82 FR 55955 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 226 (November 27, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 226 (November 27, 2017)
| Page Range | 55955-55958 | |
| FR Document | 2017-25252 |
[Federal Register Volume 82, Number 226 (Monday, November 27, 2017)] [Proposed Rules] [Pages 55955-55958] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-25252] ======================================================================= ----------------------------------------------------------------------- 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 http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office-EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 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 http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0139, 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 http://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: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: 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 http://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 [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on November 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
![Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules 55955
amend §§ 50.82(a) and 52.110 to clarify DEPARTMENT OF TRANSPORTATION the availability of this material at the
that licensees must evaluate the FAA, call 425–227–1221.
environmental impacts of Federal Aviation Administration
Examining the AD Docket
decommissioning, and whether they are
bounded, in the PSDAR; (4) to amend 14 CFR Part 39 You may examine the AD docket on
§ 50.59(d)(3); § 50.71(c); 10 CFR part 50, the Internet at http://
[Docket No. FAA–2017–1093; Product
www.regulations.gov by searching for
appendix A, Criterion 1, ‘‘Quality Identifier 2017–NM–018–AD]
and locating Docket No. FAA–2017–
standards and records’’; 10 CFR part 50, RIN 2120–AA64 1093; or in person at the Docket
appendix B, Criterion XVII, ‘‘Quality Management Facility between 9 a.m.
Assurance Records’’; and § 72.72(d) to Airworthiness Directives; Airbus and 5 p.m., Monday through Friday,
remove certain record-retention Airplanes except Federal holidays. The AD docket
requirements for structures, systems, contains this proposed AD, the
and components (SSCs) that no longer AGENCY: Federal Aviation
Administration (FAA), DOT. regulatory evaluation, any comments
remain in service during received, and other information. The
decommissioning, as well as ACTION: Notice of proposed rulemaking
street address for the Docket Operations
duplication requirements for spent fuel (NPRM). office (telephone 800–647–5527) is in
storage records; and (5) to amend 10 SUMMARY: We propose to adopt a new the ADDRESSES section. Comments will
CFR part 20, appendix G, Section III.E, airworthiness directive (AD) for certain be available in the AD docket shortly
for investigating shipments of low-level Airbus Model A318 series airplanes; after receipt.
radioactive waste (LLW) if the shipper Model A319 series airplanes; Model FOR FURTHER INFORMATION CONTACT:
has not received notification of receipt A320–211, –212, –214, –216, –231, Sanjay Ralhan, Aerospace Engineer,
within 20 days after transfer, to allow a –232, and –233 airplanes; and Model International Section, Transport
45-day notification window based on A321–111, –112, –131, –211, –212, Standards Branch, FAA, 1601 Lind
operating experience that shows this is –213, –231, and –232 airplanes. This Avenue SW., Renton, WA 98057–3356;
a reasonable delay for LLW shipments. proposed AD was prompted by reports telephone 425–227–1405; fax 425–227–
of early cracking on certain holes of the 1149.
Additionally in this regulatory basis,
crossbeam splicing at certain fuselage SUPPLEMENTARY INFORMATION:
the NRC staff recommends guidance
development and inspection procedure frames. This proposed AD would Comments Invited
require repetitive inspections for
updates for minimum staffing of non- We invite you to send any written
cracking of the fastener holes in certain
licensed operators and aging relevant data, views, or arguments about
fuselage frames, and depending on
management of certain SSCs. The NRC airplane configuration, would provide this proposal. Send your comments to
staff also determined that fatigue an optional terminating action to the an address listed under the ADDRESSES
management would not be addressed in repetitive inspections. We are proposing section. Include ‘‘Docket No. FAA–
this decommissioning rule. this AD to address the unsafe condition 2017–1093; Product Identifier 2017–
In the regulatory basis, the NRC staff on these products. NM–018–AD’’ at the beginning of your
reiterated conclusions from the draft comments. We specifically invite
DATES: We must receive comments on
comments on the overall regulatory,
regulatory basis that regulatory activities this proposed AD by January 11, 2018. economic, environmental, and energy
other than rulemaking—such as ADDRESSES: You may send comments, aspects of this proposed AD. We will
guidance development—can be pursued using the procedures found in 14 CFR consider all comments received by the
to address the appropriate role of State 11.43 and 11.45, by any of the following closing date and may amend this
and local governments in the methods: proposed AD based on those comments.
