Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 19013-19017 [2015-06785]

Download as PDF Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations (i) Repair (1) If any disbonding is confirmed during any inspection required by paragraphs (h)(1)(i) and (h)(1)(ii) of this AD, before further flight, repair as specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as applicable. (i) If disbonding is less than or equal to 50 millimeters (mm) in width and less than or equal to 150 mm in length, before further flight, vent the core, using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. Within 100 flight cycles after the UT inspection specified in paragraph (h) of this AD is done, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (ii) If disbonding is greater than 50 mm in width or greater than 150 mm in length, 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. (2) If liquid ingress is confirmed during any inspection required by paragraphs (h)(1)(i) and (h)(1)(ii) 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. (j) Inspection after Re-Installation If any rudder has been inspected as specified in Airbus Service Bulletin A300– 55–6043, Revision 01, dated December 3, 2007; or A310–55–2044, Revision 01, dated December 3, 2007; as applicable; and has been removed and re-installed on any airplane after this inspection, that rudder must be re-inspected as required by paragraph (g) of this AD; and all applicable actions required by paragraphs (h) and (i) of this AD must be done. Rmajette on DSK2VPTVN1PROD with RULES (k) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, a rudder assembly having a part number starting with A55471500, unless it has been inspected as required by paragraph (h) of this AD, and all applicable actions required by paragraph (i) of this AD have been done. (l) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind VerDate Sep<11>2014 15:10 Apr 08, 2015 Jkt 235001 19013 Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. Issued in Renton, Washington, on March 27, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (m) Related Information Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0039, dated February 26, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0123-0002. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission (AOT) A55W002–12, dated December 13, 2012, including Inspection Flowchart. The inspection flowchart attached to this AOT is referred to in the AOT as ‘‘Appendix 1’’; however, the flowchart page does not identify itself as an appendix. While the inspection flowchart page does specify the AOT document number, it does not specify a revision level or an issue date. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 [FR Doc. 2015–07799 Filed 4–8–15; 08:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0627; Directorate Identifier 2013–NM–217–AD; Amendment 39–18126; AD 2015–06–08] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2011–09– 03 for all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011–09–03 required repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This new AD requires reduced intervals for inspections of the upper rainbow fittings. This AD was prompted by analysis of in-service cracking, which has shown that a reduction in the inspection intervals is necessary for the upper rainbow fittings. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. DATES: This AD is effective May 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 14, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of May 26, 2011 (76 FR 22311, April 21, 2011). ADDRESSES: For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness SUMMARY: E:\FR\FM\09APR1.SGM 09APR1 19014 Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 30337; phone: 404–474–5554; fax: 404– 474–5606; email: carl.w.gray@faa.gov. SUPPLEMENTARY INFORMATION: received no comments on the NPRM (79 FR 55675, September 17, 2014) or on the determination of the cost to the public. Conclusion Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011). AD 2011–09–03 applied to all Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. The NPRM published in the Federal Register on September 17, 2014 (79 FR 55675). The NPRM was prompted by analysis of in-service cracking, which has shown that the initial and repetitive inspection schedules for the upper rainbow fitting need to be revised to reduce the probability of failure until the rainbow fitting is replaced. The NPRM proposed to continue to require repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This AD reduces compliance times for initial and repetitive inspections of the upper rainbow fitting. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. Comments We gave the public the opportunity to participate in developing this AD. We 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. 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–2014–0627. 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–2014– 0627; 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: We reviewed the relevant 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 (79 FR 55675, September 17, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 55675, September 17, 2014). Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Martin Aeronautics Company Service Bulletin 382–57–82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013. The service information describes procedures for repetitive eddy current inspections of the upper and lower rainbow fittings of the center wing; repetitive replacement of the upper and lower rainbow fittings; and related investigative and corrective actions. This service information is reasonably available; see ADDRESSES for ways to access this service information. Costs of Compliance We estimate that this AD affects 14 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection of upper and lower fitting [retained actions from AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)]. Fitting replacement [retained actions from AD 2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011)]. 20 work-hours × $85 per hour = $1,700 per inspection cycle. 2,438 work-hours × $85 per hour = $207,230 per replacement. None .............. $1,700, per inspection cycle. $247,230, per replacement. $23,800, per inspection cycle. $3,461,220, per replacement. Rmajette on DSK2VPTVN1PROD with RULES This AD reduces the compliance times for the upper rainbow fitting inspections and adds no additional economic burden. 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 VerDate Sep<11>2014 15:10 Apr 08, 2015 Jkt 235001 $40,000 .......... 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 have 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, E:\FR\FM\09APR1.SGM 09APR1 Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), and adding the following new AD: ■ 2015–06–08 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–18126; Docket No. FAA–2014–0627; Directorate Identifier 2013–NM–217–AD. (a) Effective Date This AD is effective May 14, 2015. (b) Affected ADs This AD replaces AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011). Rmajette on DSK2VPTVN1PROD with RULES (c) Applicability This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by an analysis of in-service cracking that has shown that the rainbow fittings are susceptible to multiple site fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the VerDate Sep<11>2014 15:10 Apr 08, 2015 Jkt 235001 upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial Inspections This paragraph restates the requirements of paragraph (g) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), with revised service information. Except as required by paragraph (m) of this AD, at the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do eddy current inspections to detect cracking of the center wing upper and lower rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382–57–82, Revision 4, including Appendixes A and B, dated May 20, 2009; or Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (m) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382–57–82, Revision 6, including Appendixes A and B, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (1) Before the accumulation of 15,000 total flight hours on the rainbow fitting. (2) Within 365 days or 600 flight hours on the rainbow fitting after May 26, 2011, (the effective date of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011)), whichever occurs first. (h) Retained Repetitive Inspection Schedule This paragraph restates the requirements of paragraph (h) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), with a new exception. Except as required by paragraph (n) of this AD, repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 3,600 flight hours on the center wing, until the rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of paragraph (n) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. (i) Retained Rainbow Fitting Replacements This paragraph restates the requirements of paragraph (i) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), with revised service information. Before the accumulation of 30,000 flight hours on the rainbow fitting, or within 600 flight hours after May 26, 2011, (the effective date of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011)), whichever occurs PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 19015 later: Replace the rainbow fitting with a new rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382–57–82, Revision 4, including Appendix C, dated May 20, 2009, except as required by paragraph (l) of this AD; or Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. Replace the rainbow fitting thereafter at intervals not to exceed 30,000 flight hours. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (j) Retained Post-Replacement Repetitive Inspections This paragraph restates the requirements of paragraph (j) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), with a new exception. For upper and lower rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD: Except as required by paragraph (o) of this AD, do the eddy current inspections specified in paragraph (g) of this AD within 15,000 flight hours after doing the replacement and repeat the eddy current inspections specified in paragraph (h) of this AD thereafter at intervals not to exceed 3,600 flight hours until the rainbow fittings are replaced in accordance with paragraph (i) or (k) of this AD. Doing the requirements of paragraph (o) of this AD terminates the requirements of this paragraph for the affected upper rainbow fitting only. (k) Retained Replacement, Related Investigative Actions, and Corrective Actions This paragraph restates the requirements of paragraph (k) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), with revised service information and revised references to inspection paragraphs. If, during any inspection required by paragraph (g), (h), (m), or (n) of this AD, any crack is detected in the rainbow fitting, before further flight, replace