83 FR 34034 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 139 (July 19, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 139 (July 19, 2018)
| Page Range | 34034-34039 | |
| FR Document | 2018-14687 |
[Federal Register Volume 83, Number 139 (Thursday, July 19, 2018)] [Rules and Regulations] [Pages 34034-34039] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-14687] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-1093; Product Identifier 2017-NM-018-AD; Amendment 39-19329; AD 2018-14-09] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting 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 AD was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. This AD requires repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 23, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 23, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 1093. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to 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. The NPRM published in the Federal Register on November 27, 2017 (82 FR 55955) (``the NPRM''). The NPRM was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. The NPRM proposed to 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 issuing this AD to address cracking at two upper rows of fasteners of the crossbeam splicing at frame (FR)16 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. 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 [[Page 34035]] for certain 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. The MCAI states: Following addition of a new airworthiness limitation item (ALI) task 531110 in the 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Requests To Revise Repair Instructions for Repairs Done Using an Airbus Repair Design Approval Sheet (RDAS) American Airlines (AAL) and United Airlines (UAL) requested that the repair instructions in paragraph (l) of the proposed AD be revised to remove requirements to obtain new repair instructions for any airplanes on which repairs were done using the instructions in an Airbus RDAS. AAL noted that the original RDAS approval was given by an EASA Design Organization Approval (DOA), so new approval should not be needed. Instead, AAL suggested that the issuer of the RDASs should be required to revise the RDASs as necessary. UAL noted that an RDAS already defines repair life and inspection instructions or limits. UAL also noted that the MCAI does not require obtaining new repair instructions, but instead says to accomplish the repair instructions given in the RDAS for repaired fastener holes. We disagree to require the issuer of the RDAS to revise the RDAS. An RDAS is an Airbus document that is not approved by the FAA, and the FAA has no authority to require Airbus to revise the RDAS. We agree with the requests to remove the requirement to obtain repair instructions in paragraph (l) of this AD. We have confirmed that EASA intended the corresponding paragraph in the MCAI to be informational, rather than a new requirement. We have revised paragraph (l) of this AD to note that the information on the next inspection and compliance time for the inspection of repaired holes is specified in the applicable RDAS; therefore, there is no requirement to obtain and follow new instructions. Request To Supersede Certain Inspections UAL requested that we revise paragraph (l) of the proposed AD to state that previous repair instructions that superseded ALI 531110 also terminate the inspections required by paragraph (g) of the proposed AD for the repaired holes. UAL noted that they had several RDASs that state that the inspection requirements of the RDAS supersede ALI 531110 for the repaired fasteners. UAL stated that these repairs involved enlarging the holes and fasteners, thereby making it impossible for them to accomplish the inspections in accordance with Airbus Service Bulletin A320-53-1286, Revision 01, dated December 22, 2015. We disagree with revising paragraph (l) of this AD to specify terminating action to paragraph (g) of this AD. An operator who is unable to complete certain requirements in this AD due to existing repairs may request an alternative method of compliance (AMOC) under the provisions of paragraph (s)(1) of this AD. Request To Remove or Revise Paragraph (n) of the Proposed AD AAL requested that paragraph (n) of the proposed AD be revised to remove requirements to obtain new repair instructions for any airplanes on which repairs were done using the instructions in an Airbus RDAS unrelated to ALI task 531110. AAL noted that the original RDAS approval was given by an EASA DOA, so new approval should not be needed. Instead, AAL suggested that the issuer of the RDASs should be required to revise the RDASs as necessary. UAL requested that paragraph (n) of the proposed AD be removed. UAL stated that determining if a repair is unrelated to ALI task 531110 may be inconclusive, since the ALI task is an inspection that may or may not be referenced in a documented repair. UAL added that each repair approval will have damage tolerance considerations regardless of how the damage was found. UAL further noted that if a repair unrelated to ALI task 531110 prevents inspection or repair as specified in the proposed AD, operators would need to request an AMOC. We disagree with the commenters' requests. EASA has determined that repairs unrelated to ALI task 531110, which could include minor repairs unrelated to the unsafe condition, may not adequately address the unsafe condition. For this reason, operators must request new corrective actions for such repairs, as specified in paragraph (n) of this AD. Requests To Revise Repair Instructions for Airplanes on Which Certain Repairs Were