Airworthiness Directives; Airbus Airplanes, 73092-73096 [2015-28886]

Download as PDF 73092 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations V. Differences Between the Banks and the Enterprises Section 1313(f) of the Safety and Soundness Act requires the Director to consider the differences between the Banks and the Enterprises whenever promulgating regulations that affect the Banks. In developing the amendments to this rule, FHFA considered the differences between the Banks and the Enterprises, but also adhered to the statutory mandate that the regulation be ‘‘consistent and comparable’’ with the regulations of the other agencies. In implementing the regulation, FHFA will define scenarios for the regulated entities, bearing in mind the key risk exposures at each regulated entity. In the final rule, FHFA requires different timeframes for reporting stress test results for the Enterprises versus the Banks. For the Enterprises, FHFA sets the dates for reporting stress test results to the regulator, the FRB, and the public in proximity to similar dates in the other agencies’ rules for institutions with over $50 billion in assets. Reporting dates for all the Banks, regardless of size, are set in proximity to similar dates for institutions with less than $50 billion in assets. As a result, the Banks have over three additional months to report results to FHFA, the FRB, and the public. VI. Paperwork Reduction Act The final rule does not contain any collections of information pursuant to the Paperwork Reduction Act of 1995 (44 U.S.C. 3501, et seq.). Therefore, FHFA has not submitted any information to the Office of Management and Budget for review. mstockstill on DSK4VPTVN1PROD with RULES List of Subjects in 12 CFR Part 1238 Administrative practice and procedure, Capital, Federal Home Loan Banks, Government-sponsored enterprises, Regulated entities, Reporting and recordkeeping requirements, Stress test. Authority and Issuance For the reasons stated in the preamble, and under the authority of 12 U.S.C. 4513, 4526, and 5365(i), FHFA 23:14 Nov 23, 2015 Jkt 238001 Authority: 12 U.S.C. 5365(i); 12 U.S.C. 4513, 4526, 4612; and 12 U.S.C. 1426. stress test results for the severely adverse scenario not earlier than November 15 and not later than November 30 of each year. The summary may be published on the regulated entity’s Web site or in any other form that is reasonably accessible to the public; * * * * * 2. Amend § 1238.3 by revising paragraphs (a)(1) and (b) to read as follows: Dated: November 11, 2015. Melvin L. Watt, Director, Federal Housing Finance Agency. PART 1238—STRESS TESTING OF REGULATED ENTITIES 1. The authority citation for part 1238 continues to read as follows: ■ ■ § 1238.3 [FR Doc. 2015–29861 Filed 11–23–15; 8:45 am] Annual stress test. (a) * * * (1) Shall complete an annual stress test of itself based on its data as of December 31 of the preceding calendar year; * * * * * (b) Scenarios provided by FHFA. In conducting its annual stress tests under this section, each regulated entity must use scenarios provided by FHFA, which shall be generally consistent with and comparable to those established by the FRB, that reflect a minimum of three sets of economic and financial conditions, including a baseline, adverse, and severely adverse scenario. Not later than 30 days after the FRB publishes its scenarios, FHFA will issue to all regulated entities a description of the baseline, adverse, and severely adverse scenarios that each regulated entity shall use to conduct its annual stress tests under this part. ■ 3. Amend § 1238.5 by revising paragraph (a) to read as follows: § 1238.5 Required report to FHFA and the FRB of stress test results and related information. VII. Regulatory Flexibility Act The final rule applies only to the regulated entities, which do not come within the meaning of small entities as defined in the Regulatory Flexibility Act (see 5 U.S.C. 601(6)). Therefore, in accordance with section 605(b) of the Regulatory Flexibility Act (5 U.S.C. 605(b)), the General Counsel of FHFA certifies that this final rule will not have a significant economic impact on a substantial number of small entities. VerDate Sep<11>2014 amends part 1238 of title 12 of the Code of Federal Regulations as follows: (a) Report required for stress tests. On or before May 20 of each year, the Enterprises must report the results of the stress tests required under § 1238.3 to FHFA, and to the FRB, in accordance with paragraph (b) of this section; and on or before August 31 of each year, the Banks must report the results of the stress tests required under § 1238.3 to FHFA, and to the FRB, in accordance with paragraph (b) of this section; * * * * * ■ 4. Amend § 1238.7 by revising paragraph (a) to read as follows: § 1238.7 Publication of results by regulated entities. (a) Public disclosure of results required for stress tests of regulated entities. The Enterprises must disclose publicly a summary of the stress test results for the severely adverse scenario not earlier than August 1 and not later than August 15 of each year. Each Bank must disclose publicly a summary of the PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 BILLING CODE 8070–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0490; Directorate Identifier 2014–NM–018–AD; Amendment 39–18322; AD 2015–23–06] 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) 2008–22– 20 for certain Airbus Model A330–200, A330–300, and A340–300 series airplanes. AD 2008–22–20 required repetitive high frequency eddy current (HFEC) inspections for cracking, repair if necessary, and modification of the upper shell structure of the fuselage. This new AD shortens certain compliance times. This AD was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of December 17, 2008 (73 FR 66747, November 12, 2008). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/#!docketDetail; SUMMARY: E:\FR\FM\24NOR1.SGM 24NOR1 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES D=FAA-2015-0490; or in person at the 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. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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–2015– 0490. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–22–20, Amendment 39–15717 (73 FR 66747, November 12, 2008). AD 2008–22–20 applied to certain Airbus Model A330– 200, A330–300, and A340–300 series airplanes. The NPRM published in the Federal Register on March 17, 2015 (80 FR 13799). The NPRM was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance times must be reduced. The NPRM also proposed to shorten certain compliance times. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity 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 2014–0012R1, dated January 24, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200, A330–300, and A340– 300 series airplanes. The MCAI states: During fatigue tests (EF3) on the A340–600, damage was found in the longitudinal doubler at the Vertical Tail Plane (VTP) VerDate Sep<11>2014 23:14 Nov 23, 2015 Jkt 238001 attachment cut out between Frame (FR) 80 and FR86. This damage occurred between 58,341 and 72,891 simulated flight cycles (FC). Due to the higher Design Service Goal and different design of the affected structural area (e.g. doubler thickness) for A330–200/–300 and A340–300 airplane series, the damage assessment concluded that these airplanes may be also potentially affected. This condition, if not detected and corrected, could affect the structural integrity of the upper shell structure between FR80 and FR86. Prompted by these findings, EASA issued AD 2007–0284 [(http://ad.easa.europa.eu/ blob/easa_ad_2007_0284_superseded.pdf/ AD_2007-0284_1)] to require implementation of an inspection programme of this structural area using a high frequency eddy current (HFEC) method and a modification to improve the upper shell structure. Since that [EASA] AD was issued, in the frame of a new fatigue and damage tolerance evaluation, taking into account the airplane utilisation, the inspection threshold and intervals have been reassessed and the conclusion was that the thresholds and intervals for inspection, as well as the threshold for modifying the airplane, must be reduced. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2007–0284, which is superseded and introduces redefined thresholds and intervals. This [EASA] AD is revised to clarify that, under some conditions, accomplishment of a repair constitutes terminating action for the repetitive inspections. One of the outcome of this clarification is the deletion of paragraph (5) of this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/#!documentDetail; D=FAA-2015-0490-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 13799, March 17, 2015) and the FAA’s response to each comment. Support for the NPRM (80 FR 13799, March 17, 2015) An anonymous commenter agreed with the safety benefit provided by the NPRM (80 FR 13799, March 17, 2015). Request for Revise Cost Delta requested that we revise the NPRM (80 FR 13799, March 17, 2015) to relay the heavy impact of accomplishing Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012. Delta explained that the modification specified in Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012, requires removal of the vertical stabilizer and the aft galley, which can heavily impact the operation. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 73093 Delta reasoned that it has consulted with its maintenance organization and it is estimated to take 400 work-hours instead of 208 work-hours. We disagree with the request to revise this AD. We made the cost estimate based on the information provided in Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012. The required work-hours defined in Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012, are based on the direct labor cost to do the work. The need to remove and reinstall the aft galley depends on the airplane interior configuration and may differ from operator to operator. We are unable to determine all possible interior configurations and thus determine the maximum work-hours which may be required for any specific configuration. This estimate assumes that the work will be done by experienced personnel, and may need to be revised upwards to suit an operator’s circumstances. The estimate does not include the time to prepare, plan, or inspect the work. We have made no changes to this AD in this regard. Conclusion We reviewed the available data 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 (80 FR 13799, March 17, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 13799, March 17, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A330–53– 3159, Revision 02, dated March 29, 2010, describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, high frequency eddy current (HFEC) inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). • Airbus Service Bulletin A330–53– 3160, Revision 03, dated January 6, 2012, describes procedures for applicable actions, including an eddy current rotating probe test for cracking of the fastener holes and an HFEC inspection for cracks in the upper shell E:\FR\FM\24NOR1.SGM 24NOR1 73094 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES of the fuselage (and including checks of the fastener position for clearance and applicable corrective actions (e.g., repair and rework)), and a modification of the airplane upper shell structure of the fuselage between FR80 and FR86. • Airbus Service Bulletin A330–53– 3168, Revision 02, dated December 21, 2011, describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. • Airbus Service Bulletin A340–53– 4165, Revision 02, dated March 29, 2010, describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). • Airbus Service Bulletin A340–53– 4172, Revision 01, dated July 8, 2009, describes procedures for inspections (e.g., rototest inspections of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and modification of the airplane upper shell structure between FR80 and FR86 (including applicable corrective actions (e.g., repair and rework). • Airbus Service Bulletin A340–53– 4174, Revision 02, dated December 21, 2011, describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. 