Airworthiness Directives; Airbus Airplanes, 19925-19928 [2018-09280]

Download as PDF Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations Issued in Kansas City, Missouri, on April 19, 2018. Melvin Johnson, Deputy Director, Policy and Innovation Division, Aircraft Certification Service. For more information about this AD, contact William O. Herderich, Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5547; fax: (404) 474–5605; email: william.o.herderich@ faa.gov. http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 1245. [FR Doc. 2018–08956 Filed 5–4–18; 8:45 am] (k) Related Information You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1245; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: BILLING CODE 4910–13–P daltland on DSKBBV9HB2PROD with RULES (l) 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 the AD specifies otherwise. (i) Gulfstream G350 Customer Bulletin Number 192A, dated June 15, 2017, that incorporates Appendix A, Gulfstream Document GIV–SGER–553, Revision A, Instructions for Continued Airworthiness for Gulfstream Repair Drawing SE05732102, dated December 14, 2016. (ii) Gulfstream G450 Customer Bulletin 192A, dated June 15, 2017, that incorporates Appendix A, Gulfstream Document GIV– SGER–553, Revision A, Instructions for Continued Airworthiness for Gulfstream Repair Drawing SE05732102, dated December 14, 2016. (iii) Gulfstream IV Customer Bulletin Number 238A, dated June 15, 2017, that incorporates Appendix A, Gulfstream Document GIV–SGER–553, Revision A, Instructions for Continued Airworthiness for Gulfstream Repair Drawing SE05732102, dated December 14, 2016. (iv) Gulfstream G300 Customer Bulletin Number 238A, dated June 15, 2017, that incorporates Appendix A, Gulfstream Document GIV–SGER–553, Revision A, Instructions for Continued Airworthiness for Gulfstream Repair Drawing SE05732102, dated December 14, 2016. (v) Gulfstream G400 Customer Bulletin Number 238A, dated June 15, 2017, that incorporates Appendix A, Gulfstream Document GIV–SGER–553, Revision A, Instructions for Continued Airworthiness for Gulfstream Repair Drawing SE05732102, dated December 14, 2016. (3) For Gulfstream Aerospace Corporation service information identified in this AD, contact Gulfstream Aerospace Corporation, P.O. Box 2206, Savannah, Georgia 31402– 2206; telephone: (800) 810–4853; fax 912– 965–3520; email: pubs@gulfstream.com; internet: http://www.gulfstream.com/ product_support/technical_pubs/pubs/ index.htm. (4) You may view this service information at FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (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/ibrlocations.html. VerDate Sep<11>2014 16:29 May 04, 2018 Jkt 244001 19925 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–1245; Product Identifier 2017–NM–099–AD; Amendment 39–19266; AD 2018–09–09] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes and Model A319 series airplanes; all Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and all Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the holes of the upper cleat to upper stringer attachments at certain areas of the left- and right-hand wings are subject to widespread fatigue damage (WFD). This AD requires modifying the holes of the upper cleat to upper stringer attachments at certain areas of the left- and right-hand wings. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 11, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 11, 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, 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 SUMMARY: PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 Examining the AD Docket 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 and Model A319 series airplanes; all Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and all Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on January 12, 2018 (83 FR 1579) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH indicating that the holes of the upper cleat to upper stringer attachments at certain areas of the leftand right-hand wings are subject to WFD. The NPRM proposed to require modifying the holes of the upper cleat to upper stringer attachments at certain areas of the left- and right-hand wings. We are issuing this AD to prevent fatigue cracking in the stringer attachment holes of the wings, which could result in reduced structural integrity of the wings. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0117, dated July 7, 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 and Model A319 series E:\FR\FM\07MYR1.SGM 07MYR1 19926 Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations airplanes; all Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and all Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: Within the scope of work of service life extension for A320 aeroplanes and of widespread fatigue damage evaluations, it has been determined that a structural modification is required to allow the aeroplanes to continue operation up to the limit of validity (LoV). This condition, if not corrected, may affect the structural integrity of the wing. To address this potential unsafe condition, Airbus issued [service bulletin] SB A320–57– 1208, providing instructions to oversize the holes of the upper cleat to upper stringer attachments at Rib 2 to Rib 7 (inclusive). For the reason described above, this [EASA] AD requires modification of the affected holes. 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– 1245. 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. United Airlines agreed with the intent of the NPRM. Request To Clarify Applicability Allegiant Air asked that we clarify the manufacturer serial numbers (MSNs) identified in the applicability section of the proposed AD. Allegiant Air stated that the effectivity specified in Airbus Service Bulletin A320–57–1208, dated November 21, 2016, identifies airplanes up to and including MSN 7493, and asked about airplanes having MSNs higher than 7493. Allegiant Air noted that it has 11 Model A320 airplanes with MSNs outside those listed in Airbus Service Bulletin A320–57–1208, dated November 21, 2016. Allegiant Air added that it understands the AD takes precedence over the service information, but there are several configurations listed therein. Allegiant Air also added that since the MSNs in question are not listed in the effectivity of the service information, an operator with an MSN outside the effectivity will not know which modification kit to order. We agree to clarify. The effectivity in Airbus Service Bulletin A320–57–1208, dated November 21, 2016, does not include all MSNs for Model A320 airplanes, and the applicability specified in paragraph (c) of this AD includes all MSNs for Model A320 airplanes, except for airplanes having certain modifications. We acknowledge that the referenced service information may not be adequate for certain airplane configurations. Therefore, we have revised paragraph (g) of this AD to provide an option for doing the modification, including identification of the appropriate modification kit, using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). In addition, Airbus has informed us that Revision 1 of the referenced service information will expand the effectivity to include MSNs up to 8555. Airbus has also informed us that, upon request, it will issue a technical adaptation as an interim method of compliance until a revised service bulletin is issued. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for 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. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Service Bulletin A320–57–1208, dated November 21, 2016. This service information describes procedures for modifying the stringer attachments at rib 2 through rib 7 of the left- and righthand wings. The modification includes oversizing the holes, doing an eddy current inspection of the affected holes for damage, and repair. 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 1,136 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Modification (by oversizing and doing eddy current inspection). 125 work-hours × $85 per hour = $10,625 .... We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. daltland on DSKBBV9HB2PROD with RULES 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, VerDate Sep<11>2014 16:29 May 04, 2018 Jkt 244001 Parts cost 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, PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 $26,260 Cost per product $36,885 Cost on U.S. operators $41,901,360 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 E:\FR\FM\07MYR1.SGM 07MYR1 Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: daltland on DSKBBV9HB2PROD with RULES ■ VerDate Sep<11>2014 16:29 May 04, 2018 Jkt 244001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2018–09–09 Airbus: Amendment 39–19266; Docket No. FAA–2017–1245; Product Identifier 2017–NM–099–AD. (a) Effective Date This AD is effective June 11, 2018. (c) Applicability This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes specified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model A318 series airplanes on which Airbus Modification (Mod) 39195 has been embodied in production or Airbus Service Bulletin A320–00–1219 has been embodied in service. (2) Model A319 series airplanes on which Airbus Mod 28238, Mod 28162, and Mod 28342 have been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. Frm 00023 Fmt 4700 This AD was prompted by an evaluation by the design approval holder indicating that the holes of the upper cleat to upper stringer attachments at rib 2 through rib 7 of the leftand right-hand wings are subject to widespread fatigue damage. We are issuing this AD to prevent fatigue cracking in the stringer attachment holes of the wings, which could result in reduced structural integrity of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (b) Affected ADs None. PO 00000 (e) Reason Sfmt 4725 (g) Modification Before reaching the upper limit, but not before reaching the lower limit, as defined in table 1 to paragraph (g) of this AD, as applicable: Modify the holes of the upper cleat to upper stringer attachments at rib 2 through rib 7 inclusive, on the left- and righthand wings by oversizing the holes, doing eddy current inspections of the holes for damage, and repairing any damage found before further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1208, dated November 21, 2016, except as required by paragraph (h) of this AD; 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). If approved by the DOA, the approval must include the DOA-authorized signature. E:\FR\FM\07MYR1.SGM 07MYR1 ER07MY18.026</GPH> 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. 19927 19928 Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations (h) Service Information Exception Where Airbus Service Bulletin A320–57– 1208, dated November 21, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (i)(2) of this AD. (i) 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 (j)(2) of this AD. Information may be emailed to 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) 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. daltland on DSKBBV9HB2PROD with RULES (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0117, dated July 7, 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–2017–1245. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. VerDate Sep<11>2014 16:29 May 04, 2018 Jkt 244001 (k) 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 A320–57–1208, dated November 21, 2016. (ii) Reserved. (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, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on April 20, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09280 Filed 5–4–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0838; Product Identifier 2017–NE–33–AD; Amendment 39– 19275; AD 2018–10–01] RIN 2120–AA64 Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A., Arriel 2E turboshaft engines. This AD was prompted by reports of ruptured front support pins on the accessory gearbox front support. This AD requires replacement of the accessory gearbox front support. We are issuing this AD to address the unsafe condition on these products. SUMMARY: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 This AD becomes effective June 11, 2018. ADDRESSES: For service information identified in this final rule, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0838. DATES: 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– 0838; 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 mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is Docket Operations, 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: Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue; phone: 781–238–7754; fax: 781–238– 7199; email: robert.green@faa.gov. 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 all Safran Helicopter Engines, S.A., Arriel 2E turboshaft engines. The NPRM published in the Federal Register on November 3, 2017 (82 FR 51170). The NPRM was prompted by reports of ruptured front support pins on the accessory gearbox front support. The NPRM proposed to require replacement of the accessory gearbox front support. We are issuing this AD to address the unsafe condition on these products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2016– 0235, dated November 24, 2016 (referred to after this as the MCAI), to E:\FR\FM\07MYR1.SGM 07MYR1

