Airworthiness Directives; Airbus Airplanes, 13387-13395 [2018-05019]

Download as PDF (iv) With the t-bolt in the 12 o’clock position, visually inspect the coupling for the attachment of the outer band to the v-retainer coupling segments by inspecting for gaps between the outer band and the v-retainer coupling segments between approximately the 1 o’clock through 11 o’clock position. It is recommended to use backlighting to see gaps. If gaps between the outer band and the v-retainer coupling segments are found, do not re-install the v-band coupling. Before further flight, you must install a new v-band coupling and restart the hours TIS for the repetitive replacement of the v-band coupling. (v) Visually inspect the bend radii of the coupling v-retainer coupling segments for cracks. Inspect the radii throughout the length of the segment. See figure 1 to paragraphs (k)(1)(iii) and (v) of this AD. If any cracks are found, do not re-install the vband coupling. Before further flight, you must install a new v-band coupling and restart the hours TIS for the repetitive replacement of the v-band coupling. (vi) Visually inspect the outer band opposite the t-bolt for damage (distortion, creases, bulging, or cracks), which may be caused from excessive spreading of the coupling during installation and/or removal. If any damage is found, do not re-install the v-band coupling. Before further flight, you must install a new v-band coupling and restart the hours TIS for the repetitive replacement of the v-band coupling. (2) If the removed exhaust tailpipe v-band coupling passes all of the inspection steps listed in paragraphs (k)(1)(i) through (vi) of this AD, you may re-install the same v-band coupling. After the coupling is re-installed and torqued as specified in Replacement of the V-Band Coupling, paragraph (i) of this AD, verify there is space between each vretainer coupling segment below the t-bolt. If there is no space between each v-retainer coupling segment below the t-bolt, before VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 further flight, you must install a new v-band coupling and restart the hours TIS for the repetitive replacement of the v-band coupling. (3) The inspections required in paragraphs (k)(1) and (2) of this AD only apply to reinstalling the same exhaust tailpipe v-band coupling that was removed as specified in paragraph (j) of this AD. It does not apply to installation of a new v-band coupling. These inspections do not terminate the 500-hour TIS repetitive replacement of the v-band coupling and do not restart the hours TIS for the repetitive replacement of the v-band coupling. (4) As of May 3, 2018 (the effective date of this AD), do not install a used exhaust tailpipe v-band coupling on the airplane except for the reinstallation of the inspected exhaust tailpipe v-band coupling that was removed as specified in paragraphs (j) and (k) of this AD. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. The Manager, Chicago ACO Branch, FAA, has the authority to approve AMOCs concerning STC SA1035WE, 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 Wichita ACO Branch, send it to the attention of the person identified in paragraph (m) of this AD. If sending information directly to the manager of the Chicago ACO Branch, send it to the attention of John Tallarovic, Aerospace Engineer, AIR–7C3 Chicago ACO Branch, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; telephone: (847) 294–8180; fax: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 13387 (847) 294–7834; email: john.m.tallarovic@ faa.gov. (2) 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. (m) Related Information For more information about this AD, contact Thomas Teplik, Aerospace Engineer, Wichita ACO Branch, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4196; fax: (316) 946–4107; email: thomas.teplik@faa.gov. (n) Material Incorporated by Reference None. Issued in Kansas City, Missouri, on March 20, 2018. Melvin J. Johnson, Deputy Director, Policy & Innovation Division, Aircraft Certification Service. [FR Doc. 2018–06092 Filed 3–28–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0902; Product Identifier 2016–NM–188–AD; Amendment 39–19224; AD 2018–06–04] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\29MRR1.SGM 29MRR1 ER29MR18.001</GPH> rmajette on DSKBCKNHB2PROD with RULES Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations 13388 ACTION: Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations Final rule. We are superseding Airworthiness Directive (AD) 2004–03– 07, which applied to certain Airbus Model A320–111, –211, –212, and –231 series airplanes. AD 2004–03–07 required repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at a certain frame (FR), adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. This new AD retains certain requirements of AD 2004–03–07, expands the applicability, and requires an inspection of the fastener holes on the pressure panel and modification or repair as applicable. This AD was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket, and by the discovery of additional cracks under the longitudinal beams at locations that are not included in the inspection area required by AD 2004–03–07. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 3, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 3, 2018. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 15, 2004 (69 FR 5907, February 9, 2004). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport 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– 0902. rmajette on DSKBCKNHB2PROD with RULES SUMMARY: 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– 0902; 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 VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 other information. The 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 206–231–3223; fax 206–231– 3398. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004–03–07, Amendment 39–13451 (69 FR 5907, February 9, 2004) (‘‘AD 2004–03–07’’). AD 2004–03–07 applied to certain Airbus Model A320–111, –211, –212, and –231 series airplanes. The NPRM published in the Federal Register on October 6, 2017 (82 FR 46729). The NPRM was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, and by the discovery of additional cracks under the longitudinal beams at locations that are not included in the inspection area required by AD 2004–03–07. The NPRM proposed to continue to require certain requirements of AD 2004–03–07. The NPRM also proposed to expand the applicability and require an inspection of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam and modification or repair as applicable. We are issuing this AD to detect and correct fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at the FR 36 adjacent to the longitudinal beams, which could result in reduced structural integrity of the airplane and possible rapid decompression of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0206, dated October 13, 2016; corrected October 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318 and Model A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321–111, –112, –131,–211, –21–, 213, PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 –231, and –232 airplanes. The MCAI states: During fatigue tests, cracks were found around the fasteners connecting the pressure panel with the flexible bracket at fuselage frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH) and right-hand (RH) sides. This condition, if not detected and corrected, could impair the structural integrity of the aeroplane. To address this unsafe condition, DGAC ´ ´ [Direction Generale de l’Aviation Civile] France issued [French] AD 2000–531–155(B) [which corresponds with FAA AD 2004–03– 07] to require repetitive inspections of the longitudinal beams of the FR 36 pressure panel and, depending on findings, the accomplishment of a repair. Since that [French] AD was issued, additional cracks have been found under the beams, but in locations not covered by the required inspections. Fatigue and damage tolerance analyses were performed, the results of which indicated that all the holes in the pressure panel above all the longitudinal beams have to be cold worked. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 2000–531–155(B), which is superseded, extends the applicability to all A320 family aeroplanes and requires [a special detailed inspection of the fastener holes on the pressure panel between FR35 and FR36 under the longitudinal beam and] modification [or repair] of all the affected holes. This [EASA] AD is republished to correct the number of the superseded DGAC AD. 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– 0902. 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. Request To Remove Reporting Requirement United Airlines (UAL) requested that we omit paragraph (k)(2)(ii) of the proposed AD, which would require operators to report any findings of cracking that exceeded the limits specified in Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016, from the proposed AD. UAL stated that paragraph (k)(2)(ii) of the proposed AD is confusing and unjustified because there is no explanation for why it is required when it was not included in EASA AD 2016–0206. UAL stated the requirement to report findings in paragraph (k)(2)(ii) is redundant with the actions of paragraph (k)(2)(i) of the proposed AD. UAL noted that for the E:\FR\FM\29MRR1.SGM 29MRR1 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations rmajette on DSKBCKNHB2PROD with RULES crack repair specified in paragraph (k)(2)(i) of the proposed AD, the findings would be reported. UAL suggested the paragraph (k)(2)(ii) of the proposed AD required using an unconventional means to report findings that might require additional procedures and training specific to the proposed AD. UAL also stated that restricting reporting to a website may cause issues if the sender does not have access and that Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016, lists alternative options for reporting, like email, fax, or mail. We agree to remove the reporting requirement specified in paragraph (k)(2)(ii) of the proposed AD from this AD. Neither Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016, nor the MCAI specifically includes reporting to a website as specified in paragraph (k)(2)(ii) of the proposed AD. We note that Airbus Service Bulletin A320–53– 1264, Revision 01, excluding Appendix 01, dated July 4, 2016, does include reporting within the required for compliance (RC) procedure for the repair, which indicates that reporting would be required regardless of whether reporting was called out in the MCAI. We also verified with EASA that reporting should be done as defined in the service information. However, we