the rainbow fitting with a new rainbow fitting, do all related investigative actions, and do all applicable corrective actions, in accordance with Paragraph 2.C. of the Accomplishment Instructions of Lockheed Service Bulletin 382–57–82, Revision 4, including Appendix C, dated May 20, 2009, except as provided by paragraph (l) of this AD; or Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendix C, dated July 11, 2013, except as required by paragraph (l) of this AD. As of the effective date of this AD, only use Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendix C, dated July 11, 2013, for accomplishing the actions specified in this paragraph. (l) Retained Exceptions to Service Information This paragraph restates the requirements of paragraph (l) of AD 2011–09–03, Amendment E:\FR\FM\09APR1.SGM 09APR1 19016 Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 39–16665 (76 FR 22311, April 21, 2011), with revised service information. Where Lockheed Service Bulletin 382–57–82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009; or Lockheed Martin Aeronautics Company Service Bulletin 382– 57–82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013; specifies to contact the manufacturer for disposition of certain repair conditions or does not specify corrective actions if certain conditions are found, this AD requires repairing those conditions using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Rmajette on DSK2VPTVN1PROD with RULES (m) New Requirement: Reduced Initial Compliance Time for Upper Rainbow Fittings At the applicable compliance time specified in paragraphs (m)(1) and (m)(2) of this AD, do eddy current inspections to detect cracking of the center wing upper rainbow fittings on the left and right side of the airplane. Do the actions in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Service Bulletin 382–57–82, Revision 6, including Appendixes A and B, dated July 11, 2013. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing the requirements of this paragraph terminates the requirements of paragraph (g) of this AD for that upper rainbow fitting only. Repeat the inspection thereafter at the interval required by paragraph (n) of this AD. (1) For upper rainbow fittings that have accumulated less than 10,000 total flight hours as of the effective date of this AD, the compliance time is at the later of the times in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. (i) Before the accumulation of 10,000 total flight hours. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (2) For upper rainbow fittings that have accumulated 10,000 total flight hours or more, but less than 15,000 total flight hours as of the effective date of this AD, the compliance time is the earlier of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (ii) Before the accumulation of 15,000 total flight hours on the rainbow fitting. (n) New Requirement: Reduced Repetitive Inspection Intervals For upper rainbow fittings on which the requirements of paragraph (g), (h), or (m) of this AD were done, do the next inspection at the earlier of the times required in paragraphs (n)(1) and (n)(2) of this AD. Thereafter, repeat the inspection required by paragraph (m) of this AD at intervals not to exceed 2,500 flight hours until the upper VerDate Sep<11>2014 15:10 Apr 08, 2015 Jkt 235001 rainbow fitting has accumulated 30,000 total flight hours. If any crack is found during the inspections required by this paragraph, before further flight, do the actions required by paragraph (k) of this AD. Doing an inspection required by this paragraph terminates the requirements of paragraph (h) of this AD for the affected upper rainbow fitting only. (1) Within 3,600 flight hours since the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest. (2) At the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. (i) Within 2,500 flight hours after the last inspection done in accordance with paragraph (g), (h), or (m) of this AD, whichever occurs latest. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (o) New Requirement: Reduced PostReplacement Repetitive Inspections For upper rainbow fittings replaced in accordance with paragraph (i) or (k) of this AD, do the inspection required by paragraph (m) of this AD at the earlier of the compliance times required in paragraph (o)(1) and (o)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 2,500 flight hours. Doing the inspections required by this paragraph terminates the requirements of paragraph (j) of this AD for the affected upper rainbow fitting only. (1) At the later of the times in paragraphs (o)(1)(i) and (o)(1)(ii) of this AD. (i) Within 10,000 total flight hours on the upper rainbow fitting. (ii) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (2) Within 15,000 total flight hours on the upper rainbow fitting. (p) Credit for Previous Actions The service information identified in paragraphs (p)(1)(i), (p)(1)(ii), (p)(1)(iii), (p)(2), and (p)(3) is not incorporated by reference in this AD. (1) This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of this AD. (i) Lockheed Service Bulletin 382–57–82, including Appendixes A and B, dated December 7, 2004. (ii) Lockheed Service Bulletin 382–57–82, Revision 1, including Appendixes A and B, dated February 24, 2005. (iii) Lockheed Service Bulletin 382–57–82, Revision 2, including Appendixes A and B, dated February 15, 2007. (2) This paragraph restates paragraph (m) of AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011). This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions were performed before May 26, 2011 (the effective date of AD 2011–09–03), using Lockheed Service PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Bulletin 382–57–82, Revision 3, including Appendixes A, B, and C, dated April 25, 2008. (3) This paragraph provides credit for actions required by paragraphs (g), (h), (i), (j), (k), (m), (n), and (o) of this AD, if those actions were performed before the effective date of this AD using Lockheed Service Bulletin 382–57–82, Revision 5, including Appendixes A, B, and C, dated August 12, 2010. (q) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO, 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 manager of the ACO, send it to the attention of the person identified in paragraph (r)(2) of this AD. (2) 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. (3) AMOCs approved for AD 2011–09–03, Amendment 39–16665 (76 FR 22311, April 21, 2011), are approved as AMOCs for the corresponding provisions of this AD. (r) Related Information (1) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404–474–5606; email: carl.w.gray@faa.gov. (2) For information about AMOCs, contact Hal Horsbough, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404–474–5606; email: hal.horsbough@faa.gov. (s) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on May 14, 2015. (i) Lockheed Martin Aeronautics Company Service Bulletin 382–57–82, Revision 6, including Appendixes A, B, and C, dated July 11, 2013. (ii) Reserved. (4) The following service information was approved for IBR on May 26, 2011 (76 FR 22311, April 21, 2011). (i) Lockheed Service Bulletin 382–57–82, Revision 4, including Appendixes A, B, and C, dated May 20, 2009. (ii) Reserved. (5) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, E:\FR\FM\09APR1.SGM 09APR1 Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 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 service information at 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. Issued in Renton, Washington, on March 12, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–06785 Filed 4–8–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0839; Directorate Identifier 2015–CE–006–AD; Amendment 39–18131; AD 2015–07–03] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Airplanes Examining the AD Docket Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 402C and 414A airplanes. This AD requires repetitively inspecting the engine mount beams for cracks and contacting Cessna for FAA-approved corrective action if cracks are found. This AD also requires sending an inspection report to the FAA and to Cessna. This AD was prompted by reports of cracks found across the engine mount beams. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective April 24, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 24, 2015. We must receive comments on this AD by May 26, 2015. Rmajette on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 15:10 Apr 08, 2015 Jkt 235001 You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Cessna Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–5800; fax: (316) 517–7271; email: customercare@ cessna.textron.com; Internet: http:// www.cessnasupport.com. You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0839. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0839; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4123; fax: (316) 946–4107; email: gary.park@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We received reports of cracks found on the engine mount beams of certain Cessna Aircraft Company (Cessna) PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 19017 Model 402C airplanes. The cracks found run across the beam and extend beyond the doubler located under the aft engine mount and aft of the forward engine mount. Investigation revealed that the cause of the cracks is fatigue. The engine beam mounts of the Cessna Model 402C airplanes are the same type design as that of the Cessna Model 414A airplanes. This condition, if not detected and corrected, could result in failure of an engine mount beam and could lead to engine separation with consequent loss of power and loss of control. We are issuing this AD to correct the unsafe condition on these products. Relevant Service Information Under 1 CFR Part 51 We reviewed Cessna Aircraft Company Multi-engine Service Letter No. MEL–54–01, dated March 20, 2015, including the undated Attachment, ‘‘Inspection Results Form.’’ The Cessna Aircraft Company Multi-engine Service Letter describes procedures for inspecting the engine mount beams for cracks and reporting the inspection results to Cessna. This information is reasonably available at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0839, or you may see ADDRESSES for other ways to access this service information. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires repetitively inspecting the engine mount beams for cracks and contacting Cessna for an FAA-approved corrective action if cracks are found. This AD also requires sending the inspection results to the FAA and to Cessna. Differences Between This AD and the Service Information Cessna Aircraft Company Multiengine Service Letter No. MEL–54–01, dated March 20, 2015, including the undated Attachment, ‘‘Inspection Results Form,’’ specifies reporting the inspection results to Cessna. In this AD, we also require that the inspection results be reported to the FAA. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this E:\FR\FM\09APR1.SGM 09APR1

