Airworthiness Directives; The Boeing Company Airplanes, 59728-59732 [2012-23049]

Download as PDF 59728 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations identified in paragraphs (i)(1) through (i)(5) of this AD (* the issue date is not specified on the drawing.) (1) Fokker Manual Change Notification— Maintenance Documentation MCNM–F100– 145, dated June 30, 2011. (2) Fokker Manual Change Notification— Operational Documentation MCNO–F100– 059, dated June 30, 2011. (3) Fokker Drawing W41190, Sheet 013, Issue P*. (4) Fokker Drawing W41190, Sheet 014, Issue P*. (5) Fokker Drawing W41190, Sheet 016, Issue P*. (j) Prohibited Modification As of the effective date of this AD, no person may modify any airplane using Fokker Service Bulletin SBF100–28–021, dated September 6, 1991 (specified in European Aviation Safety Agency (EASA) AD 2011–0158, dated August 26, 2011, and is not incorporated by reference in this AD). That service bulletin was cancelled by Fokker Service Bulletin SBF100–28–021, Revision 1, dated June 30, 2011 (not incorporated by reference in this AD). mstockstill on DSK4VPTVN1PROD with RULES (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1137; 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (l) Related Information Refer to MCAI EASA Airworthiness Directive 2011–0158, dated August 26, 2011, and the service information specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, for related information. (1) Fokker Service Bulletin SBF100–28– 029, Revision 1, dated November 30, 1993. (2) Fokker Service Bulletin SBF100–28– 030, Revision 1, dated December 5, 1994. VerDate Mar<15>2010 16:08 Sep 28, 2012 Jkt 226001 (3) Fokker Service Bulletin SBF100–28– 066, dated June 30, 2011, which includes the attachments identified in paragraphs (l)(3)(i) through (l)(3)(v) of this AD (* the issue date is not specified on the drawing). (i) Fokker Manual Change Notification— Maintenance Documentation MCNM–F100– 145, dated June 30, 2011. (ii) Fokker Manual Change Notification— Operational Documentation MCNO–F100– 059, dated June 30, 2011. (iii) Fokker Drawing W41190, Sheet 013, Issue P*. (iv) Fokker Drawing W41190, Sheet 014, Issue P*. (v) Fokker Drawing W41190, Sheet 016, Issue P*. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on November 5, 2012. (i) Fokker Service Bulletin SBF100–28– 066, dated June 30, 2011, which includes the attachments identified in paragraphs (m)(3)(i)(A) through (m)(3)(i)(E) of this AD (* the issue date is not specified on the drawing). (A) Fokker Manual Change Notification— Maintenance Documentation MCNM–F100– 145, dated June 30, 2011. (B) Fokker Manual Change Notification— Operational Documentation MCNO–F100– 059, dated June 30, 2011. (C) Fokker Drawing W41190, Sheet 013, Issue P*. (D) Fokker Drawing W41190, Sheet 014, Issue P*. (E) Fokker Drawing W41190, Sheet 016, Issue P*. (ii) Reserved. (4) The following service information was approved for IBR on April 29, 1996 (61 FR 14014, March 29, 1996). (i) Fokker Service Bulletin SBF100–28– 030, Revision 1, dated December 5, 1994. (Pages 1 through 3, 5, 8, and 10 of this document are identified as Revision 1, dated December 5, 1994. Pages 4, 6, 7, and 9 of this document are dated August 28, 1994 (original issue).) (ii) Reserved. (5) The following service information was approved for IBR on August 10, 1994 (59 FR 35237, July 11, 1994). (i) Fokker Service Bulletin SBF100–28– 029, Revision 1, dated November 30, 1993. (Pages 1 through 3 of this document are identified as Revision 1, dated November 30, 1993. Pages 4 through 7 of this document are dated November 10, 1993 (original issue).) (ii) Reserved. (6) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (7) You may review copies of the 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. (8) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 11, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–23052 Filed 9–28–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0327; Directorate Identifier 2011–NM–125–AD; Amendment 39–17198; AD 2012–19–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model DC–10–10, DC–10–10F, DC–10–15, DC– 10–30, DC–10–30F (KC–10A and KDC– 10), DC–10–40, DC–10–40F, MD–10– 10F, and MD–10–30F airplanes. That AD currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane; and for certain airplanes, repositioning or replacing two bonding straps, doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. This new AD adds airplanes to the applicability and, depending on the airplane configuration, requires installing new braided bonding straps, inspecting to determine if a certain strap is installed and replacing with or installing a braided bonding strap if necessary, measuring the electrical resistance of the bonding straps, verifying that brackets have an acceptable fillet seal, and doing corrective actions if necessary. This AD SUMMARY: E:\FR\FM\01OCR1.SGM 01OCR1 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations was prompted by fuel system reviews conducted by the manufacturer, and our determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: This AD is effective November 5, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 4, 2010 (74 FR 69268, December 31, 2009). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD of September 7, 2006 (71 FR 43962, August 3, 2006). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet. You may review copies of the 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. phone: 562–627–5262; fax: 562–627– 5210; email: Samuel.Lee@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009). That AD applies to the specified products. The NPRM published in the Federal Register on March 28, 2012 (77 FR 18719). That NPRM proposed to continue to require installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. That NPRM also proposed to continue to require, for certain airplanes, repositioning or replacing two bonding straps, doing a bonding-resistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. That NPRM also proposed to add airplanes to the applicability, and depending on the airplane configuration, installing new braided bonding straps, inspecting to determine if a certain strap is installed and replacing with or installing a braided bonding strap if necessary, measuring the electrical resistance of the bonding straps, verifying that brackets have an acceptable fillet seal, and doing corrective actions if necessary. mstockstill on DSK4VPTVN1PROD with RULES Examining the AD Docket Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 18719, March 28, 2012) and the FAA’s response to each comment. You may examine the AD docket on the Internet at https:// www.regulations.gov; 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 Document 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: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; Request To Add Credit for Previous Actions FedEx requested that previous actions accomplished on 51 of its airplanes using Boeing Service Bulletin DC10–53– 111, Revision 4, dated September 21, 2006; or Boeing Service Bulletin DC10– 53–111, Revision 7, dated March 16, 2011; be acceptable as terminating action for the actions specified in paragraph (j) of the NPRM (77 FR 18719, March 28, 2012). We partially agree. We agree that the actions are acceptable, but do not agree to change the AD. We disagree that credit for previous actions should be added to the AD. Paragraphs (m)(3) and (m)(4) of this AD already allow previous accomplishment of the actions specified in paragraphs (g), (h), (i), and (j) of this AD, if those actions were done using alternative methods of compliance VerDate Mar<15>2010 16:08 Sep 28, 2012 Jkt 226001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 59729 (AMOCs) approved in accordance with AD 2006–16–03, Amendment 39–14703 (71 FR 43962, August 3, 2006); and AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009). Boeing Service Bulletin DC10–53–111, Revision 4, dated September 21, 2006, states that it is approved as an AMOC for AD 2006–16–03. We have not changed the final rule in this regard. Request To Combine Paragraphs FedEx suggested that paragraphs (l)(3) and (l)(4) of the NPRM (77 FR 18719, March 28, 2012) be combined since they state the same thing. We do not agree to combine paragraphs (l)(3) and (l)(4) of this AD, because those paragraphs state different requirements for different airplanes. We have not changed the final rule in this regard. Request To Correct Effectivity FedEx stated that Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011, incorrectly specifies that the reason for the revision was to add fuselage 317 to the effectivity of that service bulletin. FedEx stated that fuselage 317 was not and does not need to be added to the effectivity of that service bulletin, because fuselage 317 is in the effectivity of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. We infer that FedEx is requesting that Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011, be revised to correct the discrepancy in the stated reason for the revision of that service bulletin. We do not agree. Boeing issued Service Bulletin Information Notice DC10–53–111 IN 02, dated June 17, 2011, to clarify that fuselage 317 was not added to the effectivity of Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011. No change to this final rule is necessary in this regard. Explanation of Additional Changes Made To This AD We have revised certain headings throughout this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the 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 (77 FR 18719, March 28, 2012) for correcting the unsafe condition; and E:\FR\FM\01OCR1.SGM 01OCR1 59730 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 18719, March 28, 2012). Costs of Compliance We estimate that this AD affects 208 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 Installation, inspection, and resistance measurement [retained actions from existing AD 2009–26–17, Amendment 39-16156 (74 FR 69268, December 31, 2009)]. Installation, inspection, and resistance measurement [new action]. Up to 17 work-hours × $85 per hour = $1,445. Up to $4,169 .......... Up to $5,614 .......... Up to $1,167,712. Up to 16 work-hours × $85 per hour = $1,360. Up to $33,230 ........ Up to $34,590 ........ Up to $7,194,720. Authority for This Rulemaking List of Subjects in 14 CFR Part 39 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. mstockstill on DSK4VPTVN1PROD with RULES 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, 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. VerDate Mar<15>2010 16:08 Sep 28, 2012 Jkt 226001 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) 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009), and adding the following new AD: ■ 2012–19–03 The Boeing Company: Amendment 39–17198; Docket No. FAA–2012–0327; Directorate Identifier 2011–NM–125–AD. (a) Effective Date This airworthiness directive (AD) is effective November 5, 2012. (b) Affected ADs This AD supersedes AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009). (c) Applicability This AD applies to The Boeing Company Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC– 10), DC–10–40, and DC–10–40F airplanes, and Model MD–10–10F and MD–10–30F airplanes that have been converted from Model DC–10 series airplanes; certificated in any category; as identified in paragraphs (c)(1) and (c)(2) of this AD, as applicable. (1) Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011 (for airplanes with extended wing-to-fuselage fillets). PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Cost on U.S. operators (2) Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011 (for airplanes with conventional wing-to-fuselage fillets). (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by fuel system reviews conducted by the manufacturer, and our determination that additional actions are necessary to address the identified unsafe condition. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Requirements for Installation or Replacement for Certain Airplanes, With New Service Information This paragraph restates the installation or replacement requirements of paragraph (g) of AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009), with new service information. For airplanes with manufacturer’s fuselage numbers identified in the applicable service bulletin listed in paragraph (g)(1) of this AD: Within 7,500 flight hours or 60 months after September 7, 2006 (the effective date of AD 2006–16–03, Amendment 39–14703 (71 FR 43962, August 3, 2006)), whichever occurs earlier: Install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. After February 4, 2010 (the effective date of AD 2009–26–17), use the applicable service bulletin identified in paragraph (g)(2) or (g)(3) of this AD. After the effective date of this AD, use only the applicable service bulletin identified in paragraph (g)(3) of this E:\FR\FM\01OCR1.SGM 01OCR1 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations AD to do the actions required by this paragraph. (1) McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992 (for airplanes with extended wing-tofuselage fillets); or McDonnell Douglas DC– 10 Service Bulletin 53–111, Revision 3, dated August 24, 1992 (for airplanes with conventional wing-to-fuselage fillets). (2) Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009 (for airplanes with extended wing-to-fuselage fillets); or Boeing Service Bulletin DC10–53– 111, Revision 6, dated March 3, 2009 (for airplanes with conventional wing-to-fuselage fillets). (3) Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011 (for airplanes with extended wing-to-fuselage fillets); or Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011 (for airplanes with conventional wingto-fuselage fillets). mstockstill on DSK4VPTVN1PROD with RULES (h) Retained Requirements for Installation or Replacement for Certain Other Airplanes, With New Service Information This paragraph restates the installation or replacement requirements of paragraph (h) of AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009), with new service information. For airplanes with fuselage numbers identified in the applicable service bulletin listed in paragraph (g)(2) of this AD that are not also identified in the applicable service bulletin listed in paragraph (g)(1) of this AD, except for airplanes identified in paragraph (i) or (j) of this AD: Within 7,500 flight hours or 60 months, whichever occurs first after February 4, 2010 (the effective date of AD 2009–26– 17), install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. Do the actions in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraph (g)(2) or (g)(3) of this AD. After the effective date of this AD, use only the applicable service bulletin identified in paragraph (g)(3) of this AD to do the actions required by this paragraph. (i) Retained Requirements for Strap Repositioning for Certain Airplanes, With New Service Information This paragraph restates the strap repositioning requirements of paragraph (i) of AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009), with new service information. For Group 1–4, Configuration 3 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009: Within 7,500 flight hours or 60 months after February 4, 2010 (the effective date of AD 2009–26–17), whichever occurs first, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Remove two braided bonding straps and install two longer braided bonding straps between the metallic frame of the fillet and the wing leading edge ribs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, VerDate Mar<15>2010 16:08 Sep 28, 2012 Jkt 226001 Revision 7, dated March 3, 2009; or Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, to do the actions required by this paragraph. (2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009; or Boeing Service Bulletin DC10–53– 109, Revision 8, dated March 10, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, to do the actions required by this paragraph. (j) Retained Requirements for Inspection and Corrective Action for Certain Airplanes, With New Service Information This paragraph restates the inspection requirements of paragraph (j) of AD 2009–26– 17, Amendment 39–16156 (74 FR 69268, December 31, 2009), with new service information. For Group 1–2, Configuration 2 airplanes, as identified in Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009: Within 7,500 flight hours or 60 months after February 4, 2010 (the effective date of AD 2009–26–17), whichever occurs first, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) Do a general visual inspection to verify correct installation of the braided bonding straps (one left-hand wing and one righthand wing) as shown in Sheet 7 in Figure 3 of Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009, or Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011; and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009, or Boeing Service Bulletin DC10–53– 111, Revision 7, dated March 16, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011, to do the actions required by this paragraph. (2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009; or Boeing Service Bulletin DC10–53– 111, Revision 7, dated March 16, 2011. After the effective date of this AD, use only Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011, to do the actions required by this paragraph. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g), (h), (i), and (j) this AD, if those actions were accomplished before February 4, 2010 (the effective date of AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009)), using Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008; or Boeing Service Bulletin PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 59731 DC10–53–109, Revision 6, dated July 10, 2008; as applicable; which are not incorporated by reference. (l) New Installation and Corrective Actions for Certain Airplanes Within 7,500 flight hours or 60 months after the effective date of this AD, whichever comes first: Do the applicable actions specified in paragraphs (l)(1) through (l)(6) of this AD, as applicable. (1) For Group 1–4, Configurations 1 and 2 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, except airplanes that are identified in paragraph (g) of this AD: Remove any solid metal bonding straps and install seven new braided bonding straps, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. (2) For Group 1–4, Configurations 1 and 2 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, that are also identified in paragraph (g) of this AD: Remove any solid metal bonding straps not removed during the actions required by