Airworthiness Directives; Airbus Airplanes, 55955-55958 [2017-25252]

Download as PDF Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules pmangrum on DSK3GDR082PROD with PROPOSALS1 amend §§ 50.82(a) and 52.110 to clarify that licensees must evaluate the environmental impacts of decommissioning, and whether they are bounded, in the PSDAR; (4) to amend § 50.59(d)(3); § 50.71(c); 10 CFR part 50, appendix A, Criterion 1, ‘‘Quality standards and records’’; 10 CFR part 50, appendix B, Criterion XVII, ‘‘Quality Assurance Records’’; and § 72.72(d) to remove certain record-retention requirements for structures, systems, and components (SSCs) that no longer remain in service during decommissioning, as well as duplication requirements for spent fuel storage records; and (5) to amend 10 CFR part 20, appendix G, Section III.E, for investigating shipments of low-level radioactive waste (LLW) if the shipper has not received notification of receipt within 20 days after transfer, to allow a 45-day notification window based on operating experience that shows this is a reasonable delay for LLW shipments. Additionally in this regulatory basis, the NRC staff recommends guidance development and inspection procedure updates for minimum staffing of nonlicensed operators and aging management of certain SSCs. The NRC staff also determined that fatigue management would not be addressed in this decommissioning rule. In the regulatory basis, the NRC staff reiterated conclusions from the draft regulatory basis that regulatory activities other than rulemaking—such as guidance development—can be pursued to address the appropriate role of State and local governments in the decommissioning process, the level of NRC review of the PSDAR, and the 60year limit for power reactor decommissioning. In addition to the regulatory basis, staff plans to publish a revised preliminary draft of the regulatory analysis, which will update and refine the analysis of costs and benefits. The NRC staff plans to publish a proposed rule for public comment in 2018. Dated at Rockville, Maryland, this 21st day of November 2017. For the Nuclear Regulatory Commission. Patricia K. Holahan, Director, Division of Rulemaking, Office of Nuclear Material Safety and Safeguards. [FR Doc. 2017–25552 Filed 11–24–17; 8:45 am] BILLING CODE 7590–01–P VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1093; Product Identifier 2017–NM–018–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; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. This proposed AD would require repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, would provide an optional terminating action to 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 January 11, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to 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 Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on SUMMARY: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 55955 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– 1093; 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–1093; Product Identifier 2017– NM–018–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 2016–0139, dated July 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Model A318 series airplanes; A319 series airplanes; A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: Following addition of a new airworthiness limitation item (ALI) task 531110 in the E:\FR\FM\27NOP1.SGM 27NOP1 55956 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules Airworthiness Limitation Section (ALS) Part 2 in the revision dated April 2012, numerous findings have been reported of early cracks on the four holes of the crossbeam splicing at frame (FR)16 and FR20 on both left-hand (LH) and right-hand (RH) sides. This condition, if not detected and corrected, could affect the structural integrity of the airframe. To allow an earlier crack detection, Airbus decided to transfer the repetitive inspections from ALI task 531110 to Airbus Service Bulletin (SB) A320–53–1286, later revised, including new recommended inspection thresholds. For the reasons described above, this [EASA] AD requires repetitive special detailed [rototest] inspections (SDI) of the two upper rows of fasteners of the crossbeam splicing at FR16 and FR20, on both LH and RH sides, [installation of new fasteners on crack-free frames, related investigative and corrective actions,] and, depending on aeroplane configuration, provides an optional terminating action to the repetitive inspections required by this [EASA] AD. Related investigative actions include checking the edge margins of the holes. Corrective actions include reaming affected crossbeams and frames and cold working the frames. 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– 1093. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A320–53– 1286, Revision 01, dated December 22, 2015, which describes procedures for rototest inspections for cracking of the holes in certain fuselage frames and crossbeams. • Airbus Service Bulletin A320–53– 1295, including Appendixes 01 and 02, dated June 29, 2015, which describes procedures for modifying the airplane, including cold working instructions in certain fuselage frames and crossbeams. 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. Difference Between This Proposed AD and the MCAI or Service Information Where the MCAI, paragraph (4), specifies a repair approved by EASA or under a Design Organization Approval (DOA) other than Airbus, paragraph (j) of this proposed AD refers to a repair approved by the FAA, EASA, or an EASA DOA other than Airbus. The MCAI did not specify whether FAA approved repairs are acceptable for compliance. Costs of Compliance We estimate that this proposed AD affects 928 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspections ......................... 