83 FR 5906 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 29 (February 12, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 29 (February 12, 2018)
| Page Range | 5906-5912 | |
| FR Document | 2018-02359 |
[Federal Register Volume 83, Number 29 (Monday, February 12, 2018)] [Rules and Regulations] [Pages 5906-5912] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02359] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0707; Product Identifier 2016-NM-014-AD; Amendment 39-19185; AD 2018-03-12] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). This AD requires repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 19, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 19, 2018. 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, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0707. 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- 0707; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425- 227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. The NPRM published in the Federal Register on July 25, 2017 (82 FR 34449) (``the NPRM''). The NPRM was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames. The NPRM proposed to require repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. We are issuing this AD to detect and correct cracking at the door stop fitting holes of fuselage FR66 and FR68. Such cracking could result in reduced structural integrity of the airplane due to the failure of structural components. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0238, dated December 2, 2016; corrected January 4, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, - 212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During an A320 fatigue test campaign, it was determined that fatigue damage could appear at the door stop fitting holes of fuselage frame (FR) 66 and FR 68 on left hand (LH) and right hand (RH) sides. This condition, if not detected and corrected, could affect the structural integrity of the airframe. Two inspections, Airworthiness Limitations Item (ALI) tasks 534129 and 534130, were introduced in the Airworthiness Limitations Section (ALS) Part 2 with the April 2012 revision and with some compliance time changes with Revision 3 of ALS Part 2 of October 2014. Since these ALI tasks were implemented, a significant number of reports [were] received concerning non-critical damage and early crack findings. Prompted by these reports, Airbus published SB A320- 53-1288 and SB A320-53-1290, providing inspection instructions to improve damage management and modification instructions. Consequently, EASA issued AD 2016-0015, requiring repetitive rototest inspections of the affected door stop fitting holes and, depending on findings, repair of any cracked area(s). Since that [EASA] AD was issued, ALS Part 2 Revision 04 and later on Revision 05 were published, introducing updated thresholds and/or intervals for some tasks as specified in Airbus SB A320-53- 1288, introducing new configuration of aeroplane with RETRO WING having accomplished SB A320-57-1193 (mod 160080), and keeping the threshold or interval only in flight cycles (FC). For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016-0015, which is superseded, but requires those actions within the updated thresholds and intervals. In addition, a corrected threshold for pre-mod 160021 A321 aeroplanes is introduced and the Applicability is reduced to exclude configurations that are not affected. This [EASA] AD is republished to clarify some requirements in Appendix 1 [in this EASA 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- 0707. 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 Add a Grace Period for Certain Repetitive Inspections United Airlines (UAL) requested that we revise paragraph (h) of the proposed AD to allow a 60-day grace period after [[Page 5907]] the effective date of this AD to give operators time to update their maintenance programs. UAL noted that for airplanes on which inspections were previously accomplished as specified in airworthiness limitation item (ALI) task 534129 or 534130, paragraph (h) of the proposed AD requires future inspections be done in accordance with Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. UAL noted that operators who are not yet incorporating Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, may have to schedule special inspection visits instead of doing the inspections during scheduled maintenance. We agree with the commenter's request to add a grace period to paragraph (h) of this AD to allow operators to plan for the new inspection interval. However, since the commenter did not provide adequate justification to support a 60-day grace period, we have determined that a 30-day grace period is appropriate. Additionally, under the provisions of paragraph (q)(1) of this AD, we will consider requests for approval of an extension of the compliance time if sufficient data are submitted to substantiate that the new compliance time would provide an acceptable level of safety. We have revised paragraph (h) of this AD to include a 30-day grace period. Request To Allow Deviations From the Service Information for Certain Modified Airplanes UAL requested that either the service information or the proposed AD be revised to provide alternate instructions for airplanes with modified hardware. UAL noted that ``paragraph (i)'' of the proposed AD requires repetitive inspections on airplanes modified by cold working fastener holes, which includes installing oversize hardware. UAL pointed out that the inspections must be done in accordance with Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, which requires using nominal size hardware that no longer exists on modified airplanes. We infer that the commenter meant to refer to paragraph (j) of the proposed AD, which discusses post-modification inspections, rather than paragraph (i) of the proposed AD, which discusses an optional modification. We agree with the commenter's request. We acknowledge that Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, does not specifically address oversize hardware; however, EASA has stated that ``the same inspection principle applies for post SB [Service Bulletin] 53-1290 configuration.'' Therefore, we have retained Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, in paragraph (j) of this AD. We have also revised paragraph (j) of this AD to include an option for operators to obtain inspection instructions using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA). Request To Remove a Reference to a Non-Terminating Action UAL requested that we remove the statement ``repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (g) or (j) of this AD for that repair, unless specified otherwise'' from paragraph (k) of the proposed AD. UAL suggested that statement be replaced with one instructing operators to accomplish inspections as specified in the repair instructions. UAL noted that paragraph (k) of the proposed AD states that a crack repair must be done using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA and says that such a repair does not constitute terminating action for the repetitive inspections done in accordance with Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, unless specified otherwise. UAL pointed out that Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, contains language to allow operators to accomplish crack repairs in accordance with structural repair manual (SRM) 53-41-12, and then perform inspections of the repaired area in accordance with SRM 53-41- 12. UAL noted that the SRM repair instructions do not state that they terminate the inspections in Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. UAL further noted that Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, only applies to unrepaired areas with nominal size holes (the repaired