decommissioning process, the level of • Federal eRulemaking Portal: Go to We will post all comments we
NRC review of the PSDAR, and the 60- http://www.regulations.gov. Follow the receive, without change, to http://
year limit for power reactor instructions for submitting comments. www.regulations.gov, including any
decommissioning. • Fax: 202–493–2251. personal information you provide. We
In addition to the regulatory basis, • Mail: U.S. Department of will also post a report summarizing each
Transportation, Docket Operations, M– substantive verbal contact we receive
staff plans to publish a revised
30, West Building Ground Floor, Room about this proposed AD.
preliminary draft of the regulatory
W12–140, 1200 New Jersey Avenue SE.,
analysis, which will update and refine Discussion
Washington, DC 20590.
the analysis of costs and benefits. • Hand Delivery: Deliver to Mail The European Aviation Safety Agency
The NRC staff plans to publish a address above between 9 a.m. and 5 (EASA), which is the Technical Agent
proposed rule for public comment in p.m., Monday through Friday, except for the Member States of the European
2018. Federal holidays. Union, has issued EASA AD 2016–0139,
For service information identified in dated July 14, 2016 (referred to after this
Dated at Rockville, Maryland, this 21st day
this NPRM, contact Airbus, as the Mandatory Continuing
of November 2017.
Airworthiness Office–EIAS, 1 Rond Airworthiness Information, or ‘‘the
For the Nuclear Regulatory Commission.
pmangrum on DSK3GDR082PROD with PROPOSALS1
Point Maurice Bellonte, 31707 Blagnac MCAI’’), to correct an unsafe condition
Patricia K. Holahan, Cedex, France; telephone: +33 5 61 93 for certain Model A318 series airplanes;
Director, Division of Rulemaking, Office of 36 96; fax: +33 5 61 93 44 51; email: A319 series airplanes; A320–211, –212,
Nuclear Material Safety and Safeguards. account.airworth–eas@airbus.com; –214, –216, –231, –232, and –233
[FR Doc. 2017–25552 Filed 11–24–17; 8:45 am] Internet: http://www.airbus.com. You airplanes; and A321–111, –112, –131,
BILLING CODE 7590–01–P may view this referenced service –211, –212, –213, –231, and –232
information at the FAA, Transport airplanes. The MCAI states:
Standards Branch, 1601 Lind Avenue Following addition of a new airworthiness
SW., Renton, WA. For information on limitation item (ALI) task 531110 in the
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![55956 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules
Airworthiness Limitation Section (ALS) Part www.regulations.gov by searching for in the United States. Pursuant to our
2 in the revision dated April 2012, numerous and locating Docket No. FAA–2017– bilateral agreement with the State of
findings have been reported of early cracks 1093. Design Authority, we have been notified
on the four holes of the crossbeam splicing
of the unsafe condition described in the
at frame (FR)16 and FR20 on both left-hand Related Service Information Under 1
(LH) and right-hand (RH) sides. MCAI and service information
CFR Part 51
This condition, if not detected and referenced above. We are proposing this
corrected, could affect the structural integrity Airbus has issued the following AD because we evaluated all pertinent
of the airframe. service information: information and determined an unsafe
To allow an earlier crack detection, Airbus • Airbus Service Bulletin A320–53– condition exists and is likely to exist or
decided to transfer the repetitive inspections 1286, Revision 01, dated December 22, develop on other products of these same
from ALI task 531110 to Airbus Service 2015, which describes procedures for type designs.
Bulletin (SB) A320–53–1286, later revised, rototest inspections for cracking of the
including new recommended inspection holes in certain fuselage frames and Difference Between This Proposed AD
thresholds. and the MCAI or Service Information
crossbeams.