116 work-hours × $85 per hour = $9,860 per inspection. 28 work-hours × $85 per hour = $2,380 ........................ Optional Modification .......... We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. pmangrum on DSK3GDR082PROD with PROPOSALS1 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 VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 Parts cost products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings Frm 00003 Fmt 4702 $960 $10,820 3,020 5,400 Cost on U.S. operators $10,040,960. Up to $5,011,200. 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 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. PO 00000 Cost per product Sfmt 4702 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: E:\FR\FM\27NOP1.SGM 27NOP1 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2017–1093; Product Identifier 2017–NM–018–AD. (a) Comments Due Date We must receive comments by January 11, 2018. (b) Affected ADs None. 111, –112, –131, –211, –212, –213, –231, and –232 airplanes, certificated in any category, all manufacturer serial numbers, except the airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airplanes on which Airbus modification 161255 has been embodied in production. (2) Model A319 series airplanes on which Airbus modifications 28238, 28162, and 28342 have been concurrently embodied in production. (3) Model A318 series airplanes on which Airbus modification 39195 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason (c) Applicability This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; A319– 111, –112, –113, –114, –115, –131, –132, and –133 airplanes; A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and A321– This AD was prompted by reports of early cracking on the four holes of the crossbeam splicing at certain fuselage frames (FR). We are issuing this AD to detect and correct cracking at two upper rows of fasteners of the crossbeam splicing at FR16 and FR20, on both the left-hand (LH) and right-hand (RH) 55957 sides, which can result in reduced structural integrity of the airplane due to the failure of structural components. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Rototest Inspections Before exceeding the threshold specified in table 1 to paragraph (g) of this AD, or table 2 to paragraph (g) of this AD, as applicable to airplane configuration (pre- or postmodification 20416 or pre- or postmodification 21999): Do a special detailed (rototest) inspection of the two upper rows of fasteners of the crossbeam splicing at FR16 and FR20 on both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1286, Revision 01, dated December 22, 2015. Thereafter, repeat the inspection at the intervals specified in table 1 to paragraph (g) of this AD, or table 2 to paragraph (g) of this AD, as applicable to airplane configuration (pre- or post-modification 20416 or pre- or post-modification 21999). TABLE 1 TO PARAGRAPH (g) OF THIS AD—INSPECTION OF PRE-MODIFICATION 20416 OR PRE-MODIFICATION 21999 AIRPLANES Threshold (A or B or C, whichever occurs later). Repetitive Inspection Interval (Not to exceed). A: Before exceeding 36,800 flight cycles (FC) or 73,600 flight hours (FH), whichever occurs first since the first flight of the airplane. B: Within 27,400 FC or 54,900 FH, whichever occurs first since the last inspection as specified in airworthiness limitation item (ALI) task 531110–01–1 accomplished before the effective date of this AD. C: Within 30 days after the effective date of this AD, without exceeding 38,800 FC or 77,600 FH, whichever occurs first since the first flight of the airplane. 27,400 FC or 54,900 FH, whichever occurs first. TABLE 2 TO PARAGRAPH (g) OF THIS AD—INSPECTION OF POST-MODIFICATION 20416 OR POST-MODIFICATION 21999 AIRPLANES Threshold (A or B or C, whichever occurs later). Repetitive Inspection Interval (Not to exceed). A: Before exceeding 34,700 FC or 69,400 FH, whichever occurs first since the first flight of the airplane. B: Within 12,900 FC or 25,800 FH, whichever occurs first since the last inspection as specified in ALI task 531110–01–2 accomplished before the effective date of this AD. C: Within 30 days after the effective date of this AD, without exceeding 38,900 FC or 77,900 FH, whichever occurs first since the first flight of the airplane. 12,900 FC or 25,800 FH, whichever occurs first. pmangrum on DSK3GDR082PROD with PROPOSALS1 (h) Post-Inspection Actions Depending on the results from any inspection required by paragraph (g) of this AD, do the actions in paragraphs (h)(1) or (h)(2) of this AD, as applicable. (1) If, during any inspection required by paragraph (g) of this AD, any crack is detected: Before further flight, do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1286, Revision 01, dated December 22, 2015; except where Airbus Service Bulletin A320–53–1286, Revision 01, dated December 22, 2015, specifies to contact Airbus for appropriate repair, and specifies that action as ‘‘RC’’ (Required for Compliance), accomplish corrective actions before further flight in accordance with the procedures specified in VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 paragraph (r)(2) of this AD. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane, unless specified otherwise in the repair instructions. (2) If, during any inspection required by paragraph (g) of this AD, no cracks are detected: Before further flight, do all applicable fastener installations, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1286, Revision 01, dated December 22, 2015. 