areas would have oversized holes). We disagree with the commenter's request. We acknowledge that Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, allows repairs to be done using an SRM. However, this AD does not include that allowance since SRMs published before the effective date of this AD might not address the unsafe condition identified in this AD. Therefore, paragraph (k) of this AD requires repairs to be done using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Additionally, the statement that the commenter requested us to remove from paragraph (k) of this proposed AD aligns with the MCAI. The statement is meant to clarify that doing a repair does not necessarily terminate the repetitive inspections; the repetitive inspections would only be terminated if the repair approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA specifically states that the inspections are terminated. If the approved repair does not state that the inspections are terminated, operators must continue to inspect using Airbus Service Bulletin A320- 53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016, or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Therefore, we have not changed the requirements in paragraph (k) of this AD nor have we removed the statement identified by the commenter. However, we have revised paragraph (g) of this AD to include an option for operators to obtain inspection instructions using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Request To Remove Requirement To Obtain Certain Inspection Instructions UAL requested that we remove paragraph (l)(2) of the proposed AD because it has no real purpose. UAL noted that paragraph (l)(2) of the proposed AD requires operators to obtain inspection instructions and corrective actions for all repaired fastener holes by contacting the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. UAL claimed that if a repair was accomplished using the instructions in an SRM or repair design approval sheet (RDAS), the repair approval contains, at a minimum, the initial compliance threshold. UAL added that it is standard [[Page 5908]] practice for operators to contact Airbus prior to the inspection threshold if the compliance method and intervals are not yet defined. We disagree with the commenter's request. Airbus intends to provide specific instructions for airplanes inspected in accordance with ALI task 534129 or task 534130 and repaired in accordance with an SRM or RDAS published before the effective date of this AD. Since repair instructions published before the effective date of this AD might not address the unsafe condition identified in this AD, the SRM or RDAS instructions might need to be re-evaluated or revised to address the unsafe condition. In addition, we do not rely on an operator's standard practices, and instead require operators to obtain inspections and corrective actions to address the unsafe condition. We have not revised this AD regarding this issue. Request To Clarify Actions for Airplanes With Certain Repairs UAL requested that we delete paragraph (n) of the proposed AD. UAL noted that paragraph (n) of the proposed AD requires operators to determine if a repair was done using an RDAS that is unrelated to ALI task 534129 or task 534130. UAL suggested that the repair instructions would have to state that the damage was found as a result of the applicable ALI, but noted that the ALI task is an inspection that may not be referenced in a documented repair. UAL questioned the relevance of whether or not a repair was related to ALI task 534129 or task 534130, noting that the same considerations are given to repair instructions, regardless of how damage was found. UAL stated that operators would know to seek an alternative method of compliance (AMOC) if they cannot inspect a previously repaired area in accordance with Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. We disagree with the commenter's request. The intent of paragraph (n) of the proposed AD is to require operators to re-evaluate existing repairs performed using an Airbus RDAS unrelated to ALI task 534129 or task 534130 because those repairs may not address the findings from the specific inspection types required by the ALI tasks. Therefore, the corresponding repairs might not address the unsafe condition and operators might need new instructions. We have not changed this AD in this regard. Request To Verify the Latest Service Information is Referenced UAL requested that, prior to the release of this final rule, we verify that we are referencing the latest revisions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; and Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016. We agree with the commenter's request. We have verified that no later revisions of the service information have been issued, and no change is needed to this AD. Explanation of Change to the Final Rule In the proposed AD, Table 1 to paragraphs (g) and (j) of this AD and Table 2 to paragraphs (g) and (j) of this AD included a compliance time that stated ``. . . or before November 30, 2017. . . .'' Since this final rule will become effective after November 30, 2017, we have changed this statement to read ``. . . or within 30 days after the effective date of this AD. . . .'' We have determined that this revised compliance time addresses the unsafe condition. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. This service information describes procedures for rototest inspections for cracking of the fastener holes in the airframe structure for the door stop fittings installation in FR66 and FR68. Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016. This service information describes procedures for cold working the fastener holes in the airframe structure for the door stop fittings installation in FR66 and FR68. 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 1,084 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections................ 23 work-hours x $85 $0 $1,955 per inspection $2,119,220 per per hour = $1,955 cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the required inspection. We have no way of determining the number of aircraft that might need this repair. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair..................................... 27 work-hours x $85 per hour = $610 $2,905 $2,295. ---------------------------------------------------------------------------------------------------------------- [[Page 5909]] 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. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2018-03-12 Airbus: Amendment 39-19185; Docket No. FAA-2017-0707; Product Identifier 2016-NM-014-AD. (a) Effective Date This AD is effective March 19, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and - 133 airplanes; Model A320-211, -212, -214, 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airplanes on which Airbus modification (Mod) 157039 has been embodied in production. (2) Model A319 series airplanes on which Mod 28238, Mod 28162, and Mod 28342 have been embodied in production. (3) Model A318 series airplanes on which Mod 39195 has been embodied in production or Airbus Service Bulletin A320-00-1219 has been embodied in service. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). We are issuing this AD to detect and correct cracking at the door stop fitting holes of fuselage FR66 and FR68. Such cracking could result in reduced structural integrity of the airplane due to the failure of structural components. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Rototest Inspections Within the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD: Do a rototest inspection of all holes below each door stop fitting at fuselage FR66 and FR68, both left-hand (LH) and right-hand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; or 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). Repeat the inspections thereafter at the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, until the modification specified in paragraph (i) of this AD is done. Where the ``Threshold'' column of table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD, specifies compliance times in ``FC'' (flight cycles), those compliance times are total flight cycles since the first flight of the airplane. BILLING CODE 4910-13-P [[Page 5910]] [GRAPHIC] [TIFF OMITTED] TR12FE18.000 [GRAPHIC] [TIFF OMITTED] TR12FE18.001 [[Page 5911]] [GRAPHIC] [TIFF OMITTED] TR12FE18.002 BILLING CODE 4910-13-C (h) Airworthiness Limitations Item (ALI) Inspections Accomplished Before the Effective Date of This AD Inspections accomplished as specified in ALI task 534129 or task 534130 before the effective date of this AD are acceptable for compliance with the initial inspection required by paragraph (g) of this AD. As of 30 days after the effective date of this AD, repetitive inspections must be continued as required by paragraph (g) of this AD. (i) Optional Modification For airplanes on which no cracks were detected during any rototest inspection required by paragraph (g) of this AD: Modifying the affected area by cold working the fastener holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, terminates the repetitive inspections required by paragraph (g) of this AD for the modified area only. (j) Post-Modification Repetitive Inspections For airplanes on which the modification specified in paragraph (i) of this AD has been done: At the compliance time specified in paragraphs (j)(1), (j)(2), or (j)(3) of this AD, as applicable, accomplish a rototest inspection of all holes at the door stop fitting locations at fuselage FR66 and FR68, both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016; or 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). Repeat the inspection thereafter at intervals not to exceed the applicable compliance times specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD. (1) For airplanes with less than 1,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: At the applicable initial compliance time specified in table 1 to paragraphs (g) and (j) of this AD and table 2 to paragraphs (g) and (j) of this AD. (2) For airplanes with 1,800 flight cycles or more and less than 13,800 flight cycles accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 48,000 flight cycles since first flight of the airplane. (3) For airplanes with 13,800 flight cycles or more accumulated since first flight of the airplane at the time of accomplishing the modification specified in paragraph (i) of this AD: Before the accumulation of 60,000 flight cycles since first flight of the airplane. (k) Repair If, during any inspection required by paragraph (g) or (j) of this AD, any crack is detected, before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (g) or (j) of this AD for that airplane, unless specified otherwise in instructions obtained using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. (l) Post-Repair Actions for Certain Airplanes For an airplane that has been inspected as specified in ALI task 534129 or task 534130 and repaired before the effective date of this AD as specified in the applicable structural repair manual (SRM) or as specified in an Airbus repair design approval sheet (RDAS): Comply with the requirements of paragraphs (l)(1) and (l)(2) of this AD. (1) For all fastener holes where no damage or cracks were detected (i.e., those not repaired), accomplish the actions required by paragraph (g) of this AD, unless the terminating action specified in paragraph (m) of this AD has been done. (2) For all repaired fastener holes: Within 30 days after the effective date of this AD, or within a compliance time approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA, whichever occurs later, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA; for inspection instructions and applicable corrective actions, and do the inspections and applicable corrective actions accordingly. (m) Terminating Action for Certain Airplanes For airplanes that have been inspected, as specified in ALI task 534129 or task 534130, and repaired before the effective date of this AD, as specified in the applicable SRM, or as specified in an Airbus RDAS: Modification of the four fastener holes at door stop locations where no damage or crack was detected (i.e., door stop locations not repaired) by cold working holes before further flight after no cracks were detected, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016, constitutes terminating action for the repetitive inspections of those four fastener holes at those door stop locations as required by paragraphs (g) or (l)(1) of this AD for that airplane. (n) Actions for Airplanes With Certain Repairs For an airplane that has been repaired before the effective date of this AD in the areas described in this AD using an Airbus RDAS unrelated to ALI task 534129 or task 534130: Before exceeding the compliance times specified in paragraph (g) of this AD, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA; for corrective action instructions and accomplish those instructions accordingly. Accomplishment of corrective action(s) on an airplane, as required by this paragraph, does not constitute terminating action for the repetitive inspections as required by paragraphs (g) or (j) of this AD for that airplane, as applicable, unless specified otherwise in the instructions. [[Page 5912]] (o) Terminating Action for ALI Tasks (1) Accomplishment of inspections on an airplane, as required by paragraphs (g), (j), or (l) of this AD, as applicable, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for that airplane. (2) Modification of the four fastener holes at a door stop location of an airplane as specified in paragraphs (i) or (m) of this AD, as applicable, and subsequent initial inspection required by paragraph (j) of this AD, constitutes terminating action for the inspection requirements of ALI task 534129 or task 534130, as applicable, for those holes for that airplane. Subsequent repetitive inspections are required by paragraph (j) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1288, including Appendixes 01 and 02, dated October 10, 2014. (2) This paragraph provides credit for actions required by paragraphs (i) and (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-53-1290, dated October 10, 2014. (q) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): 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. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0238, dated December 2, 2016; corrected January 4, 2017, 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-2017-0707. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(3) and (s)(4) of this AD. (s) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-53-1288, Revision 01, including Appendixes 01, 02, and 03, dated October 3, 2016. (ii) Airbus Service Bulletin A320-53-1290, Revision 01, dated October 3, 2016. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; internet: http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on January 29, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-02359 Filed 2-9-18; 8:45 am] BILLING CODE 4910-13-P
![5906 Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations
(j) Material Incorporated by Reference for and locating Docket No. FAA–2017– Model A320–211, –212, –214, –231,
None. 0707. –232, and –233 airplanes; and Model
Issued in Renton, Washington, on January A321–111, –112, –131, –211, –212,
Examining the AD Docket
2, 2018. –213, –231, and –232 airplanes. The
Michael Kaszycki,
You may examine the AD docket on MCAI states:
the internet at http:// During an A320 fatigue test campaign, it
Acting Director, System Oversight Division,
Aircraft Certification Service.
