Airworthiness Directives; Airbus Airplanes, 44903-44907 [2017-20567]

Download as PDF Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations (j) New Provision: No Alternative Actions or Intervals After the action required by paragraph (i) of this AD has been done, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (k)(1) of this AD. asabaliauskas on DSKBBXCHB2PROD with RULES (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2014–26–10 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (iii) AMOCs approved previously for AD 2014–26–10, which are included in the AMOC letters specified in paragraphs (k)(1)(iii)(A) and (k)(1)(iii)(B), are approved as AMOCs for the provisions of paragraph (i) of this AD. (A) AMOC letter ANM–116–17–002R1, dated November 14, 2016. (B) AMOC letter ANM–116–17–323, dated June 12, 2017. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0093, dated May 13, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017–0248. (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. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. VerDate Sep<11>2014 17:24 Sep 26, 2017 Jkt 241001 (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on November 1, 2017. (i) Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 4, ‘‘System Equipment Maintenance Requirements (SEMR),’’ Revision 03 at Issue 02, dated January 22, 2016. (ii) Reserved. (4) The following service information was approved for IBR on February 25, 2015 (80 FR 2813, January 21, 2015). (i) Airbus A318/A319/A320/A321 Airworthiness Limitations Section, ALS Part 4, ‘‘Aging Systems Maintenance,’’ Revision 01, dated June 15, 2012. The revision level of this document is identified on only the title page and in the Record of Revisions. The revision date is not identified on the title page of this document. (ii) Reserved. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@ airbus.com; Internet: http://www.airbus.com. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 14, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–20113 Filed 9–26–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 44903 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0498; Product Identifier 2016–NM–175–AD; Amendment 39–19053; AD 2017–19–23] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2015–15– 10, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015–15–10 required repetitive inspections of the trimmable horizontal stabilizer actuator (THSA) for damage, and replacement if necessary; and replacement of the THSA after reaching a certain life limit. This AD requires repetitive detailed inspections of certain THSAs, and related investigative and corrective actions if necessary. This AD was prompted by the establishment of an additional life limit for the THSA, based on flight cycles. In addition, the THSA manufacturer has issued service information which, when accomplished, increases the life limit of the THSA. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 1, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 1, 2017. 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– 0498. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\27SER1.SGM 27SER1 44904 Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations www.regulations.gov by searching for and locating Docket No. FAA–2017– 0498; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 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 to supersede AD 2015–15–10, Amendment 39–18219 (80 FR 43928, July 24, 2015) (‘‘AD 2015–15–10’’). AD 2015–15–10 applied to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on June 2, 2017 (82 FR 25542). The NPRM was prompted by the establishment of an additional life limit for the THSA, based on flight cycles. The NPRM proposed to require repetitive detailed inspections of certain THSAs, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct wear of the THSA, which could reduce the remaining life of the THSA, possibly resulting in premature failure and consequent reduced controllability of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0184, dated September 13, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318 and 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: In the frame of the A320 Extended Service Goal (ESG) project and the study on the Trimmable Horizontal Stabilizer Actuator (THSA), a sampling programme of in-service units was performed and several cases of wear at different THSA levels were reported. This condition, if not detected and corrected, would reduce the remaining life of the THSA, possibly resulting in premature failure and consequent reduced control of the aeroplane. Prompted by these findings, Airbus issued Service Bulletin (SB) A320–27–1227 to provide THSA inspection instructions. Consequently, EASA issued AD 2014–0011 (later revised) [which corresponds to AD 2015–15–10] to require repetitive inspections of the THSA [and related investigative and corrective actions] and to introduce a life limit for the THSA, based on flight hours (FH). Since EASA AD 2014–0011R1 was issued, an additional life limitation has been established, based on flight cycles (FC). Furthermore, United Technologies Corporation Aerospace Systems (UTAS), the THSA manufacturer, issued an SB which, after accomplishment on THSA, increases the life limit of the THSA. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014–0011R1, which is superseded, and introduces an additional FC life limit for the affected THSA. This [EASA] AD also provides a revised life limit for the THSA after UTAS SB accomplishment on that THSA. 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– 0498. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Air Line Pilots Association, International (ALPA) and United Airlines expressed their support for the NPRM. Changes Made to This AD The NPRM specified that a THSA that had been repaired in-shop as specified in UTAS Component Maintenance Manual 27–44–51 would be an equivalent method of compliance for the initial inspection required by paragraph (h) of this AD. We have revised paragraph (m) of this AD to specify that a THSA that has been repaired in-shop using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus’s EASA Design Organization Approval (DOA), is acceptable for compliance with the initial inspection required by paragraph (h) of this AD. We have also added Note 1 to paragraph (m) of this AD to reference UTAS Component Maintenance Manual 27–44–51 as an additional source of guidance for the inshop repair of the THSA. 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 Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. This service information describes procedures for repetitive special detailed inspections for wear of the THSA, and related investigative and corrective actions. 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 1,182 airplanes of U.S. registry. We estimate the following costs to comply with this AD: asabaliauskas on DSKBBXCHB2PROD with RULES ESTIMATED COSTS Action Labor cost Inspections ............. 6 work-hours × $85 per hour = $510 per inspection cycle. VerDate Sep<11>2014 17:24 Sep 26, 2017 Jkt 241001 PO 00000 Parts cost Frm 00026 Cost per product $0 Fmt 4700 Cost on U.S. operators $510 per inspection cycle ........... Sfmt 4700 E:\FR\FM\27SER1.SGM $602,820 per inspection cycle. 27SER1 Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations We have received no definitive data that would enable us to provide cost estimates for the spectrometric analysis of the oil drained from the THSA gearbox. We estimate the following costs to do any necessary replacements or overhauls that would be required based on the results of the inspection. We 44905 have no way of determining the number of aircraft that might need these replacements or overhauls: ON-CONDITION COSTS Labor cost Replacement of THSA (retained from AD 2015–15– 10). Overhaul of THSA (new action) ................................... 11 work-hours × $85 per hour = $935 ......................... $240,000 $240,935 66 work-hours × $85 per hour = $5,610 ...................... 115,000 120,610 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. the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Regulatory Findings § 39.13 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 asabaliauskas on DSKBBXCHB2PROD with RULES Parts cost Cost per product Action [Amended] ■ 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–15–10, Amendment 39–18219 (80 FR 43928, July 24, 2015), and adding the following new AD: 2017–19–23 Airbus: Amendment 39–19053; Docket No. FAA–2017–0498; Product Identifier 2016–NM–175–AD. (a) Effective Date This AD is effective November 1, 2017. (b) Affected ADs This AD replaces AD 2015–15–10, Amendment 39–18219 (80 FR 43928, July 24, 2015) (‘‘AD 2015–15–10’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by reports of wear at different levels in the trimmable horizontal stabilizer actuator (THSA). We are issuing this AD to detect and correct wear of the THSA, which could reduce the remaining life of the THSA, possibly resulting in premature failure and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Serviceable THSA Definition For the purposes of this AD, a serviceable THSA is a THSA that does not exceed the life limits as identified in table 1 to paragraphs (g) and (j) of this AD. TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits Configuration, based on service bulletin (SB) embodiment Compliance time (whichever occurs first) THSA on which United Technologies Corporation Aerospace Systems (UTAS) SB 47145–27–19 has not been embodied. Before exceeding 67,500 flight hours (FH) since first installation on an airplane, or before exceeding 48,000 flight cycles (FC) since first installation on an airplane. VerDate Sep<11>2014 17:24 Sep 26, 2017 Jkt 241001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\27SER1.SGM 27SER1 44906 Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations TABLE 1 TO PARAGRAPHS (G) AND (J) OF THIS AD—THSA Life Limits—Continued Configuration, based on service bulletin (SB) embodiment Compliance time (whichever occurs first) THSA on which UTAS SB 47145–27–19 has been embodied ............... Before exceeding 52,500 FH after embodiment of UTAS SB 47145– 27–19 on an airplane, without exceeding 120,000 FH since first installation on an airplane; or before exceeding 27,000 FC after embodiment of UTAS SB 47145–27–19 on an airplane, without exceeding 75,000 FC since first installation on an airplane. (h) Repetitive Inspection and Related Investigative Actions For any airplane on which UTAS Service Bulletin 47145–27–19 has not been embodied: Before the THSA exceeds 48,000 flight hours or 30,000 flight cycles, whichever occurs first since first installation on an airplane, do a special detailed inspection of the THSA and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. Do all applicable related investigative actions at the applicable times specified in paragraph 1.E., ‘‘Compliance’’ of Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. Repeat the inspections thereafter at intervals not to exceed 24 months. (i) Corrective Action If, during any inspection required by paragraph (h) of this AD, any finding as described in the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1227, Revision 03, dated April 29, 2016, is identified: At the applicable time (depending on the applicable finding) specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016, replace the THSA with a serviceable THSA, as specified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. asabaliauskas on DSKBBXCHB2PROD with RULES (j) THSA Replacement Within the applicable compliance time specified in table 1 to paragraphs (g) and (j) of this AD, replace each THSA with a serviceable THSA, as specified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. (k) Replacement of a THSA: Not Terminating Action Replacement of a THSA on an airplane, as required by paragraph (i) or (j) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD for that airplane, unless the THSA has been overhauled as specified in UTAS Service Bulletin 47145–27–19 (i.e., post-service bulletin). (l) Optional Terminating Action: Overhaul of THSA Accomplishment of a modification of an airplane by installing a THSA that has been overhauled as specified in UTAS Service Bulletin 47145–27–19 constitutes terminating action for the repetitive inspections required VerDate Sep<11>2014 17:24 Sep 26, 2017 Jkt 241001 by paragraph (h) of this AD, provided that, following modification, no THSA is reinstalled on the airplane unless it has been overhauled as specified in UTAS Service Bulletin 47145–27–19. (m) Replacement THSA Equivalency As of the effective date of this AD: A THSA that has been repaired in-shop is acceptable for compliance with the initial inspection required by paragraph (h) of this AD, provided that repair was done 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). Note 1 to paragraph (m) of this AD: Guidance for THSA repair in-shop can be found in UTAS Component Maintenance Manual 27–44–51. (n) Parts Installation Limitation As of the effective date of this AD: Do not install on any airplane a THSA unless it is a serviceable THSA as specified in paragraph (g) of this AD. (o) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using any of the service information specified in paragraphs (o)(1), (o)(2), or (o)(3) of this AD. (1) Airbus Service Bulletin A320–27–1227, dated July 1, 2013, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A320–27–1227, Revision 01, dated October 7, 2013, which was incorporated by reference in AD 2015– 15–10. (3) Airbus Service Bulletin A320–27–1227, Revision 02, dated February 2, 2015, which is not incorporated by reference in this AD. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (q)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 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 the 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0184, dated September 13, 3016, 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–2017–0498. (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 (r)(3) and (r)(4) of this AD. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–27–1227, Revision 03, dated April 29, 2016. (ii) Reserved. (3) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, E:\FR\FM\27SER1.SGM 27SER1 Federal Register / Vol. 82, No. 186 / Wednesday, September 27, 2017 / Rules and Regulations asabaliauskas on DSKBBXCHB2PROD with RULES 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/ibrlocations.html. This AD is effective October 12, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 28, 2017 (82 FR 34251, July 24, 2017). We must receive comments on this AD by November 13, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the Issued in Renton, Washington, on instructions for submitting comments. September 14, 2017. • Fax: 202–493–2251. Jeffrey E. Duven, • Mail: U.S. Department of Director, System Oversight Division, Aircraft Transportation, Docket Operations, M– Certification Service. 