have determined that a specific reporting requirement is not necessary. As stated by the commenter, operators will report findings to obtain the repair, which is specified in paragraph (k)(2)(i) of the proposed AD. We have removed paragraphs (k)(2)(i) and (k)(2)(ii) from this AD and revised paragraph (k)(2) of this AD to include the information that was in paragraph (k)(2)(i) of the proposed AD. We have also added paragraph (n) to this AD to specify that reporting is not required for this AD and redesignated the subsequent paragraphs accordingly. Request To Refer to Latest Service Information Two commenters requested that we refer to the latest service information. UAL requested that we update paragraph (k) of the proposed AD to use Airbus Service Bulletin A320–53–1264, Revision 02, dated March 14, 2017, which corrects an error with the fastener lengths for part number (P/N) EN6115K3. We infer that UAL intended to refer to Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, because there is no Revision 02 for Airbus Service Bulletin A320–53–1264, and because P/N EN6115K3 is referenced in Airbus VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017. Airbus requested that we refer to Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, in the proposed AD. We agree to refer to the latest service information in this AD. In addition to Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, we have also reviewed Airbus Service Bulletin A320–53–1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017, which updates kit information and figures among other minor changes. We have revised paragraph (k)(1) of this AD accordingly. We have also provided credit for Airbus Service Bulletin A320– 53–1240, Revision 01, dated April 4, 2016; and Airbus Service Bulletin A320–53–1263, Revision 01, dated February 29, 2016; in paragraphs (o)(3)(ii) and (o)(3)(iv) of this AD, respectively. Request To Include Additional Airplane Models in the Applicability Airbus requested that Model A320– 215 and Model A320–216 airplanes be in included in the applicability of the proposed AD. The commenter noted that these airplane models are included in the MCAI. We do not agree with the commenter’s request. We have not certified Model A320–215 airplanes for operation in the U.S., and therefore, we did not include that model in the applicability of this AD. We did not include Model A320– 216 airplanes in the applicability of this AD because the MCAI was already added to the required airworthiness action list (RAAL) for Model A320–216 airplanes. We have not changed this AD in this regard. Request To Revise Service Bulletin Descriptions in the Related Service Information Under 1 CFR Part 51 Paragraph in the Preamble of the NPRM Airbus stated that the proposed AD identifies the means of inspection, i.e., rototest inspection, using three different wordings in the descriptions of the service bulletins specified in the Related Service Information under 1 CFR part 51 paragraph in the preamble of the NPRM. Airbus also stated that Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, no longer contains a rototest inspection requirement. In addition, Airbus noted that Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, does not contain repair instructions. We infer the commenter is requesting that we revise the service bulletin descriptions in the PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 13389 Related Service Information under 1 CFR part 51 paragraph in the preamble of the NPRM. We acknowledge the description of the rototest inspection is different for each service bulletin specified in the Related Service Information under 1 CFR part 51 paragraph in the preamble of the NPRM. In the NPRM, we matched the description of the inspection as given in each service bulletin specified in the Related Service Information under 1 CFR part 51 paragraph. We have revised the description of Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017, to remove the reference to an inspection and repair. Request To Clarify What Prompted the Proposed AD Airbus requested that we revise paragraph (e) of the proposed AD to clarify that the proposed AD was prompted by a report of cracking in an additional area. Airbus stated that paragraph (e) of the proposed AD describes only the fatigue test results that prompted AD 2004–03–07. We agree to revise paragraph (e) of this AD for clarity. This AD was prompted by the original report of cracking and the additional report. We have revised paragraph (e) of this AD to include the additional cracking that prompted the issuance of this AD. Request To Revise Repair Language in Paragraph (k)(2)(i) of the Proposed AD Airbus requested that we revise the language in paragraph (k)(2)(i) of the proposed AD, which specifies to repair any cracking in accordance with Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016. Airbus stated that this service information does not provide direct repair instructions and instead specifies to contact Airbus. We agree to clarify the language in paragraph (k)(2) of this AD (which corresponds with paragraph (k)(2)(i) of the proposed AD). Paragraph (k)(2) of this AD also specifies that where Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance), operators must request approval of repair instructions using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD, and accomplish the repair accordingly within the compliance time specified in those instructions. We have not changed this AD in this regard. E:\FR\FM\29MRR1.SGM 29MRR1 13390 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations Request To Include Wording From the MCAI in Paragraph (m)(1)(iii) of the Proposed AD Airbus requested that we revise paragraph (m)(1)(iii) of the proposed AD. Airbus stated the wording is similar to paragraph (9) of the MCAI except that the important wording ‘‘in accordance with Airbus approved instructions that identify the repair as technically equivalent to the accomplishment of Airbus SB A320–53–1240 or SB A320– 53–1263’’ is omitted. We disagree with the commenter’s request. The intent of paragraph (m)(1)(iii) of this AD is to obtain corrective actions from the manufacturer that are approved by the FAA, EASA, or Airbus’s EASA Design Organization Approval (DOA). These approved instructions will provide an equivalent level of safety. We have not changed this AD in this regard. Conclusion We reviewed the available data, including 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 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. 1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017, which describe procedures for modifying the pressure panel above the left and right longitudinal beams, including related investigative actions (e.g., eddy current rotating probe inspection of the fastener holes) and corrective actions (e.g., repair), by adding a doubler and a filler, and cold expansion of the holes under the longitudinal beam at FR 36 for airplanes on which cracking was found. These documents are distinct because they are different revision levels. Airbus has also issued Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016. The service information describes procedures for a special detailed inspection (rotating probe) for cracking of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam and repair of any crack. 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. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–53–1029, Revision 01, including Appendix 01, dated April 29, 2002. The service information describes procedures for repairing cracking. Airbus has also issued Service Bulletin A320–53–1240, Revision 01, dated April 4, 2016; and A320–53–1240, Revision 02, dated March 14, 2017, which describe procedures for modifying the pressure panel above the left and right longitudinal beams, by cold working the attachment holes under the longitudinal beam at FR 36 for airplanes on which no cracking was found. Service Bulletin A320–53–1240, Revision 01, dated April 4, 2016 also includes related investigative action (e.g., high frequency eddy current (rototest) inspection of all the removed fastener holes) and corrective actions (e.g., repair). These documents are distinct since they are different revision levels. Airbus has also issued Service Bulletin A320–53–1263, Revision 01, dated February 29, 2016; and A320–53– Costs of Compliance We estimate that this AD affects 737 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection [Retained from AD 2004–03– 07]. Inspection [new proposed requirement] Up to 2 work-hours × $85 per hour = $170 per inspection cycle. 13 work-hours × $85 per hour = $1,105 We estimate the following costs to do any necessary modifications that will be Cost per product Parts cost $0 $0 required based on the results of the inspection. We have no way of Cost on U.S. operators Up to $170 per inspection cycle. $1,105 .................... Up to $125,290 per inspection cycle. $814,385. determining the number of aircraft that might need these modifications: ON-CONDITION COSTS Labor cost Parts cost Modification ...................................................... rmajette on DSKBCKNHB2PROD with RULES Action Up to 213 work-hours × $85 per hour = $18,105. Up to $8,510 .............. We have received no definitive data that will enable us to provide a cost estimate for the on-condition repairs specified in this AD. 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 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: VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Cost per product Up to $26,615. 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. E:\FR\FM\29MRR1.SGM 29MRR1 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (Airworthiness Directive (AD) 2004–03– 07, Amendment 39–13451 (69 FR 5907, February 9, 2004), and adding the following new AD: rmajette on DSKBCKNHB2PROD with RULES ■ 2018–06–04 Airbus: Amendment 39–19224; Docket No. FAA–2017–0902; Product Identifier 2016–NM–188–AD. (a) Effective Date This AD is effective May 3, 2018. VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 (b) Affected ADs This AD replaces AD 2004–03–07, Amendment 39–13451 (69 FR 5907, February 9, 2004) (‘‘AD 2004–03–07’’). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 151574 was embodied in production. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by fatigue tests which revealed cracking around the fasteners attaching the pressure panel to the flexible bracket at frame (FR) 36, adjacent to the longitudinal beams on the left and right sides of the airplane, and by the discovery of additional cracks under the longitudinal beams at locations that are not included in the inspection area required by AD 2004–03– 07. We are issuing this AD to detect and correct fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at the FR 36 adjacent to the longitudinal beams, which could result in reduced structural integrity of the airplane and possible rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Follow-on Actions, With No Changes This paragraph restates the requirements of paragraphs (a) and (b) of AD 2004–03–07, with no changes. (1) For Model A320–211, –212, and –231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or on which Airbus Service Bulletin A320–53–1029, Revision 01, including Appendix 01, dated April 29, 2002, has been incorporated in service: Prior to the accumulation of 30,000 total flight cycles, do a rotating probe inspection on airplanes with a center fuel tank, or a detailed inspection on airplanes without a center fuel tank, to detect cracking around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1030, Revision 01, excluding Appendix 01, dated May 21, 2002. (2) If no crack is detected by the inspection required by paragraph (g)(1) of this AD, PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 13391 repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank. (h) Retained Corrective Actions, With Specific Delegation Approval Language This paragraph restates the requirements of paragraphs (c) and (d) of AD 2004–03–07, with specific delegation approval language. (1) If any crack is detected during any inspection required by paragraph (g)(1) of this AD, before further flight, repair the affected structure by accomplishing all applicable actions in accordance with paragraphs 3.B. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320–53–1030, Revision 01, excluding Appendix 01, dated May 21, 2002. Repeat the applicable inspection thereafter at intervals not to exceed 6,000 flight cycles for airplanes without a center fuel tank, and at intervals not to exceed 18,000 flight cycles for airplanes with a center fuel tank. For any area where cracking is repaired, the repair constitutes terminating action for the repetitive inspection of that area. Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin A320–53–1030 references Airbus Service Bulletin A320–53– 1029, Revision 01, including Appendix 01, dated April 29, 2002, as an additional source of service information for certain repairs. (2) If Airbus Service Bulletin A320–53– 1030, Revision 01, excluding Appendix 01, dated May 21, 2002, specifies to contact the manufacturer for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD. (i) Retained Optional Terminating Action, With Revised Compliance Language This paragraph restates the requirements of paragraph (e) of AD 2004–03–07, with revised compliance language, to provide optional terminating action for paragraphs (g) and (h) of this AD. For Model A320–211, –212, and –231 series airplanes having serial numbers 0002 through 0107 inclusive, except those airplanes on which Airbus Modification 21202/K1432 has been incorporated in production, or Airbus Service Bulletin A320–53–1029, Revision 01, including Appendix 01, dated April 29, 2002, has been incorporated in service: Modification, before the effective date of this AD, of the structure around the fasteners that attach the pressure panel to the flexible bracket at FR 36, adjacent to the longitudinal beams on the left and right sides of the airplane, by accomplishing all applicable actions in accordance with paragraphs 3.A. through 3.E. of the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1029, Revision 01, including Appendix 01, dated April 29, 2002, constitutes terminating action for the actions required by paragraphs (g) and (h) of this AD. (j) New Requirement of This AD: Inspection For all airplanes, except for airplanes identified in paragraph (l) of this AD: At the applicable time specified in table 1 to paragraph (j) of this AD, do a special detailed inspection for cracking of the fastener holes E:\FR\FM\29MRR1.SGM 29MRR1 13392 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations on the pressure panel between FR 35 and FR 36 under the longitudinal beam, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016. Table 1 to Paragraph (j) of this AD - Pressure Panel Inspection /Modification Threshold Affected airplanes Time accumulated by the airplane on the effective date of this AD Compliance time (flight cycles and flight hours since the airplane's first flight) (flight cycles or flight hours, whichever occurs first) A: Before accumulating 12,000 flight cycles or 24,000 flight hours since the airplane's first flight; or All airplanes, except Model A318 Elite airplanes; Model A319CJ airplanes (Corporate Jet - airplanes equipped with Modifications 28238, 28162, and 28342); Airbus Model A319 series airplanes on which the actions specified in Airbus Service Bulletin A320-57-ll93 have been embodied (sharklets installed as retrofit); Airbus Model A320 series airplanes on which the actions specified in Airbus Service Bulletin A320-57-1193 have been embodied (sharklets installed as retrofit) Less than 12,000 flight cycles and 24,000 flight hours B: Within 5,000 flight cycles or 10,000 flight hours after the effective date of this AD; whichever occurs later, A orB Within 5,000 flight cycles or 10,000 flight hours after the effective date of this AD, without exceeding 33,000 flight cycles or 66,000 flight hours since the airplane's first flight 30,000 flight cycles or 60,000 flight hours or more, but less than 40,000 flight cycles and 80,000 flight hours Within 3,000 flight cycles or 6,000 flight hours after the effective date of this AD, without exceeding 41,800 flight cycles or 83,600 flight hours since the airplane's first flight 40,000 flight cycles or 80,000 flight hours or more, but less than 44,000 flight cycles and 88,000 flight hours Within 1,800 flight cycles or 3,600 flight hours after the effective date of this AD, without exceeding 44,600 flight cycles or 89,200 flight hours since the airplane's first flight 44,000 flight cycles or 88,000 flight hours or more Affected airplanes 12,000 flight cycles or 24,000 flight hours or more, but less than 30,000 flight cycles and 60,000 flight hours Within 600 flight cycles or 1,200 flight hours after the effective date of this AD Time accumulated by the airplane on the effective date of this AD Compliance time (flight cycles and flight hours since the airplane's first flight) (flight cycles or flight hours, whichever occurs first) A: Before accumulating 11,300 flight cycles or 33,900 flight hours since airplane first flight; or Less than 11,300 flight cycles and 33,900 flight hours B: Within 2,500 flight cycles or 7,600 flight hours after the effective date of this AD; Model A318 Elite airplanes whichever occurs later, A orB Within 2,500 flight cycles or 7,600 flight hours after the effective date of this AD 11,300 flight cycles or 33,900 flight hours or more A: Before accumulating 6,300 flight cycles or 27,000 flight hours since airplane first flight; or B: Within 2,300 flight cycles or 11,300 flight hours after the effective date of this AD; whichever occurs later, A orB 15:09 Mar 28, 2018 Within 2,300 flight cycles or 11,300 flight hours after the effective date of this AD, without exceeding 15,700 flight cycles or 75,100 flight hours since the airplane's first flight 14,300 flight cycles or 68,300 flight hours or more VerDate Sep<11>2014 6,300 flight cycles or 27,000 flight hours or more, but less than 14,300 flight cycles and 68,300 flight hours Within 1,400 flight cycles or 6,800 flight hours after the effective date of this AD Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4725 E:\FR\FM\29MRR1.SGM 29MRR1 ER29MR18.008</GPH> Model A319CJ airplanes on which the actions specified in Airbus Service Bulletin A320-57-1193 havenotbeen embodied (sharklets not installed) ER29MR18.007</GPH> rmajette on DSKBCKNHB2PROD with RULES Less than 6,300 flight cycles and 27,000 flight hours Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations Time accumulated by the airplane on the effective date of this AD Affected airplanes 13393 Compliance time (flight cycles or flight hours, whichever occurs first) (flight cycles and flight hours since the airplane's first flight) A: Before accumulating 9,800 flight cycles or 19,600 flight hours since the airplane's first flight; or Less than 9,000 flight cycles and 18,000 flight hours B: Within 3,300 flight cycles or 6,600 flight hours after the effective date of this AD; whichever occurs later, A orB* Model A319 and A320 series airplanes on which the actions specified in Airbus Service Bulletin A320-57-1193 have been embodied (sharklets installed) 9,000 flight cycles or 18,000 flight hours or more, but less than 24,000 flight cycles and 48,000 flight hours 24,000 flight cycles or 48,000 flight hours or more, but less than 30,000 flight cycles and 60,000 flight hours 30,000 flight cycles or 60,000 flight hours or more, but less than 32,000 flight cycles and 64,000 flight hours 32,000 flight cycles or 64,000 flight hours or more, but less than 33,000 flight cycles and 66,000 flight hours Within 3,300 flight cycles or 6,600 flight hours after the effective date of this AD, without exceeding 25,300 flight cycles or 50,600 flight hours since the airplane's first flight* Within 1,300 flight cycles or 2,600 flight hours after the effective date of this AD, without exceeding 30,700 flight cycles or 61,400 flight hours since the airplane's first flight* Within 700 flight cycles or 1,400 flight hours after the effective date of this AD, without exceeding 32,300 flight cycles or 64,600 flight hours since the airplane's first flight* Within 300 flight cycles or 600 flight hours after the effective date of this AD, without exceeding 33,000 flight cycles or 66,000 flight hours since the airplane's first flight; or within 30 days after the effective date of this AD; whichever occurs later* Time accumulated by the airplane on the effective date of this AD Affected airplanes (flight cycles and flight hours since the airplane's first flight) Compliance time (flight cycles or flight hours, whichever occurs first) Less than 4,200 flight cycles and 18,000 flight hours 4,200 flight cycles or 18,000 flight hours or more, but less than 14,300 flight cycles and 61,400 flight hours Within 1,600 flight cycles or 6,800 flight hours after the effective date of this AD, without exceeding 15,300 flight cycles or 65,700 flight hours since the airplane's first flight** 14,300 flight cycles or 61,400 flight hours or more but less than 18,000 flight cycles or 77,400 flight hours Model A319 airplanes used as CJ post Airbus Service Bulletin A320-57 -1193 A: Before accumulating 4,500 flight cycles or 19,600 flight hours since the airplane's first flight; or B: Within 1,600 flight cycles or 6,800 flight hours after the effective date of this