Agencies

[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)]
[Rules and Regulations]
[Pages 19013-19017]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-06785]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0627; Directorate Identifier 2013-NM-217-AD; 
Amendment 39-18126; AD 2015-06-08]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-09-03 for 
all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required 
repetitive eddy current inspections to detect cracks in the center wing 
upper and lower rainbow fittings, and corrective actions if necessary; 
and repetitive replacement of rainbow fittings, which would extend the 
repetitive interval for the next inspection. This new AD requires 
reduced intervals for inspections of the upper rainbow fittings. This 
AD was prompted by analysis of in-service cracking, which has shown 
that a reduction in the inspection intervals is necessary for the upper 
rainbow fittings. We are issuing this AD to detect and correct fatigue 
cracking of the upper and lower rainbow fittings on the center wings, 
which could grow large and lead to the failure of the fitting and a 
catastrophic failure of the center wing.

DATES: This AD is effective May 14, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 
26, 2011 (76 FR 22311, April 21, 2011).

ADDRESSES: For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness

[[Page 19014]]

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. 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-
0627.

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-2014-
0627; 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: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-
5554; fax: 404-474-5606; email: carl.w.gray@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 
April 21, 2011). AD 2011-09-03 applied to all Lockheed Martin 
Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 
382F, and 382G airplanes. The NPRM published in the Federal Register on 
September 17, 2014 (79 FR 55675). The NPRM was prompted by analysis of 
in-service cracking, which has shown that the initial and repetitive 
inspection schedules for the upper rainbow fitting need to be revised 
to reduce the probability of failure until the rainbow fitting is 
replaced. The NPRM proposed to continue to require repetitive eddy 
current inspections to detect cracks in the center wing upper and lower 
rainbow fittings, and corrective actions if necessary; and repetitive 
replacement of rainbow fittings, which would extend the repetitive 
interval for the next inspection. This AD reduces compliance times for 
initial and repetitive inspections of the upper rainbow fitting. We are 
issuing this AD to detect and correct fatigue cracking of the upper and 
lower rainbow fittings on the center wings, which could grow large and 
lead to the failure of the fitting and a catastrophic failure of the 
center wing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 55675, September 
17, 2014) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant 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 (79 FR 55675, September 17, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 55675, September 17, 2014).

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Aeronautics Company Service Bulletin 
382-57-82, Revision 6, including Appendixes A, B, and C, dated July 11, 
2013. The service information describes procedures for repetitive eddy 
current inspections of the upper and lower rainbow fittings of the 
center wing; repetitive replacement of the upper and lower rainbow 
fittings; and related investigative and corrective actions. This 
service information is reasonably available; see ADDRESSES for ways to 
access this service information.

Costs of Compliance

    We estimate that this AD affects 14 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of upper and lower     20 work-hours x     None..............  $1,700, per         $23,800, per
 fitting [retained actions from    $85 per hour =                          inspection cycle.   inspection cycle.
 AD 2011[dash]09[dash]03,          $1,700 per
 Amendment 39[dash]16665 (76 FR    inspection cycle.
 22311, April 21, 2011)].
Fitting replacement [retained     2,438 work-hours x  $40,000...........  $247,230, per       $3,461,220, per
 actions from AD                   $85 per hour =                          replacement.        replacement.
 2011[dash]09[dash]03, Amendment   $207,230 per
 39[dash]16665 (76 FR 22311,       replacement.
 April 21, 2011)].
----------------------------------------------------------------------------------------------------------------

    This AD reduces the compliance times for the upper rainbow fitting 
inspections and adds no additional economic burden.

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 have 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,

[[Page 19015]]

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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), and 
adding the following new AD:

2015-06-08 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-18126; Docket No. FAA-2014-0627; Directorate 
Identifier 2013-NM-217-AD.

(a) Effective Date

    This AD is effective May 14, 2015.

(b) Affected ADs

    This AD replaces AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 
April 21, 2011).

(c) Applicability

    This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an analysis of in-service cracking that 
has shown that the rainbow fittings are susceptible to multiple site 
fatigue damage. We are issuing this AD to detect and correct fatigue 
cracking of the upper and lower rainbow fittings on the center 
wings, which could grow large and lead to the failure of the fitting 
and a catastrophic failure of the center wing.