www.regulations.gov by searching for was determined that fatigue damage could
and locating Docket No. FAA–2017– appear at the door stop fitting holes of
[FR Doc. 2018–02751 Filed 2–9–18; 8:45 am]
0707; or in person at the Docket fuselage frame (FR) 66 and FR 68 on left hand
BILLING CODE 4910–13–P
Management Facility between 9 a.m. (LH) and right hand (RH) sides.
and 5 p.m., Monday through Friday, This condition, if not detected and
except Federal holidays. The AD docket corrected, could affect the structural integrity
DEPARTMENT OF TRANSPORTATION of the airframe.
contains this AD, the regulatory
Two inspections, Airworthiness
Federal Aviation Administration evaluation, any comments received, and Limitations Item (ALI) tasks 534129 and
other information. The street address for 534130, were introduced in the
14 CFR Part 39 the Docket Office (telephone: 800–647– Airworthiness Limitations Section (ALS) Part
5527) is Docket Management Facility, 2 with the April 2012 revision and with some
[Docket No. FAA–2017–0707; Product U.S. Department of Transportation, compliance time changes with Revision 3 of
Identifier 2016–NM–014–AD; Amendment ALS Part 2 of October 2014.
39–19185; AD 2018–03–12]
Docket Operations, M–30, West
Building Ground Floor, Room W12–140, Since these ALI tasks were implemented,
RIN 2120–AA64 1200 New Jersey Avenue SE, a significant number of reports [were]
received concerning non-critical damage and
Washington, DC 20590. early crack findings. Prompted by these
Airworthiness Directives; Airbus
FOR FURTHER INFORMATION CONTACT: reports, Airbus published SB A320–53–1288
Airplanes
Sanjay Ralhan, Aerospace Engineer, and SB A320–53–1290, providing inspection
AGENCY: Federal Aviation International Section, Transport instructions to improve damage management
Administration (FAA), Department of Standards Branch, FAA, 1601 Lind and modification instructions.
Transportation (DOT). Avenue SW, Renton, WA 98057–3356; Consequently, EASA issued AD 2016–
telephone: 425–227–1405; fax: 425– 0015, requiring repetitive rototest inspections
ACTION: Final rule.
of the affected door stop fitting holes and,
227–1149. depending on findings, repair of any cracked
SUMMARY: We are adopting a new
SUPPLEMENTARY INFORMATION: area(s).
airworthiness directive (AD) for certain
Since that [EASA] AD was issued, ALS
Airbus Model A318 series airplanes; Discussion Part 2 Revision 04 and later on Revision 05
Model A319 series airplanes; Model We issued a notice of proposed were published, introducing updated
A320–211, –212, –214, –231, –232, and rulemaking (NPRM) to amend 14 CFR thresholds and/or intervals for some tasks as
–233 airplanes; and Model A321–111, part 39 by adding an AD that would specified in Airbus SB A320–53–1288,
–112, –131, –211, –212, –213, –231, and apply to certain Airbus Model A318 introducing new configuration of aeroplane
–232 airplanes. This AD was prompted with RETRO WING having accomplished SB
series airplanes; Model A319 series A320–57–1193 (mod 160080), and keeping
by reports of fatigue damage in the airplanes; Model A320–211, –212, –214,
structure for the door stop fittings on the threshold or interval only in flight cycles
–231, –232, and –233 airplanes; and (FC).
certain fuselage frames (FR). This AD Model A321–111, –112, –131, –211, For the reasons described above, this
requires repetitive rototest inspections –212, –213, –231, and –232 airplanes. [EASA] AD retains the requirements of EASA
for cracking of the fastener holes in The NPRM published in the Federal AD 2016–0015, which is superseded, but
certain door stop fittings, and repair if Register on July 25, 2017 (82 FR 34449) requires those actions within the updated
necessary. We are issuing this AD to (‘‘the NPRM’’). The NPRM was thresholds and intervals. In addition, a
address the unsafe condition on these prompted by reports of fatigue damage corrected threshold for pre-mod 160021 A321
products. aeroplanes is introduced and the
in the structure for the door stop fittings Applicability is reduced to exclude
DATES: This AD is effective March 19, on certain fuselage frames. The NPRM configurations that are not affected.