24 months after the effective date of this AD, modify the repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (i) Airplanes on Which Airbus Repair Instruction R53112926 Was Applied For airplanes on which Airbus Repair Instruction R53112926 at issue A or B was applied on the frame and/or crossbeam at FR16 LH or RH, or at FR20 LH or RH: Within For airplanes on which a repair with installation of EN6114 countersunk fasteners, approved by the FAA, EASA, or an EASA DOA other than Airbus, was applied on the frame and/or crossbeam at FR16 LH or RH, or at FR20 LH or RH, in the area covered by PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 (j) Airplanes on Which a Repair With Installation of EN6114 Countersunk Fasteners Was Applied on the Frame and/or Crossbeam E:\FR\FM\27NOP1.SGM 27NOP1 55958 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules paragraph (g) of this AD: Within 24 months after the effective date of this AD, modify the repair using a method approved by the Manager, International Section, Transport Standards Branch FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Optional Terminating Action for Airplanes Post-Modification 20416 or PostModification 21999 Modification of an airplane postmodification 20416 or post-modification 21999 in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1295, including Appendixes 01 and 02, dated June 29, 2015, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. (l) Post-Repair Actions for Certain Airplanes For an airplane that has been inspected per ALI task 531110 and repaired before the effective date of this AD using the instructions in an Airbus Repair Design Approval Sheet (RDAS): Within 30 days after the effective date of this AD, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA for instructions and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. Accomplishment of the instructions required by this paragraph, does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane, unless specified otherwise in the instructions. pmangrum on DSK3GDR082PROD with PROPOSALS1 (m) Partial Terminating Action for Airplanes Post-Modification 20416 or PostModification 21999 For an airplane post-modification 20416 or post-modification 21999, modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1295, including Appendixes 01 and 02, dated June 29, 2015, for the applicable fastener holes, where no damage or cracks were detected (i.e., those not repaired) during the latest inspection as required by paragraph (g) of this AD, constitutes terminating action for the repetitive inspections of those fastener holes as required by paragraph (g) of this AD for that airplane. (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 the instructions in an Airbus RDAS unrelated to ALI task 531110: Before exceeding the compliance times specified in table 1 to paragraph (g) of this AD or table 2 to paragraph (g) of this AD, as applicable, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA for corrective action instructions and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOAauthorized signature. Accomplishment of corrective action(s) on an airplane, as VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 required by this paragraph, does not constitute terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane, as applicable, unless specified otherwise in the instructions. (o) Terminating Action for ALI Tasks (1) Accomplishment of an inspection as required by paragraph (g) of this AD or instructions as required by paragraph (l) of this AD, as applicable, constitutes terminating action for the inspection requirements of ALI task 531110, for that airplane. (2) Modification of the two upper rows of fasteners of the crossbeam splicing at FR16 and FR20 on both LH and RH sides of an airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1295, including Appendixes 01 and 02, dated June 29, 2015, as specified in paragraphs (k) and (m) of this AD, constitutes terminating action for the inspection requirements of ALI task 531110, for those holes for that airplane. (p) No Reporting Requirement Although Airbus Service Bulletin A320– 53–1286, Revision 01, dated December 22, 2015, specifies to submit certain information to the manufacturer, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD does not include that requirement. (q) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1286, dated June 29, 2015. (r) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Section, send it to the attention of the person identified in paragraph (s)(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 Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (h)(1) and (p) of this AD: If any service information contains procedures or tests that are identified as RC, PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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. (s) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0139, dated July 14, 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– 2017–1093. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425– 227–1405; fax 425–227–1149. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 7, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–25252 Filed 11–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1421; Product Identifier 2014–NM–177–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. AGENCY: We are revising an earlier proposal for certain The Boeing Company Model 767–300 and –300F SUMMARY: E:\FR\FM\27NOP1.SGM 27NOP1