(f) Compliance

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

(g) Retained Initial Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information. Except as required by paragraph (m) of 
this AD, at the later of the times specified in paragraphs (g)(1) 
and (g)(2) of this AD: Do eddy current inspections to detect 
cracking of the center wing upper and lower rainbow fittings on the 
left and right side of the airplane. Do the actions in accordance 
with the Accomplishment Instructions of Lockheed Service Bulletin 
382-57-82, Revision 4, including Appendixes A and B, dated May 20, 
2009; or Lockheed Martin Aeronautics Company Service Bulletin 382-
57-82, Revision 6, including Appendixes A and B, dated July 11, 
2013. If any crack is found during the inspections required by this 
paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing the requirements of paragraph (m) of 
this AD terminates the requirements of this paragraph for the 
affected upper rainbow fitting only. As of the effective date of 
this AD, only use Lockheed Martin Aeronautics Company Service 
Bulletin 382-57-82, Revision 6, including Appendixes A and B, dated 
July 11, 2013, for accomplishing the actions specified in this 
paragraph.
    (1) Before the accumulation of 15,000 total flight hours on the 
rainbow fitting.
    (2) Within 365 days or 600 flight hours on the rainbow fitting 
after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 
39-16665 (76 FR 22311, April 21, 2011)), whichever occurs first.

(h) Retained Repetitive Inspection Schedule

    This paragraph restates the requirements of paragraph (h) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a 
new exception. Except as required by paragraph (n) of this AD, 
repeat the inspection required by paragraph (g) of this AD at 
intervals not to exceed 3,600 flight hours on the center wing, until 
the rainbow fitting has accumulated 30,000 total flight hours. If 
any crack is found during the inspections required by this 
paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing the requirements of paragraph (n) of 
this AD terminates the requirements of this paragraph for the 
affected upper rainbow fitting only.

(i) Retained Rainbow Fitting Replacements

    This paragraph restates the requirements of paragraph (i) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information. Before the accumulation of 30,000 
flight hours on the rainbow fitting, or within 600 flight hours 
after May 26, 2011, (the effective date of AD 2011-09-03, Amendment 
39-16665 (76 FR 22311, April 21, 2011)), whichever occurs later: 
Replace the rainbow fitting with a new rainbow fitting, do all 
related investigative actions, and do all applicable corrective 
actions, in accordance with paragraph 2.C. of the Accomplishment 
Instructions of Lockheed Service Bulletin 382-57-82, Revision 4, 
including Appendix C, dated May 20, 2009, except as required by 
paragraph (l) of this AD; or Lockheed Martin Aeronautics Company 
Service Bulletin 382-57-82, Revision 6, including Appendix C, dated 
July 11, 2013, except as required by paragraph (l) of this AD. 
Replace the rainbow fitting thereafter at intervals not to exceed 
30,000 flight hours. As of the effective date of this AD, only use 
Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, 
Revision 6, including Appendix C, dated July 11, 2013, for 
accomplishing the actions specified in this paragraph.

(j) Retained Post-Replacement Repetitive Inspections

    This paragraph restates the requirements of paragraph (j) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with a 
new exception. For upper and lower rainbow fittings replaced in 
accordance with paragraph (i) or (k) of this AD: Except as required 
by paragraph (o) of this AD, do the eddy current inspections 
specified in paragraph (g) of this AD within 15,000 flight hours 
after doing the replacement and repeat the eddy current inspections 
specified in paragraph (h) of this AD thereafter at intervals not to 
exceed 3,600 flight hours until the rainbow fittings are replaced in 
accordance with paragraph (i) or (k) of this AD. Doing the 
requirements of paragraph (o) of this AD terminates the requirements 
of this paragraph for the affected upper rainbow fitting only.

