83 FR 13387 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 61 (March 29, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 61 (March 29, 2018)
| Page Range | 13387-13395 | |
| FR Document | 2018-05019 |
[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)] [Rules and Regulations] [Pages 13387-13395] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-05019] ----------------------------------------------------------------------- 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 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. 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: 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 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/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
![13388 Federal Register / Vol. 83, No. 61 / Thursday, March 29, 2018 / Rules and Regulations
ACTION: Final rule. other information. The address for the –231, and –232 airplanes. The MCAI
Docket Office (telephone 800–647–5527) states:
SUMMARY: We are superseding is Docket Management Facility, U.S.
Airworthiness Directive (AD) 2004–03– During fatigue tests, cracks were found
Department of Transportation, Docket around the fasteners connecting the pressure
07, which applied to certain Airbus Operations, M–30, West Building panel with the flexible bracket at fuselage
Model A320–111, –211, –212, and –231 Ground Floor, Room W12–140, 1200 frame (FR) 36, adjacent to the longitudinal
series airplanes. AD 2004–03–07 New Jersey Avenue SE, Washington, DC beams on left-hand (LH) and right-hand (RH)
required repetitive inspections for 20590. sides.
fatigue cracking around the fasteners This condition, if not detected and
FOR FURTHER INFORMATION CONTACT: corrected, could impair the structural
attaching the pressure panel to the
flexible bracket at a certain frame (FR), Sanjay Ralhan, Aerospace Engineer, integrity of the aeroplane.
adjacent to the longitudinal beams on International Section, Transport To address this unsafe condition, DGAC
the left and right sides of the airplane; Standards Branch, FAA, 2200 South [Direction Générale de l’Aviation Civile]
216th St., Des Moines, WA 98198; France issued [French] AD 2000–531–155(B)
and repair as necessary. This new AD [which corresponds with FAA AD 2004–03–
retains certain requirements of AD telephone 206–231–3223; fax 206–231–
3398. 07] to require repetitive inspections of the
2004–03–07, expands the applicability, longitudinal beams of the FR 36 pressure
and requires an inspection of the SUPPLEMENTARY INFORMATION: panel and, depending on findings, the
fastener holes on the pressure panel and Discussion accomplishment of a repair.
modification or repair as applicable. Since that [French] AD was issued,
This AD was prompted by fatigue tests We issued a notice of proposed additional cracks have been found under the
which revealed cracking around the rulemaking (NPRM) to amend 14 CFR beams, but in locations not covered by the
part 39 to supersede AD 2004–03–07, required inspections. Fatigue and damage
fasteners attaching the pressure panel to
Amendment 39–13451 (69 FR 5907, tolerance analyses were performed, the
the flexible bracket, and by the results of which indicated that all the holes
discovery of additional cracks under the February 9, 2004) (‘‘AD 2004–03–07’’).
in the pressure panel above all the
longitudinal beams at locations that are AD 2004–03–07 applied to certain longitudinal beams have to be cold worked.
not included in the inspection area Airbus Model A320–111, –211, –212, For the reasons described above, this
required by AD 2004–03–07. We are and –231 series airplanes. The NPRM [EASA] AD retains the requirements of DGAC
issuing this AD to address the unsafe published in the Federal Register on France AD 2000–531–155(B), which is
condition on these products. October 6, 2017 (82 FR 46729). The superseded, extends the applicability to all
NPRM was prompted by fatigue tests A320 family aeroplanes and requires [a
DATES: This AD is effective May 3, 2018.
which revealed cracking around the special detailed inspection of the fastener
The Director of the Federal Register holes on the pressure panel between FR35
approved the incorporation by reference fasteners attaching the pressure panel to
and FR36 under the longitudinal beam and]
of certain publications listed in this AD the flexible bracket at FR 36, adjacent to modification [or repair] of all the affected
as of May 3, 2018. the longitudinal beams on the left and holes.
The Director of the Federal Register right sides of the airplane, and by the This [EASA] AD is republished to correct
approved the incorporation by reference discovery of additional cracks under the the number of the superseded DGAC AD.
of a certain other publication listed in longitudinal beams at locations that are You may examine the MCAI in the
this AD as of March 15, 2004 (69 FR not included in the inspection area AD docket on the internet at http://
5907, February 9, 2004). required by AD 2004–03–07. The NPRM www.regulations.gov by searching for
ADDRESSES: For service information proposed to continue to require certain and locating Docket No. FAA–2017–
identified in this final rule, contact requirements of AD 2004–03–07. The 0902.
