Airworthiness Directives; Airbus Airplanes, 72569-72573 [2015-28895]

Download as PDF Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(5) and (o)(6) of this AD. DEPARTMENT OF TRANSPORTATION (o) 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 the AD specifies otherwise. (3) The following service information was approved for IBR on December 28, 2015. (i) Lockheed Service Bulletin 382–57–85 (82–790), Revision 3, dated July 8, 2013, including Appendix A, Revision 3, dated July 8, 2013, and Appendixes B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. (ii) Reserved. (4) The following service information was approved for IBR on June 22, 2011 (76 FR 28626, May 18, 2011). (i) Lockheed Service Bulletin 382–57–85 (82–790), Revision 2, dated August 23, 2007, including Appendixes A, B, C, D, E, F, and G, all Revision 1, all dated March 8, 2007. (ii) Reserved. (5) For Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company service information identified in this AD, contact Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494– 5444; fax 770–494–5445; email ams.portal@ lmco.com; Internet http:// www.lockheedmartin.com/ams/tools/ TechPubs.html. (6) 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. (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–2014–1043; Directorate Identifier 2013–NM–079–AD; Amendment 39–18321; AD 2015–23–05] Federal Aviation Administration Issued in Renton, Washington, on October 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–28464 Filed 11–19–15; 8:45 am] tkelley on DSK3SPTVN1PROD with RULES BILLING CODE 4910–13–P VerDate Sep<11>2014 17:28 Nov 19, 2015 Jkt 238001 RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. DATES: This AD becomes effective December 28, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 28, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-1043 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 SUMMARY: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 72569 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–2014– 1043. 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 by adding an AD that would apply to all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3510). The NPRM was prompted by reports of cracked support strut body ends at a certain frame location of the THS. The NPRM proposed to require repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0068, dated March 18, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. The MCAI states: During scheduled maintenance on A330 aeroplanes, several Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 91 were found cracked at strut body ends. The THS is supported and articulated at FR 91 by four struts to fix the hinges (Y-bolts) and keep the structural integrity in lateral direction. Analysis revealed that cracks can reduce ability of the support struts to carry specified tension loads. This condition, if not detected and corrected, could lead to the loss of all four E:\FR\FM\20NOR1.SGM 20NOR1 tkelley on DSK3SPTVN1PROD with RULES 72570 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations THS support struts at FR91, which would make the remaining structure unable to carry limit loads, resulting in the loss of Horizontal Tail Plane. A340–500/600 aeroplanes are not affected by this [EASA] AD as different material is used on THS support struts. To address this potentially unsafe condition, EASA issued AD 2013–0076 [http://ad.easa.europa.eu/blob/easa_ad_ 2013_0076_superseded.pdf/AD_2013-0076_ 1] to require repetitive special detailed inspections [high frequency eddy current (HFEC) inspections for cracking] of all 8 strut ends of the THS support located at FR91 in the tail cone and, depending on findings, replacement of THS support struts. That [EASA] AD also required, for aeroplanes on which Airbus Modification 203493 had not been embodied in production, or Airbus Service Bulletin (SB) A330–53–3204 or SB A340–53–4199, as applicable, has not been embodied in service, the installation of a clamping device on each support strut end to stop growth of possible cracks (crack stopper function) in order to secure integrity of the struts. Since issuance of EASA AD 2013–0076 [http://ad.easa.europa.eu/blob/easa_ad_ 2013_0076_superseded.pdf/AD_2013-0076_ 1], it has been discovered that several aeroplanes are fitted with another strut ´ configuration (SARMA Strut) [Societe ´ Anonyme de Recherche Mecanique ´ Appliquee] than the TAC (Technical Airborne Components Industries) strut, which caused the other strut not to be considered. Consequently, Airbus revised Airbus SB A330–53–3206 and SB A340–53– 4208, accordingly in order to add a one-time [HFEC] inspection [for cracking] for SARMA struts and in case of finding to replace it with a TAC strut and thereafter to accomplish repetitive inspections and EASA issued AD 2013–0219 [http://ad.easa.europa.eu/blob/ easa_ad_2013_0219_superseded.pdf/AD_ 2013-0219_1], which is superseded, and required accomplishment of the instructions as specified in the latest revision of each SB, as applicable. Since issuance of EASA AD 2013–0219 [http://ad.easa.europa.eu/blob/easa_ad_ 2013_0219_superseded.pdf/AD_2013-0219_ 1], based on the reporting received from operators, it has been determined that repetitive inspections are also to be accomplished for aeroplanes equipped with SARMA strut. Airbus introduced that inspection in the applicable SB at revision 3. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2013–0219, which is superseded, and requires accomplishment of repetitive [HFEC] inspective inspection [for cracking] for aeroplanes equipped with SARMA strut. This [EASA] AD is considered as an interim action, pending the development of a terminating action. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-10430002. VerDate Sep<11>2014 17:28 Nov 19, 2015 Jkt 238001 Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 3510, January 23, 2015) and the FAA’s response to each comment. Request To Add Inspection for Identifying Struts Delta Air Lines, Inc. (DAL) requested that we add a physical inspection to paragraph (g) of the proposed AD (80 FR 3510, January 23, 2015) to distinguish a ´ Societe Anonyme de Recherche ´ ´ Mecanique Appliquee (SARMA) strut from a Technical Airborne Components Industries (TAC) strut. DAL stated that paragraph (g) of the proposed AD only identifies the dimensional diameter of SARMA struts; however, DAL stated that both TAC and SARMA struts have the same manufacturer part numbers but have different rod end diameters. DAL suggested language for doing a physical inspection of the strut end of each support strut for identification purposes. We agree that a physical inspection is necessary to determine the rod end diameter in order to distinguish between SARMA and TAC struts. However, that inspection is optional. Paragraph (g) of this AD defines SARMA struts as having a diameter that is less than 43 millimeters, and states that all other struts are TAC struts. Paragraph (h) of this AD requires inspecting TAC struts. Thus, operators must inspect all struts unless the strut is inspected to determine the diameter is less than 43 millimeters, i.e., it is a SARMA strut. We have not changed this AD in this regard. Request To Include Airbus Modification 203834 for Installing Reinforced Clamps DAL requested that we revise paragraph (h) of the proposed AD (80 FR 3510, January 23, 2015) to include Airbus Modification 203834 as an optional modification for installation of the reinforced clamps. DAL stated that Airbus has confirmed that Airbus Modification 203834 installs the same reinforced clamps as Airbus Modification 203493 specified in paragraph (h) of the proposed AD. We agree with the commenter’s request. The FAA has approved two Airbus modifications for installing the reinforced clamps into production airplanes: Modification 203493 for airplanes having manufacturer serial number (MSN) 1466 to 1509 inclusive, and Modification 203834 for airplanes having MSN 1510 and on. Modification PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 203834 supersedes Modification 203493, and the first airplane delivered with Modification 203834 installed was MSN 1511. Thus, operators may have the two populations of airplanes: Those with Modification 203834 and those with Modification 203493. This AD must address both groups of airplanes accordingly. We have revised paragraph (h) of this AD to specify that, for airplanes on which Airbus Modification 203493 or 203834 has been embodied in production; or on which Airbus Service Bulletin A330–53–3204 or Airbus Service Bulletin A340 53–4199, as applicable; has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by paragraph (h) of this AD. Request To Include Additional Service Information DAL requested that we revise paragraphs (j)(1), (j)(2), and (l) of the proposed AD (80 FR 3510, January 23, 2015) to include Airbus Service Bulletin A330–53–3204. DAL stated that, when clamps were not previously installed, Airbus Service Bulletin A330–53–3204 becomes the source document for installing the clamps. We agree that Airbus Service Bulletin A330–53–3204, Revision 03, dated February 28, 2014, is an appropriate source of service information for installing clamps. However, we do not agree to revise this AD because that service information is already referenced in Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014, which is referred to as one of the appropriate sources of service information for the actions required by paragraphs (j)(1), (j)(2), and (l) of this AD. As specified in the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014., ‘‘if no clamps were previously installed, accomplish Service Bulletin A330–53– 3204 before next flight, to install them.’’ Therefore, no change to this AD is necessary in this regard. Request To Clarify Flight With Cracking DAL requested that we clarify/ confirm that the NPRM (80 FR 3510, January 23, 2015) will apply more strict replacement criteria when cracks are found than what is currently published in Airbus Service Bulletin A330–53– 3206, Revision 03, dated February 28, 2014. DAL stated that Subtask 533206– 280–201–001 of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014, contains instructions E:\FR\FM\20NOR1.SGM 20NOR1 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations to allow continued operation of the airplane with small crack findings without immediate strut replacement. We agree. In the ‘‘Differences Between this Proposed AD and the MCAI or Service Information’’ section of the NPRM (80 FR 3510, January 23, 2015), we stated that ‘‘Although EASA Airworthiness Directive 2014–0068, dated March 18, 2014, Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014, and Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014, allow further flight after certain cracks are found during compliance with the proposed action, paragraph (j)(2) of this AD would require that any cracked THS support strut be replaced with a new or serviceable TAC strut before further flight.’’ No change to this AD is necessary in this regard. 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 (80 FR 3510, January 23, 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 3510, January 23, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. tkelley on DSK3SPTVN1PROD with RULES Interim Action We consider this AD interim action. If final action is later identified, we might consider further rulemaking then. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. • Airbus Service Bulletin A330–53– 3206, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone. • Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means VerDate Sep<11>2014 17:28 Nov 19, 2015 Jkt 238001 identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 84 airplanes of U.S. registry. We also estimate that it will take about 9 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $64,260, or $765 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition replacement specified in this AD. We estimate that any necessary follow-on strut reinforcements will take about 2 work-hours and require parts costing $5,680, for a cost of $5,850 per product. We have no way of determining the number of aircraft that might need this action. 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. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 72571 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/#!docket Detail;D=FAA-2014-1043; 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 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 adding the following new airworthiness directive (AD): ■ 2015–23–05 Airbus: Amendment 39–18321. Docket No. FAA–2014–1043; Directorate Identifier 2013–NM–079–AD. (a) Effective Date This AD becomes effective December 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A330–201, –202, –203, –223, –223F, –243, and –243F airplanes. E:\FR\FM\20NOR1.SGM 20NOR1 72572 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations (3) For Model A330 series airplanes having manufacturer serial numbers 423 and subsequent, and Model A340 series airplanes having manufacturer serial numbers 450 through 955 inclusive: Within 36 months after the effective date of this AD or since the first flight of the airplane, whichever occurs later. (2) Airbus Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (3) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts and which would make the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Strut Types ´ For the purpose of this AD, a Societe ´ Anonyme de Recherche Mecanique ´ Appliquee (SARMA) strut is a strut on which the diameter of the strut end is less than 43 millimeters. All other struts are Technical Airborne Components Industries (TAC) struts. tkelley on DSK3SPTVN1PROD with RULES (h) Repetitive Inspections of TAC Strut Ends At the applicable time specified in paragraph (i) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of all TAC strut ends of the THS support located at frame (FR) 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 42 months or 20,000 flight hours, whichever occurs first. For airplanes on which Airbus Modification 203493 or 203834 has been embodied in production, or Airbus Service Bulletin A330–53–3204 or Airbus Service Bulletin A340–53–4199, as applicable, has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by this paragraph. (i) Compliance Times for the Actions Required by Paragraphs (h) and (k) of This AD Do the inspections required by paragraphs (h) and (k) of this AD at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) For Model A330 series airplanes having manufacturer serial numbers 012 through 209 inclusive, and Model A340 series airplanes having manufacturer serial numbers 002 through 210 inclusive: Within 6 months after the effective date of this AD. (2) For Model A330 series airplanes having manufacturer serial numbers 211 through 422 inclusive, and Model A340 series airplanes having manufacturer serial numbers 212 through 447 inclusive: Within 24 months after the effective date of this AD. VerDate Sep<11>2014 17:28 Nov 19, 2015 Jkt 238001 (j) Corrective Action for TAC Strut Ends and Installation of Reinforcing Clamps (1) If, during any inspection required by paragraph (h) of this AD, no cracks are found: Before further flight, reinstall or install, as applicable, reinforcing clamps on the strut ends, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014; as applicable. (2) If, during any inspection required by paragraph (h) of this AD, any crack is found: Before further flight, replace any affected strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014; as applicable. (k) Repetitive Inspections of SARMA Strut Ends At the applicable time specified in paragraph (i) of this AD, do an HFEC inspection for