Agencies

[Federal Register Volume 82, Number 226 (Monday, November 27, 2017)]
[Proposed Rules]
[Pages 55955-55958]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25252]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1093; Product Identifier 2017-NM-018-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; Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. This proposed AD was prompted by reports of early 
cracking on certain holes of the crossbeam splicing at certain fuselage 
frames. This proposed AD would require repetitive inspections for 
cracking of the fastener holes in certain fuselage frames, and 
depending on airplane configuration, would provide an optional 
terminating action to 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 January 11, 
2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to 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 Standards Branch, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 425-
227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1093; 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 Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-1093; 
Product Identifier 2017-NM-018-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 
2016-0139, dated July 14, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Model A318 series airplanes; A319 series 
airplanes; A320-211, -212, -214, -216, -231, -232, and -233 airplanes; 
and A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. 
The MCAI states:

    Following addition of a new airworthiness limitation item (ALI) 
task 531110 in the

[[Page 55956]]

Airworthiness Limitation Section (ALS) Part 2 in the revision dated 
April 2012, numerous findings have been reported of early cracks on 
the four holes of the crossbeam splicing at frame (FR)16 and FR20 on 
both left-hand (LH) and right-hand (RH) sides.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    To allow an earlier crack detection, Airbus decided to transfer 
the repetitive inspections from ALI task 531110 to Airbus Service 
Bulletin (SB) A320-53-1286, later revised, including new recommended 
inspection thresholds.
    For the reasons described above, this [EASA] AD requires 
repetitive special detailed [rototest] inspections (SDI) of the two 
upper rows of fasteners of the crossbeam splicing at FR16 and FR20, 
on both LH and RH sides, [installation of new fasteners on crack-
free frames, related investigative and corrective actions,] and, 
depending on aeroplane configuration, provides an optional 
terminating action to the repetitive inspections required by this 
[EASA] AD.

    Related investigative actions include checking the edge margins of 
the holes. Corrective actions include reaming affected crossbeams and 
frames and cold working the frames. 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-2017-1093.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A320-53-1286, Revision 01, dated 
December 22, 2015, which describes procedures for rototest inspections 
for cracking of the holes in certain fuselage frames and crossbeams.
     Airbus Service Bulletin A320-53-1295, including Appendixes 
01 and 02, dated June 29, 2015, which describes procedures for 
modifying the airplane, including cold working instructions in certain 
fuselage frames and crossbeams.
    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.

Difference Between This Proposed AD and the MCAI or Service Information

    Where the MCAI, paragraph (4), specifies a repair approved by EASA 
or under a Design Organization Approval (DOA) other than Airbus, 
paragraph (j) of this proposed AD refers to a repair approved by the 
FAA, EASA, or an EASA DOA other than Airbus. The MCAI did not specify 
whether FAA approved repairs are acceptable for compliance.

Costs of Compliance

    We estimate that this proposed AD affects 928 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                        Cost per
            Action                  Labor cost         Parts cost        product       Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspections..................  116 work-hours x $85            $960         $10,820  $10,040,960.
                                per hour = $9,860
                                per inspection.
Optional Modification........  28 work-hours x $85            3,020           5,400  Up to $5,011,200.
                                per hour = $2,380.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 55957]]

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-2017-1093; Product Identifier 2017-NM-018-AD.