Previously Applied UAL and AAL requested that paragraphs (i) and (j) of the proposed AD be revised to list specific affected manufacturer serial numbers (MSNs). In addition, UAL and AAL requested that the original equipment manufacturer (OEM) revise the Airbus RDASs to correct any problems. AAL pointed out that the original RDAS was approved by an EASA DOA and stated that operators should therefore not be required to obtain a new approval. UAL requested that if we do not provide revised RDASs or a list of affected MSNs, we instead provide a pre-defined solution for the repair. UAL suggested that we should provide instructions for replacing EN6114 fasteners with EN6115 fasteners. UAL further requested that if the repairs require case-by-case evaluations, the repair instructions should define the repair compliance time, rather than having a set 24 month compliance time, which may not work for every configuration. UAL also noted that the issue with Airbus Repair Instruction R53112926 issue A or B is that it called out the wrong fastener; EN6115 should have been used instead of EN6114. UAL requested that we add a statement to paragraph (j) of this AD stating that no additional repair instructions are needed if a repair was accomplished using Airbus Repair Instruction R53112926 issue A or B and EN6115 fasteners. [[Page 34036]] We disagree with the commenters' requests to revise paragraphs (i) and (j) of this AD to list specific affected MSNs. EASA, as the state of design authority, and Airbus have both stated that they do not have knowledge of prior approved repairs; therefore we do not have a list of affected MSNs. In addition, an RDAS is an Airbus document that is not approved by the FAA, and the FAA has no authority to require Airbus to revise the RDAS. Therefore, each existing repair must be individually analyzed before a new corrective action can be provided. For this reason, we are not able to provide a single pre-defined solution for the repair that would address every affected configuration. We have determined that 24 months is an appropriate time frame to address the unsafe condition related to the EN6114 fasteners. An AMOC in accordance with paragraph (s)(1) of this AD may be requested if additional time is needed to address the unsafe condition. We do not agree to add a statement to paragraphs (i) or (j) of this AD regarding no additional repair instructions are necessary if those repairs were applied with the installation of EN6115 fasteners, but we do agree to clarify that paragraphs (i) and (j) of this AD only apply to airplanes on which Airbus Repair Instruction R53112926 issue A or B or any other repair involving the installation of EN6114 fasteners was applied. If EN6115 fasteners were installed in the accomplishment of Airbus Repair Instruction R53112926 issue A or B or any other repair, the actions specified in paragraphs (i) or (j) of this AD are not required on the repaired airplane. Request To Include Corrections to Service Information UAL requested that we update paragraph (k) of the proposed AD to reflect corrections to Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015. UAL noted that Airbus has released Operators Information Transmission (OIT) 15-0097, Revision 01, dated January 7, 2016, to correct discrepancies in the effectivity section and existing hole diameters for certain subtasks in Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015. We agree with the commenter's request for the reasons provided. We have added paragraph (r) to this AD to clarify the hole-diameter correction provided in Airbus OIT 15-0097, Revision 01, dated January 7, 2016. We have also updated other paragraphs of this AD that refer to Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015, to include this exception. We also acknowledge the discrepancy in the effectivity section of Airbus Service Bulletin A320- 53-1295, including Appendixes 01 and 02, dated June 29, 2015, and the correction provided in Airbus OIT 15-0097, Revision 01, dated January 7, 2016. However, the applicability of this AD does not refer to Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015. Therefore, we have not changed this AD in this regard. Request To Verify Title of Table 1 to Paragraphs (g) and (n) of This AD Virgin America requested that we review the title of table 1 to paragraphs (g) and (n) of this AD. Virgin America noted that the related MCAI table refers to airplanes having not embodied any of ``mod 20416 and mod 21999,'' while the proposed AD refers to ``pre- modification 20416 or pre-modification 21999'' airplanes. Virgin America suggested this might be a typographical error, and asked that it be corrected if it is in error. We acknowledge that the wording in the MCAI and this AD is not the same and agree to clarify. Table 1 of the MCAI is intended to apply to airplanes that have not embodied any part of modification 20416 or any part of modification 21999. Therefore, it is accurate to state ``pre- modification 20416 or pre-modification 21999 airplanes.'' We have not changed this AD in this regard. Request To Verify Referenced Service Information is at the Latest Revision UAL requested that we verify the service bulletins referenced in the proposed AD are at the latest revision level. UAL noted this would eliminate the need to request an AMOC immediately following publication of this AD. We agree with the commenter's request. We have verified that no revisions of the referenced service information have been published since we issued our proposed AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. 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. 