AD; whichever occurs later, A orB** Within 1,000 flight cycles or 4,300 flight hours after the effective date of this AD** For A319 and A320 airplanes with a sharklet installed as a retrofit (post-Airbus Service Bulletin A320-57-1193 (post-mod 160080)): Guidance on determining an alternative compliance time for the initial inspection can be found in in "Compliance Time" of Part 2, Damage Tolerant Airworthiness Limitation Items, of the Model A318/A319/A320/A321 Airworthiness Limitations Section; however, to use that alternative compliance time, operators must request an alternative method of compliance using a method approved in accordance with the procedures specified in paragraph (p)(l) ofthis AD. * Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A320 airplane, pre-Airbus Service Bulletin A320-57 -1193 (pre-mod 160080). (1) If, during any inspection required by paragraph (j) of this AD, no cracking is found, or cracking is found that is within the limits specified in Airbus Service Bulletin A320– VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016: Before further flight, modify the pressure panel above the left and right longitudinal beams, including doing all applicable related investigative and PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017; or Service Bulletin A320–53–1263, Revision 02, excluding E:\FR\FM\29MRR1.SGM 29MRR1 ER29MR18.010</GPH> (k) On-Condition Actions ER29MR18.009</GPH> rmajette on DSKBCKNHB2PROD with RULES **Without exceeding the time at which an inspection is required through the threshold or compliance time of a Model A319CJ airplane, pre-Airbus Service Bulletin A320-57 -1193 (pre-mod 160080). 13394 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations Appendix 01 and including Appendix 02, dated December 6, 2017, as applicable. Do all related investigative and corrective actions before further flight. Where Airbus Service Bulletin A320–53–1240, Revision 02, dated March 14, 2017; or Service Bulletin A320– 53–1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017; specify to contact Airbus for appropriate action: Before further flight, accomplish the repair using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD. (2) If, during any inspection required by paragraph (j) of this AD, any cracking is found that exceeds the limits specified in Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016: Before further flight, repair any cracking in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016. Where Airbus Service Bulletin A320–53– 1264, Revision 01, excluding Appendix 01, dated July 4, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance), before further flight, request approval of repair instructions using a method approved in accordance with the procedures specified in paragraph (p)(2) of this AD, and accomplish the repair accordingly within the compliance time specified in those instructions. If no compliance time is defined in the repair instructions, accomplish the repair before further flight. rmajette on DSKBCKNHB2PROD with RULES (l) Actions for Certain Airplanes For Model A319 and Model A320 series airplanes on which the actions specified in Airbus Service Bulletin A320–57–1193 have been embodied and the airplane has accumulated 33,000 flight cycles or 66,000 flight hours or more since the airplane’s first flight on the effective date of this AD: Within 30 days after the effective date of this AD, contact the Manager, International Section, Transport Standards Branch FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA) for approved repair instructions and within the compliance time specified in those instructions, accomplish the repair accordingly. If approved by the DOA, the approval must include the DOAauthorized signature. If no compliance time is defined in the repair instructions, accomplish the repair before the next flight. (m) Terminating Action for Repetitive Inspections (1) Modification of an airplane as specified in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes terminating action for the repetitive inspection required by paragraph (g)(2) of this AD for that airplane only. (i) Modification of an airplane as required by paragraph (k)(1) of this AD. (ii) Modification of an airplane prior to the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1240, Revision 01, dated April 4, 2016; or Airbus Service Bulletin A320–53–1263, Revision 01, dated February 29, 2016; as applicable. VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 (iii) Modification of an airplane using instructions obtained in accordance with the procedures specified in paragraph (p)(2) of this AD. (2) Repair of an airplane as required by paragraph (k)(2) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g)(2) of this AD for that airplane, unless specified otherwise in the repair instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (n) No Reporting Requirement Although Airbus Service Bulletin A320– 53–1264, Revision 01, excluding Appendix 01, dated July 4, 2016, specifies to submit certain information to the manufacturer, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD does not include that requirement. (o) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (h)(1) of this AD, if those actions were performed before March 15, 2004 (the effective date of AD 2004–03–07) using Airbus Service Bulletin A320–53–1030, dated January 5, 2000; or Airbus Service Bulletin A320–53– 1029, dated January 5, 2000. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1264, dated March 19, 2015. (3) This paragraph provides credit for actions required by paragraph (k)(1) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (o)(3)(i) through (o)(3)(iv) of this AD, for that airplane only. (i) Airbus Service Bulletin A320–53–1240, dated March 19, 2015. (ii) Airbus Service Bulletin A320–53–1240, Revision 01, dated April 4, 2016. (iii) Airbus Service Bulletin A320–53– 1263, dated March 19, 2015. (iv) Airbus Service Bulletin A320–53– 1263, Revision 01, dated February 29, 2016. (4) This paragraph provides credit for actions required by paragraph (m)(1)(ii) of this AD if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1240, dated March 19, 2015; or Service Bulletin A320–53–1263, dated March 19, 2015. (p) 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 Branch, send it to the attention of the person identified in PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 paragraph (q)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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: As of the effective date of this AD, 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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (k)(2) and (n) 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0206, dated October 13, 2016; corrected October 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–2017–0902. (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 206–231– 3223; fax 206–231–3398. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(5) and (r)(6) of this AD. (r) 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. (3) The following service information was approved for IBR on May 3, 2018. (i) Airbus Service Bulletin A320–53–1029, Revision 01, including Appendix 01, dated April 29, 2002. (ii) Airbus Service Bulletin A320–53–1240, Revision 01, dated April 4, 2016. (iii) Airbus Service Bulletin A320–53– 1240, Revision 02, dated March 14, 2017. E:\FR\FM\29MRR1.SGM 29MRR1 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations (iv) Airbus Service Bulletin A320–53– 1263, Revision 01, dated February 29, 2016. (v) Airbus Service Bulletin A320–53–1263, Revision 02, excluding Appendix 01 and including Appendix 02, dated December 6, 2017. (vi) Airbus Service Bulletin A320–53– 1264, Revision 01, excluding Appendix 01, dated July 4, 2016. (4) The following service information was approved for IBR on March 15, 2004 (69 FR 5907, February 9, 2004). (i) Airbus Service Bulletin A320–53–1030, Revision 01, excluding Appendix 01, dated May 21, 2002. (ii) Reserved. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. (6) 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. (7) 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/ibrlocations.html. Issued in Renton, Washington, on March 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–05019 Filed 3–28–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0940; Product Identifier 2017–SW–058–AD; Amendment 39–19233; AD 2018–07–02] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD requires inspecting the main rotor blade (MRB) tip cap for disbonding. This AD is prompted by a report of the in-flight loss of an MRB tip rmajette on DSKBCKNHB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 cap. The actions of this AD are intended to prevent an unsafe condition on these products. DATES: This AD becomes effective April 13, 2018. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of April 13, 2018. We must receive comments on this AD by May 29, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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– 0940; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-byreference service information, the economic evaluation, any comments received, and other information. The street address for Docket Operations (telephone 800- 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this final rule, contact Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39–0331–711756; fax +39– 0331–229046; or at http:// www.leonardocompany.com/-/bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0940. Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft FOR FURTHER INFORMATION CONTACT: PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 13395 Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued AD No. 2017–0176– E, dated September 14, 2017, to correct an unsafe condition for Leonardo S.p.A. (previously Agusta) Model A109E, A109LUH, A109S, AW109SP, A119, and AW119 MKII helicopters. EASA advises of an in-flight loss of an MRB tip cap on an AW109SP helicopter where the pilot was able to safely land the helicopter. EASA further advises that an investigation determined the cause as incorrect bonding procedures used between specific dates and identified the affected MRBs by part number and serial number. According to EASA, this condition could result in loss of an MRB tip cap, increased pilot workload, and reduced control of the helicopter. To address this unsafe condition, the EASA AD requires repetitive inspections of the MRB tip caps and replacing certain partnumbered MRBs. The FAA is in the process of updating Agusta’s name change to Leonardo Helicopters on its type certificate. Because this name change is not yet effective, this AD specifies Agusta. E:\FR\FM\29MRR1.SGM 29MRR1