(k) Retained Replacement, Related Investigative Actions, and Corrective 
Actions

    This paragraph restates the requirements of paragraph (k) of AD 
2011-09-03, Amendment 39-16665 (76 FR 22311, April 21, 2011), with 
revised service information and revised references to inspection 
paragraphs. If, during any inspection required by paragraph (g), 
(h), (m), or (n) of this AD, any crack is detected in the rainbow 
fitting, before further flight, replace the rainbow fitting with a 
new rainbow fitting, do all related investigative actions, and do 
all applicable corrective actions, in accordance with Paragraph 2.C. 
of the Accomplishment Instructions of Lockheed Service Bulletin 382-
57-82, Revision 4, including Appendix C, dated May 20, 2009, except 
as provided by paragraph (l) of this AD; or Lockheed Martin 
Aeronautics Company Service Bulletin 382-57-82, Revision 6, 
including Appendix C, dated July 11, 2013, except as required by 
paragraph (l) of this AD. As of the effective date of this AD, only 
use Lockheed Martin Aeronautics Company Service Bulletin 382-57-82, 
Revision 6, including Appendix C, dated July 11, 2013, for 
accomplishing the actions specified in this paragraph.

(l) Retained Exceptions to Service Information

    This paragraph restates the requirements of paragraph (l) of AD 
2011-09-03, Amendment

[[Page 19016]]

39-16665 (76 FR 22311, April 21, 2011), with revised service 
information. Where Lockheed Service Bulletin 382-57-82, Revision 4, 
including Appendixes A, B, and C, dated May 20, 2009; or Lockheed 
Martin Aeronautics Company Service Bulletin 382-57-82, Revision 6, 
including Appendixes A, B, and C, dated July 11, 2013; specifies to 
contact the manufacturer for disposition of certain repair 
conditions or does not specify corrective actions if certain 
conditions are found, this AD requires repairing those conditions 
using a method approved by the Manager, Atlanta Aircraft 
Certification Office (ACO), FAA. For a repair method to be approved 
by the Manager, Atlanta ACO, as required by this paragraph, the 
Manager's approval letter must specifically refer to this AD.

(m) New Requirement: Reduced Initial Compliance Time for Upper Rainbow 
Fittings

    At the applicable compliance time specified in paragraphs (m)(1) 
and (m)(2) of this AD, do eddy current inspections to detect 
cracking of the center wing upper rainbow fittings on the left and 
right side of the airplane. Do the actions in accordance with the 
Accomplishment Instructions of Lockheed Martin Aeronautics Company 
Service Bulletin 382-57-82, Revision 6, including Appendixes A and 
B, dated July 11, 2013. If any crack is found during the inspections 
required by this paragraph, before further flight, do the actions 
required by paragraph (k) of this AD. Doing the requirements of this 
paragraph terminates the requirements of paragraph (g) of this AD 
for that upper rainbow fitting only. Repeat the inspection 
thereafter at the interval required by paragraph (n) of this AD.
    (1) For upper rainbow fittings that have accumulated less than 
10,000 total flight hours as of the effective date of this AD, the 
compliance time is at the later of the times in paragraphs (m)(1)(i) 
and (m)(1)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight hours.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.
    (2) For upper rainbow fittings that have accumulated 10,000 
total flight hours or more, but less than 15,000 total flight hours 
as of the effective date of this AD, the compliance time is the 
earlier of the times specified in paragraphs (m)(2)(i) and 
(m)(2)(ii) of this AD.
    (i) Within 365 days or 600 flight hours after the effective date 
of this AD, whichever occurs first.
    (ii) Before the accumulation of 15,000 total flight hours on the 
rainbow fitting.

(n) New Requirement: Reduced Repetitive Inspection Intervals

    For upper rainbow fittings on which the requirements of 
paragraph (g), (h), or (m) of this AD were done, do the next 
inspection at the earlier of the times required in paragraphs (n)(1) 
and (n)(2) of this AD. Thereafter, repeat the inspection required by 
paragraph (m) of this AD at intervals not to exceed 2,500 flight 
hours until the upper rainbow fitting has accumulated 30,000 total 
flight hours. If any crack is found during the inspections required 
by this paragraph, before further flight, do the actions required by 
paragraph (k) of this AD. Doing an inspection required by this 
paragraph terminates the requirements of paragraph (h) of this AD 
for the affected upper rainbow fitting only.
    (1) Within 3,600 flight hours since the last inspection done in 
accordance with paragraph (g), (h), or (m) of this AD, whichever 
occurs latest.
    (2) At the later of the times specified in paragraphs (n)(2)(i) 
and (n)(2)(ii) of this AD.
    (i) Within 2,500 flight hours after the last inspection done in 
accordance with paragraph (g), (h), or (m) of this AD, whichever 
occurs latest.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.