paragraph (g) of this AD and install a 7th new braided bonding strap (paragraph (g) of this AD requires installing 6 straps), in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. (3) For Group 1–4, Configuration 3 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, except airplanes identified in paragraph (i) of this AD: Do the actions specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this AD. (i) Replace one strap with new braided bonding strap, inspect to determine the existence of an installed solid metal bonding strap and replace any missing strap and any solid metal bonding strap with a new braided bonding strap, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. (ii) Measure the electrical resistance across each bonding joint of the six previouslyinstalled braided strap assemblies and verify that brackets have an acceptable fillet seal, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. Do all applicable corrective actions before further flight. (4) For Group 1–4, Configuration 3 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011, that are also identified in paragraph (i) of this AD: Do the actions specified in paragraphs (l)(4)(i) and (l)(4)(ii) of this AD. (i) Inspect to determine the existence of an installed solid metal bonding strap and replace any missing strap and any solid metal bonding strap with a new braided bonding strap, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. E:\FR\FM\01OCR1.SGM 01OCR1 59732 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations (ii) Measure the electrical resistance across each bonding joint of the six previouslyinstalled braided strap assemblies and verify that brackets have an acceptable fillet seal, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. Do all applicable corrective actions before further flight. (5) For Group 1–4, Configuration 4 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011: Do the actions specified in paragraphs (l)(5)(i) and (l)(5)(ii) of this AD. (i) Inspect to determine the existence of an installed solid metal bonding strap, and replace any missing strap and any solid metal bonding strap with a new braided bonding strap, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. (ii) Measure the electrical resistance across each bonding joint of the six previouslyinstalled braided strap assemblies and verify that brackets have an acceptable fillet seal, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. Do all applicable corrective actions before further flight. (6) For Group 1–4, Configuration 5 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011: Inspect to determine the existence of an installed solid metal bonding strap, and replace any missing strap and any solid metal bonding strap with a new braided bonding strap, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. mstockstill on DSK4VPTVN1PROD with RULES (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (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 the Related Information section 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 previously in accordance with AD 2006–16–03, Amendment 39–14703 (71 FR 43962, August 3, 2006), are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), (i), and (j) of this AD. (4) AMOCs approved previously in accordance with AD 2009–26–17, Amendment 39–16156 (74 FR 69268, December 31, 2009), are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), (i), and (j) of this AD. VerDate Mar<15>2010 16:08 Sep 28, 2012 Jkt 226001 (n) Related Information (1) For more information about this AD, contact Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562–627–5262; fax: 562– 627–5210; email: Samuel.Lee@faa.gov. (2) For service information specified in this AD that is not incorporated by reference, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766– 5683; Internet https://www.myboeingfleet. (o) 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 November 5, 2012. (i) Boeing Service Bulletin DC10–53–109, Revision 8, dated March 10, 2011. (ii) Boeing Service Bulletin DC10–53–111, Revision 7, dated March 16, 2011. (4) The following service information was approved for IBR on February 4, 2010 (74 FR 69268, December 31, 2009). (i) Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009. (ii) Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009. (5) The following service information was approved for IBR on September 7, 2006 (71 FR 43962, August 3, 2006). (i) McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992. (ii) McDonnell Douglas DC–10 Service Bulletin 53–111, Revision 3, dated August 24, 1992. (6) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet. (7) You may review copies of the 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. (8) You may also review copies of the 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: https://www.archives.gov/federal-register/ cfr/ibr_locations.html. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on September 11, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–23049 Filed 9–28–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0996; Directorate Identifier 2011–NM–040–AD; Amendment 39–17202; AD 2012–19–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A340–500 and –600 series airplanes. This AD requires repetitive inspections for corrosion of the drag stay lower arm assembly of the nose landing gear (NLG), and replacement if necessary. This AD also requires eventual replacement of the drag stay lower arm assembly of the NLG with an improved assembly having corrosion protection, which terminates the repetitive inspections required by this AD. This AD was prompted by findings of corrosion traces in the lugs and on the bearing outer surface of the NLG during routine maintenance checks. We are issuing this AD to prevent failure of the drag stay lower arm, which could result in NLG collapse and consequent reduced controllability of the airplane during takeoff. DATES: This AD becomes effective October 16, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 16, 2012. We must receive comments on this AD by November 15, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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. SUMMARY: E:\FR\FM\01OCR1.SGM 01OCR1