For the reasons described above, this
[EASA] AD requires repetitive special
• Airbus Service Bulletin A320–53– Where the MCAI, paragraph (4),
detailed [rototest] inspections (SDI) of the 1295, including Appendixes 01 and 02, specifies a repair approved by EASA or
two upper rows of fasteners of the crossbeam dated June 29, 2015, which describes under a Design Organization Approval
splicing at FR16 and FR20, on both LH and procedures for modifying the airplane, (DOA) other than Airbus, paragraph (j)
RH sides, [installation of new fasteners on including cold working instructions in of this proposed AD refers to a repair
crack-free frames, related investigative and certain fuselage frames and crossbeams.
corrective actions,] and, depending on approved by the FAA, EASA, or an
This service information is reasonably
aeroplane configuration, provides an optional EASA DOA other than Airbus. The
available because the interested parties
terminating action to the repetitive MCAI did not specify whether FAA
have access to it through their normal
inspections required by this [EASA] AD. approved repairs are acceptable for
course of business or by the means
Related investigative actions include compliance.
identified in the ADDRESSES section.
checking the edge margins of the holes. Costs of Compliance
Corrective actions include reaming FAA’s Determination and Requirements
affected crossbeams and frames and of This Proposed AD We estimate that this proposed AD
cold working the frames. You may This product has been approved by affects 928 airplanes of U.S. registry.
examine the MCAI in the AD docket on the aviation authority of another We estimate the following costs to
the Internet at http:// country, and is approved for operation comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspections ......................... 116 work-hours × $85 per hour = $9,860 per inspec- $960 $10,820 $10,040,960.
tion.
Optional Modification .......... 28 work-hours × $85 per hour = $2,380 ........................ 3,020 5,400 Up to $5,011,200.
We have received no definitive data products identified in this rulemaking For the reasons discussed above, I
that would enable us to provide cost action. certify this proposed regulation:
estimates for the on-condition actions This proposed AD is issued in 1. Is not a ‘‘significant regulatory
specified in this proposed AD. accordance with authority delegated by action’’ under Executive Order 12866;
Authority for This Rulemaking the Executive Director, Aircraft
2. Is not a ‘‘significant rule’’ under the
Certification Service, as authorized by
Title 49 of the United States Code DOT Regulatory Policies and Procedures
FAA Order 8000.51C. In accordance
specifies the FAA’s authority to issue with that order, issuance of ADs is (44 FR 11034, February 26, 1979);
rules on aviation safety. Subtitle I, normally a function of the Compliance 3. Will not affect intrastate aviation in
section 106, describes the authority of and Airworthiness Division, but during Alaska; and
the FAA Administrator. ‘‘Subtitle VII: this transition period, the Executive 4. Will not have a significant
Aviation Programs,’’ describes in more Director has delegated the authority to economic impact, positive or negative,
detail the scope of the Agency’s issue ADs applicable to transport on a substantial number of small entities
authority. category airplanes to the Director of the under the criteria of the Regulatory
We are issuing this rulemaking under System Oversight Division. Flexibility Act.
the authority described in ‘‘Subtitle VII, Regulatory Findings
Part A, Subpart III, Section 44701: List of Subjects in 14 CFR Part 39
General requirements.’’ Under that We determined that this proposed AD
Air transportation, Aircraft, Aviation
pmangrum on DSK3GDR082PROD with PROPOSALS1
section, Congress charges the FAA with would not have federalism implications
promoting safe flight of civil aircraft in under Executive Order 13132. This safety, Incorporation by reference,
air commerce by prescribing regulations proposed AD would not have a Safety.
for practices, methods, and procedures substantial direct effect on the States, on The Proposed Amendment
the Administrator finds necessary for the relationship between the national
safety in air commerce. This regulation Government and the States, or on the Accordingly, under the authority
is within the scope of that authority distribution of power and delegated to me by the Administrator,
because it addresses an unsafe condition responsibilities among the various the FAA proposes to amend 14 CFR part
that is likely to exist or develop on levels of government. 39 as follows:
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![Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules 55957
PART 39—AIRWORTHINESS 111, –112, –131, –211, –212, –213, –231, and sides, which can result in reduced structural
DIRECTIVES –232 airplanes, certificated in any category, integrity of the airplane due to the failure of
all manufacturer serial numbers, except the structural components.
■ 1. The authority citation for part 39 airplanes specified in paragraphs (c)(1),
(f) Compliance
continues to read as follows: (c)(2), and (c)(3) of this AD.