Agencies

[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)]
[Rules and Regulations]
[Pages 13387-13395]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-05019]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD; Amendment 
39-19224; AD 2018-06-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

[[Page 13388]]


ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2004-03-07, 
which applied to certain Airbus Model A320-111, -211, -212, and -231 
series airplanes. AD 2004-03-07 required repetitive inspections for 
fatigue cracking around the fasteners attaching the pressure panel to 
the flexible bracket at a certain frame (FR), adjacent to the 
longitudinal beams on the left and right sides of the airplane; and 
repair as necessary. This new AD retains certain requirements of AD 
2004-03-07, expands the applicability, and requires an inspection of 
the fastener holes on the pressure panel and modification or repair as 
applicable. This AD was prompted by fatigue tests which revealed 
cracking around the fasteners attaching the pressure panel to the 
flexible bracket, and by the discovery of additional cracks under the 
longitudinal beams at locations that are not included in the inspection 
area required by AD 2004-03-07. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective May 3, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 3, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
15, 2004 (69 FR 5907, February 9, 2004).

ADDRESSES: For service information identified in this final rule, 
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, 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-
0902.

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-
0902; 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 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 206-231-3223; fax 206-231-
3398.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2004-03-07, Amendment 39-13451 (69 FR 5907, 
February 9, 2004) (``AD 2004-03-07''). AD 2004-03-07 applied to certain 
Airbus Model A320-111, -211, -212, and -231 series airplanes. The NPRM 
published in the Federal Register on October 6, 2017 (82 FR 46729). The 
NPRM was prompted by fatigue tests which revealed cracking around the 
fasteners attaching the pressure panel to the flexible bracket at FR 
36, adjacent to the longitudinal beams on the left and right sides of 
the airplane, and by the discovery of additional cracks under the 
longitudinal beams at locations that are not included in the inspection 
area required by AD 2004-03-07. The NPRM proposed to continue to 
require certain requirements of AD 2004-03-07. The NPRM also proposed 
to expand the applicability and require an inspection of the fastener 
holes on the pressure panel between FR 35 and FR 36 under the 
longitudinal beam and modification or repair as applicable. We are 
issuing this AD to detect and correct fatigue cracking around the 
fasteners attaching the pressure panel to the flexible bracket at the 
FR 36 adjacent to the longitudinal beams, which could result in reduced 
structural integrity of the airplane and possible rapid decompression 
of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0206, dated October 13, 2016; corrected 
October 14, 2016 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus Model A318 and Model A319 series 
airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, 
and Model A321-111, -112, -131,-211, -21-, 213, -231, and -232 
airplanes. The MCAI states:

    During fatigue tests, cracks were found around the fasteners 
connecting the pressure panel with the flexible bracket at fuselage 
frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH) 
and right-hand (RH) sides.
    This condition, if not detected and corrected, could impair the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [French] 
AD 2000-531-155(B) [which corresponds with FAA AD 2004-03-07] to 
require repetitive inspections of the longitudinal beams of the FR 
36 pressure panel and, depending on findings, the accomplishment of 
a repair.
    Since that [French] AD was issued, additional cracks have been 
found under the beams, but in locations not covered by the required 
inspections. Fatigue and damage tolerance analyses were performed, 
the results of which indicated that all the holes in the pressure 
panel above all the longitudinal beams have to be cold worked.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2000-531-155(B), which is superseded, 
extends the applicability to all A320 family aeroplanes and requires 
[a special detailed inspection of the fastener holes on the pressure 
panel between FR35 and FR36 under the longitudinal beam and] 
modification [or repair] of all the affected holes.
    This [EASA] AD is republished to correct the number of the 
superseded DGAC AD.