Agencies

[Federal Register Volume 83, Number 88 (Monday, May 7, 2018)]
[Rules and Regulations]
[Pages 19925-19928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09280]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD; Amendment 
39-19266; AD 2018-09-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318 series airplanes and Model A319 series airplanes; all 
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and 
all Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the holes of the upper cleat to upper 
stringer attachments at certain areas of the left- and right-hand wings 
are subject to widespread fatigue damage (WFD). This AD requires 
modifying the holes of the upper cleat to upper stringer attachments at 
certain areas of the left- and right-hand wings. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective June 11, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 11, 
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: [email protected]; 
internet: http://www.airbus.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195. It is also available on the 
internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2017-1245.

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-
1245; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A318 
series airplanes and Model A319 series airplanes; all Model A320-211, -
212, -214, -216, -231, -232, and -233 airplanes; and all Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM 
published in the Federal Register on January 12, 2018 (83 FR 1579) 
(``the NPRM''). The NPRM was prompted by an evaluation by the DAH 
indicating that the holes of the upper cleat to upper stringer 
attachments at certain areas of the left- and right-hand wings are 
subject to WFD. The NPRM proposed to require modifying the holes of the 
upper cleat to upper stringer attachments at certain areas of the left- 
and right-hand wings. We are issuing this AD to prevent fatigue 
cracking in the stringer attachment holes of the wings, which could 
result in reduced structural integrity of the wings.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0117, dated July 7, 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 and 
Model A319 series

[[Page 19926]]

airplanes; all Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and all Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes. The MCAI states:

    Within the scope of work of service life extension for A320 
aeroplanes and of widespread fatigue damage evaluations, it has been 
determined that a structural modification is required to allow the 
aeroplanes to continue operation up to the limit of validity (LoV).
    This condition, if not corrected, may affect the structural 
integrity of the wing.
    To address this potential unsafe condition, Airbus issued 
[service bulletin] SB A320-57-1208, providing instructions to 
oversize the holes of the upper cleat to upper stringer attachments 
at Rib 2 to Rib 7 (inclusive).
    For the reason described above, this [EASA] AD requires 
modification of the affected holes.

    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-
1245.

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. United Airlines agreed with the 
intent of the NPRM.