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 of this AD. Costs of Compliance We estimate that this AD affects 26 airplanes of U.S. registry. We also estimate that it will take about 208 work-hours per product to comply with the basic requirements (inspection and modification) of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $28,360 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,197,040, or $46,040 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the VerDate Sep<11>2014 23:14 Nov 23, 2015 Jkt 238001 cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. Regulatory Findings office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2008–22–20, Amendment 39–15717 (73 FR 66747, November 12, 2008), and adding the following new AD: ■ 2015–23–06 Airbus: Amendment 39–18322. Docket No. FAA–2015–0490; Directorate Identifier 2014–NM–018–AD. 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. (a) Effective Date Examining the AD Docket (e) Reason You may examine the AD docket on the Internet at http:// www.regulations.gov/#!docket Detail;D=FAA-2015-0490; 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 Operations This AD was prompted by the results of a fatigue and damage tolerance evaluation that concluded existing compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 This AD becomes effective December 29, 2015. (b) Affected ADs This AD replaces AD 2008–22–20, Amendment 39–15717 (73 FR 66747, November 12, 2008). (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–311, –312, and –313 airplanes; certificated in any category; all manufacturer serial numbers on which Airbus Modification 44205 has been embodied in production, except those on which Airbus Modification 52974 or 53223 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\24NOR1.SGM 24NOR1 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations (h) Corrective Action for Airbus Model A330–300 and A340–300 Airplanes, Except Model A340–300 WV 027 Airplanes mstockstill on DSK4VPTVN1PROD with RULES (g) Inspection for Airbus Model A330–300 and A340–300 Airplanes, Except Model A340–300 Weight Variant (WV) 027 Airplanes For Model A330–300 and A340–300 airplanes, except Model A340–300 WV 027 airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the upper shell structure between frame (FR) 80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340–53–4174, Revision 02, dated December 21, 2011; as applicable. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340–53–4174, Revision 02, dated December 21, 2011; as applicable. (1) For airplanes that, as of the effective date of this AD, have not been inspected in accordance with Airbus Service Bulletin A330–53–3168; or Airbus Service Bulletin A340–53–4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Before reaching the applicable threshold specified in paragraph 1.E., ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340–53–4174, Revision 02, dated December 21, 2011; as applicable for airplane model, configuration, and utilization, since the airplane’s first flight. (ii) Within the threshold defined in paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340–53–4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization since the airplane’s first flight; or within 12 months after the effective date of this AD; whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have been inspected in accordance with Airbus Service Bulletin A330–53–3168; or Airbus Service Bulletin A340–53–4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the applicable interval specified in paragraph 1.E., ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340–53–4174, Revision 02, dated December 21, 2011; as applicable; to be counted from the last inspection. (ii) Within 12 months after the effective date of this AD without exceeding the intervals defined in paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340– 53–4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization to be counted from the last inspection. VerDate Sep<11>2014 23:14 Nov 23, 2015 Jkt 238001 If any crack is detected during any HFEC inspection required by the introductory text to paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Accomplishment of a repair for a specific area, as required by this paragraph, is terminating action for the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, as applicable, for that specific repaired area only. The need and definition of subsequent repetitive inspections (if any) for that specific repaired area will be defined in the applicable repair method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) or Airbus’s EASA Design Organization Approval (DOA). 73095 (k) Inspection and Modification for Airbus Model A340–300 Airplanes, Only WV 027 For Model A340–300 airplanes, WV 027 only: Before the accumulation of 14,200 total flight cycles from the airplane’s first flight, do all applicable inspections and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–53–4172, Revision 01, dated July 8, 2009. (l) Corrective Action for Airbus Model A330– 200 Airplanes; and Model A340–300 Airplanes, only WV 027 If any crack is detected during the inspection required by the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA; concurrently with modification required by paragraph the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD. (j) Inspection and Modification for Airbus Model A330–200 Airplanes (m) Definition of ‘‘Threshold’’ and ‘‘Interval’’ (1) For the purposes of this AD, the term ‘‘Threshold,’’ as used in paragraph 1.E., ‘‘COMPLIANCE,’’ of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the airplane’s first flight. (2) For the purposes of this AD, the term ‘‘Interval’’ as used in paragraph 1.E., ‘‘COMPLIANCE,’’ of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the last inspection, as applicable. (i) Airbus Service Bulletin A330–53–3168, dated September 19, 2007. (ii) Airbus Service Bulletin A330–53–3168, Revision 01, dated February 15, 2008. (iii) Airbus Service Bulletin A330–53– 