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. Costs of Compliance We estimate that this AD affects 928 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections..................... 116 work-hours x $85 $960 $10,820 per $10,040,960 per per hour = $9,860 inspection cycle. inspection cycle. per inspection cycle. Optional Modification........... 28 work-hours x 3,020 $5,400.............. Up to $5,011,200. times; $85 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 AD. Authority for this Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue [[Page 34037]] rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2018-14-09 Airbus: Amendment 39-19329; Docket No. FAA-2017-1093; Product Identifier 2017-NM-018-AD. (a) Effective Date This AD is effective August 23, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and - 133 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, 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 paragraphs (g) and (n) of this AD, or table 2 to paragraphs (g) and (n) 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 paragraphs (g) and (n) of this AD, or table 2 to paragraphs (g) and (n) of this AD, as applicable to airplane configuration (pre- or post-modification 20416 or pre- or post- modification 21999). BILLING CODE 4910-13-P [[Page 34038]] [GRAPHIC] [TIFF OMITTED] TR19JY18.002 [GRAPHIC] [TIFF OMITTED] TR19JY18.003 BILLING CODE 4910-13-C (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 (s)(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 With Installation of EN6114 Countersunk Fasteners Was Applied on the Frame and/or Crossbeam For airplanes on which Airbus Repair Instruction R53112926 at issue A or B with installation of EN6114 countersunk fasteners 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, Airbus's EASA DOA, or an EASA DOA (other than Airbus's EASA DOA), was applied on the frame and/or crossbeam at FR16 LH or RH, or at FR20 LH or RH, in the area covered by 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. [[Page 34039]] (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, except as required by paragraph (r) of this AD, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. (l) Information on 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): each applicable RDAS contains next inspection and compliance time for the inspection for each repaired hole. (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, except as required by paragraph (r) of this AD, 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 paragraphs (g) and (n) of this AD or table 2 to paragraphs (g) and (n) 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, except as required by paragraph (r) of this AD, 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) Service Information Exceptions Where Subtasks 531295-960-001-001 and 532195-960-002-001 of Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015, refer to actions when an existing hole diameter is ``more than or equal to the minimum starting hole diameter,'' this AD requires applicable actions in cases where the hole diameter is ``more than or equal to the maximum starting hole diameter.'' (s) 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 International Section, send it to the attention of the person identified in paragraph (t)(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. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 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, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(3) and (u)(4) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-53-1286, Revision 01, dated December 22, 2015. (ii) Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated June 29, 2015. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Des Moines, Washington, on June 29, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-14687 Filed 7-18-18; 8:45 am] BILLING CODE 4910-13-P
![34034 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations
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Acting Director, System Oversight Division,
Branch, send it to the attention of the person Aircraft Certification Service. You may examine the AD docket on
identified in paragraph (l)(2) of this AD. [FR Doc. 2018–14809 Filed 7–18–18; 8:45 am] the internet at http://
Information may be emailed to: 9-ANM-116- BILLING CODE 4910–13–P www.regulations.gov by searching for
AMOC-REQUESTS@faa.gov. Before using and locating Docket No. FAA–2017–
any approved AMOC, notify your appropriate 1093; or in person at the Docket
principal inspector, or lacking a principal DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
inspector, the manager of the local flight and 5 p.m., Monday through Friday,
standards district office/certificate holding Federal Aviation Administration except Federal holidays. The AD docket
district office. contains this AD, the regulatory
(2) Contacting the Manufacturer: For any 14 CFR Part 39 evaluation, any comments received, and
requirement in this AD to obtain corrective
[Docket No. FAA–2017–1093; Product other information. The street address for
actions from a manufacturer, the action must
Identifier 2017–NM–018–AD; Amendment the Docket Office (telephone 800–647–
be accomplished using a method approved
39–19329; AD 2018–14–09] 5527) is Docket Management Facility,
by the Manager, International Section,
U.S. Department of Transportation,
Transport Standards Branch, FAA; or the RIN 2120–AA64
European Aviation Safety Agency (EASA); or
Docket Operations, M–30, West
EASA Design Organization Approval (DOA). Airworthiness Directives; Airbus Building Ground Floor, Room W12–140,
If approved by the DOA, the approval must Airplanes 1200 New Jersey Avenue SE,
include the DOA-authorized signature. Washington, DC 20590.
AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT:
(l) Related Information Administration (FAA), Department of Sanjay Ralhan, Aerospace Engineer,
(1) Refer to Mandatory Continuing Transportation (DOT). International Section, Transport
Airworthiness Information (MCAI) EASA AD ACTION: Final rule. Standards Branch, FAA, 2200 South
2017–0223R1, dated December 15, 2017, for 216th St., Des Moines, WA 98198;
related information. This MCAI may be SUMMARY: We are adopting a new telephone and fax 206–231–3223.
found in the AD docket on the internet at airworthiness directive (AD) for certain
SUPPLEMENTARY INFORMATION:
http://www.regulations.gov by searching for Airbus Model A318 series airplanes;
and locating Docket No. FAA–2018–0166. Model A319 series airplanes; Model Discussion
(2) For more information about this AD, A320–211, –212, –214, –216, –231, We issued a notice of proposed
contact Shahram Daneshmandi, Aerospace –232, and –233 airplanes; and Model rulemaking (NPRM) to amend 14 CFR
Engineer, International Section, Transport A321–111, –112, –131, –211, –212, part 39 by adding an AD that would
Standards Branch, FAA, 2200 South 216th –213, –231, and –232 airplanes. This AD
St., Des Moines, WA 98198; telephone and
apply to certain Airbus Model A318
was prompted by reports of early series airplanes; Model A319 series
fax 206–231–3220. cracking on certain holes of the airplanes; Model A320–211, –212, –214,
(m) Material Incorporated by Reference crossbeam splicing at certain fuselage –216, –231, –232, and –233 airplanes;
frames. This AD requires repetitive and Model A321–111, –112, –131, –211,
(1) The Director of the Federal Register
inspections for cracking of the fastener –212, –213, –231, and –232 airplanes.
approved the incorporation by reference
holes in certain fuselage frames, and The NPRM published in the Federal
(IBR) of the service information listed in this
depending on airplane configuration, Register on November 27, 2017 (82 FR
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
provides an optional terminating action 55955) (‘‘the NPRM’’). The NPRM was
(2) You must use this service information to the repetitive inspections. We are prompted by reports of early cracking
as applicable to do the actions required by issuing this AD to address the unsafe on certain holes of the crossbeam
this AD, unless this AD specifies otherwise. condition on these products. splicing at certain fuselage frames. The
(i) ATR72 Time Limits document, Revision DATES: This AD is effective August 23, NPRM proposed to require repetitive
15, dated May 2, 2017. 2018. inspections for cracking of the fastener
(ii) Reserved. The Director of the Federal Register holes in certain fuselage frames, and
(3) For service information identified in approved the incorporation by reference depending on airplane configuration,
this AD, contact ATR–GIE Avions de of certain publications listed in this AD would provide an optional terminating
Transport Régional, 1, Allée Pierre Nadot, as of August 23, 2018. action to the repetitive inspections. We
31712 Blagnac Cedex, France; telephone +33 ADDRESSES: For service information are issuing this AD to address cracking
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
identified in this final rule, contact at two upper rows of fasteners of the
email continued.airworthiness@atr-
Airbus, Airworthiness Office—EIAS, crossbeam splicing at frame (FR)16 and
aircraft.com.
Rond-Point Emile Dewoitine No: 2, FR20, on both the left-hand (LH) and
(4) You may view this service information
at the FAA, Transport Standards Branch,
31700 Blagnac Cedex, France; telephone right-hand (RH) sides, which can result
2200 South 216th St., Des Moines, WA. For +33 5 61 93 36 96; fax +33 5 61 93 44 in reduced structural integrity of the
information on the availability of this 51; email account.airworth-eas@ airplane due to the failure of structural
material at the FAA, call 206–231–3195. airbus.com; internet http:// components.
(5) You may view this service information www.airbus.com. You may view this The European Aviation Safety Agency
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that is incorporated by reference at the referenced service information at the (EASA), which is the Technical Agent
National Archives and Records FAA, Transport Standards Branch, 2200 for the Member States of the European
Administration (NARA). For information on South 216th St., Des Moines, WA. For Union, has issued EASA AD 2016–0139,
the availability of this material at NARA, call information on the availability of this dated July 14, 2016 (referred to after this
202–741–6030, or go to: http:// material at the FAA, call 206–231–3195. as the Mandatory Continuing
www.archives.gov/federal-register/cfr/ibr- It is also available on the internet at Airworthiness Information, or ‘‘the
locations.html. http://www.regulations.gov by searching MCAI’’), to correct an unsafe condition
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![Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34035
for certain Model A318 series airplanes; repair life and inspection instructions or issuer of the RDASs should be required
Model A319 series airplanes; Model limits. UAL also noted that the MCAI to revise the RDASs as necessary.