    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-
0902.

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.

Request To Remove Reporting Requirement

    United Airlines (UAL) requested that we omit paragraph (k)(2)(ii) 
of the proposed AD, which would require operators to report any 
findings of cracking that exceeded the limits specified in Airbus 
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, 
dated July 4, 2016, from the proposed AD. UAL stated that paragraph 
(k)(2)(ii) of the proposed AD is confusing and unjustified because 
there is no explanation for why it is required when it was not included 
in EASA AD 2016-0206. UAL stated the requirement to report findings in 
paragraph (k)(2)(ii) is redundant with the actions of paragraph 
(k)(2)(i) of the proposed AD. UAL noted that for the

[[Page 13389]]

crack repair specified in paragraph (k)(2)(i) of the proposed AD, the 
findings would be reported. UAL suggested the paragraph (k)(2)(ii) of 
the proposed AD required using an unconventional means to report 
findings that might require additional procedures and training specific 
to the proposed AD. UAL also stated that restricting reporting to a 
website may cause issues if the sender does not have access and that 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 
01, dated July 4, 2016, lists alternative options for reporting, like 
email, fax, or mail.
    We agree to remove the reporting requirement specified in paragraph 
(k)(2)(ii) of the proposed AD from this AD. Neither Airbus Service 
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 
4, 2016, nor the MCAI specifically includes reporting to a website as 
specified in paragraph (k)(2)(ii) of the proposed AD. We note that 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding Appendix 
01, dated July 4, 2016, does include reporting within the required for 
compliance (RC) procedure for the repair, which indicates that 
reporting would be required regardless of whether reporting was called 
out in the MCAI. We also verified with EASA that reporting should be 
done as defined in the service information. However, we have determined 
that a specific reporting requirement is not necessary. As stated by 
the commenter, operators will report findings to obtain the repair, 
which is specified in paragraph (k)(2)(i) of the proposed AD. We have 
removed paragraphs (k)(2)(i) and (k)(2)(ii) from this AD and revised 
paragraph (k)(2) of this AD to include the information that was in 
paragraph (k)(2)(i) of the proposed AD. We have also added paragraph 
(n) to this AD to specify that reporting is not required for this AD 
and redesignated the subsequent paragraphs accordingly.

Request To Refer to Latest Service Information

    Two commenters requested that we refer to the latest service 
information. UAL requested that we update paragraph (k) of the proposed 
AD to use Airbus Service Bulletin A320-53-1264, Revision 02, dated 
March 14, 2017, which corrects an error with the fastener lengths for 
part number (P/N) EN6115K3. We infer that UAL intended to refer to 
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 
2017, because there is no Revision 02 for Airbus Service Bulletin A320-
53-1264, and because P/N EN6115K3 is referenced in Airbus Service 
Bulletin A320-53-1240, Revision 02, dated March 14, 2017. Airbus 
requested that we refer to Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017, in the proposed AD.
    We agree to refer to the latest service information in this AD. In 
addition to Airbus Service Bulletin A320-53-1240, Revision 02, dated 
March 14, 2017, we have also reviewed Airbus Service Bulletin A320-53-
1263, Revision 02, excluding Appendix 01 and including Appendix 02, 
dated December 6, 2017, which updates kit information and figures among 
other minor changes. We have revised paragraph (k)(1) of this AD 
accordingly. We have also provided credit for Airbus Service Bulletin 
A320-53-1240, Revision 01, dated April 4, 2016; and Airbus Service 
Bulletin A320-53-1263, Revision 01, dated February 29, 2016; in 
paragraphs (o)(3)(ii) and (o)(3)(iv) of this AD, respectively.

Request To Include Additional Airplane Models in the Applicability

    Airbus requested that Model A320-215 and Model A320-216 airplanes 
be in included in the applicability of the proposed AD. The commenter 
noted that these airplane models are included in the MCAI.
    We do not agree with the commenter's request. We have not certified 
Model A320-215 airplanes for operation in the U.S., and therefore, we 
did not include that model in the applicability of this AD. We did not 
include Model A320-216 airplanes in the applicability of this AD 
because the MCAI was already added to the required airworthiness action 
list (RAAL) for Model A320-216 airplanes. We have not changed this AD 
in this regard.

Request To Revise Service Bulletin Descriptions in the Related Service 
Information Under 1 CFR Part 51 Paragraph in the Preamble of the NPRM

    Airbus stated that the proposed AD identifies the means of 
inspection, i.e., rototest inspection, using three different wordings 
in the descriptions of the service bulletins specified in the Related 
Service Information under 1 CFR part 51 paragraph in the preamble of 
the NPRM. Airbus also stated that Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017, no longer contains a rototest 
inspection requirement. In addition, Airbus noted that Service Bulletin 
A320-53-1240, Revision 02, dated March 14, 2017, does not contain 
repair instructions. We infer the commenter is requesting that we 
revise the service bulletin descriptions in the Related Service 
Information under 1 CFR part 51 paragraph in the preamble of the NPRM.
    We acknowledge the description of the rototest inspection is 
different for each service bulletin specified in the Related Service 
Information under 1 CFR part 51 paragraph in the preamble of the NPRM. 
In the NPRM, we matched the description of the inspection as given in 
each service bulletin specified in the Related Service Information 
under 1 CFR part 51 paragraph. We have revised the description of 
Airbus Service Bulletin A320-53-1240, Revision 02, dated March 14, 
2017, to remove the reference to an inspection and repair.

Request To Clarify What Prompted the Proposed AD

    Airbus requested that we revise paragraph (e) of the proposed AD to 
clarify that the proposed AD was prompted by a report of cracking in an 
additional area. Airbus stated that paragraph (e) of the proposed AD 
describes only the fatigue test results that prompted AD 2004-03-07.
    We agree to revise paragraph (e) of this AD for clarity. This AD 
was prompted by the original report of cracking and the additional 
report. We have revised paragraph (e) of this AD to include the 
additional cracking that prompted the issuance of this AD.

Request To Revise Repair Language in Paragraph (k)(2)(i) of the 
Proposed AD

    Airbus requested that we revise the language in paragraph (k)(2)(i) 
of the proposed AD, which specifies to repair any cracking in 
accordance with Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016. Airbus stated that this 
service information does not provide direct repair instructions and 
instead specifies to contact Airbus.
    We agree to clarify the language in paragraph (k)(2) of this AD 
(which corresponds with paragraph (k)(2)(i) of the proposed AD). 
Paragraph (k)(2) of this AD also specifies that where Airbus Service 
Bulletin A320-53-1264, Revision 01, excluding Appendix 01, dated July 
4, 2016, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance), operators 
must request approval of repair instructions using a method approved in 
accordance with the procedures specified in paragraph (p)(2) of this 
AD, and accomplish the repair accordingly within the compliance time 
specified in those instructions. We have not changed this AD in this 
regard.