3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340–53– 4174, dated September 19, 2007. (v) Airbus Service Bulletin A340–53–4174, Revision 01, dated February 15, 2008. (vi) Airbus Service Bulletin A340–53– 4174, Revision 02, dated December 21, 2011. Within the compliance times specified in paragraph (j)(1) or (j)(2) of this AD, whichever occurs later: Do all applicable actions, including an eddy current rotating probe test and an HFEC inspection for cracks, and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012. (1) Within the compliance times identified in paragraph 1.E., ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012, as applicable for airplane configuration and utilization since the airplane’s first flight. (2) Within 12 months after the effective date of this AD without exceeding the threshold defined in paragraph 1.E, ‘‘COMPLIANCE,’’ of Airbus Service Bulletin A330–53–3160, Revision 02, dated March 29, 2010, since the airplane’s first flight. (n) Credit for Previous Actions (1) For Model A330–300 and A340–300 airplanes, except Model A340–300 WV 027 airplanes: This paragraph provides credit for the modification specified in paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330–53–3159, dated September 19, 2007. (ii) Airbus Service Bulletin A330–53–3159, Revision 01, dated June 15, 2009. (iii) Airbus Service Bulletin A340–53– 4165, dated September 19, 2007. (iv) Airbus Service Bulletin A340–53– 4165, Revision 01, dated June 17, 2009. (2) For Model A330–200 airplanes: This paragraph provides credit for the inspection (i) Optional Terminating Action For Airbus Model A330–300 and A340– 300 airplanes, except Model A340–300 WV 027 airplanes: Modification, which includes inspections and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340–53–4165, Revision 02, dated March 29, 2010; as applicable; terminates the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, except where Airbus Service Bulletin A330–53–3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340–53–4165, Revision 02, dated March 29, 2010; as applicable; specifies to contact the manufacturer, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\24NOR1.SGM 24NOR1 73096 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations and modification required by the introductory text to paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as applicable. (i) Airbus Service Bulletin A330–53–3160, dated July 9, 2007, which was incorporated by reference in AD 2008–22–20, Amendment 39–15717 (73 FR 66747, November 12, 2008). (ii) Airbus Service Bulletin A330–53–3160, Revision 01, dated April 28, 2009, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A330–53– 3160, Revision 02, dated March 29, 2010, which is not incorporated by reference in this AD. (3) For Model A340–300 airplanes, WV 027 only: This paragraph provides credit for the inspection and modification required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340– 53–4172, dated July 10, 2007, which is was incorporated by reference in AD 2008–22–20, Amendment 39–15717 (73 FR 66747, November 12, 2008). mstockstill on DSK4VPTVN1PROD with RULES (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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. The AMOC approval letter must specifically reference this AD. (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 Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0012R1, dated January 24, 2014, 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–2015–0490. VerDate Sep<11>2014 23:14 Nov 23, 2015 Jkt 238001 (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. DEPARTMENT OF TRANSPORTATION (q) Material Incorporated by Reference 14 CFR Part 39 (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 December 29, 2015. (i) Airbus Service Bulletin A330–53–3159, Revision 02, dated March 29, 2010. (ii) Airbus Service Bulletin A330–53–3160, Revision 03, dated January 6, 2012. (iii) Airbus Service Bulletin A330–53– 3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340–53– 4165, Revision 02, dated March 29, 2010. (v) Airbus Service Bulletin A340–53–4172, Revision 01, dated July 8, 2009. (vi) Airbus Service Bulletin A340–53– 4174, Revision 02, dated December 21, 2011. (4) The following service information was approved for IBR on December 17, 2008 (73 FR 66747, November 12, 2008). (i) Airbus Service Bulletin A330–53–3168, Revision 01, dated February 15, 2008. (ii) Airbus Service Bulletin A340–53–4174, Revision 01, dated February 15, 2008. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 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. [Docket No. FAA–2015–0682; Directorate Identifier 2014–NM–074–AD; Amendment 39–18329; AD 2015–23–12] Issued in Renton, Washington, on October 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–28886 Filed 11–23–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; ATR—GIE ´ Avions de Transport Regional Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all ATR—GIE Avions de Transport ´ Regional Model ATR42 and ATR72 airplanes. This AD was prompted by new occurrences of certain cracked main landing gear (MLG) rear hinge pins. This AD requires identifying the serial number and part number of the MLG rear hinge pins, and replacing pins or the MLG if necessary. We are issuing this AD to detect and correct cracked rear hinge pins, which could lead to MLG structural failure, possibly resulting in collapse of the MLG and consequent injury to the occupants of the airplane. DATES: This AD becomes effective December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 29, 2015. ADDRESSES: You may examine the AD docket on the Internet at http://www. regulations.gov/#!docketDetail;D=FAA2015-0682; or in person at the 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. For service information identified in this AD, contact ATR—GIE Avions de ´ ´ Transport Regional, 1, Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atr.fr; Internet http://www.aerochain.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 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 SUMMARY: E:\FR\FM\24NOR1.SGM 24NOR1