cracking of all SARMA strut ends of the THS support located at FR 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 12 months. (l) Corrective Action for SARMA Strut Ends If any crack is found on a strut end during the inspection required by paragraph (k) of this AD: Before further flight, replace any affected SARMA strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014; as applicable. (m) No Terminating Action Replacement of THS struts on an airplane does not constitute terminating action for the repetitive inspections required by this AD. (n) No Reporting Although Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014; and Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014; specify to submit certain information to the manufacturer, this AD does not include that requirement. (o) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (h), (j), and (k) of PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (n)(1) through (n)(6) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–53–3206, dated February 7, 2013. (2) Airbus Service Bulletin A330–53–3206, Revision 01, dated June 10, 2013. (3) Airbus Service Bulletin A330–53–3206, Revision 02, dated August 8, 2013. (4) Airbus Service Bulletin A340–53–4208, dated February 7, 2013. (5) Airbus Service Bulletin A340–53–4208, Revision 01, dated June 10, 2013. (6) Airbus Service Bulletin A340–53–4208, Revision 02, dated August 8, 2013. (p) 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: 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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0068, dated March 18, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-1043-0002. (2) 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. E:\FR\FM\20NOR1.SGM 20NOR1 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations (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 A330–53–3206, Revision 03, dated February 28, 2014. (ii) Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014. (3) 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on October 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–28895 Filed 11–19–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1266; Directorate Identifier 2014–NM–151–AD; Amendment 39–18327; AD 2015–23–11] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage skin lap joints are subject to widespread fatigue damage (WFD). This AD requires repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which tkelley on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 17:28 Nov 19, 2015 Jkt 238001 could result in rapid depressurization of the airplane. DATES: This AD is effective December 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 28, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.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– 1266. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1266; 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 (phone: 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on May 5, 2015 (80 FR 25630). The NPRM was prompted by an evaluation by the DAH indicating that certain fuselage PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 72573 skin lap joints are subject to WFD. The NPRM proposed to require repetitive post-modification inspections for cracking of the skin or internal doubler along the edge fastener rows of the modification, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in certain fuselage skin lap joints, which could result in rapid depressurization of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 25630, May 5, 2015) and the FAA’s response to each comment. Request To Remove Warranty Statement Boeing requested that we remove the statement that ‘‘some of the costs of this proposed AD may be covered under warranty’’ in the Costs of Compliance section of the NPRM (80 FR 25630, May 5, 2015). Boeing stated that the actions in the NPRM are not covered by warranty. We agree with the commenter’s request. We have revised the Costs of Compliance section of this final rule accordingly. Request To Revise Paragraph Headings Boeing requested that we revise the headings of paragraphs (g), (h), (j), and (k) of the proposed AD (80 FR 25630, May 5, 2015) by removing reference to the inspections as ‘‘repetitive’’ or ‘‘initial.’’ Boeing stated that these revisions will provide consistency among paragraph headings because paragraphs (g), (j), and (k) of the proposed AD do not have an initial inspection program, yet paragraph (h) of the proposed AD has only an initial inspection. We acknowledge the commenter’s concern and agree to clarify the headings. We do not presume that the term ‘‘repetitive’’ necessarily excludes the initial action. An action cannot be repeated without accomplishment of the initial action. In addition, in many ADs we use the term ‘‘repetitive’’ actions for paragraphs that include the initial action and repetitive actions. Paragraphs (g), (j), and (k) of this AD include both a sentence specifying the initial inspection and a sentence specifying the repetitive inspections. We have not changed this AD in this regard. Request To Clarify Compliance Time Boeing requested that we clarify the compliance time in paragraphs (g), (h), (j), and (k) of the proposed AD (80 FR E:\FR\FM\20NOR1.SGM 20NOR1