2018. proposed to require repetitive rototest This [EASA] AD is republished to clarify
The Director of the Federal Register inspections for cracking of the fastener some requirements in Appendix 1 [in this
approved the incorporation by reference holes in certain door stop fittings, and EASA AD].
of certain publications listed in this AD repair if necessary. We are issuing this You may examine the MCAI in the
as of March 19, 2018. AD to detect and correct cracking at the AD docket on the internet at http://
ADDRESSES: For service information door stop fitting holes of fuselage FR66 www.regulations.gov by searching for
identified in this final rule, contact and FR68. Such cracking could result in and locating Docket No. FAA–2017–
Airbus, Airworthiness Office—EIAS, 1 reduced structural integrity of the 0707.
Rond Point Maurice Bellonte, 31707 airplane due to the failure of structural
Blagnac Cedex, France; telephone: +33 5 components. Comments
61 93 36 96; fax: +33 5 61 93 44 51; The European Aviation Safety Agency We gave the public the opportunity to
email: account.airworth-eas@ (EASA), which is the Technical Agent participate in developing this AD. The
airbus.com; internet: http:// for the Member States of the European following presents the comments
www.airbus.com. You may view this Union, has issued EASA AD 2016–0238, received on the NPRM and the FAA’s
referenced service information at the dated December 2, 2016; corrected
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response to each comment.
FAA, Transport Standards Branch, 1601 January 4, 2017 (referred to after this as
Lind Avenue SW, Renton, WA. For the Mandatory Continuing Request To Add a Grace Period for
information on the availability of this Airworthiness Information, or ‘‘the Certain Repetitive Inspections
material at the FAA, call 425–227–1221. MCAI’’), to correct an unsafe condition United Airlines (UAL) requested that
It is also available on the internet at for certain Airbus Model A318 series we revise paragraph (h) of the proposed
http://www.regulations.gov by searching airplanes; Model A319 series airplanes; AD to allow a 60-day grace period after
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![Federal Register / Vol. 83, No. 29 / Monday, February 12, 2018 / Rules and Regulations 5907
the effective date of this AD to give dated October 3, 2016, does not We disagree with the commenter’s
operators time to update their specifically address oversize hardware; request. We acknowledge that Airbus
maintenance programs. UAL noted that however, EASA has stated that ‘‘the Service Bulletin A320–53–1288,
for airplanes on which inspections were same inspection principle applies for Revision 01, including Appendixes 01,
previously accomplished as specified in post SB [Service Bulletin] 53–1290 02, and 03, dated October 3, 2016,
airworthiness limitation item (ALI) task configuration.’’ Therefore, we have allows repairs to be done using an SRM.
534129 or 534130, paragraph (h) of the retained Airbus Service Bulletin A320– However, this AD does not include that
proposed AD requires future inspections 53–1288, Revision 01, including allowance since SRMs published before
be done in accordance with Airbus Appendixes 01, 02, and 03, dated the effective date of this AD might not
Service Bulletin A320–53–1288, October 3, 2016, in paragraph (j) of this address the unsafe condition identified
Revision 01, including Appendixes 01, AD. We have also revised paragraph (j) in this AD. Therefore, paragraph (k) of
02, and 03, dated October 3, 2016. UAL of this AD to include an option for this AD requires repairs to be done
noted that operators who are not yet operators to obtain inspection using a method approved by the
incorporating Airbus Service Bulletin instructions using a method approved Manager, International Section,
A320–53–1288, Revision 01, including by the Manager, International Section, Transport Standards Branch, FAA; or
Appendixes 01, 02, and 03, dated Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA.
October 3, 2016, may have to schedule EASA; or Airbus’s EASA Design Additionally, the statement that the
special inspection visits instead of Organization Approval (DOA). commenter requested us to remove from
doing the inspections during scheduled paragraph (k) of this proposed AD aligns
maintenance. Request To Remove a Reference to a with the MCAI. The statement is meant
We agree with the commenter’s Non-Terminating Action to clarify that doing a repair does not
request to add a grace period to UAL requested that we remove the necessarily terminate the repetitive
paragraph (h) of this AD to allow statement ‘‘repair of an airplane as inspections; the repetitive inspections
operators to plan for the new inspection required by this paragraph does not would only be terminated if the repair
interval. However, since the commenter constitute terminating action for the approved by the Manager, International
did not provide adequate justification to repetitive inspections required by Section, Transport Standards Branch,
support a 60-day grace period, we have paragraph (g) or (j) of this AD for that FAA; or EASA; or Airbus’s EASA DOA
determined that a 30-day grace period is repair, unless specified otherwise’’ from specifically states that the inspections
appropriate. Additionally, under the paragraph (k) of the proposed AD. UAL are terminated. If the approved repair
provisions of paragraph (q)(1) of this suggested that statement be replaced does not state that the inspections are
AD, we will consider requests for with one instructing operators to terminated, operators must continue to
approval of an extension of the accomplish inspections as specified in inspect using Airbus Service Bulletin
compliance time if sufficient data are the repair instructions. A320–53–1288, Revision 01, including
submitted to substantiate that the new Appendixes 01, 02, and 03, dated
UAL noted that paragraph (k) of the
compliance time would provide an October 3, 2016, or using a method
proposed AD states that a crack repair
acceptable level of safety. We have approved by the Manager, International
must be done using a method approved
revised paragraph (h) of this AD to Section, Transport Standards Branch,
by the Manager, International Section,
include a 30-day grace period. FAA; or EASA; or Airbus’s EASA DOA.