Airbus, Airworthiness Office—EIAS, 1 NPRM also proposed to expand the
Rond Point Maurice Bellonte, 31707 applicability and require an inspection Comments
Blagnac Cedex, France; telephone +33 5 of the fastener holes on the pressure We gave the public the opportunity to
61 93 36 96; fax +33 5 61 93 44 51; email panel between FR 35 and FR 36 under participate in developing this AD. The
account.airworth-eas@airbus.com; the longitudinal beam and modification following presents the comments
internet http://www.airbus.com. You or repair as applicable. We are issuing received on the NPRM and the FAA’s
may view this referenced service this AD to detect and correct fatigue response to each comment.
information at the FAA, Transport cracking around the fasteners attaching
the pressure panel to the flexible bracket Request To Remove Reporting
Standards Branch, 2200 South 216th St.,
at the FR 36 adjacent to the longitudinal Requirement
Des Moines, WA. For information on the
availability of this material at the FAA, beams, which could result in reduced United Airlines (UAL) requested that
call 206–231–3195. It is also available structural integrity of the airplane and we omit paragraph (k)(2)(ii) of the
on the internet at http:// possible rapid decompression of the proposed AD, which would require
www.regulations.gov by searching for airplane. operators to report any findings of
and locating Docket No. FAA–2017– The European Aviation Safety Agency cracking that exceeded the limits
0902. (EASA), which is the Technical Agent specified in Airbus Service Bulletin
for the Member States of the European A320–53–1264, Revision 01, excluding
Examining the AD Docket Union, has issued EASA Airworthiness Appendix 01, dated July 4, 2016, from
You may examine the AD docket on Directive 2016–0206, dated October 13, the proposed AD. UAL stated that
the internet at http:// 2016; corrected October 14, 2016 paragraph (k)(2)(ii) of the proposed AD
www.regulations.gov by searching for (referred to after this as the Mandatory is confusing and unjustified because
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and locating Docket No. FAA–2017– Continuing Airworthiness Information, there is no explanation for why it is
0902; or in person at the Docket or ‘‘the MCAI’’), to correct an unsafe required when it was not included in
Management Facility between 9 a.m. condition for certain Airbus Model EASA AD 2016–0206. UAL stated the
and 5 p.m., Monday through Friday, A318 and Model A319 series airplanes, requirement to report findings in
except Federal holidays. The AD docket Model A320–211, –212, –214, –231, paragraph (k)(2)(ii) is redundant with
contains this AD, the regulatory –232, and –233 airplanes, and Model the actions of paragraph (k)(2)(i) of the
evaluation, any comments received, and A321–111, –112, –131,–211, –21–, 213, proposed AD. UAL noted that for the
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Request To Include Wording From the • Do not add any additional burden 1263, Revision 02, excluding Appendix
MCAI in Paragraph (m)(1)(iii) of the upon the public than was already 01 and including Appendix 02, dated
Proposed AD proposed in the NPRM. December 6, 2017, which describe
We also determined that these procedures for modifying the pressure
Airbus requested that we revise changes will not increase the economic panel above the left and right
paragraph (m)(1)(iii) of the proposed burden on any operator or increase the longitudinal beams, including related
AD. Airbus stated the wording is similar scope of this AD. investigative actions (e.g., eddy current
to paragraph (9) of the MCAI except that rotating probe inspection of the fastener
the important wording ‘‘in accordance Related Service Information Under 1
CFR Part 51 holes) and corrective actions (e.g.,
with Airbus approved instructions that repair), by adding a doubler and a filler,
identify the repair as technically Airbus has issued Service Bulletin and cold expansion of the holes under
equivalent to the accomplishment of A320–53–1029, Revision 01, including the longitudinal beam at FR 36 for
Airbus SB A320–53–1240 or SB A320– Appendix 01, dated April 29, 2002. The airplanes on which cracking was found.