(a) Comments Due Date

    We must receive comments by January 11, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes; A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and A321-111, -112, -131, -211, -212, -213, -231, and -
232 airplanes, certificated in any category, all manufacturer serial 
numbers, except the airplanes specified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD.
    (1) Airplanes on which Airbus modification 161255 has been 
embodied in production.
    (2) Model A319 series airplanes on which Airbus modifications 
28238, 28162, and 28342 have been concurrently embodied in 
production.
    (3) Model A318 series airplanes on which Airbus modification 
39195 has been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of early cracking on the four 
holes of the crossbeam splicing at certain fuselage frames (FR). We 
are issuing this AD to detect and correct cracking at two upper rows 
of fasteners of the crossbeam splicing at FR16 and FR20, on both the 
left-hand (LH) and right-hand (RH) sides, which can result in 
reduced structural integrity of the airplane due to the failure of 
structural components.

(f) Compliance

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

(g) Repetitive Rototest Inspections

    Before exceeding the threshold specified in table 1 to paragraph 
(g) of this AD, or table 2 to paragraph (g) of this AD, as 
applicable to airplane configuration (pre- or post-modification 
20416 or pre- or post-modification 21999): Do a special detailed 
(rototest) inspection of the two upper rows of fasteners of the 
crossbeam splicing at FR16 and FR20 on both LH and RH sides, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1286, Revision 01, dated December 22, 2015. 
Thereafter, repeat the inspection at the intervals specified in 
table 1 to paragraph (g) of this AD, or table 2 to paragraph (g) of 
this AD, as applicable to airplane configuration (pre- or post-
modification 20416 or pre- or post-modification 21999).

   Table 1 to Paragraph (g) of This AD--Inspection of Pre-Modification
                20416 or Pre-Modification 21999 Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
Threshold (A or B or C,        A: Before exceeding 36,800 flight cycles
 whichever occurs later).       (FC) or 73,600 flight hours (FH),
                                whichever occurs first since the first
                                flight of the airplane.
                               B: Within 27,400 FC or 54,900 FH,
                                whichever occurs first since the last
                                inspection as specified in airworthiness
                                limitation item (ALI) task 531110-01-1
                                accomplished before the effective date
                                of this AD.
                               C: Within 30 days after the effective
                                date of this AD, without exceeding
                                38,800 FC or 77,600 FH, whichever occurs
                                first since the first flight of the
                                airplane.
Repetitive Inspection          27,400 FC or 54,900 FH, whichever occurs
 Interval (Not to exceed).      first.
------------------------------------------------------------------------


  Table 2 to Paragraph (g) of This AD--Inspection of Post-Modification
               20416 or Post-Modification 21999 Airplanes
------------------------------------------------------------------------
 
------------------------------------------------------------------------
Threshold (A or B or C,        A: Before exceeding 34,700 FC or 69,400
 whichever occurs later).       FH, whichever occurs first since the
                                first flight of the airplane.
                               B: Within 12,900 FC or 25,800 FH,
                                whichever occurs first since the last
                                inspection as specified in ALI task
                                531110-01-2 accomplished before the
                                effective date of this AD.
                               C: Within 30 days after the effective
                                date of this AD, without exceeding
                                38,900 FC or 77,900 FH, whichever occurs
                                first since the first flight of the
                                airplane.
Repetitive Inspection          12,900 FC or 25,800 FH, whichever occurs
 Interval (Not to exceed).      first.
------------------------------------------------------------------------

(h) Post-Inspection Actions

    Depending on the results from any inspection required by 
paragraph (g) of this AD, do the actions in paragraphs (h)(1) or 
(h)(2) of this AD, as applicable.
    (1) If, during any inspection required by paragraph (g) of this 
AD, any crack is detected: Before further flight, do all applicable 
related investigative and corrective actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1286, 
Revision 01, dated December 22, 2015; except where Airbus Service 
Bulletin A320-53-1286, Revision 01, dated December 22, 2015, 
specifies to contact Airbus for appropriate repair, and specifies 
that action as ``RC'' (Required for Compliance), accomplish 
corrective actions before further flight in accordance with the 
procedures specified in paragraph (r)(2) of this AD. Repair of an 
airplane as required by this paragraph does not constitute 
terminating action for the repetitive inspections required by 
paragraph (g) of this AD for that airplane, unless specified 
otherwise in the repair instructions.
    (2) If, during any inspection required by paragraph (g) of this 
AD, no cracks are detected: Before further flight, do all applicable 
fastener installations, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1286, Revision 01, 
dated December 22, 2015.