Agencies

[Federal Register Volume 77, Number 190 (Monday, October 1, 2012)]
[Rules and Regulations]
[Pages 59728-59732]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-23049]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0327; Directorate Identifier 2011-NM-125-AD; 
Amendment 39-17198; AD 2012-19-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-
10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, 
and MD-10-30F airplanes. That AD currently requires installing or 
replacing with improved parts, as applicable, the bonding straps 
between the metallic frame of the fillet and the wing leading edge 
ribs, on both the left and right sides of the airplane; and for certain 
airplanes, repositioning or replacing two bonding straps, doing a 
bonding-resistance check and an inspection to determine correct 
installation of certain bonding straps, and applicable corrective 
actions. This new AD adds airplanes to the applicability and, depending 
on the airplane configuration, requires installing new braided bonding 
straps, inspecting to determine if a certain strap is installed and 
replacing with or installing a braided bonding strap if necessary, 
measuring the electrical resistance of the bonding straps, verifying 
that brackets have an acceptable fillet seal, and doing corrective 
actions if necessary. This AD

[[Page 59729]]

was prompted by fuel system reviews conducted by the manufacturer, and 
our determination that additional actions are necessary to address the 
identified unsafe condition. We are issuing this AD to reduce the 
potential of ignition sources inside fuel tanks in the event of a 
severe lightning strike, which, in combination with flammable fuel 
vapors, could result in fuel tank explosions and consequent loss of the 
airplane.