[[Page 13390]]

Request To Include Wording From the MCAI in Paragraph (m)(1)(iii) of 
the Proposed AD

    Airbus requested that we revise paragraph (m)(1)(iii) of the 
proposed AD. Airbus stated the wording is similar to paragraph (9) of 
the MCAI except that the important wording ``in accordance with Airbus 
approved instructions that identify the repair as technically 
equivalent to the accomplishment of Airbus SB A320-53-1240 or SB A320-
53-1263'' is omitted.
    We disagree with the commenter's request. The intent of paragraph 
(m)(1)(iii) of this AD is to obtain corrective actions from the 
manufacturer that are approved by the FAA, EASA, or Airbus's EASA 
Design Organization Approval (DOA). These approved instructions will 
provide an equivalent level of safety. We have not changed this AD in 
this regard.

Conclusion

    We reviewed the available data, including 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 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 Service Bulletin A320-53-1029, Revision 01, 
including Appendix 01, dated April 29, 2002. The service information 
describes procedures for repairing cracking.
    Airbus has also issued Service Bulletin A320-53-1240, Revision 01, 
dated April 4, 2016; and A320-53-1240, Revision 02, dated March 14, 
2017, which describe procedures for modifying the pressure panel above 
the left and right longitudinal beams, by cold working the attachment 
holes under the longitudinal beam at FR 36 for airplanes on which no 
cracking was found. Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016 also includes related investigative action (e.g., high 
frequency eddy current (rototest) inspection of all the removed 
fastener holes) and corrective actions (e.g., repair). These documents 
are distinct since they are different revision levels.
    Airbus has also issued Service Bulletin A320-53-1263, Revision 01, 
dated February 29, 2016; and A320-53-1263, Revision 02, excluding 
Appendix 01 and including Appendix 02, dated December 6, 2017, which 
describe procedures for modifying the pressure panel above the left and 
right longitudinal beams, including related investigative actions 
(e.g., eddy current rotating probe inspection of the fastener holes) 
and corrective actions (e.g., repair), by adding a doubler and a 
filler, and cold expansion of the holes under the longitudinal beam at 
FR 36 for airplanes on which cracking was found. These documents are 
distinct because they are different revision levels.
    Airbus has also issued Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016. The service information 
describes procedures for a special detailed inspection (rotating probe) 
for cracking of the fastener holes on the pressure panel between FR 35 
and FR 36 under the longitudinal beam and repair of any crack.
    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 737 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
----------------------------------------------------------------------------------------------------------------
Inspection [Retained from AD     Up to 2 work-hours x                 $0  Up to $170 per      Up to $125,290 per
 2004-03-07].                     $85 per hour = $170                      inspection cycle.   inspection cycle.
                                  per inspection cycle.
Inspection [new proposed         13 work-hours x $85 per              $0  $1,105............  $814,385.
 requirement].                    hour = $1,105.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
that will be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.......................  Up to 213 work-hours x $85   Up to $8,510..........  Up to $26,615.
                                      per hour = $18,105.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
a cost estimate for the on-condition repairs specified in this 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 AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C.

[[Page 13391]]

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 removing Airworthiness Directive 
(Airworthiness Directive (AD) 2004-03-07, Amendment 39-13451 (69 FR 
5907, February 9, 2004), and adding the following new AD:

2018-06-04 Airbus: Amendment 39-19224; Docket No. FAA-2017-0902; 
Product Identifier 2016-NM-188-AD.

(a) Effective Date

    This AD is effective May 3, 2018.

(b) Affected ADs

    This AD replaces AD 2004-03-07, Amendment 39-13451 (69 FR 5907, 
February 9, 2004) (``AD 2004-03-07'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except for airplanes on which Airbus Modification 151574 was 
embodied in production.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by fatigue tests which revealed cracking 
around the fasteners attaching the pressure panel to the flexible 
bracket at frame (FR) 36, adjacent to the longitudinal beams on the 
left and right sides of the airplane, and by the discovery of 
additional cracks under the longitudinal beams at locations that are 
not included in the inspection area required by AD 2004-03-07. We 
are issuing this AD to detect and correct fatigue cracking around 
the fasteners attaching the pressure panel to the flexible bracket 
at the FR 36 adjacent to the longitudinal beams, which could result 
in reduced structural integrity of the airplane and possible rapid 
decompression of the airplane.

(f) Compliance

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

(g) Retained Inspection and Follow-on Actions, With No Changes

    This paragraph restates the requirements of paragraphs (a) and 
(b) of AD 2004-03-07, with no changes.
    (1) For Model A320-211, -212, and -231 series airplanes having 
serial numbers 0002 through 0107 inclusive, except those airplanes 
on which Airbus Modification 21202/K1432 has been incorporated in 
production, or on which Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, has been 
incorporated in service: Prior to the accumulation of 30,000 total 
flight cycles, do a rotating probe inspection on airplanes with a 
center fuel tank, or a detailed inspection on airplanes without a 
center fuel tank, to detect cracking around the fasteners that 
attach the pressure panel to the flexible bracket at FR 36, adjacent 
to the longitudinal beams on the left and right sides of the 
airplane, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1030, Revision 01, excluding 
Appendix 01, dated May 21, 2002.
    (2) If no crack is detected by the inspection required by 
paragraph (g)(1) of this AD, repeat the applicable inspection 
thereafter at intervals not to exceed 6,000 flight cycles for 
airplanes without a center fuel tank, and at intervals not to exceed 
18,000 flight cycles for airplanes with a center fuel tank.

(h) Retained Corrective Actions, With Specific Delegation Approval 
Language

    This paragraph restates the requirements of paragraphs (c) and 
(d) of AD 2004-03-07, with specific delegation approval language.
    (1) If any crack is detected during any inspection required by 
paragraph (g)(1) of this AD, before further flight, repair the 
affected structure by accomplishing all applicable actions in 
accordance with paragraphs 3.B. through 3.E. of the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, 
excluding Appendix 01, dated May 21, 2002. Repeat the applicable 
inspection thereafter at intervals not to exceed 6,000 flight cycles 
for airplanes without a center fuel tank, and at intervals not to 
exceed 18,000 flight cycles for airplanes with a center fuel tank. 
For any area where cracking is repaired, the repair constitutes 
terminating action for the repetitive inspection of that area.
    Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin 
A320-53-1030 references Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, as an 
additional source of service information for certain repairs.
    (2) If Airbus Service Bulletin A320-53-1030, Revision 01, 
excluding Appendix 01, dated May 21, 2002, specifies to contact the 
manufacturer for appropriate action: Before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (p)(2) of this AD.