Transport Standards Branch, FAA; or Therefore, we have not changed the
Request To Allow Deviations From the EASA; or Airbus’s EASA DOA and says requirements in paragraph (k) of this AD
Service Information for Certain that such a repair does not constitute nor have we removed the statement
Modified Airplanes terminating action for the repetitive identified by the commenter. However,
UAL requested that either the service inspections done in accordance with we have revised paragraph (g) of this AD
information or the proposed AD be Airbus Service Bulletin A320–53–1288, to include an option for operators to
revised to provide alternate instructions Revision 01, including Appendixes 01, obtain inspection instructions using a
for airplanes with modified hardware. 02, and 03, dated October 3, 2016, method approved by the Manager,
UAL noted that ‘‘paragraph (i)’’ of the unless specified otherwise. International Section, Transport
proposed AD requires repetitive UAL pointed out that Airbus Service Standards Branch, FAA; or EASA; or
inspections on airplanes modified by Bulletin A320–53–1288, Revision 01, Airbus’s EASA DOA.
cold working fastener holes, which including Appendixes 01, 02, and 03,
includes installing oversize hardware. dated October 3, 2016, contains Request To Remove Requirement To
UAL pointed out that the inspections language to allow operators to Obtain Certain Inspection Instructions
must be done in accordance with Airbus accomplish crack repairs in accordance UAL requested that we remove
Service Bulletin A320–53–1288, with structural repair manual (SRM) 53– paragraph (l)(2) of the proposed AD
Revision 01, including Appendixes 01, 41–12, and then perform inspections of because it has no real purpose. UAL
02, and 03, dated October 3, 2016, the repaired area in accordance with noted that paragraph (l)(2) of the
which requires using nominal size SRM 53–41–12. UAL noted that the proposed AD requires operators to
hardware that no longer exists on SRM repair instructions do not state that obtain inspection instructions and
modified airplanes. they terminate the inspections in Airbus corrective actions for all repaired
We infer that the commenter meant to Service Bulletin A320–53–1288, fastener holes by contacting the
refer to paragraph (j) of the proposed Revision 01, including Appendixes 01, Manager, International Section,
AD, which discusses post-modification 02, and 03, dated October 3, 2016. UAL Transport Standards Branch, FAA; or
inspections, rather than paragraph (i) of further noted that Airbus Service EASA; or Airbus’s EASA DOA. UAL
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the proposed AD, which discusses an Bulletin A320–53–1288, Revision 01, claimed that if a repair was
optional modification. We agree with including Appendixes 01, 02, and 03, accomplished using the instructions in
the commenter’s request. We dated October 3, 2016, only applies to an SRM or repair design approval sheet
acknowledge that Airbus Service unrepaired areas with nominal size (RDAS), the repair approval contains, at
Bulletin A320–53–1288, Revision 01, holes (the repaired areas would have a minimum, the initial compliance
including Appendixes 01, 02, and 03, oversized holes). threshold. UAL added that it is standard
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Authority for This Rulemaking 2. Is not a ‘‘significant rule’’ under the (2) Model A319 series airplanes on which
DOT Regulatory Policies and Procedures Mod 28238, Mod 28162, and Mod 28342
Title 49 of the United States Code (44 FR 11034, February 26, 1979); have been embodied in production.
specifies the FAA’s authority to issue 3. Will not affect intrastate aviation in (3) Model A318 series airplanes on which
rules on aviation safety. Subtitle I, Alaska; and Mod 39195 has been embodied in production
section 106, describes the authority of 4. Will not have a significant or Airbus Service Bulletin A320–00–1219 has
the FAA Administrator. ‘‘Subtitle VII: economic impact, positive or negative, been embodied in service.
Aviation Programs,’’ describes in more on a substantial number of small entities (d) Subject
detail the scope of the Agency’s under the criteria of the Regulatory
authority. Air Transport Association (ATA) of
Flexibility Act.
America Code 53, Fuselage.
We are issuing this rulemaking under List of Subjects in 14 CFR Part 39
the authority described in ‘‘Subtitle VII, (e) Reason
Part A, Subpart III, Section 44701: Air transportation, Aircraft, Aviation This AD was prompted by reports of
General requirements.’’ Under that safety, Incorporation by reference, fatigue damage in the structure for the door
section, Congress charges the FAA with Safety. stop fittings on certain fuselage frames (FR).
promoting safe flight of civil aircraft in Adoption of the Amendment We are issuing this AD to detect and correct
air commerce by prescribing regulations cracking at the door stop fitting holes of
for practices, methods, and procedures Accordingly, under the authority fuselage FR66 and FR68. Such cracking could
the Administrator finds necessary for delegated to me by the Administrator, result in reduced structural integrity of the
safety in air commerce. This regulation the FAA amends 14 CFR part 39 as airplane due to the failure of structural
is within the scope of that authority follows: components.
because it addresses an unsafe condition PART 39—AIRWORTHINESS (f) Compliance
that is likely to exist or develop on DIRECTIVES Comply with this AD within the
products identified in this rulemaking compliance times specified, unless already
action. ■ 1. The authority citation for part 39 done.