(o) New Requirement: Reduced Post-Replacement Repetitive Inspections

    For upper rainbow fittings replaced in accordance with paragraph 
(i) or (k) of this AD, do the inspection required by paragraph (m) 
of this AD at the earlier of the compliance times required in 
paragraph (o)(1) and (o)(2) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 2,500 flight hours. Doing the 
inspections required by this paragraph terminates the requirements 
of paragraph (j) of this AD for the affected upper rainbow fitting 
only.
    (1) At the later of the times in paragraphs (o)(1)(i) and 
(o)(1)(ii) of this AD. (i) Within 10,000 total flight hours on the 
upper rainbow fitting.
    (ii) Within 365 days or 600 flight hours after the effective 
date of this AD, whichever occurs first.
    (2) Within 15,000 total flight hours on the upper rainbow 
fitting.

(p) Credit for Previous Actions

    The service information identified in paragraphs (p)(1)(i), 
(p)(1)(ii), (p)(1)(iii), (p)(2), and (p)(3) is not incorporated by 
reference in this AD.
    (1) This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), (j), and (k) of this AD, if those actions 
were performed before the effective date of this AD using the 
service information identified in paragraphs (p)(1)(i), (p)(1)(ii), 
and (p)(1)(iii) of this AD.
    (i) Lockheed Service Bulletin 382-57-82, including Appendixes A 
and B, dated December 7, 2004.
    (ii) Lockheed Service Bulletin 382-57-82, Revision 1, including 
Appendixes A and B, dated February 24, 2005.
    (iii) Lockheed Service Bulletin 382-57-82, Revision 2, including 
Appendixes A and B, dated February 15, 2007.
    (2) This paragraph restates paragraph (m) of AD 2011-09-03, 
Amendment 39-16665 (76 FR 22311, April 21, 2011). This paragraph 
provides credit for actions required by paragraphs (g), (h), (i), 
(j), and (k) of this AD, if those actions were performed before May 
26, 2011 (the effective date of AD 2011-09-03), using Lockheed 
Service Bulletin 382-57-82, Revision 3, including Appendixes A, B, 
and C, dated April 25, 2008.
    (3) This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), (j), (k), (m), (n), and (o) of this AD, if 
those actions were performed before the effective date of this AD 
using Lockheed Service Bulletin 382-57-82, Revision 5, including 
Appendixes A, B, and C, dated August 12, 2010.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO, 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 manager of the 
ACO, send it to the attention of the person identified in paragraph 
(r)(2) of this AD.
    (2) 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.
    (3) AMOCs approved for AD 2011-09-03, Amendment 39-16665 (76 FR 
22311, April 21, 2011), are approved as AMOCs for the corresponding 
provisions of this AD.

(r) Related Information

    (1) For more information about this AD, contact Carl Gray, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 
30337; phone: 404-474-5554; fax: 404-474-5606; email: 
carl.w.gray@faa.gov.
    (2) For information about AMOCs, contact Hal Horsbough, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 
30337; phone: 404-474-5554; fax: 404-474-5606; email: 
hal.horsbough@faa.gov.

(s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 14, 2015.
    (i) Lockheed Martin Aeronautics Company Service Bulletin 382-57-
82, Revision 6, including Appendixes A, B, and C, dated July 11, 
2013.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 26, 2011 (76 FR 22311, April 21, 2011).
    (i) Lockheed Service Bulletin 382-57-82, Revision 4, including 
Appendixes A, B, and C, dated May 20, 2009.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M,

[[Page 19017]]

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 service information at 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 March 12, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-06785 Filed 4-8-15; 8:45 am]
 BILLING CODE 4910-13-P