Agencies

[Federal Register Volume 80, Number 226 (Tuesday, November 24, 2015)]
[Rules and Regulations]
[Pages 73092-73096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-28886]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-AD; 
Amendment 39-18322; AD 2015-23-06]
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) 2008-22-20 for 
certain Airbus Model A330-200, A330-300, and A340-300 series airplanes. 
AD 2008-22-20 required repetitive high frequency eddy current (HFEC) 
inspections for cracking, repair if necessary, and modification of the 
upper shell structure of the fuselage. This new AD shortens certain 
compliance times. This AD was prompted by a determination from a 
fatigue and damage tolerance evaluation that the compliance times must 
be reduced. We are issuing this AD to prevent fatigue cracking of the 
upper shell structure of the fuselage, which could result in reduced 
structural integrity of the airplane.

DATES: This AD becomes effective December 29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 29, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
December 17, 2008 (73 FR 66747, November 12, 2008).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;

[[Page 73093]]

D=FAA-2015-0490; or in person at the 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.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 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-2015-
0490.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2008-22-20, Amendment 39-15717 (73 FR 66747, 
November 12, 2008). AD 2008-22-20 applied to certain Airbus Model A330-
200, A330-300, and A340-300 series airplanes. The NPRM published in the 
Federal Register on March 17, 2015 (80 FR 13799). The NPRM was prompted 
by a determination from a fatigue and damage tolerance evaluation that 
the compliance times must be reduced. The NPRM also proposed to shorten 
certain compliance times. We are issuing this AD to prevent fatigue 
cracking of the upper shell structure of the fuselage, which could 
result in reduced structural integrity 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 2014-0012R1, dated January 24, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200, A330-300, and A340-300 series airplanes. The MCAI states:

    During fatigue tests (EF3) on the A340-600, damage was found in 
the longitudinal doubler at the Vertical Tail Plane (VTP) attachment 
cut out between Frame (FR) 80 and FR86. This damage occurred between 
58,341 and 72,891 simulated flight cycles (FC).
    Due to the higher Design Service Goal and different design of 
the affected structural area (e.g. doubler thickness) for A330-200/-
300 and A340-300 airplane series, the damage assessment concluded 
that these airplanes may be also potentially affected.
    This condition, if not detected and corrected, could affect the 
structural integrity of the upper shell structure between FR80 and 
FR86.
    Prompted by these findings, EASA issued AD 2007-0284 [(http://ad.easa.europa.eu/blob/easa_ad_2007_0284_superseded.pdf/AD_2007-0284_1)] to require implementation of an inspection programme of 
this structural area using a high frequency eddy current (HFEC) 
method and a modification to improve the upper shell structure.
    Since that [EASA] AD was issued, in the frame of a new fatigue 
and damage tolerance evaluation, taking into account the airplane 
utilisation, the inspection threshold and intervals have been 
reassessed and the conclusion was that the thresholds and intervals 
for inspection, as well as the threshold for modifying the airplane, 
must be reduced.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2007-0284, which is superseded and 
introduces redefined thresholds and intervals.
    This [EASA] AD is revised to clarify that, under some 
conditions, accomplishment of a repair constitutes terminating 
action for the repetitive inspections. One of the outcome of this 
clarification is the deletion of paragraph (5) of this [EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0490-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 13799, March 17, 2015) and the FAA's response to each comment.

