. (h) Terminating Action Limitation Repair of an airplane, as required by paragraph (g) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD unless otherwise specified in the instructions obtained using the procedures specified in paragraph (j)(2) of this AD. asabaliauskas on DSKBBY8HB2PROD with PROPOSALS (i) Optional Terminating Action Modification of the wings including a detailed inspection of the lower rib feet (rib 2) and bottom skin upper surface of the wings for cracking and all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1207, including Appendix 01 and Appendix 02, dated May 26, 2016, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. If, during modification of an airplane as specified in this paragraph, accomplishment of any modification instruction is not possible due to configuration difficulties, accomplish the modification using the procedures specified in paragraph (j)(1) of this AD. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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 manager of the International Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116- VerDate Sep<11>2014 17:17 Jul 24, 2017 Jkt 241001 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 Branch, ANM– 116, Transport Airplane Directorate, 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): 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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0222, dated November 7, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0709. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 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 PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 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 Airplane Directorate, 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 July 14, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–15481 Filed 7–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [REG–112800–16] RIN 1545–BN42 Nuclear Decommissioning Funds; Hearing Internal Revenue Service (IRS), Treasury. ACTION: Notice of a public hearing on notice of proposed rulemaking. AGENCY: This document provides a notice of public hearing on proposed changes to the regulations under section 468A of the Internal Revenue Code of 1986 (Code) relating to deductions for contributions to trusts maintained for decommissioning nuclear power plants and the use of the amounts in those trusts to decommission nuclear plants. DATES: The public hearing is being held on Wednesday, October 25, 2017 at SUMMARY: E:\FR\FM\25JYP1.SGM 25JYP1

Agencies

[Federal Register Volume 82, Number 141 (Tuesday, July 25, 2017)]
[Proposed Rules]
[Pages 34453-34456]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15481]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0709; Directorate Identifier 2016-NM-200-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 
certain Airbus Model A318 series airplanes; Model A319 series 
airplanes; and Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes. This proposed AD was prompted by a report indicating that 
the lower rib foot angle of the center wing box did not match with the 
bottom skin panel inner surface. This proposed AD would require 
repetitive inspections for cracking of the external bottom skin in 
certain areas on the left and right wings, and corrective actions if 
necessary. This proposed AD also provides an optional terminating 
modification for the repetitive inspections. We are proposing this AD 
to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 8, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR

[[Page 34454]]

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 Airplane Directorate, 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-
0709; 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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, 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-2017-0709; 
Directorate Identifier 2016-NM-200-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0222, dated November 7, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A318 and A319 
series airplanes; and Model A320-211, -212, -214, -216, -231, -232, and 
-233 airplanes. The MCAI states:

    During installation in production of new wing box ribs on post-
mod 39729 aeroplanes, it was discovered that the centre wing lower 
rib foot angle was not matching with the bottom skin panel inner 
surface.
    This condition, if not detected and corrected, could induce 
fatigue cracking of the skin panel at the rib foot attachment, with 
possible detrimental effect on wing structural integrity.
    This condition was initially addressed by Airbus on the 
production line through adaptation mod 152155, then through mod 
152200. For affected aeroplanes in service, Airbus issued Service 
Bulletin (SB) A320-57-1205, providing instructions for repetitive 
detailed inspections (DET) or special detailed inspections (SDI), 
and SB A320-57-1207, providing modification instructions.
    For the reasons described above, this [EASA] AD requires 
repetitive inspections (DET or SDI) of the wing bottom skin lower 
surface for crack detection and, depending on findings, the 
accomplishment of applicable corrective action(s). This [EASA] AD 
also includes reference to an optional modification (Airbus SB A320-
57-1207), providing terminating action for the repetitive 
inspections required by this [EASA] AD.

    The corrective action for cracking is to repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; EASA; or Airbus's EASA Design Organization 
Approval. 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-2017-0709.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-57-1205, dated May 26, 
2016. This service information describes procedures for inspecting the 
external bottom skin for cracking in the area of the rib 2 attachment 
between stringer 8 and stringer 11 on both wings, and repairing any 
cracks.
    Airbus has also issued Service Bulletin A320-57-1207, including 
Appendix 01 and Appendix 02, dated May 26, 2016. This service 
information describes procedures for inspecting the lower rib feet (rib 
2) and the bottom skin upper surface on both wings for cracking, 
modifying the wings by installing shims between the lower rib foot (rib 
2) and the bottom skin upper surface, and repairing any cracks.
    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.

Costs of Compliance

    We estimate that this proposed AD affects 10 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
           Action                  Labor cost         Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.................  5 work-hours x $85                 $0  $425 per inspection    $4,250 per inspection
                              per hour = $425 per                    cycle.                 cycle.
                              inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 34455]]


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Modification..................................  32 work-hours x $85 per hour =            $5,750          $8,470
                                                 $2,720.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of the optional 
modification of this proposed AD may be covered under warranty, thereby 
reducing the cost impact on affected individuals. We do not control 
warranty coverage for affected individuals. As a result, we have 
included all available costs in our cost estimate.

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.