This AD is issued in accordance with continues to read as follows:
(g) Repetitive Rototest Inspections
authority delegated by the Executive Authority: 49 U.S.C. 106(g), 40113, 44701.
Director, Aircraft Certification Service, Within the applicable compliance times
as authorized by FAA Order 8000.51C. § 39.13 [Amended] specified in table 1 to paragraphs (g) and (j)
In accordance with that order, issuance ■ 2. The FAA amends § 39.13 by adding of this AD and table 2 to paragraphs (g) and
of ADs is normally a function of the (j) of this AD: Do a rototest inspection of all
the following new airworthiness
Compliance and Airworthiness holes below each door stop fitting at fuselage
directive (AD):
FR66 and FR68, both left-hand (LH) and
Division, but during this transition 2018–03–12 Airbus: Amendment 39–19185; right-hand (RH) sides, in accordance with the
period, the Executive Director has Docket No. FAA–2017–0707; Product Accomplishment Instructions of Airbus
delegated the authority to issue ADs Identifier 2016–NM–014–AD. Service Bulletin A320–53–1288, Revision 01,
applicable to transport category
(a) Effective Date including Appendixes 01, 02, and 03, dated
airplanes to the Director of the System October 3, 2016; or using a method approved
Oversight Division. This AD is effective March 19, 2018.
by the Manager, International Section,
Regulatory Findings (b) Affected ADs Transport Standards Branch, FAA; or the
None. European Aviation Safety Agency (EASA); or
We determined that this AD will not Airbus’s EASA Design Organization
(c) Applicability
have federalism implications under Approval (DOA). Repeat the inspections
Executive Order 13132. This AD will This AD applies to Airbus Model A318– thereafter at the applicable compliance times
not have a substantial direct effect on 111, –112, –121, and –122 airplanes; Model specified in table 1 to paragraphs (g) and (j)
A319–111, –112, –113, –114, –115, –131, of this AD and table 2 to paragraphs (g) and
the States, on the relationship between
–132, and –133 airplanes; Model A320–211,
the national government and the States, (j) of this AD, until the modification specified
–212, –214, 231, –232, and –233 airplanes;
or on the distribution of power and in paragraph (i) of this AD is done. Where the
and Model A321–111, –112, –131, –211,
responsibilities among the various ‘‘Threshold’’ column of table 1 to paragraphs
–212, –213, –231, and –232 airplanes;
levels of government. certificated in any category; all manufacturer (g) and (j) of this AD and table 2 to
serial numbers, except airplanes specified in paragraphs (g) and (j) of this AD, specifies
For the reasons discussed above, I compliance times in ‘‘FC’’ (flight cycles),
paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
certify that this AD: those compliance times are total flight cycles
(1) Airplanes on which Airbus
1. Is not a ‘‘significant regulatory modification (Mod) 157039 has been since the first flight of the airplane.
action’’ under Executive Order 12866; embodied in production. BILLING CODE 4910–13–P
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(o) Terminating Action for ALI Tasks the procedures and tests identified as RC can DEPARTMENT OF TRANSPORTATION
(1) Accomplishment of inspections on an be done and the airplane can be put back in
airplane, as required by paragraphs (g), (j), or an airworthy condition. Any substitutions or Federal Aviation Administration
(l) of this AD, as applicable, constitutes changes to procedures or tests identified as
terminating action for the inspection RC require approval of an AMOC. 14 CFR Part 39
requirements of ALI task 534129 or task
534130, as applicable, for that airplane. (r) Related Information [Docket No. FAA–2017–0901; Product
(2) Modification of the four fastener holes (1) Refer to Mandatory Continuing Identifier 2017–NM–106–AD; Amendment
at a door stop location of an airplane as 39–19183; AD 2018–03–10]
Airworthiness Information (MCAI) EASA AD
specified in paragraphs (i) or (m) of this AD, 2016–0238, dated December 2, 2016; RIN 2120–AA64
as applicable, and subsequent initial
corrected January 4, 2017, for related
inspection required by paragraph (j) of this Airworthiness Directives; The Boeing
AD, constitutes terminating action for the information. This MCAI may be found in the
inspection requirements of ALI task 534129 AD docket on the internet at http:// Company Airplanes
or task 534130, as applicable, for those holes www.regulations.gov by searching for and
AGENCY: Federal Aviation
for that airplane. Subsequent repetitive locating Docket No. FAA–2017–0707.
(2) For more information about this AD,
Administration (FAA), DOT.
inspections are required by paragraph (j) of
this AD. contact Sanjay Ralhan, Aerospace Engineer, ACTION: Final rule.
(p) Credit for Previous Actions International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
SUMMARY: We are adopting a new
(1) This paragraph provides credit for
Renton, WA 98057–3356; telephone: 425–
airworthiness directive (AD) for all The
actions required by paragraphs (g) and (j) of Boeing Company Model 757–300 series
this AD, if those actions were performed 227–1405; fax: 425–227–1149.