Support for the NPRM (80 FR 13799, March 17, 2015)

    An anonymous commenter agreed with the safety benefit provided by 
the NPRM (80 FR 13799, March 17, 2015).

Request for Revise Cost

    Delta requested that we revise the NPRM (80 FR 13799, March 17, 
2015) to relay the heavy impact of accomplishing Airbus Service 
Bulletin A330-53-3160, Revision 03, dated January 6, 2012. Delta 
explained that the modification specified in Airbus Service Bulletin 
A330-53-3160, Revision 03, dated January 6, 2012, requires removal of 
the vertical stabilizer and the aft galley, which can heavily impact 
the operation. Delta reasoned that it has consulted with its 
maintenance organization and it is estimated to take 400 work-hours 
instead of 208 work-hours.
    We disagree with the request to revise this AD. We made the cost 
estimate based on the information provided in Airbus Service Bulletin 
A330-53-3160, Revision 03, dated January 6, 2012. The required work-
hours defined in Airbus Service Bulletin A330-53-3160, Revision 03, 
dated January 6, 2012, are based on the direct labor cost to do the 
work. The need to remove and reinstall the aft galley depends on the 
airplane interior configuration and may differ from operator to 
operator. We are unable to determine all possible interior 
configurations and thus determine the maximum work-hours which may be 
required for any specific configuration. This estimate assumes that the 
work will be done by experienced personnel, and may need to be revised 
upwards to suit an operator's circumstances. The estimate does not 
include the time to prepare, plan, or inspect the work. We have made no 
changes to this AD in this regard.

Conclusion

    We reviewed the available data 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 (80 FR 13799, March 17, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 13799, March 17, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-53-3159, Revision 02, dated 
March 29, 2010, describes procedures for a modification of the 
fuselage, which includes inspections (e.g., eddy current rotating probe 
test of fastener holes for cracking, high frequency eddy current (HFEC) 
inspections for cracking of the upper shell structure of the fuselage, 
and checks of the fastener position for clearance) and applicable 
corrective actions (e.g., repair and rework).
     Airbus Service Bulletin A330-53-3160, Revision 03, dated 
January 6, 2012, describes procedures for applicable actions, including 
an eddy current rotating probe test for cracking of the fastener holes 
and an HFEC inspection for cracks in the upper shell

[[Page 73094]]

of the fuselage (and including checks of the fastener position for 
clearance and applicable corrective actions (e.g., repair and rework)), 
and a modification of the airplane upper shell structure of the 
fuselage between FR80 and FR86.
     Airbus Service Bulletin A330-53-3168, Revision 02, dated 
December 21, 2011, describes procedures for a HFEC inspection for 
cracking of the upper shell structure of the fuselage between FR80 and 
FR86.
     Airbus Service Bulletin A340-53-4165, Revision 02, dated 
March 29, 2010, describes procedures for a modification of the 
fuselage, which includes inspections (e.g., eddy current rotating probe 
test of fastener holes for cracking, HFEC inspections for cracking of 
the upper shell structure of the fuselage, and checks of the fastener 
position for clearance) and applicable corrective actions (e.g., repair 
and rework).
     Airbus Service Bulletin A340-53-4172, Revision 01, dated 
July 8, 2009, describes procedures for inspections (e.g., rototest 
inspections of fastener holes for cracking, HFEC inspections for 
cracking of the upper shell structure of the fuselage, and checks of 
the fastener position for clearance) and modification of the airplane 
upper shell structure between FR80 and FR86 (including applicable 
corrective actions (e.g., repair and rework).
     Airbus Service Bulletin A340-53-4174, Revision 02, dated 
December 21, 2011, describes procedures for a HFEC inspection for 
cracking of the upper shell structure of the fuselage between FR80 and 
FR86.
    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 of this 
AD.