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-2017-0709; Directorate Identifier 2016-NM-
200-AD.

(a) Comments Due Date

    We must receive comments by September 8, 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 on which Airbus Modification 39729 
was embodied in production, except those airplanes on which Airbus 
Modification 152155 or Modification 152200 was embodied in 
production.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, wings.

(e) Reason

    This AD was prompted by a report indicating that the lower rib 
foot angle of the center wing box did not match with the bottom skin 
panel inner surface. Misalignment of the lower rib foot angle of the 
center wing box with the bottom skin panel inner surface could 
induce fatigue cracking of the skin panel at the rib foot 
attachment. We are issuing this AD to detect and correct cracking of 
the external bottom skin in the area of the rib 2 attachment of the 
wings, which could result in reduced structural integrity of the 
wing.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections

    Before exceeding the applicable compliance time specified in 
table 1 to paragraph (g) of this AD, or within 3 months after the 
effective date of this AD, whichever occurs later: Do a detailed 
inspection or a special detailed inspection for cracking of the 
external bottom skin in the area of the rib 2 attachment between 
stringer 8 and stringer 11 of the left and right wings, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1205, dated May 26, 
2016. Do all applicable corrective actions before further flight. 
Repeat the inspection thereafter at the applicable intervals, based 
on the method used for the most recent inspection, as specified in 
table 2 to paragraph (g) of this AD.

      Table 1 to Paragraph (g) of This AD--Initial Inspection Times
------------------------------------------------------------------------
                                            Compliance time--whichever
    Airplane model and configuration     occurs first since first flight
                                                 of the airplane
------------------------------------------------------------------------
Model A318 series airplanes; Model A319  Before the accumulation of
 series airplanes; and Model A320-211, -  14,500 total flight cycles or
 212, -214, -216, -231, -232, and -233    29,000 total flight hours.
 airplanes; pre-Airbus Modification
 155374; not used as VIP or Elite.
Model A318 series airplanes; Model A319  Before the accumulation of
 series airplanes; and Model A320-211, -  13,600 total flight cycles or
 212, -214, -216, -231, -232, and -233    27,300 total flight hours.
 airplanes; post-Airbus Modification
 155374; not used as VIP or Elite.

[[Page 34456]]

 
Model A319 series airplanes; post-       Before the accumulation of
 Airbus Modifications 28162, 28238, and   7,400 total flight cycles or
 28342; used as VIP or CJ.                32,000 total flight hours.
Model A318 series airplanes; post-       Before the accumulation of
 Airbus Modification 39195; used as VIP   14,500 total flight cycles or
 or Elite.                                43,500 total flight hours.
------------------------------------------------------------------------


                      Table 2 to Paragraph (g) of This AD--Repetitive Inspection Intervals
----------------------------------------------------------------------------------------------------------------
                                                                                 Special detailed inspection--
     Airplane model and configuration        Detailed inspection--whichever          whichever occurs first
                                                      occurs first
----------------------------------------------------------------------------------------------------------------
Model A318 series airplanes; Model A319    4,000 flight cycles or 8,000        5,000 flight cycles or 10,000
 series airplanes; and Model A320-211, -    flight hours.                       flight hours.
 212, -214, -216, -231, -232, and -233
 airplanes; not used as VIP or Elite.
Model A319 series airplanes; post-Airbus   2,000 flight cycles or 8,600        2,500 flight cycles or 11,000
 Modifications 28162, 28238, and 28342;     flight hours.                       flight hours.
 used as VIP or CJ.
Model A318 series airplanes; post-Airbus   4,000 flight cycles or 12,000       5,000 flight cycles or 15,000
 Modification 39195; used as VIP or Elite.  flight hours.                       flight hours.
----------------------------------------------------------------------------------------------------------------

    Note 1 to paragraph (g) of this AD: Airbus Modification 155374 
defines the minimum airplane configuration for operation on 
Commonwealth of Independent States runway profiles.

(h) Terminating Action Limitation

    Repair of an airplane, as required by paragraph (g) of this AD, 
does not constitute terminating action for the repetitive 
inspections required by paragraph (g) of this AD unless otherwise 
specified in the instructions obtained using the procedures 
specified in paragraph (j)(2) of this AD.

(i) Optional Terminating Action

    Modification of the wings including a detailed inspection of the 
lower rib feet (rib 2) and bottom skin upper surface of the wings 
for cracking and all applicable corrective actions, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-57-1207, including Appendix 01 and Appendix 02, dated May 26, 
2016, constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD for that airplane. If, during 
modification of an airplane as specified in this paragraph, 
accomplishment of any modification instruction is not possible due 
to configuration difficulties, accomplish the modification using the 
procedures specified in paragraph (j)(1) of this AD.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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 manager of the 
International Branch, send it to the attention of the person 
identified in paragraph (k)(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 
Branch, ANM-116, Transport Airplane Directorate, 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): 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0222, dated November 7, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2017-0709.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, 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 Airplane Directorate, 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 July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15481 Filed 7-24-17; 8:45 am]
 BILLING CODE 4910-13-P