(3) Service information identified in this airplanes. This AD was prompted by
before the effective date of this AD using reports of scribe line damage on fuselage
Airbus Service Bulletin A320–53–1288, AD that is not incorporated by reference is
available at the addresses specified in skin. This AD requires detailed
including Appendixes 01 and 02, dated
October 10, 2014. paragraphs (s)(3) and (s)(4) of this AD. inspections of fuselage skin for the
(2) This paragraph provides credit for presence of scribe lines, and applicable
actions required by paragraphs (i) and (m) of (s) Material Incorporated by Reference on-condition actions. We are issuing
this AD, if those actions were performed (1) The Director of the Federal Register this AD to address the unsafe condition
before the effective date of this AD using approved the incorporation by reference on these products.
Airbus Service Bulletin A320–53–1290, (IBR) of the service information listed in this DATES: This AD is effective March 19,
dated October 10, 2014. paragraph under 5 U.S.C. 552(a) and 1 CFR 2018.
(q) Other FAA AD Provisions part 51. The Director of the Federal Register
The following provisions also apply to this (2) You must use this service information approved the incorporation by reference
AD: as applicable to do the actions required by of a certain publication listed in this AD
(1) Alternative Methods of Compliance this AD, unless this AD specifies otherwise. as of March 19, 2018.
(AMOCs): The Manager, International (i) Airbus Service Bulletin A320–53–1288,
ADDRESSES: For service information
Section, Transport Standards Branch, FAA, Revision 01, including Appendixes 01, 02,
has the authority to approve AMOCs for this identified in this final rule, contact
and 03, dated October 3, 2016.
AD, if requested using the procedures found Boeing Commercial Airplanes,
(ii) Airbus Service Bulletin A320–53–1290,
in 14 CFR 39.19. In accordance with 14 CFR Revision 01, dated October 3, 2016.
Attention: Contractual & Data Services
39.19, send your request to your principal (3) For service information identified in
(C&DS), 2600 Westminster Blvd., MC
inspector or local Flight Standards District
this AD, contact Airbus, Airworthiness
110–SK57, Seal Beach, CA 90740–5600;
Office, as appropriate. If sending information telephone 562–797–1717; internet
directly to the International Section, send it Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; https://www.myboeingfleet.com. You
to the attention of the person identified in may view this service information at the
paragraph (r)(2) of this AD. Information may telephone: +33 5 61 93 36 96; fax: +33 5 61
93 44 51; email: account.airworth-eas@ FAA, Transport Standards Branch, 1601
be emailed to: 9-ANM-116-AMOC-
REQUESTS@faa.gov. Before using any airbus.com; internet: http://www.airbus.com. Lind Avenue SW, Renton, WA. For
approved AMOC, notify your appropriate (4) You may view this service information information on the availability of this
principal inspector, or lacking a principal at the FAA, Transport Standards Branch, material at the FAA, call 425–227–1221.
inspector, the manager of the local flight 1601 Lind Avenue SW, Renton, WA. For It is also available on the internet at
standards district office/certificate holding information on the availability of this http://www.regulations.gov by searching
district office. material at the FAA, call 425–227–1221. for and locating Docket No. FAA–2017–
(2) Contacting the Manufacturer: For any 0901.
(5) You may view this service information
requirement in this AD to obtain corrective
that is incorporated by reference at the Examining the AD Docket
actions from a manufacturer, the action must
be accomplished using a method approved National Archives and Records
Administration (NARA). For information on You may examine the AD docket on
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA; the availability of this material at NARA, call the internet at http://
or Airbus’s EASA DOA. If approved by the 202–741–6030, or go to: http:// www.regulations.gov by searching for
DOA, the approval must include the DOA- www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2017–
authorized signature. locations.html. 0901; or in person at the Docket
(3) Required for Compliance (RC): If any Management Facility between 9 a.m.
service information contains procedures or Issued in Renton, Washington, on January
and 5 p.m., Monday through Friday,
tests that are identified as RC, those 29, 2018.
except Federal holidays. The AD docket
procedures and tests must be done to comply Michael Kaszycki, contains this final rule, the regulatory
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with this AD; any procedures or tests that are Acting Director, System Oversight Division, evaluation, any comments received, and
not identified as RC are recommended. Those Aircraft Certification Service.
procedures and tests that are not identified other information. The address for the
as RC may be deviated from using accepted [FR Doc. 2018–02359 Filed 2–9–18; 8:45 am] Docket Office (phone: 800–647–5527) is
methods in accordance with the operator’s BILLING CODE 4910–13–P Docket Management Facility, U.S.
maintenance or inspection program without Department of Transportation, Docket
obtaining approval of an AMOC, provided Operations, M–30, West Building
VerDate Sep<11>2014 18:49 Feb 09, 2018 Jkt 244001 PO 00000 Frm 00042 Fmt 4700 Sfmt 4700 E:\FR\FM\12FER1.SGM 12FER1](https://thefederalregister.org/doc/83_FR_5935/page/7.svg)
Document Created: 2018-11-01 08:42:36
Document Modified: 2018-11-01 08:42:36
| 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 March 19, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425- 227-1149. | |
| FR Citation | 83 FR 5906 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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