53–1263’’ is omitted. service information describes These documents are distinct because
We disagree with the commenter’s procedures for repairing cracking. they are different revision levels.
request. The intent of paragraph Airbus has also issued Service
Bulletin A320–53–1240, Revision 01, Airbus has also issued Service
(m)(1)(iii) of this AD is to obtain Bulletin A320–53–1264, Revision 01,
corrective actions from the dated April 4, 2016; and A320–53–1240,
Revision 02, dated March 14, 2017, excluding Appendix 01, dated July 4,
manufacturer that are approved by the 2016. The service information describes
FAA, EASA, or Airbus’s EASA Design which describe procedures for
modifying the pressure panel above the procedures for a special detailed
Organization Approval (DOA). These inspection (rotating probe) for cracking
approved instructions will provide an left and right longitudinal beams, by
cold working the attachment holes of the fastener holes on the pressure
equivalent level of safety. We have not panel between FR 35 and FR 36 under
changed this AD in this regard. under the longitudinal beam at FR 36
for airplanes on which no cracking was the longitudinal beam and repair of any
Conclusion found. Service Bulletin A320–53–1240, crack.
Revision 01, dated April 4, 2016 also This service information is reasonably
We reviewed the available data, includes related investigative action available because the interested parties
including the comments received, and (e.g., high frequency eddy current have access to it through their normal
determined that air safety and the (rototest) inspection of all the removed course of business or by the means
public interest require adopting this AD fastener holes) and corrective actions identified in the ADDRESSES section.
with the changes described previously (e.g., repair). These documents are
and minor editorial changes. We have Costs of Compliance
distinct since they are different revision
determined that these changes: levels. We estimate that this AD affects 737
• Are consistent with the intent that Airbus has also issued Service airplanes of U.S. registry.
was proposed in the NPRM for Bulletin A320–53–1263, Revision 01, We estimate the following costs to
correcting the unsafe condition; and dated February 29, 2016; and A320–53– comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection [Retained from AD 2004–03– Up to 2 work-hours × $85 per hour = $0 Up to $170 per in- Up to $125,290 per
07]. $170 per inspection cycle. spection cycle. inspection cycle.
Inspection [new proposed requirement] 13 work-hours × $85 per hour = $1,105 $0 $1,105 .................... $814,385.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary modifications that will be inspection. We have no way of might need these modifications:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Modification ...................................................... Up to 213 work-hours × $85 per hour = Up to $8,510 .............. Up to $26,615.
$18,105.
We have received no definitive data Aviation Programs,’’ describes in more the Administrator finds necessary for
that will enable us to provide a cost detail the scope of the Agency’s safety in air commerce. This regulation
estimate for the on-condition repairs authority. is within the scope of that authority
specified in this AD. We are issuing this rulemaking under because it addresses an unsafe condition
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the authority described in ‘‘Subtitle VII, that is likely to exist or develop on
Authority for This Rulemaking
Part A, Subpart III, Section 44701: products identified in this rulemaking
Title 49 of the United States Code General requirements.’’ Under that action.
specifies the FAA’s authority to issue section, Congress charges the FAA with This AD is issued in accordance with
rules on aviation safety. Subtitle I, promoting safe flight of civil aircraft in authority delegated by the Executive
section 106, describes the authority of air commerce by prescribing regulations Director, Aircraft Certification Service,
the FAA Administrator. ‘‘Subtitle VII: for practices, methods, and procedures as authorized by FAA Order 8000.51C.
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In accordance with that order, issuance (b) Affected ADs repeat the applicable inspection thereafter at
of ADs is normally a function of the This AD replaces AD 2004–03–07, intervals not to exceed 6,000 flight cycles for
Compliance and Airworthiness Amendment 39–13451 (69 FR 5907, February airplanes without a center fuel tank, and at
9, 2004) (‘‘AD 2004–03–07’’). intervals not to exceed 18,000 flight cycles
Division, but during this transition for airplanes with a center fuel tank.
period, the Executive Director has (c) Applicability
delegated the authority to issue ADs (h) Retained Corrective Actions, With
This AD applies to the Airbus airplanes Specific Delegation Approval Language
applicable to transport category identified in paragraphs (c)(1) through (c)(4)
airplanes to the Director of the System of this AD, certificated in any category, This paragraph restates the requirements of
Oversight Division. except for airplanes on which Airbus paragraphs (c) and (d) of AD 2004–03–07,
Modification 151574 was embodied in with specific delegation approval language.