Agencies

[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)]
[Rules and Regulations]
[Pages 72569-72573]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-28895]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-AD; 
Amendment 39-18321; AD 2015-23-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Model A340-200 and A340-300 series airplanes. This AD 
was prompted by reports of cracked support strut body ends at a certain 
frame location of the trimmable horizontal stabilizer (THS). This AD 
requires repetitive inspections for cracking of the strut ends of the 
THS support located at a certain frame in the tail cone, and 
replacement if necessary; and reinstallation or installation of 
reinforcing clamps on certain strut ends. We are issuing this AD to 
detect and correct cracked support strut body ends of the THS, which 
could lead to the loss of all four THS support struts, making the 
remaining structure unable to carry limit loads, resulting in the loss 
of the horizontal tail plane.

DATES: This AD becomes effective December 28, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 28, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-1043 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-2014-
1043.

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 by adding an AD that would apply to all Airbus Model A330-200, 
A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 
and A340-300 series airplanes. The NPRM published in the Federal 
Register on January 23, 2015 (80 FR 3510). The NPRM was prompted by 
reports of cracked support strut body ends at a certain frame location 
of the THS. The NPRM proposed to require repetitive inspections for 
cracking of the strut ends of the THS support located at a certain 
frame in the tail cone, and replacement if necessary; and 
reinstallation or installation of reinforcing clamps on certain strut 
ends. We are issuing this AD to detect and correct cracked support 
strut body ends of the THS, which could lead to the loss of all four 
THS support struts, making the remaining structure unable to carry 
limit loads, resulting in the loss of the horizontal tail plane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0068, dated March 18, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model 
A340-200 and A340-300 series airplanes. The MCAI states:

    During scheduled maintenance on A330 aeroplanes, several 
Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 
91 were found cracked at strut body ends.
    The THS is supported and articulated at FR 91 by four struts to 
fix the hinges (Y-bolts) and keep the structural integrity in 
lateral direction.
    Analysis revealed that cracks can reduce ability of the support 
struts to carry specified tension loads.
    This condition, if not detected and corrected, could lead to the 
loss of all four

[[Page 72570]]

THS support struts at FR91, which would make the remaining structure 
unable to carry limit loads, resulting in the loss of Horizontal 
Tail Plane.
    A340-500/600 aeroplanes are not affected by this [EASA] AD as 
different material is used on THS support struts.
    To address this potentially unsafe condition, EASA issued AD 
2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD_2013-0076_1] to require 
repetitive special detailed inspections [high frequency eddy current 
(HFEC) inspections for cracking] of all 8 strut ends of the THS 
support located at FR91 in the tail cone and, depending on findings, 
replacement of THS support struts. That [EASA] AD also required, for 
aeroplanes on which Airbus Modification 203493 had not been embodied 
in production, or Airbus Service Bulletin (SB) A330-53-3204 or SB 
A340-53-4199, as applicable, has not been embodied in service, the 
installation of a clamping device on each support strut end to stop 
growth of possible cracks (crack stopper function) in order to 
secure integrity of the struts.
    Since issuance of EASA AD 2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD_2013-0076_1], it has been 
discovered that several aeroplanes are fitted with another strut 
configuration (SARMA Strut) [Societ[eacute] Anonyme de Recherche 
M[eacute]canique Appliqu[eacute]e] than the TAC (Technical Airborne 
Components Industries) strut, which caused the other strut not to be 
considered. Consequently, Airbus revised Airbus SB A330-53-3206 and 
SB A340-53-4208, accordingly in order to add a one-time [HFEC] 
inspection [for cracking] for SARMA struts and in case of finding to 
replace it with a TAC strut and thereafter to accomplish repetitive 
inspections and EASA issued AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD_2013-0219_1], which is 
superseded, and required accomplishment of the instructions as 
specified in the latest revision of each SB, as applicable.
    Since issuance of EASA AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD_2013-0219_1], based on the 
reporting received from operators, it has been determined that 
repetitive inspections are also to be accomplished for aeroplanes 
equipped with SARMA strut. Airbus introduced that inspection in the 
applicable SB at revision 3.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0219, which is superseded, and requires 
accomplishment of repetitive [HFEC] inspective inspection [for 
cracking] for aeroplanes equipped with SARMA strut.
    This [EASA] AD is considered as an interim action, pending the 
development of a terminating action.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1043-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 3510, January 23, 2015) and the FAA's response to each comment.

Request To Add Inspection for Identifying Struts

    Delta Air Lines, Inc. (DAL) requested that we add a physical 
inspection to paragraph (g) of the proposed AD (80 FR 3510, January 23, 
2015) to distinguish a Societ[eacute] Anonyme de Recherche 
M[eacute]canique Appliqu[eacute]e (SARMA) strut from a Technical 
Airborne Components Industries (TAC) strut. DAL stated that paragraph 
(g) of the proposed AD only identifies the dimensional diameter of 
SARMA struts; however, DAL stated that both TAC and SARMA struts have 
the same manufacturer part numbers but have different rod end 
diameters. DAL suggested language for doing a physical inspection of 
the strut end of each support strut for identification purposes.
    We agree that a physical inspection is necessary to determine the 
rod end diameter in order to distinguish between SARMA and TAC struts. 
However, that inspection is optional. Paragraph (g) of this AD defines 
SARMA struts as having a diameter that is less than 43 millimeters, and 
states that all other struts are TAC struts. Paragraph (h) of this AD 
requires inspecting TAC struts. Thus, operators must inspect all struts 
unless the strut is inspected to determine the diameter is less than 43 
millimeters, i.e., it is a SARMA strut. We have not changed this AD in 
this regard.