A320–211, –212, –214, –216, –231, does not require obtaining new repair UAL requested that paragraph (n) of
–232, and –233 airplanes; and Model instructions, but instead says to the proposed AD be removed. UAL
A321–111, –112, –131, –211, –212, accomplish the repair instructions given stated that determining if a repair is
–213, –231, and –232 airplanes. The in the RDAS for repaired fastener holes. unrelated to ALI task 531110 may be
MCAI states: We disagree to require the issuer of inconclusive, since the ALI task is an
Following addition of a new airworthiness the RDAS to revise the RDAS. An RDAS inspection that may or may not be
limitation item (ALI) task 531110 in the is an Airbus document that is not referenced in a documented repair. UAL
Airworthiness Limitation Section (ALS) Part approved by the FAA, and the FAA has added that each repair approval will
2 in the revision dated April 2012, numerous no authority to require Airbus to revise have damage tolerance considerations
findings have been reported of early cracks the RDAS. regardless of how the damage was
on the four holes of the crossbeam splicing found. UAL further noted that if a repair
at frame (FR)16 and FR20 on both left-hand
We agree with the requests to remove
(LH) and right-hand (RH) sides. the requirement to obtain repair unrelated to ALI task 531110 prevents
This condition, if not detected and instructions in paragraph (l) of this AD. inspection or repair as specified in the
corrected, could affect the structural integrity We have confirmed that EASA intended proposed AD, operators would need to
of the airframe. the corresponding paragraph in the request an AMOC.
To allow an earlier crack detection, Airbus MCAI to be informational, rather than a We disagree with the commenters’
decided to transfer the repetitive inspections new requirement. We have revised requests. EASA has determined that
from ALI task 531110 to Airbus Service paragraph (l) of this AD to note that the repairs unrelated to ALI task 531110,
Bulletin (SB) A320–53–1286, later revised,
information on the next inspection and which could include minor repairs
including new recommended inspection
thresholds. compliance time for the inspection of unrelated to the unsafe condition, may
For the reasons described above, this repaired holes is specified in the not adequately address the unsafe
[EASA] AD requires repetitive special applicable RDAS; therefore, there is no condition. For this reason, operators
detailed [rototest] inspections (SDI) of the requirement to obtain and follow new must request new corrective actions for
two upper rows of fasteners of the crossbeam instructions. such repairs, as specified in paragraph
splicing at FR16 and FR20, on both LH and (n) of this AD.
RH sides, [installation of new fasteners on Request To Supersede Certain
crack-free frames, related investigative and Inspections Requests To Revise Repair Instructions
corrective actions,] and, depending on for Airplanes on Which Certain Repairs
aeroplane configuration, provides an optional UAL requested that we revise
Were Previously Applied
terminating action to the repetitive paragraph (l) of the proposed AD to state
inspections required by this [EASA] AD. that previous repair instructions that UAL and AAL requested that
superseded ALI 531110 also terminate paragraphs (i) and (j) of the proposed
Related investigative actions include
the inspections required by paragraph AD be revised to list specific affected
checking the edge margins of the holes.
(g) of the proposed AD for the repaired manufacturer serial numbers (MSNs). In
Corrective actions include reaming
holes. UAL noted that they had several addition, UAL and AAL requested that
affected crossbeams and frames and
RDASs that state that the inspection the original equipment manufacturer
cold working the frames. You may
requirements of the RDAS supersede (OEM) revise the Airbus RDASs to
examine the MCAI in the AD docket on
ALI 531110 for the repaired fasteners. correct any problems. AAL pointed out
the internet at http://
UAL stated that these repairs involved that the original RDAS was approved by
www.regulations.gov by searching for
enlarging the holes and fasteners, an EASA DOA and stated that operators
and locating Docket No. FAA–2017–
thereby making it impossible for them to should therefore not be required to
1093.
accomplish the inspections in obtain a new approval. UAL requested
Comments accordance with Airbus Service Bulletin that if we do not provide revised RDASs
We gave the public the opportunity to A320–53–1286, Revision 01, dated or a list of affected MSNs, we instead
participate in developing this AD. The December 22, 2015. provide a pre-defined solution for the
following presents the comments We disagree with revising paragraph repair. UAL suggested that we should
received on the NPRM and the FAA’s (l) of this AD to specify terminating provide instructions for replacing
response to each comment. action to paragraph (g) of this AD. An EN6114 fasteners with EN6115
operator who is unable to complete fasteners. UAL further requested that if
Requests To Revise Repair Instructions certain requirements in this AD due to the repairs require case-by-case
for Repairs Done Using an Airbus existing repairs may request an evaluations, the repair instructions
Repair Design Approval Sheet (RDAS) alternative method of compliance should define the repair compliance
American Airlines (AAL) and United (AMOC) under the provisions of time, rather than having a set 24 month
Airlines (UAL) requested that the repair paragraph (s)(1) of this AD. compliance time, which may not work
instructions in paragraph (l) of the for every configuration.