30, West Building Ground Floor, Room [FR Doc. 2017–20567 Filed 9–26–17; 8:45 am] W12–140, 1200 New Jersey Avenue SE., BILLING CODE 4910–13–P Washington, DC 20590. • Hand Delivery: U.S. Department of DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Federal Aviation Administration Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except 14 CFR Part 39 Federal holidays. [Docket No. FAA–2017–0813; Product For Airbus service information Identifier 2017–NM–109–AD; Amendment identified in this final rule, contact 39–19059; AD 2017–20–02] Airbus, Airworthiness Office–EIAS, 1 RIN 2120–AA64 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 Airworthiness Directives; Airbus 61 93 36 96; fax: +33 5 61 93 44 51; Airplanes email: account.airworth-eas@ airbus.com; Internet: http:// AGENCY: Federal Aviation www.airbus.com. Administration (FAA), Department of You may view this referenced service Transportation (DOT). information at the FAA, Transport ACTION: Final rule; request for Standards Branch, 1601 Lind Avenue comments. SW., Renton, WA. For information on SUMMARY: We are superseding the availability of this material at the Airworthiness Directive (AD) 2017–13– FAA, call 425–227–1221. It is also 05, which applied to all Airbus Model available on the Internet at http:// A330–200, A330–300, A340–200, A340– www.regulations.gov by searching for 300, A340–500, and A340–600 series and locating Docket No. FAA–2017– airplanes. AD 2017–13–05 required an 0813. inspection, corrective actions if Examining the AD Docket necessary, lubrication of the ball-nut, You may examine the AD docket on modification of the trimmable the Internet at http:// horizontal stabilizer actuator (THSA), www.regulations.gov by searching for and additional work for previously and locating Docket No. FAA–2017– modified airplanes. For certain 0813; or in person at the Docket airplanes, AD 2017–13–05 required Management Facility between 9 a.m. installation of an electronic harness, and 5 p.m., Monday through Friday, terminating actions, and a ball-screw except Federal holidays. The AD docket assembly inspection. This AD clarifies contains this AD, the regulatory the formatting of a figure in the evaluation, any comments received, and published version of AD 2017–13–05. other information. The street address for This AD was prompted by reports the Docket Office (telephone 800–647– indicating that affected parties 5527) is Docket Management Facility, misinterpreted the intent of a figure as U.S. Department of Transportation, formatted in the published version of Docket Operations, M–30, West AD 2017–13–05, which could result in Building Ground Floor, Room W12–140, a negative effect on compliance. We are 1200 New Jersey Avenue SE., issuing this AD to address the unsafe Washington, DC 20590. condition on these products. VerDate Sep<11>2014 17:24 Sep 26, 2017 Jkt 241001 DATES: PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 44907 FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Discussion On June 15, 2017, we issued AD 2017–13–05, Amendment 39–18935 (82 FR 34251, July 24, 2017) (‘‘AD 2017–13– 05’’), which applied to all Airbus Model A330–200, A330–300, A340–200, A340– 300, A340–500, and A340–600 series airplanes. AD 2017–13–05 was prompted by the need for a modification that automatically detects failure of the ball-screw assembly. AD 2017–13–05 required an inspection, corrective actions if necessary, lubrication of the ball-nut, modification of the trimmable horizontal stabilizer actuator (THSA), and additional work for previously modified airplanes. For certain airplanes, AD 2017–13–05 required installation of an electronic harness, terminating actions, and a ball-screw assembly inspection. We issued AD 2017–13–05 to detect and correct wear on the THSA, possibly resulting in damage to the ball-screw and fail-safe nut, which could jam the THSA and result in reduced control of the airplane. Since we issued AD 2017–13–05, we have received reports indicating that affected parties could misinterpret the identity of applicable service information to use for the modification, due to the formatting of figure 2 to paragraphs (h) and (i) in the published version of AD 2017–13–05. Since the published figure could result in a negative effect on compliance, we have determined that clarification of the formatting of the published figure is necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014–0219, dated September 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330 and Model A340 series airplanes. (Model A330– 223F and A330–243F airplanes were removed from AD 2017–13–05 to correspond with the MCAI.) The EASA AD is referenced in AD 2017–13–05. EASA has not revised its AD since the issuance of AD 2017–13–05. 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– 0813. E:\FR\FM\27SER1.SGM 27SER1