Costs of Compliance

    We estimate that this AD affects 26 airplanes of U.S. registry. We 
also estimate that it will take about 208 work-hours per product to 
comply with the basic requirements (inspection and modification) of 
this AD. The average labor rate is $85 per work-hour. Required parts 
will cost about $28,360 per product. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $1,197,040, or 
$46,040 per product.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0490; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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) 
2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and 
adding the following new AD:

2015-23-06 Airbus: Amendment 39-18322. Docket No. FAA-2015-0490; 
Directorate Identifier 2014-NM-018-AD.

(a) Effective Date

    This AD becomes effective December 29, 2015.

(b) Affected ADs

    This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747, 
November 12, 2008).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-311, -312, and -313 airplanes; 
certificated in any category; all manufacturer serial numbers on 
which Airbus Modification 44205 has been embodied in production, 
except those on which Airbus Modification 52974 or 53223 has been 
embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by the results of a fatigue and damage 
tolerance evaluation that concluded existing compliance times must 
be reduced. We are issuing this AD to prevent fatigue cracking of 
the upper shell structure of the fuselage, which could result in 
reduced structural integrity of the airplane.

(f) Compliance

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

[[Page 73095]]

(g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except 
Model A340-300 Weight Variant (WV) 027 Airplanes

    For Model A330-300 and A340-300 airplanes, except Model A340-300 
WV 027 airplanes: At the applicable time specified in paragraph 
(g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) 
inspection for cracking of the upper shell structure between frame 
(FR) 80 and FR86, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 
21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, 
dated December 21, 2011; as applicable. Repeat the inspection 
thereafter at the applicable time specified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable.
    (1) For airplanes that, as of the effective date of this AD, 
have not been inspected in accordance with Airbus Service Bulletin 
A330-53-3168; or Airbus Service Bulletin A340-53-4174; as 
applicable: Inspect at the later of the times specified in 
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Before reaching the applicable threshold specified in 
paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-
3168, Revision 02, dated December 21, 2011; or Airbus Service 
Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as 
applicable for airplane model, configuration, and utilization, since 
the airplane's first flight.
    (ii) Within the threshold defined in paragraph 1.E, 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
01, dated February 15, 2008; or Airbus Service Bulletin A340-53-
4174, Revision 01, dated February 15, 2008; as applicable for 
airplane model, configuration, and utilization since the airplane's 
first flight; or within 12 months after the effective date of this 
AD; whichever occurs first.
    (2) For airplanes that, as of the effective date of this AD, 
have been inspected in accordance with Airbus Service Bulletin A330-
53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: 
Inspect at the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD.
    (i) Within the applicable interval specified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable; to be 
counted from the last inspection.
    (ii) Within 12 months after the effective date of this AD 
without exceeding the intervals defined in paragraph 1.E, 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
01, dated February 15, 2008; or Airbus Service Bulletin A340-53-
4174, Revision 01, dated February 15, 2008; as applicable for 
airplane model, configuration, and utilization to be counted from 
the last inspection.

(h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes, 
Except Model A340-300 WV 027 Airplanes

    If any crack is detected during any HFEC inspection required by 
the introductory text to paragraph (g) of this AD: Before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). Accomplishment of a repair for a 
specific area, as required by this paragraph, is terminating action 
for the repetitive HFEC inspections required by the introductory 
text to paragraph (g) of this AD, as applicable, for that specific 
repaired area only. The need and definition of subsequent repetitive 
inspections (if any) for that specific repaired area will be defined 
in the applicable repair method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) or Airbus's EASA 
Design Organization Approval (DOA).

(i) Optional Terminating Action

    For Airbus Model A330-300 and A340-300 airplanes, except Model 
A340-300 WV 027 airplanes: Modification, which includes inspections 
and applicable corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, 
Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-
53-4165, Revision 02, dated March 29, 2010; as applicable; 
terminates the repetitive HFEC inspections required by the 
introductory text to paragraph (g) of this AD, except where Airbus 
Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or 
Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 
2010; as applicable; specifies to contact the manufacturer, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA.

(j) Inspection and Modification for Airbus Model A330-200 Airplanes

    Within the compliance times specified in paragraph (j)(1) or 
(j)(2) of this AD, whichever occurs later: Do all applicable 
actions, including an eddy current rotating probe test and an HFEC 
inspection for cracks, and modify the airplane upper shell structure 
between FR80 and FR86; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, 
dated January 6, 2012.
    (1) Within the compliance times identified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 
03, dated January 6, 2012, as applicable for airplane configuration 
and utilization since the airplane's first flight.
    (2) Within 12 months after the effective date of this AD without 
exceeding the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of 
Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 
2010, since the airplane's first flight.