Request To Remove or Revise UAL also noted that the issue with
proposed AD be revised to remove
Paragraph (n) of the Proposed AD Airbus Repair Instruction R53112926
requirements to obtain new repair
instructions for any airplanes on which AAL requested that paragraph (n) of issue A or B is that it called out the
repairs were done using the instructions the proposed AD be revised to remove wrong fastener; EN6115 should have
in an Airbus RDAS. AAL noted that the requirements to obtain new repair been used instead of EN6114.
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original RDAS approval was given by an instructions for any airplanes on which UAL requested that we add a
EASA Design Organization Approval repairs were done using the instructions statement to paragraph (j) of this AD
(DOA), so new approval should not be in an Airbus RDAS unrelated to ALI stating that no additional repair
needed. Instead, AAL suggested that the task 531110. AAL noted that the original instructions are needed if a repair was
issuer of the RDASs should be required RDAS approval was given by an EASA accomplished using Airbus Repair
to revise the RDASs as necessary. UAL DOA, so new approval should not be Instruction R53112926 issue A or B and
noted that an RDAS already defines needed. Instead, AAL suggested that the EN6115 fasteners.
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rules on aviation safety. Subtitle I, 2. Is not a ‘‘significant rule’’ under the in paragraphs (c)(1), (c)(2), and (c)(3) of this
section 106, describes the authority of DOT Regulatory Policies and Procedures AD.
the FAA Administrator. Subtitle VII: (44 FR 11034, February 26, 1979), (1) Airplanes on which Airbus
Aviation Programs, describes in more 3. Will not affect intrastate aviation in modification 161255 has been embodied in
Alaska, and production.
detail the scope of the Agency’s (2) Model A319 series airplanes on which
authority. 4. Will not have a significant
Airbus modifications 28238, 28162, and
We are issuing this rulemaking under economic impact, positive or negative, 28342 have been concurrently embodied in
the authority described in Subtitle VII, on a substantial number of small entities production.
Part A, Subpart III, Section 44701: under the criteria of the Regulatory (3) Model A318 series airplanes on which
‘‘General requirements.’’ Under that Flexibility Act. Airbus modification 39195 has been
section, Congress charges the FAA with embodied in production.
List of Subjects in 14 CFR Part 39
promoting safe flight of civil aircraft in Air transportation, Aircraft, Aviation (d) Subject
air commerce by prescribing regulations safety, Incorporation by reference, Air Transport Association (ATA) of
for practices, methods, and procedures Safety. America Code 53, Fuselage.
the Administrator finds necessary for
safety in air commerce. This regulation Adoption of the Amendment (e) Reason
is within the scope of that authority Accordingly, under the authority This AD was prompted by reports of early
because it addresses an unsafe condition cracking on the four holes of the crossbeam
delegated to me by the Administrator, splicing at certain fuselage frames (FR). We
that is likely to exist or develop on the FAA amends 14 CFR part 39 as are issuing this AD to detect and correct
products identified in this rulemaking follows: cracking at two upper rows of fasteners of the
action. crossbeam splicing at FR16 and FR20, on
This AD is issued in accordance with PART 39—AIRWORTHINESS both the left-hand (LH) and right-hand (RH)
authority delegated by the Executive DIRECTIVES sides, which can result in reduced structural
Director, Aircraft Certification Service, integrity of the airplane due to the failure of
■ 1. The authority citation for part 39 structural components.
as authorized by FAA Order 8000.51C.
continues to read as follows:
In accordance with that order, issuance (f) Compliance
of ADs is normally a function of the Authority: 49 U.S.C. 106(g), 40113, 44701.
Comply with this AD within the
Compliance and Airworthiness § 39.13 [Amended] compliance times specified, unless already
Division, but during this transition done.