(i) Retained Optional Terminating Action, With Revised Compliance 
Language

    This paragraph restates the requirements of paragraph (e) of AD 
2004-03-07, with revised compliance language, to provide optional 
terminating action for paragraphs (g) and (h) of this AD. For Model 
A320-211, -212, and -231 series airplanes having serial numbers 0002 
through 0107 inclusive, except those airplanes on which Airbus 
Modification 21202/K1432 has been incorporated in production, or 
Airbus Service Bulletin A320-53-1029, Revision 01, including 
Appendix 01, dated April 29, 2002, has been incorporated in service: 
Modification, before the effective date of this AD, of the structure 
around the fasteners that attach the pressure panel to the flexible 
bracket at FR 36, adjacent to the longitudinal beams on the left and 
right sides of the airplane, by accomplishing all applicable actions 
in accordance with paragraphs 3.A. through 3.E. of the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1029, 
Revision 01, including Appendix 01, dated April 29, 2002, 
constitutes terminating action for the actions required by 
paragraphs (g) and (h) of this AD.

(j) New Requirement of This AD: Inspection

    For all airplanes, except for airplanes identified in paragraph 
(l) of this AD: At the applicable time specified in table 1 to 
paragraph (j) of this AD, do a special detailed inspection for 
cracking of the fastener holes

[[Page 13392]]

on the pressure panel between FR 35 and FR 36 under the longitudinal 
beam, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1264, Revision 01, excluding Appendix 01, 
dated July 4, 2016.
[GRAPHIC] [TIFF OMITTED] TR29MR18.007

[GRAPHIC] [TIFF OMITTED] TR29MR18.008


[[Page 13393]]


[GRAPHIC] [TIFF OMITTED] TR29MR18.009

[GRAPHIC] [TIFF OMITTED] TR29MR18.010

(k) On-Condition Actions

    (1) If, during any inspection required by paragraph (j) of this 
AD, no cracking is found, or cracking is found that is within the 
limits specified in Airbus Service Bulletin A320-53-1264, Revision 
01, excluding Appendix 01, dated July 4, 2016: Before further 
flight, modify the pressure panel above the left and right 
longitudinal beams, including doing all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, 
Revision 02, excluding

[[Page 13394]]

Appendix 01 and including Appendix 02, dated December 6, 2017, as 
applicable. Do all related investigative and corrective actions 
before further flight. Where Airbus Service Bulletin A320-53-1240, 
Revision 02, dated March 14, 2017; or Service Bulletin A320-53-1263, 
Revision 02, excluding Appendix 01 and including Appendix 02, dated 
December 6, 2017; specify to contact Airbus for appropriate action: 
Before further flight, accomplish the repair using a method approved 
in accordance with the procedures specified in paragraph (p)(2) of 
this AD.
    (2) If, during any inspection required by paragraph (j) of this 
AD, any cracking is found that exceeds the limits specified in 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding 
Appendix 01, dated July 4, 2016: Before further flight, repair any 
cracking in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1264, Revision 01, excluding 
Appendix 01, dated July 4, 2016. Where Airbus Service Bulletin A320-
53-1264, Revision 01, excluding Appendix 01, dated July 4, 2016, 
specifies to contact Airbus for appropriate action, and specifies 
that action as ``RC'' (Required for Compliance), before further 
flight, request approval of repair instructions using a method 
approved in accordance with the procedures specified in paragraph 
(p)(2) of this AD, and accomplish the repair accordingly within the 
compliance time specified in those instructions. If no compliance 
time is defined in the repair instructions, accomplish the repair 
before further flight.

(l) Actions for Certain Airplanes

    For Model A319 and Model A320 series airplanes on which the 
actions specified in Airbus Service Bulletin A320-57-1193 have been 
embodied and the airplane has accumulated 33,000 flight cycles or 
66,000 flight hours or more since the airplane's first flight on the 
effective date of this AD: Within 30 days after the effective date 
of this AD, contact the Manager, International Section, Transport 
Standards Branch FAA; or the European Aviation Safety Agency (EASA); 
or Airbus's EASA Design Organization Approval (DOA) for approved 
repair instructions and within the compliance time specified in 
those instructions, accomplish the repair accordingly. If approved 
by the DOA, the approval must include the DOA-authorized signature. 
If no compliance time is defined in the repair instructions, 
accomplish the repair before the next flight.

(m) Terminating Action for Repetitive Inspections

    (1) Modification of an airplane as specified in paragraph 
(m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes 
terminating action for the repetitive inspection required by 
paragraph (g)(2) of this AD for that airplane only.
    (i) Modification of an airplane as required by paragraph (k)(1) 
of this AD.
    (ii) Modification of an airplane prior to the effective date of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1240, Revision 01, dated April 4, 
2016; or Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016; as applicable.
    (iii) Modification of an airplane using instructions obtained in 
accordance with the procedures specified in paragraph (p)(2) of this 
AD.
    (2) Repair of an airplane as required by paragraph (k)(2) of 
this AD constitutes terminating action for the repetitive 
inspections required by paragraph (g)(2) of this AD for that 
airplane, unless specified otherwise in the repair instructions 
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.

(n) No Reporting Requirement

    Although Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016, specifies to submit 
certain information to the manufacturer, and specifies that action 
as ``RC'' (Required for Compliance), this AD does not include that 
requirement.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h)(1) of this AD, if those actions were 
performed before March 15, 2004 (the effective date of AD 2004-03-
07) using Airbus Service Bulletin A320-53-1030, dated January 5, 
2000; or Airbus Service Bulletin A320-53-1029, dated January 5, 
2000.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1264, dated March 19, 2015.
    (3) This paragraph provides credit for actions required by 
paragraph (k)(1) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information specified in paragraphs (o)(3)(i) through (o)(3)(iv) of 
this AD, for that airplane only.
    (i) Airbus Service Bulletin A320-53-1240, dated March 19, 2015.
    (ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016.
    (iii) Airbus Service Bulletin A320-53-1263, dated March 19, 
2015.
    (iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016.
    (4) This paragraph provides credit for actions required by 
paragraph (m)(1)(ii) of this AD if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-53-1240, dated March 19, 2015; or Service Bulletin A320-53-
1263, dated March 19, 2015.

(p) 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 Branch, send it to the attention of 
the person identified in paragraph (q)(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: As of the effective date of 
this AD, 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 the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (k)(2) and (n) 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0206, dated October 13, 2016; corrected October 
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-2017-0902.
    (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 
206-231-3223; fax 206-231-3398.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(5) and (r)(6) of this AD.

(r) 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.
    (3) The following service information was approved for IBR on 
May 3, 2018.
    (i) Airbus Service Bulletin A320-53-1029, Revision 01, including 
Appendix 01, dated April 29, 2002.
    (ii) Airbus Service Bulletin A320-53-1240, Revision 01, dated 
April 4, 2016.
    (iii) Airbus Service Bulletin A320-53-1240, Revision 02, dated 
March 14, 2017.

[[Page 13395]]

    (iv) Airbus Service Bulletin A320-53-1263, Revision 01, dated 
February 29, 2016.
    (v) Airbus Service Bulletin A320-53-1263, Revision 02, excluding 
Appendix 01 and including Appendix 02, dated December 6, 2017.
    (vi) Airbus Service Bulletin A320-53-1264, Revision 01, 
excluding Appendix 01, dated July 4, 2016.
    (4) The following service information was approved for IBR on 
March 15, 2004 (69 FR 5907, February 9, 2004).
    (i) Airbus Service Bulletin A320-53-1030, Revision 01, excluding 
Appendix 01, dated May 21, 2002.
    (ii) Reserved.
    (5) 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.
    (6) 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.
    (7) 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 Renton, Washington, on March 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-05019 Filed 3-28-18; 8:45 am]
 BILLING CODE 4910-13-P