Regulatory Findings production. (1) If any crack is detected during any
(1) Model A318–111, –112, –121, and –122 inspection required by paragraph (g)(1) of
We determined that this AD will not airplanes. this AD, before further flight, repair the
have federalism implications under (2) Model A319–111, –112, –113, –114, affected structure by accomplishing all
Executive Order 13132. This AD will –115, –131, –132, and –133 airplanes. applicable actions in accordance with
not have a substantial direct effect on (3) Model A320–211, –212, –214, –231, paragraphs 3.B. through 3.E. of the
the States, on the relationship between –232, and –233 airplanes. Accomplishment Instructions of Airbus
(4) Model A321–111, –112, –131, –211, Service Bulletin A320–53–1030, Revision 01,
the national government and the States, excluding Appendix 01, dated May 21, 2002.
or on the distribution of power and –212, –213, –231, and –232 airplanes.
Repeat the applicable inspection thereafter at
responsibilities among the various (d) Subject intervals not to exceed 6,000 flight cycles for
levels of government. Air Transport Association (ATA) of airplanes without a center fuel tank, and at
For the reasons discussed above, I America Code 53, Fuselage. intervals not to exceed 18,000 flight cycles
for airplanes with a center fuel tank. For any
certify that this AD: (e) Reason area where cracking is repaired, the repair
1. Is not a ‘‘significant regulatory This AD was prompted by fatigue tests constitutes terminating action for the
action’’ under Executive Order 12866; which revealed cracking around the fasteners repetitive inspection of that area.
attaching the pressure panel to the flexible Note 1 to paragraph (h)(1) of this AD:
2. Is not a ‘‘significant rule’’ under the
bracket at frame (FR) 36, adjacent to the Airbus Service Bulletin A320–53–1030
DOT Regulatory Policies and Procedures longitudinal beams on the left and right sides references Airbus Service Bulletin A320–53–
(44 FR 11034, February 26, 1979); of the airplane, and by the discovery of 1029, Revision 01, including Appendix 01,
3. Will not affect intrastate aviation in additional cracks under the longitudinal dated April 29, 2002, as an additional source
Alaska; and beams at locations that are not included in of service information for certain repairs.
the inspection area required by AD 2004–03– (2) If Airbus Service Bulletin A320–53–
4. Will not have a significant 07. We are issuing this AD to detect and 1030, Revision 01, excluding Appendix 01,
economic impact, positive or negative, correct fatigue cracking around the fasteners dated May 21, 2002, specifies to contact the
on a substantial number of small entities attaching the pressure panel to the flexible manufacturer for appropriate action: Before
under the criteria of the Regulatory bracket at the FR 36 adjacent to the further flight, repair using a method
Flexibility Act. longitudinal beams, which could result in approved in accordance with the procedures
reduced structural integrity of the airplane specified in paragraph (p)(2) of this AD.
List of Subjects in 14 CFR Part 39 and possible rapid decompression of the
(i) Retained Optional Terminating Action,
airplane.
Air transportation, Aircraft, Aviation With Revised Compliance Language
safety, Incorporation by reference, (f) Compliance This paragraph restates the requirements of
Safety. Comply with this AD within the paragraph (e) of AD 2004–03–07, with
compliance times specified, unless already revised compliance language, to provide
Adoption of the Amendment done. optional terminating action for paragraphs (g)
and (h) of this AD. For Model A320–211,
Accordingly, under the authority (g) Retained Inspection and Follow-on –212, and –231 series airplanes having serial
delegated to me by the Administrator, Actions, With No Changes numbers 0002 through 0107 inclusive, except
the FAA amends 14 CFR part 39 as This paragraph restates the requirements of those airplanes on which Airbus
follows: paragraphs (a) and (b) of AD 2004–03–07, Modification 21202/K1432 has been
with no changes. incorporated in production, or Airbus
PART 39—AIRWORTHINESS (1) For Model A320–211, –212, and –231 Service Bulletin A320–53–1029, Revision 01,
DIRECTIVES series airplanes having serial numbers 0002 including Appendix 01, dated April 29, 2002,
through 0107 inclusive, except those has been incorporated in service:
airplanes on which Airbus Modification Modification, before the effective date of this
■ 1. The authority citation for part 39 21202/K1432 has been incorporated in AD, of the structure around the fasteners that
continues to read as follows: production, or on which Airbus Service attach the pressure panel to the flexible
Authority: 49 U.S.C. 106(g), 40113, 44701. Bulletin A320–53–1029, Revision 01, bracket at FR 36, adjacent to the longitudinal
including Appendix 01, dated April 29, 2002, beams on the left and right sides of the
§ 39.13 [Amended] has been incorporated in service: Prior to the airplane, by accomplishing all applicable
accumulation of 30,000 total flight cycles, do actions in accordance with paragraphs 3.A.