(k) Inspection and Modification for Airbus Model A340-300 Airplanes, 
Only WV 027

    For Model A340-300 airplanes, WV 027 only: Before the 
accumulation of 14,200 total flight cycles from the airplane's first 
flight, do all applicable inspections and modify the airplane upper 
shell structure between FR80 and FR86; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, 
Revision 01, dated July 8, 2009.

(l) Corrective Action for Airbus Model A330-200 Airplanes; and Model 
A340-300 Airplanes, only WV 027

    If any crack is detected during the inspection required by the 
introductory text to paragraph (j) of this AD, or paragraph (k) of 
this AD, before further flight, repair using a method approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA; concurrently with 
modification required by paragraph the introductory text to 
paragraph (j) of this AD, or paragraph (k) of this AD.

(m) Definition of ``Threshold'' and ``Interval''

    (1) For the purposes of this AD, the term ``Threshold,'' as used 
in paragraph 1.E., ``COMPLIANCE,'' of the service information 
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD 
means the total flight cycles or flight hours accumulated since the 
airplane's first flight.
    (2) For the purposes of this AD, the term ``Interval'' as used 
in paragraph 1.E., ``COMPLIANCE,'' of the service information 
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD 
means the total flight cycles or flight hours accumulated since the 
last inspection, as applicable.
    (i) Airbus Service Bulletin A330-53-3168, dated September 19, 
2007.
    (ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated 
February 15, 2008.
    (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated 
December 21, 2011.
    (iv) Airbus Service Bulletin A340-53-4174, dated September 19, 
2007.
    (v) Airbus Service Bulletin A340-53-4174, Revision 01, dated 
February 15, 2008.
    (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated 
December 21, 2011.

(n) Credit for Previous Actions

    (1) For Model A330-300 and A340-300 airplanes, except Model 
A340-300 WV 027 airplanes: This paragraph provides credit for the 
modification specified in paragraph (i) of this AD, if those actions 
were performed before the effective date of this AD using the 
service information identified in paragraph (n)(1)(i), (n)(1)(ii), 
(n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service 
information is not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A330-53-3159, dated September 19, 
2007.
    (ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated 
June 15, 2009.
    (iii) Airbus Service Bulletin A340-53-4165, dated September 19, 
2007.
    (iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated 
June 17, 2009.
    (2) For Model A330-200 airplanes: This paragraph provides credit 
for the inspection

[[Page 73096]]

and modification required by the introductory text to paragraph (j) 
of this AD, if those actions were performed before the effective 
date of this AD using the service information identified in 
paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as 
applicable.
    (i) Airbus Service Bulletin A330-53-3160, dated July 9, 2007, 
which was incorporated by reference in AD 2008-22-20, Amendment 39-
15717 (73 FR 66747, November 12, 2008).
    (ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated 
April 28, 2009, which is not incorporated by reference in this AD.
    (iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated 
March 29, 2010, which is not incorporated by reference in this AD.
    (3) For Model A340-300 airplanes, WV 027 only: This paragraph 
provides credit for the inspection and modification required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A340-53-
4172, dated July 10, 2007, which is was incorporated by reference in 
AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008).

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. 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. The 
AMOC approval letter must specifically reference this AD.
    (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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0012R1, dated January 24, 
2014, 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-2015-0490.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 
December 29, 2015.
    (i) Airbus Service Bulletin A330-53-3159, Revision 02, dated 
March 29, 2010.
    (ii) Airbus Service Bulletin A330-53-3160, Revision 03, dated 
January 6, 2012.
    (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated 
December 21, 2011.
    (iv) Airbus Service Bulletin A340-53-4165, Revision 02, dated 
March 29, 2010.
    (v) Airbus Service Bulletin A340-53-4172, Revision 01, dated 
July 8, 2009.
    (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated 
December 21, 2011.
    (4) The following service information was approved for IBR on 
December 17, 2008 (73 FR 66747, November 12, 2008).
    (i) Airbus Service Bulletin A330-53-3168, Revision 01, dated 
February 15, 2008.
    (ii) Airbus Service Bulletin A340-53-4174, Revision 01, dated 
February 15, 2008.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 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/ibr-locations.html.

    Issued in Renton, Washington, on October 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-28886 Filed 11-23-15; 8:45 am]
 BILLING CODE 4910-13-P