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 https://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 https://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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, 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 https://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 https:// 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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 https:// 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 https://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 https://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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus,
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 https://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 https://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 https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

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
https://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.

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 https://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 https://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

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