■ 2. The FAA amends § 39.13 by a rotating probe inspection on airplanes with through 3.E. of the Accomplishment
removing Airworthiness Directive a center fuel tank, or a detailed inspection on Instructions of Airbus Service Bulletin A320–
(Airworthiness Directive (AD) 2004–03– airplanes without a center fuel tank, to detect 53–1029, Revision 01, including Appendix
07, Amendment 39–13451 (69 FR 5907, cracking around the fasteners that attach the 01, dated April 29, 2002, constitutes
pressure panel to the flexible bracket at FR terminating action for the actions required by
February 9, 2004), and adding the
36, adjacent to the longitudinal beams on the
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paragraphs (g) and (h) of this AD.
following new AD: left and right sides of the airplane, in
2018–06–04 Airbus: Amendment 39–19224; accordance with the Accomplishment (j) New Requirement of This AD: Inspection
Docket No. FAA–2017–0902; Product Instructions of Airbus Service Bulletin A320– For all airplanes, except for airplanes
Identifier 2016–NM–188–AD. 53–1030, Revision 01, excluding Appendix identified in paragraph (l) of this AD: At the
01, dated May 21, 2002. applicable time specified in table 1 to
(a) Effective Date (2) If no crack is detected by the inspection paragraph (j) of this AD, do a special detailed
This AD is effective May 3, 2018. required by paragraph (g)(1) of this AD, inspection for cracking of the fastener holes
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(iv) Airbus Service Bulletin A320–53– cap. The actions of this AD are intended Standards Branch, FAA, 10101
1263, Revision 01, dated February 29, 2016. to prevent an unsafe condition on these Hillwood Pkwy., Fort Worth, TX 76177;
(v) Airbus Service Bulletin A320–53–1263, products. telephone (817) 222–5110; email
Revision 02, excluding Appendix 01 and
DATES: This AD becomes effective April matthew.fuller@faa.gov.
including Appendix 02, dated December 6,
2017. 13, 2018. SUPPLEMENTARY INFORMATION:
(vi) Airbus Service Bulletin A320–53– The Director of the Federal Register
1264, Revision 01, excluding Appendix 01, approved the incorporation by reference Comments Invited
dated July 4, 2016. of certain documents listed in this AD
(4) The following service information was as of April 13, 2018. This AD is a final rule that involves
approved for IBR on March 15, 2004 (69 FR We must receive comments on this requirements affecting flight safety, and
5907, February 9, 2004). AD by May 29, 2018. we did not provide you with notice and
(i) Airbus Service Bulletin A320–53–1030, an opportunity to provide your
Revision 01, excluding Appendix 01, dated ADDRESSES: You may send comments by
comments prior to it becoming effective.
May 21, 2002. any of the following methods:
However, we invite you to participate in
(ii) Reserved. • Federal eRulemaking Docket: Go to
this rulemaking by submitting written
(5) For service information identified in http://www.regulations.gov. Follow the
comments, data, or views. We also
this AD, contact Airbus, Airworthiness online instructions for sending your
Office—EIAS, 1 Rond Point Maurice invite comments relating to the
comments electronically.
Bellonte, 31707 Blagnac Cedex, France; • Fax: 202–493–2251. economic, environmental, energy, or
telephone +33 5 61 93 36 96; fax +33 5 61 • Mail: Send comments to the U.S. federalism impacts that resulted from
93 44 51; email account.airworth-eas@ Department of Transportation, Docket adopting this AD. The most helpful
airbus.com; internet http://www.airbus.com. comments reference a specific portion of
(6) You may view this service information
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200 the AD, explain the reason for any
at the FAA, Transport Standards Branch, recommended change, and include
2200 South 216th St., Des Moines, WA. For New Jersey Avenue SE, Washington, DC
20590–0001. supporting data. To ensure the docket
information on the availability of this
material at the FAA, call 206–231–3195. • Hand Delivery: Deliver to the does not contain duplicate comments,
(7) You may view this service information ‘‘Mail’’ address between 9 a.m. and 5 commenters should send only one copy
that is incorporated by reference at the p.m., Monday through Friday, except of written comments, or if comments are
National Archives and Records Federal holidays. filed electronically, commenters should
Administration (NARA). For information on submit them only one time. We will file
the availability of this material at NARA, call Examining the AD Docket in the docket all comments that we
202–741–6030, or go to: http:// You may examine the AD docket on receive, as well as a report summarizing
www.archives.gov/federal-register/cfr/ibr- each substantive public contact with
locations.html.