period, the Executive Director has ■ 2. The FAA amends § 39.13 by adding
delegated the authority to issue ADs the following new airworthiness (g) Repetitive Rototest Inspections
applicable to transport category directive (AD): Before exceeding the threshold specified in
airplanes to the Director of the System 2018–14–09 Airbus: Amendment 39–19329; table 1 to paragraphs (g) and (n) of this AD,
Oversight Division. Docket No. FAA–2017–1093; Product or table 2 to paragraphs (g) and (n) of this AD,
Identifier 2017–NM–018–AD. as applicable to airplane configuration (pre-
Regulatory Findings or post-modification 20416 or pre- or post-
(a) Effective Date modification 21999): Do a special detailed
We determined that this AD will not This AD is effective August 23, 2018. (rototest) inspection of the two upper rows of
have federalism implications under fasteners of the crossbeam splicing at FR16
(b) Affected ADs
Executive Order 13132. This AD will and FR20 on both LH and RH sides, in
not have a substantial direct effect on None. accordance with the Accomplishment
the States, on the relationship between (c) Applicability Instructions of Airbus Service Bulletin A320–
the national government and the States, 53–1286, Revision 01, dated December 22,
This AD applies to Airbus Model A318– 2015. Thereafter, repeat the inspection at the
or on the distribution of power and 111, –112, –121, and –122 airplanes; Model intervals specified in table 1 to paragraphs (g)
responsibilities among the various A319–111, –112, –113, –114, –115, –131,
and (n) of this AD, or table 2 to paragraphs
levels of government. –132, and –133 airplanes; Model A320–211,
(g) and (n) of this AD, as applicable to
For the reasons discussed above, I –212, –214, –216, –231, –232, and –233
airplane configuration (pre- or post-
airplanes; and Model A321–111, –112, –131,
certify that this AD: –211, –212, –213, –231, and –232 airplanes,
modification 20416 or pre- or post-
1. Is not a ‘‘significant regulatory modification 21999).
certificated in any category, all manufacturer
action’’ under Executive Order 12866, serial numbers, except the airplanes specified BILLING CODE 4910–13–P
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![Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34039
(k) Optional Terminating Action for (2) Modification of the two upper rows of that are not identified as RC are
Airplanes Post-Modification 20416 or Post- fasteners of the crossbeam splicing at FR16 recommended. Those procedures and tests
Modification 21999 and FR20 on both LH and RH sides of an that are not identified as RC may be deviated
Modification of an airplane post- airplane, in accordance with the from using accepted methods in accordance
modification 20416 or post-modification Accomplishment Instructions of Airbus with the operator’s maintenance or
21999 in accordance with the Service Bulletin A320–53–1295, including inspection program without obtaining
Accomplishment Instructions of Airbus Appendixes 01 and 02, dated June 29, 2015, approval of an AMOC, provided the
Service Bulletin A320–53–1295, including except as required by paragraph (r) of this procedures and tests identified as RC can be
Appendixes 01 and 02, dated June 29, 2015, AD, as specified in paragraphs (k) and (m) of done and the airplane can be put back in an
except as required by paragraph (r) of this this AD, constitutes terminating action for airworthy condition. Any substitutions or
AD, constitutes terminating action for the the inspection requirements of ALI task changes to procedures or tests identified as
repetitive inspections required by paragraph 531110, for those holes for that airplane.
RC require approval of an AMOC.
(g) of this AD for that airplane. (p) No Reporting Requirement
(t) Related Information
(l) Information on Post-Repair Actions for Although Airbus Service Bulletin A320–
53–1286, Revision 01, dated December 22, (1) Refer to Mandatory Continuing
Certain Airplanes
2015, specifies to submit certain information Airworthiness Information (MCAI) EASA AD
For an airplane that has been inspected per 2016–0139, dated July 14, 2016, for related
ALI task 531110 and repaired before the to the manufacturer, and specifies that action
as ‘‘RC’’ (Required for Compliance), this AD information. This MCAI may be found in the
effective date of this AD using the AD docket on the internet at http://
instructions in an Airbus Repair Design does not include that requirement.
www.regulations.gov by searching for and
Approval Sheet (RDAS): each applicable (q) Credit for Previous Actions locating Docket No. FAA–2017–1093.
RDAS contains next inspection and This paragraph provides credit for actions (2) For more information about this AD,
compliance time for the inspection for each required by paragraph (g) and (h) of this AD, contact Sanjay Ralhan, Aerospace Engineer,
repaired hole. if those actions were performed before the International Section, Transport Standards
(m) Partial Terminating Action for Airplanes effective date of this AD using Airbus Service Branch, FAA, 2200 South 216th St., Des
Post-Modification 20416 or Post- Bulletin A320–53–1286, dated June 29, 2015. Moines, WA 98198; telephone and fax 206–
Modification 21999 231–3223.
(r) Service Information Exceptions
For an airplane post-modification 20416 or (3) Service information identified in this
Where Subtasks 531295–960–001–001 and AD that is not incorporated by reference is
post-modification 21999, modification in 532195–960–002–001 of Airbus Service
accordance with the Accomplishment available at the addresses specified in
Bulletin A320–53–1295, including paragraphs (u)(3) and (u)(4) of this AD.