(i) Airplanes on Which Airbus Repair Instruction R53112926 Was Applied

    For airplanes on which Airbus Repair Instruction R53112926 at 
issue A or B was applied on the frame and/or crossbeam at FR16 LH or 
RH, or at FR20 LH or RH: Within 24 months after the effective date 
of this AD, modify the repair using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(j) Airplanes on Which a Repair With Installation of EN6114 Countersunk 
Fasteners Was Applied on the Frame and/or Crossbeam

    For airplanes on which a repair with installation of EN6114 
countersunk fasteners, approved by the FAA, EASA, or an EASA DOA 
other than Airbus, was applied on the frame and/or crossbeam at FR16 
LH or RH, or at FR20 LH or RH, in the area covered by

[[Page 55958]]

paragraph (g) of this AD: Within 24 months after the effective date 
of this AD, modify the repair using a method approved by the 
Manager, International Section, Transport Standards Branch FAA; or 
EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Optional Terminating Action for Airplanes Post-Modification 20416 
or Post-Modification 21999

    Modification of an airplane post-modification 20416 or post-
modification 21999 in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1295, including 
Appendixes 01 and 02, dated June 29, 2015, constitutes terminating 
action for the repetitive inspections required by paragraph (g) of 
this AD for that airplane.

(l) Post-Repair Actions for Certain Airplanes

    For an airplane that has been inspected per ALI task 531110 and 
repaired before the effective date of this AD using the instructions 
in an Airbus Repair Design Approval Sheet (RDAS): Within 30 days 
after the effective date of this AD, contact the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus's EASA DOA for instructions and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature. Accomplishment of the instructions 
required by this paragraph, does not constitute terminating action 
for the repetitive inspections required by paragraph (g) of this AD 
for that airplane, unless specified otherwise in the instructions.

(m) Partial Terminating Action for Airplanes Post-Modification 20416 or 
Post-Modification 21999

    For an airplane post-modification 20416 or post-modification 
21999, modification in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1295, including 
Appendixes 01 and 02, dated June 29, 2015, for the applicable 
fastener holes, where no damage or cracks were detected (i.e., those 
not repaired) during the latest inspection as required by paragraph 
(g) of this AD, constitutes terminating action for the repetitive 
inspections of those fastener holes as required by paragraph (g) of 
this AD for that airplane.

(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 the instructions 
in an Airbus RDAS unrelated to ALI task 531110: Before exceeding the 
compliance times specified in table 1 to paragraph (g) of this AD or 
table 2 to paragraph (g) of this AD, as applicable, contact the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA for corrective action instructions and 
accomplish those instructions accordingly. If approved by the DOA, 
the approval must include the DOA-authorized signature. 
Accomplishment of corrective action(s) on an airplane, as required 
by this paragraph, does not constitute terminating action for the 
repetitive inspections required by paragraph (g) of this AD for that 
airplane, as applicable, unless specified otherwise in the 
instructions.

(o) Terminating Action for ALI Tasks

    (1) Accomplishment of an inspection as required by paragraph (g) 
of this AD or instructions as required by paragraph (l) of this AD, 
as applicable, constitutes terminating action for the inspection 
requirements of ALI task 531110, for that airplane.
    (2) Modification of the two upper rows of fasteners of the 
crossbeam splicing at FR16 and FR20 on both LH and RH sides of an 
airplane, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 
02, dated June 29, 2015, as specified in paragraphs (k) and (m) of 
this AD, constitutes terminating action for the inspection 
requirements of ALI task 531110, for those holes for that airplane.

(p) No Reporting Requirement

    Although Airbus Service Bulletin A320-53-1286, Revision 01, 
dated December 22, 2015, specifies to submit certain information to 
the manufacturer, and specifies that action as ``RC'' (Required for 
Compliance), this AD does not include that requirement.

(q) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) and (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1286, dated June 29, 2015.

(r) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Section, send it to the 
attention of the person identified in paragraph (s)(2) of this AD. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (h)(1) and (p) of this AD: If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0139, dated July 14, 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-2017-1093.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on November 7, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-25252 Filed 11-24-17; 8:45 am]
 BILLING CODE 4910-13-P
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