the internet at http://
www.regulations.gov by searching for FAA personnel concerning this
Issued in Renton, Washington, on March 2, and locating Docket No. FAA–2017– rulemaking during the comment period.
2018. 0940; or in person at Docket Operations We will consider all the comments we
Michael Kaszycki, between 9 a.m. and 5 p.m., Monday receive and may conduct additional
Acting Director, System Oversight Division, through Friday, except Federal holidays. rulemaking based on those comments.
Aircraft Certification Service. The AD docket contains this AD, the Discussion
[FR Doc. 2018–05019 Filed 3–28–18; 8:45 am] European Aviation Safety Agency
BILLING CODE 4910–13–P (EASA) AD, any incorporated-by- EASA, which is the Technical Agent
reference service information, the for the Member States of the European
economic evaluation, any comments Union, has issued AD No. 2017–0176–
DEPARTMENT OF TRANSPORTATION received, and other information. The E, dated September 14, 2017, to correct
street address for Docket Operations an unsafe condition for Leonardo S.p.A.
Federal Aviation Administration (telephone 800- 647–5527) is in the (previously Agusta) Model A109E,
ADDRESSES section. Comments will be A109LUH, A109S, AW109SP, A119,
14 CFR Part 39
available in the AD docket shortly after and AW119 MKII helicopters. EASA
[Docket No. FAA–2017–0940; Product receipt. advises of an in-flight loss of an MRB tip
Identifier 2017–SW–058–AD; Amendment For service information identified in cap on an AW109SP helicopter where
39–19233; AD 2018–07–02] this final rule, contact Leonardo S.p.A. the pilot was able to safely land the
RIN 2120–AA64 Helicopters, Matteo Ragazzi, Head of helicopter. EASA further advises that an
Airworthiness, Viale G.Agusta 520, investigation determined the cause as
Airworthiness Directives; Agusta 21017 C.Costa di Samarate (Va) Italy; incorrect bonding procedures used
S.p.A. Helicopters telephone +39–0331–711756; fax +39– between specific dates and identified
0331–229046; or at http:// the affected MRBs by part number and
AGENCY: Federal Aviation www.leonardocompany.com/-/bulletins. serial number. According to EASA, this
Administration (FAA), Department of You may review the referenced service condition could result in loss of an MRB
Transportation (DOT). information at the FAA, Office of the tip cap, increased pilot workload, and
ACTION: Final rule; request for Regional Counsel, Southwest Region, reduced control of the helicopter. To
comments. 10101 Hillwood Pkwy., Room 6N–321, address this unsafe condition, the EASA
SUMMARY: We are adopting a new Fort Worth, TX 76177. It is also AD requires repetitive inspections of the
available on the internet at http:// MRB tip caps and replacing certain part-
rmajette on DSKBCKNHB2PROD with RULES
airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model A109E, A109S, www.regulations.gov by searching for numbered MRBs.
AW109SP, A119, and AW119 MKII and locating Docket No. FAA–2017– The FAA is in the process of updating
helicopters. This AD requires inspecting 0940. Agusta’s name change to Leonardo
the main rotor blade (MRB) tip cap for FOR FURTHER INFORMATION CONTACT: Matt Helicopters on its type certificate.
disbonding. This AD is prompted by a Fuller, Senior Aviation Safety Engineer, Because this name change is not yet
report of the in-flight loss of an MRB tip Safety Management Section, Rotorcraft effective, this AD specifies Agusta.
VerDate Sep<11>2014 15:09 Mar 28, 2018 Jkt 244001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\29MRR1.SGM 29MRR1](https://thefederalregister.org/doc/83_FR_13448/page/9.svg)
Document Created: 2018-03-29 00:25:20
Document Modified: 2018-03-29 00:25:20
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective May 3, 2018. | |
| 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. | |
| FR Citation | 83 FR 13387 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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