Request To Include Airbus Modification 203834 for Installing Reinforced 
Clamps

    DAL requested that we revise paragraph (h) of the proposed AD (80 
FR 3510, January 23, 2015) to include Airbus Modification 203834 as an 
optional modification for installation of the reinforced clamps. DAL 
stated that Airbus has confirmed that Airbus Modification 203834 
installs the same reinforced clamps as Airbus Modification 203493 
specified in paragraph (h) of the proposed AD.
    We agree with the commenter's request. The FAA has approved two 
Airbus modifications for installing the reinforced clamps into 
production airplanes: Modification 203493 for airplanes having 
manufacturer serial number (MSN) 1466 to 1509 inclusive, and 
Modification 203834 for airplanes having MSN 1510 and on. Modification 
203834 supersedes Modification 203493, and the first airplane delivered 
with Modification 203834 installed was MSN 1511.
    Thus, operators may have the two populations of airplanes: Those 
with Modification 203834 and those with Modification 203493. This AD 
must address both groups of airplanes accordingly. We have revised 
paragraph (h) of this AD to specify that, for airplanes on which Airbus 
Modification 203493 or 203834 has been embodied in production; or on 
which Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin 
A340 53-4199, as applicable; has been embodied in service, remove the 
clamp from each strut end before accomplishing the inspections required 
by paragraph (h) of this AD.

Request To Include Additional Service Information

    DAL requested that we revise paragraphs (j)(1), (j)(2), and (l) of 
the proposed AD (80 FR 3510, January 23, 2015) to include Airbus 
Service Bulletin A330-53-3204. DAL stated that, when clamps were not 
previously installed, Airbus Service Bulletin A330-53-3204 becomes the 
source document for installing the clamps.
    We agree that Airbus Service Bulletin A330-53-3204, Revision 03, 
dated February 28, 2014, is an appropriate source of service 
information for installing clamps. However, we do not agree to revise 
this AD because that service information is already referenced in 
Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 
2014, which is referred to as one of the appropriate sources of service 
information for the actions required by paragraphs (j)(1), (j)(2), and 
(l) of this AD. As specified in the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 
2014., ``if no clamps were previously installed, accomplish Service 
Bulletin A330-53-3204 before next flight, to install them.'' Therefore, 
no change to this AD is necessary in this regard.

Request To Clarify Flight With Cracking

    DAL requested that we clarify/confirm that the NPRM (80 FR 3510, 
January 23, 2015) will apply more strict replacement criteria when 
cracks are found than what is currently published in Airbus Service 
Bulletin A330-53-3206, Revision 03, dated February 28, 2014. DAL stated 
that Subtask 533206-280-201-001 of Airbus Service Bulletin A330-53-
3206, Revision 03, dated February 28, 2014, contains instructions

[[Page 72571]]

to allow continued operation of the airplane with small crack findings 
without immediate strut replacement.
    We agree. In the ``Differences Between this Proposed AD and the 
MCAI or Service Information'' section of the NPRM (80 FR 3510, January 
23, 2015), we stated that ``Although EASA Airworthiness Directive 2014-
0068, dated March 18, 2014, Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014, and Airbus Service Bulletin A340-
53-4208, Revision 03, dated February 28, 2014, allow further flight 
after certain cracks are found during compliance with the proposed 
action, paragraph (j)(2) of this AD would require that any cracked THS 
support strut be replaced with a new or serviceable TAC strut before 
further flight.'' No change to this AD is necessary in this regard.

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 (80 FR 3510, January 23, 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 3510, January 23, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Airbus Service Bulletin A330-53-3206, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone.
     Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone.
    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 84 airplanes of U.S. registry.
    We also estimate that it will take about 9 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $64,260, or $765 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition replacement specified in this AD.
    We estimate that any necessary follow-on strut reinforcements will 
take about 2 work-hours and require parts costing $5,680, for a cost of 
$5,850 per product. We have no way of determining the number of 
aircraft that might need this action.
    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-2014-1043; 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 adding the following new airworthiness 
directive (AD):

2015-23-05 Airbus: Amendment 39-18321. Docket No. FAA-2014-1043; 
Directorate Identifier 2013-NM-079-AD.

(a) Effective Date

    This AD becomes effective December 28, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and -
243F airplanes.