Request To Clarify Applicability

    Allegiant Air asked that we clarify the manufacturer serial numbers 
(MSNs) identified in the applicability section of the proposed AD. 
Allegiant Air stated that the effectivity specified in Airbus Service 
Bulletin A320-57-1208, dated November 21, 2016, identifies airplanes up 
to and including MSN 7493, and asked about airplanes having MSNs higher 
than 7493. Allegiant Air noted that it has 11 Model A320 airplanes with 
MSNs outside those listed in Airbus Service Bulletin A320-57-1208, 
dated November 21, 2016. Allegiant Air added that it understands the AD 
takes precedence over the service information, but there are several 
configurations listed therein. Allegiant Air also added that since the 
MSNs in question are not listed in the effectivity of the service 
information, an operator with an MSN outside the effectivity will not 
know which modification kit to order.
    We agree to clarify. The effectivity in Airbus Service Bulletin 
A320-57-1208, dated November 21, 2016, does not include all MSNs for 
Model A320 airplanes, and the applicability specified in paragraph (c) 
of this AD includes all MSNs for Model A320 airplanes, except for 
airplanes having certain modifications. We acknowledge that the 
referenced service information may not be adequate for certain airplane 
configurations. Therefore, we have revised paragraph (g) of this AD to 
provide an option for doing the modification, including identification 
of the appropriate modification kit, using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA Design Organization Approval (DOA).
    In addition, Airbus has informed us that Revision 1 of the 
referenced service information will expand the effectivity to include 
MSNs up to 8555. Airbus has also informed us that, upon request, it 
will issue a technical adaptation as an interim method of compliance 
until a revised service bulletin is issued.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for 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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A320-57-1208, dated 
November 21, 2016. This service information describes procedures for 
modifying the stringer attachments at rib 2 through rib 7 of the left- 
and right-hand wings. The modification includes oversizing the holes, 
doing an eddy current inspection of the affected holes for damage, and 
repair. 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 1,136 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification (by oversizing and      125 work-hours x $85 per            $26,260         $36,885     $41,901,360
 doing eddy current inspection).      hour = $10,625.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue 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

[[Page 19927]]

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):

2018-09-09 Airbus: Amendment 39-19266; Docket No. FAA-2017-1245; 
Product Identifier 2017-NM-099-AD.

(a) Effective Date

    This AD is effective June 11, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all 
manufacturer serial numbers, except airplanes specified in 
paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A318 series airplanes on which Airbus Modification 
(Mod) 39195 has been embodied in production or Airbus Service 
Bulletin A320-00-1219 has been embodied in service.
    (2) Model A319 series airplanes on which Airbus Mod 28238, Mod 
28162, and Mod 28342 have been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that the holes of the upper cleat to upper 
stringer attachments at rib 2 through rib 7 of the left- and right-
hand wings are subject to widespread fatigue damage. We are issuing 
this AD to prevent fatigue cracking in the stringer attachment holes 
of the wings, which could result in reduced structural integrity of 
the wings.

(f) Compliance

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

(g) Modification

    Before reaching the upper limit, but not before reaching the 
lower limit, as defined in table 1 to paragraph (g) of this AD, as 
applicable: Modify the holes of the upper cleat to upper stringer 
attachments at rib 2 through rib 7 inclusive, on the left- and 
right-hand wings by oversizing the holes, doing eddy current 
inspections of the holes for damage, and repairing any damage found 
before further flight, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-57-1208, dated November 
21, 2016, except as required by paragraph (h) of this AD; 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). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
[GRAPHIC] [TIFF OMITTED] TR07MY18.026


[[Page 19928]]



(h) Service Information Exception

    Where Airbus Service Bulletin A320-57-1208, dated November 21, 
2016, specifies to contact Airbus for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance): Before 
further flight, accomplish corrective actions in accordance with the 
procedures specified in paragraph (i)(2) of this AD.

(i) 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 (j)(2) of this AD. Information 
may be emailed to [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, 
the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0117, dated July 7, 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-2017-1245.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.

(k) 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 A320-57-1208, dated November 21, 
2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 44 51; email: [email protected]; internet: 
http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on April 20, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-09280 Filed 5-4-18; 8:45 am]
BILLING CODE 4910-13-P