(1) Airplanes on which Airbus Comply with this AD within the
Authority: 49 U.S.C. 106(g), 40113, 44701. modification 161255 has been embodied in compliance times specified, unless already
production. done.
§ 39.13 [Amended]
(2) Model A319 series airplanes on which (g) Repetitive Rototest Inspections
■ 2. The FAA amends § 39.13 by adding Airbus modifications 28238, 28162, and
the following new airworthiness 28342 have been concurrently embodied in Before exceeding the threshold specified in
directive (AD): production. table 1 to paragraph (g) of this AD, or table
(3) Model A318 series airplanes on which 2 to paragraph (g) of this AD, as applicable
Airbus: Docket No. FAA–2017–1093; Product to airplane configuration (pre- or post-
Identifier 2017–NM–018–AD. Airbus modification 39195 has been
embodied in production. modification 20416 or pre- or post-
(a) Comments Due Date modification 21999): Do a special detailed
(d) Subject (rototest) inspection of the two upper rows of
We must receive comments by January 11,
2018. Air Transport Association (ATA) of fasteners of the crossbeam splicing at FR16
America Code 53, Fuselage. and FR20 on both LH and RH sides, in
(b) Affected ADs accordance with the Accomplishment
(e) Reason Instructions of Airbus Service Bulletin A320–
None.
This AD was prompted by reports of early 53–1286, Revision 01, dated December 22,
(c) Applicability cracking on the four holes of the crossbeam 2015. Thereafter, repeat the inspection at the
This AD applies to Airbus Model A318– splicing at certain fuselage frames (FR). We intervals specified in table 1 to paragraph (g)
111, –112, –121, and –122 airplanes; A319– are issuing this AD to detect and correct of this AD, or table 2 to paragraph (g) of this
111, –112, –113, –114, –115, –131, –132, and cracking at two upper rows of fasteners of the AD, as applicable to airplane configuration
–133 airplanes; A320–211, –212, –214, –216, crossbeam splicing at FR16 and FR20, on (pre- or post-modification 20416 or pre- or
–231, –232, and –233 airplanes; and A321– both the left-hand (LH) and right-hand (RH) 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 (FC) or 73,600 flight hours (FH), whichever occurs first since the first
whichever occurs later). 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 oc-
curs first since the first flight of the airplane.
Repetitive Inspection Interval 27,400 FC or 54,900 FH, whichever occurs first.
(Not to exceed).
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 FH, whichever occurs first since the first flight of the airplane.
whichever occurs later). 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 oc-
curs first since the first flight of the airplane.
Repetitive Inspection Interval 12,900 FC or 25,800 FH, whichever occurs first.
(Not to exceed).
(h) Post-Inspection Actions paragraph (r)(2) of this AD. Repair of an 24 months after the effective date of this AD,
Depending on the results from any airplane as required by this paragraph does modify the repair using a method approved
inspection required by paragraph (g) of this not constitute terminating action for the by the Manager, International Section,
AD, do the actions in paragraphs (h)(1) or repetitive inspections required by paragraph Transport Standards Branch, FAA; or the
(g) of this AD for that airplane, unless European Aviation Safety Agency (EASA); or
(h)(2) of this AD, as applicable.
specified otherwise in the repair instructions. Airbus’s EASA Design Organization
(1) If, during any inspection required by
(2) If, during any inspection required by Approval (DOA). If approved by the DOA,
paragraph (g) of this AD, any crack is paragraph (g) of this AD, no cracks are
detected: Before further flight, do all the approval must include the DOA-
detected: Before further flight, do all
applicable related investigative and applicable fastener installations, in authorized signature.