Agencies

[Federal Register Volume 82, Number 186 (Wednesday, September 27, 2017)]
[Rules and Regulations]
[Pages 44903-44907]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20567]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0498; Product Identifier 2016-NM-175-AD; Amendment 
39-19053; AD 2017-19-23]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-15-10, 
which applied to all Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2015-15-10 required repetitive inspections of the 
trimmable horizontal stabilizer actuator (THSA) for damage, and 
replacement if necessary; and replacement of the THSA after reaching a 
certain life limit. This AD requires repetitive detailed inspections of 
certain THSAs, and related investigative and corrective actions if 
necessary. This AD was prompted by the establishment of an additional 
life limit for the THSA, based on flight cycles. In addition, the THSA 
manufacturer has issued service information which, when accomplished, 
increases the life limit of the THSA. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective November 1, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 1, 
2017.

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-
0498.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://

[[Page 44904]]

www.regulations.gov by searching for and locating Docket No. FAA-2017-
0498; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 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 to supersede AD 2015-15-10, Amendment 39-18219 (80 FR 43928, 
July 24, 2015) (``AD 2015-15-10''). AD 2015-15-10 applied to all Airbus 
Model A318, A319, A320, and A321 series airplanes. The NPRM published 
in the Federal Register on June 2, 2017 (82 FR 25542). The NPRM was 
prompted by the establishment of an additional life limit for the THSA, 
based on flight cycles. The NPRM proposed to require repetitive 
detailed inspections of certain THSAs, and related investigative and 
corrective actions if necessary. We are issuing this AD to detect and 
correct wear of the THSA, which could reduce the remaining life of the 
THSA, possibly resulting in premature failure and consequent reduced 
controllability of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0184, dated September 13, 2016 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A318 
and 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:

    In the frame of the A320 Extended Service Goal (ESG) project and 
the study on the Trimmable Horizontal Stabilizer Actuator (THSA), a 
sampling programme of in-service units was performed and several 
cases of wear at different THSA levels were reported.
    This condition, if not detected and corrected, would reduce the 
remaining life of the THSA, possibly resulting in premature failure 
and consequent reduced control of the aeroplane.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A320-27-1227 to provide THSA inspection instructions. Consequently, 
EASA issued AD 2014-0011 (later revised) [which corresponds to AD 
2015-15-10] to require repetitive inspections of the THSA [and 
related investigative and corrective actions] and to introduce a 
life limit for the THSA, based on flight hours (FH).
    Since EASA AD 2014-0011R1 was issued, an additional life 
limitation has been established, based on flight cycles (FC). 
Furthermore, United Technologies Corporation Aerospace Systems 
(UTAS), the THSA manufacturer, issued an SB which, after 
accomplishment on THSA, increases the life limit of the THSA.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0011R1, which is superseded, and 
introduces an additional FC life limit for the affected THSA. This 
[EASA] AD also provides a revised life limit for the THSA after UTAS 
SB accomplishment on that THSA.

    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-
0498.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received. Air Line Pilots 
Association, International (ALPA) and United Airlines expressed their 
support for the NPRM.

Changes Made to This AD

    The NPRM specified that a THSA that had been repaired in-shop as 
specified in UTAS Component Maintenance Manual 27-44-51 would be an 
equivalent method of compliance for the initial inspection required by 
paragraph (h) of this AD. We have revised paragraph (m) of this AD to 
specify that a THSA that has been repaired in-shop using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA Design Organization Approval 
(DOA), is acceptable for compliance with the initial inspection 
required by paragraph (h) of this AD. We have also added Note 1 to 
paragraph (m) of this AD to reference UTAS Component Maintenance Manual 
27-44-51 as an additional source of guidance for the in-shop repair of 
the THSA.

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 Service Bulletin A320-27-1227, Revision 03, dated 
April 29, 2016. This service information describes procedures for 
repetitive special detailed inspections for wear of the THSA, and 
related investigative and corrective actions.
    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 1,182 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......................  6 work-hours x $85               $0  $510 per inspection  $602,820 per
                                    per hour = $510                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 44905]]

    We have received no definitive data that would enable us to provide 
cost estimates for the spectrometric analysis of the oil drained from 
the THSA gearbox. We estimate the following costs to do any necessary 
replacements or overhauls that would be required based on the results 
of the inspection. We have no way of determining the number of aircraft 
that might need these replacements or overhauls:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of THSA (retained from AD 2015-15-  11 work-hours x $85 per hour =          $240,000        $240,935
 10).                                            $935.
Overhaul of THSA (new action).................  66 work-hours x $85 per hour =           115,000         120,610
                                                 $5,610.
----------------------------------------------------------------------------------------------------------------

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 removing Airworthiness Directive (AD) 
2015-15-10, Amendment 39-18219 (80 FR 43928, July 24, 2015), and adding 
the following new AD:

2017-19-23 Airbus: Amendment 39-19053; Docket No. FAA-2017-0498; 
Product Identifier 2016-NM-175-AD.

(a) Effective Date

    This AD is effective November 1, 2017.

(b) Affected ADs

    This AD replaces AD 2015-15-10, Amendment 39-18219 (80 FR 43928, 
July 24, 2015) (``AD 2015-15-10'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by reports of wear at different levels in 
the trimmable horizontal stabilizer actuator (THSA). We are issuing 
this AD to detect and correct wear of the THSA, which could reduce 
the remaining life of the THSA, possibly resulting in premature 
failure and consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Serviceable THSA Definition

    For the purposes of this AD, a serviceable THSA is a THSA that 
does not exceed the life limits as identified in table 1 to 
paragraphs (g) and (j) of this AD.