[[Page 72572]]

    (2) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
    (3) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracked support strut body 
ends at a certain frame location of the trimmable horizontal 
stabilizer (THS). We are issuing this AD to detect and correct 
cracked support strut body ends of the THS, which could lead to the 
loss of all four THS support struts and which would make the 
remaining structure unable to carry limit loads, resulting in the 
loss of the horizontal tail plane.

(f) Compliance

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

(g) Definition of Strut Types

    For the purpose of this AD, a Societ[eacute] Anonyme de 
Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut is a strut 
on which the diameter of the strut end is less than 43 millimeters. 
All other struts are Technical Airborne Components Industries (TAC) 
struts.

(h) Repetitive Inspections of TAC Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
a high frequency eddy current (HFEC) inspection for cracking of all 
TAC strut ends of the THS support located at frame (FR) 91 in the 
tail cone, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3206, Revision 03, dated February 
28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, 
dated February 28, 2014; as applicable. Repeat the inspection 
thereafter at intervals not to exceed 42 months or 20,000 flight 
hours, whichever occurs first. For airplanes on which Airbus 
Modification 203493 or 203834 has been embodied in production, or 
Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin 
A340-53-4199, as applicable, has been embodied in service, remove 
the clamp from each strut end before accomplishing the inspections 
required by this paragraph.

(i) Compliance Times for the Actions Required by Paragraphs (h) and (k) 
of This AD

    Do the inspections required by paragraphs (h) and (k) of this AD 
at the applicable times specified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD.
    (1) For Model A330 series airplanes having manufacturer serial 
numbers 012 through 209 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 002 through 210 inclusive: Within 
6 months after the effective date of this AD.
    (2) For Model A330 series airplanes having manufacturer serial 
numbers 211 through 422 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 212 through 447 inclusive: Within 
24 months after the effective date of this AD.
    (3) For Model A330 series airplanes having manufacturer serial 
numbers 423 and subsequent, and Model A340 series airplanes having 
manufacturer serial numbers 450 through 955 inclusive: Within 36 
months after the effective date of this AD or since the first flight 
of the airplane, whichever occurs later.

(j) Corrective Action for TAC Strut Ends and Installation of 
Reinforcing Clamps

    (1) If, during any inspection required by paragraph (h) of this 
AD, no cracks are found: Before further flight, reinstall or 
install, as applicable, reinforcing clamps on the strut ends, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or 
Airbus Service Bulletin A340-53-4208, Revision 03, dated February 
28, 2014; as applicable.
    (2) If, during any inspection required by paragraph (h) of this 
AD, any crack is found: Before further flight, replace any affected 
strut with a new or serviceable TAC strut and install reinforcing 
clamps on the strut end, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014; as applicable.

(k) Repetitive Inspections of SARMA Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
an HFEC inspection for cracking of all SARMA strut ends of the THS 
support located at FR 91 in the tail cone, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 12 
months.

(l) Corrective Action for SARMA Strut Ends

    If any crack is found on a strut end during the inspection 
required by paragraph (k) of this AD: Before further flight, replace 
any affected SARMA strut with a new or serviceable TAC strut and 
install reinforcing clamps on the strut end, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable.

(m) No Terminating Action

    Replacement of THS struts on an airplane does not constitute 
terminating action for the repetitive inspections required by this 
AD.

(n) No Reporting

    Although Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014; and Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014; specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(o) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), (j), and (k) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information identified in paragraphs (n)(1) through (n)(6) 
of this AD. This service information is not incorporated by 
reference in this AD.
    (1) Airbus Service Bulletin A330-53-3206, dated February 7, 
2013.
    (2) Airbus Service Bulletin A330-53-3206, Revision 01, dated 
June 10, 2013.
    (3) Airbus Service Bulletin A330-53-3206, Revision 02, dated 
August 8, 2013.
    (4) Airbus Service Bulletin A340-53-4208, dated February 7, 
2013.
    (5) Airbus Service Bulletin A340-53-4208, Revision 01, dated 
June 10, 2013.
    (6) Airbus Service Bulletin A340-53-4208, Revision 02, dated 
August 8, 2013.

(p) 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: 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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0068, dated March 18, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-1043-0002.
    (2) 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.

[[Page 72573]]

    (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 A330-53-3206, Revision 03, dated 
February 28, 2014.
    (ii) Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014.
    (3) 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.
    (4) 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.
    (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 October 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-28895 Filed 11-19-15; 8:45 am]
 BILLING CODE 4910-13-P