corrective actions in accordance with the accordance with the Accomplishment (j) Airplanes on Which a Repair With
pmangrum on DSK3GDR082PROD with PROPOSALS1
Accomplishment Instructions of Airbus Instructions of Airbus Service Bulletin A320– Installation of EN6114 Countersunk
Service Bulletin A320–53–1286, Revision 01, 53–1286, Revision 01, dated December 22, Fasteners Was Applied on the Frame and/or
dated December 22, 2015; except where 2015. Crossbeam
Airbus Service Bulletin A320–53–1286,
Revision 01, dated December 22, 2015, (i) Airplanes on Which Airbus Repair For airplanes on which a repair with
specifies to contact Airbus for appropriate Instruction R53112926 Was Applied installation of EN6114 countersunk fasteners,
repair, and specifies that action as ‘‘RC’’ For airplanes on which Airbus Repair approved by the FAA, EASA, or an EASA
(Required for Compliance), accomplish Instruction R53112926 at issue A or B was DOA other than Airbus, was applied on the
corrective actions before further flight in applied on the frame and/or crossbeam at frame and/or crossbeam at FR16 LH or RH,
accordance with the procedures specified in FR16 LH or RH, or at FR20 LH or RH: Within or at FR20 LH or RH, in the area covered by
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![55958 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules
paragraph (g) of this AD: Within 24 months required by this paragraph, does not those procedures and tests must be done to
after the effective date of this AD, modify the constitute terminating action for the comply with this AD; any procedures or tests
repair using a method approved by the repetitive inspections required by paragraph that are not identified as RC are
Manager, International Section, Transport (g) of this AD for that airplane, as applicable, recommended. Those procedures and tests
Standards Branch FAA; or EASA; or Airbus’s unless specified otherwise in the that are not identified as RC may be deviated
EASA DOA. If approved by the DOA, the instructions. from using accepted methods in accordance
approval must include the DOA-authorized with the operator’s maintenance or
signature. (o) Terminating Action for ALI Tasks
inspection program without obtaining
(1) Accomplishment of an inspection as approval of an AMOC, provided the
(k) Optional Terminating Action for required by paragraph (g) of this AD or procedures and tests identified as RC can be
Airplanes Post-Modification 20416 or Post- instructions as required by paragraph (l) of done and the airplane can be put back in an
Modification 21999 this AD, as applicable, constitutes airworthy condition. Any substitutions or
Modification of an airplane post- terminating action for the inspection changes to procedures or tests identified as
modification 20416 or post-modification requirements of ALI task 531110, for that RC require approval of an AMOC.
21999 in accordance with the airplane.
Accomplishment Instructions of Airbus (2) Modification of the two upper rows of (s) Related Information
Service Bulletin A320–53–1295, including fasteners of the crossbeam splicing at FR16 (1) Refer to Mandatory Continuing
Appendixes 01 and 02, dated June 29, 2015, and FR20 on both LH and RH sides of an Airworthiness Information (MCAI) EASA
constitutes terminating action for the airplane, in accordance with the Airworthiness Directive 2016–0139, dated
repetitive inspections required by paragraph Accomplishment Instructions of Airbus July 14, 2016, for related information. This
(g) of this AD for that airplane. Service Bulletin A320–53–1295, including MCAI may be found in the AD docket on the
Appendixes 01 and 02, dated June 29, 2015, Internet at http://www.regulations.gov by
(l) Post-Repair Actions for Certain Airplanes as specified in paragraphs (k) and (m) of this searching for and locating Docket No. FAA–
For an airplane that has been inspected per AD, constitutes terminating action for the 2017–1093.
ALI task 531110 and repaired before the inspection requirements of ALI task 531110, (2) For more information about this AD,
effective date of this AD using the for those holes for that airplane. contact Sanjay Ralhan, Aerospace Engineer,
instructions in an Airbus Repair Design International Section, Transport Standards
Approval Sheet (RDAS): Within 30 days after (p) No Reporting Requirement
Branch, FAA, 1601 Lind Avenue SW.,
the effective date of this AD, contact the Although Airbus Service Bulletin A320– Renton, WA 98057–3356; telephone 425–
Manager, International Section, Transport 53–1286, Revision 01, dated December 22, 227–1405; fax 425–227–1149.