Instructions of Airbus Service Bulletin A320– Appendixes 01 and 02, dated June 29, 2015,
53–1295, including Appendixes 01 and 02, refer to actions when an existing hole (u) Material Incorporated by Reference
dated June 29, 2015, except as required by diameter is ‘‘more than or equal to the
paragraph (r) of this AD, for the applicable (1) The Director of the Federal Register
minimum starting hole diameter,’’ this AD approved the incorporation by reference
fastener holes, where no damage or cracks requires applicable actions in cases where
were detected (i.e., those not repaired) during (IBR) of the service information listed in this
the hole diameter is ‘‘more than or equal to paragraph under 5 U.S.C. 552(a) and 1 CFR
the latest inspection as required by paragraph the maximum starting hole diameter.’’
(g) of this AD, constitutes terminating action part 51.
for the repetitive inspections of those fastener (s) Other FAA AD Provisions (2) You must use this service information
holes as required by paragraph (g) of this AD The following provisions also apply to this as applicable to do the actions required by
for that airplane. AD: this AD, unless this AD specifies otherwise.
(1) Alternative Methods of Compliance (i) Airbus Service Bulletin A320–53–1286,
(n) Actions for Airplanes With Certain Revision 01, dated December 22, 2015.
(AMOCs): The Manager, International
Repairs (ii) Airbus Service Bulletin A320–53–1295,
Section, Transport Standards Branch, FAA,
For an airplane that has been repaired has the authority to approve AMOCs for this including Appendixes 01 and 02, dated June
before the effective date of this AD in the AD, if requested using the procedures found 29, 2015.
areas described in this AD using the in 14 CFR 39.19. In accordance with 14 CFR (3) For service information identified in
instructions in an Airbus RDAS unrelated to 39.19, send your request to your principal this AD, contact Airbus, Airworthiness
ALI task 531110: Before exceeding the inspector or local Flight Standards District Office—EIAS, Rond-Point Emile Dewoitine
compliance times specified in table 1 to Office, as appropriate. If sending information No: 2, 31700 Blagnac Cedex, France;
paragraphs (g) and (n) of this AD or table 2 directly to the International Section, send it telephone +33 5 61 93 36 96; fax +33 5 61
to paragraphs (g) and (n) of this AD, as to the attention of the person identified in 93 44 51; email account.airworth-eas@
applicable, contact the Manager, paragraph (t)(2) of this AD. Information may airbus.com; internet http://www.airbus.com.
International Section, Transport Standards be emailed to: 9-ANM-116-AMOC- (4) You may view this service information
Branch, FAA; or EASA; or Airbus’s EASA REQUESTS@faa.gov. Before using any at the FAA, Transport Standards Branch,
DOA for corrective action instructions and approved AMOC, notify your appropriate 2200 South 216th St., Des Moines, WA. For
accomplish those instructions accordingly. If principal inspector, or lacking a principal information on the availability of this
approved by the DOA, the approval must inspector, the manager of the local flight material at the FAA, call 206–231–3195.
include the DOA-authorized signature. standards district office/certificate holding (5) You may view this service information
Accomplishment of corrective action(s) on an district office. that is incorporated by reference at the
airplane, as required by this paragraph, does (2) Contacting the Manufacturer: For any National Archives and Records
not constitute terminating action for the requirement in this AD to obtain corrective Administration (NARA). For information on
repetitive inspections required by paragraph actions from a manufacturer, the action must the availability of this material at NARA, call
(g) of this AD for that airplane, as applicable, be accomplished using a method approved 202–741–6030, or go to: http://
unless specified otherwise in the by the Manager, International Section,
www.archives.gov/federal-register/cfr/ibr-
instructions. Transport Standards Branch, FAA; or EASA;
locations.html.
or Airbus’s EASA DOA. If approved by the
(o) Terminating Action for ALI Tasks
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DOA, the approval must include the DOA- Issued in Des Moines, Washington, on June
(1) Accomplishment of an inspection as authorized signature. 29, 2018.
required by paragraph (g) of this AD or (3) Required for Compliance (RC): Except Jeffrey E. Duven,
instructions as required by paragraph (l) of as required by paragraphs (h)(1) and (p) of
Director, System Oversight Division, Aircraft
this AD, as applicable, constitutes this AD: If any service information contains
Certification Service.
terminating action for the inspection procedures or tests that are identified as RC,
requirements of ALI task 531110, for that those procedures and tests must be done to [FR Doc. 2018–14687 Filed 7–18–18; 8:45 am]
airplane. comply with this AD; any procedures or tests BILLING CODE 4910–13–P
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Document Created: 2018-07-19 01:34:44
Document Modified: 2018-07-19 01:34:44
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective August 23, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3223. | |
| FR Citation | 83 FR 34034 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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