     Table 1 to Paragraphs (g) and (j) of This AD--THSA Life Limits
------------------------------------------------------------------------
    Configuration, based on service         Compliance time (whichever
        bulletin (SB) embodiment                  occurs first)
------------------------------------------------------------------------
THSA on which United Technologies        Before exceeding 67,500 flight
 Corporation Aerospace Systems (UTAS)     hours (FH) since first
 SB 47145-27-19 has not been embodied.    installation on an airplane,
                                          or before exceeding 48,000
                                          flight cycles (FC) since first
                                          installation on an airplane.

[[Page 44906]]

 
THSA on which UTAS SB 47145-27-19 has    Before exceeding 52,500 FH
 been embodied.                           after embodiment of UTAS SB
                                          47145-27-19 on an airplane,
                                          without exceeding 120,000 FH
                                          since first installation on an
                                          airplane; or before exceeding
                                          27,000 FC after embodiment of
                                          UTAS SB 47145-27-19 on an
                                          airplane, without exceeding
                                          75,000 FC since first
                                          installation on an airplane.
------------------------------------------------------------------------

(h) Repetitive Inspection and Related Investigative Actions

    For any airplane on which UTAS Service Bulletin 47145-27-19 has 
not been embodied: Before the THSA exceeds 48,000 flight hours or 
30,000 flight cycles, whichever occurs first since first 
installation on an airplane, do a special detailed inspection of the 
THSA and do all applicable related investigative actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Do all 
applicable related investigative actions at the applicable times 
specified in paragraph 1.E., ``Compliance'' of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016. Repeat the 
inspections thereafter at intervals not to exceed 24 months.

(i) Corrective Action

    If, during any inspection required by paragraph (h) of this AD, 
any finding as described in the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29, 
2016, is identified: At the applicable time (depending on the 
applicable finding) specified in paragraph 1.E., ``Compliance,'' of 
Airbus Service Bulletin A320-27-1227, Revision 03, dated April 29, 
2016, replace the THSA with a serviceable THSA, as specified in 
paragraph (g) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1227, Revision 03, 
dated April 29, 2016.

(j) THSA Replacement

    Within the applicable compliance time specified in table 1 to 
paragraphs (g) and (j) of this AD, replace each THSA with a 
serviceable THSA, as specified in paragraph (g) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1227, Revision 03, dated April 29, 2016.

(k) Replacement of a THSA: Not Terminating Action

    Replacement of a THSA on an airplane, as required by paragraph 
(i) or (j) of this AD, does not constitute terminating action for 
the repetitive inspections required by paragraph (h) of this AD for 
that airplane, unless the THSA has been overhauled as specified in 
UTAS Service Bulletin 47145-27-19 (i.e., post-service bulletin).

(l) Optional Terminating Action: Overhaul of THSA

    Accomplishment of a modification of an airplane by installing a 
THSA that has been overhauled as specified in UTAS Service Bulletin 
47145-27-19 constitutes terminating action for the repetitive 
inspections required by paragraph (h) of this AD, provided that, 
following modification, no THSA is reinstalled on the airplane 
unless it has been overhauled as specified in UTAS Service Bulletin 
47145-27-19.

(m) Replacement THSA Equivalency

    As of the effective date of this AD: A THSA that has been 
repaired in-shop is acceptable for compliance with the initial 
inspection required by paragraph (h) of this AD, provided that 
repair was done 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).
    Note 1 to paragraph (m) of this AD: Guidance for THSA repair in-
shop can be found in UTAS Component Maintenance Manual 27-44-51.

(n) Parts Installation Limitation

    As of the effective date of this AD: Do not install on any 
airplane a THSA unless it is a serviceable THSA as specified in 
paragraph (g) of this AD.

(o) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using any of the service 
information specified in paragraphs (o)(1), (o)(2), or (o)(3) of 
this AD.
    (1) Airbus Service Bulletin A320-27-1227, dated July 1, 2013, 
which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A320-27-1227, Revision 01, dated 
October 7, 2013, which was incorporated by reference in AD 2015-15-
10.
    (3) Airbus Service Bulletin A320-27-1227, Revision 02, dated 
February 2, 2015, which is not incorporated by reference in this AD.

(p) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (q)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0184, dated September 13, 
3016, 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-2017-0498.
    (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 (r)(3) and (r)(4) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-27-1227, Revision 03, dated 
April 29, 2016.
    (ii) Reserved.
    (3) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex,

[[Page 44907]]

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 September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20567 Filed 9-26-17; 8:45 am]
 BILLING CODE 4910-13-P