Standards Branch, FAA; or EASA; or 2015, specifies to submit certain information (3) For service information identified in
Airbus’s EASA DOA for instructions and to the manufacturer, and specifies that action this AD, contact Airbus, Airworthiness
accomplish those instructions accordingly. If as ‘‘RC’’ (Required for Compliance), this AD Office—EIAS, 1 Rond Point Maurice
approved by the DOA, the approval must does not include that requirement. Bellonte, 31707 Blagnac Cedex, France;
include the DOA-authorized signature. telephone +33 5 61 93 36 96; fax +33 5 61
(q) Credit for Previous Actions
Accomplishment of the instructions required 93 44 51; email account.airworth-eas@
by this paragraph, does not constitute This paragraph provides credit for actions
required by paragraph (g) and (h) of this AD, airbus.com; Internet http://www.airbus.com.
terminating action for the repetitive
if those actions were performed before the You may view this service information at the
inspections required by paragraph (g) of this
effective date of this AD using Airbus Service FAA, Transport Standards Branch, 1601 Lind
AD for that airplane, unless specified
Bulletin A320–53–1286, dated June 29, 2015. Avenue SW., Renton, WA. For information
otherwise in the instructions.
on the availability of this material at the
(m) Partial Terminating Action for Airplanes (r) Other FAA AD Provisions FAA, call 425–227–1221.
Post-Modification 20416 or Post- The following provisions also apply to this Issued in Renton, Washington, on
Modification 21999 AD: November 7, 2017.
For an airplane post-modification 20416 or (1) Alternative Methods of Compliance Dionne Palermo,
post-modification 21999, modification in (AMOCs): The Manager, International
Section, Transport Standards Branch, FAA, Acting Director, System Oversight Division,
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320– has the authority to approve AMOCs for this Aircraft Certification Service.
53–1295, including Appendixes 01 and 02, AD, if requested using the procedures found [FR Doc. 2017–25252 Filed 11–24–17; 8:45 am]
dated June 29, 2015, for the applicable in 14 CFR 39.19. In accordance with 14 CFR BILLING CODE 4910–13–P
fastener holes, where no damage or cracks 39.19, send your request to your principal
were detected (i.e., those not repaired) during inspector or local Flight Standards District
the latest inspection as required by paragraph Office, as appropriate. If sending information DEPARTMENT OF TRANSPORTATION
(g) of this AD, constitutes terminating action directly to the manager of the International
for the repetitive inspections of those fastener Section, send it to the attention of the person Federal Aviation Administration
holes as required by paragraph (g) of this AD identified in paragraph (s)(2) of this AD.
for that airplane. Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using 14 CFR Part 39
(n) Actions for Airplanes With Certain any approved AMOC, notify your appropriate
Repairs [Docket No. FAA–2015–1421; Product
principal inspector, or lacking a principal
Identifier 2014–NM–177–AD]
For an airplane that has been repaired inspector, the manager of the local flight
before the effective date of this AD in the standards district office/certificate holding RIN 2120–AA64
areas described in this AD using the district office.
instructions in an Airbus RDAS unrelated to (2) Contacting the Manufacturer: For any Airworthiness Directives; The Boeing
ALI task 531110: Before exceeding the requirement in this AD to obtain corrective Company Airplanes
compliance times specified in table 1 to actions from a manufacturer, the action must
pmangrum on DSK3GDR082PROD with PROPOSALS1
paragraph (g) of this AD or table 2 to be accomplished using a method approved AGENCY: Federal Aviation
paragraph (g) of this AD, as applicable, by the Manager, International Section, Administration (FAA), DOT.
contact the Manager, International Section, Transport Standards Branch, FAA; or EASA;
Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the ACTION: Supplemental notice of
or Airbus’s EASA DOA for corrective action DOA, the approval must include the DOA- proposed rulemaking (SNPRM);
instructions and accomplish those authorized signature. reopening of comment period.
instructions accordingly. If approved by the (3) Required for Compliance (RC): Except
DOA, the approval must include the DOA- as required by paragraphs (h)(1) and (p) of SUMMARY: We are revising an earlier
authorized signature. Accomplishment of this AD: If any service information contains proposal for certain The Boeing
corrective action(s) on an airplane, as procedures or tests that are identified as RC, Company Model 767–300 and –300F
VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\27NOP1.SGM 27NOP1](https://thefederalregister.org/doc/82_FR_56181/page/4.svg)
Document Created: 2017-11-25 01:09:11
Document Modified: 2017-11-25 01:09:11
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by January 11, 2018. | |
| 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. | |
| FR Citation | 82 FR 55955 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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