DATES: This AD is effective November 5, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 5, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 4, 2010 (74 FR 69268, December 31, 2009).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD of September 
7, 2006 (71 FR 43962, August 3, 2006).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; Internet 
https://www.myboeingfleet. You may review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; 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 Document 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: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
phone: 562-627-5262; fax: 562-627-5210; email: Samuel.Lee@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-26-17, Amendment 39-16156 (74 FR 69268, 
December 31, 2009). That AD applies to the specified products. The NPRM 
published in the Federal Register on March 28, 2012 (77 FR 18719). That 
NPRM proposed to continue to require installing or replacing with 
improved parts, as applicable, the bonding straps between the metallic 
frame of the fillet and the wing leading edge ribs, on both the left 
and right sides of the airplane. That NPRM also proposed to continue to 
require, for certain airplanes, repositioning or replacing two bonding 
straps, doing a bonding-resistance check and an inspection to determine 
correct installation of certain bonding straps, and applicable 
corrective actions. That NPRM also proposed to add airplanes to the 
applicability, and depending on the airplane configuration, installing 
new braided bonding straps, inspecting to determine if a certain strap 
is installed and replacing with or installing a braided bonding strap 
if necessary, measuring the electrical resistance of the bonding 
straps, verifying that brackets have an acceptable fillet seal, and 
doing corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 18719, March 28, 2012) and the FAA's response to each comment.

Request To Add Credit for Previous Actions

    FedEx requested that previous actions accomplished on 51 of its 
airplanes using Boeing Service Bulletin DC10-53-111, Revision 4, dated 
September 21, 2006; or Boeing Service Bulletin DC10-53-111, Revision 7, 
dated March 16, 2011; be acceptable as terminating action for the 
actions specified in paragraph (j) of the NPRM (77 FR 18719, March 28, 
2012).
    We partially agree. We agree that the actions are acceptable, but 
do not agree to change the AD. We disagree that credit for previous 
actions should be added to the AD. Paragraphs (m)(3) and (m)(4) of this 
AD already allow previous accomplishment of the actions specified in 
paragraphs (g), (h), (i), and (j) of this AD, if those actions were 
done using alternative methods of compliance (AMOCs) approved in 
accordance with AD 2006-16-03, Amendment 39-14703 (71 FR 43962, August 
3, 2006); and AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 
31, 2009). Boeing Service Bulletin DC10-53-111, Revision 4, dated 
September 21, 2006, states that it is approved as an AMOC for AD 2006-
16-03. We have not changed the final rule in this regard.

Request To Combine Paragraphs

    FedEx suggested that paragraphs (l)(3) and (l)(4) of the NPRM (77 
FR 18719, March 28, 2012) be combined since they state the same thing.
    We do not agree to combine paragraphs (l)(3) and (l)(4) of this AD, 
because those paragraphs state different requirements for different 
airplanes. We have not changed the final rule in this regard.

Request To Correct Effectivity

    FedEx stated that Boeing Service Bulletin DC10-53-111, Revision 7, 
dated March 16, 2011, incorrectly specifies that the reason for the 
revision was to add fuselage 317 to the effectivity of that service 
bulletin. FedEx stated that fuselage 317 was not and does not need to 
be added to the effectivity of that service bulletin, because fuselage 
317 is in the effectivity of Boeing Service Bulletin DC10-53-109, 
Revision 8, dated March 10, 2011.
    We infer that FedEx is requesting that Boeing Service Bulletin 
DC10-53-111, Revision 7, dated March 16, 2011, be revised to correct 
the discrepancy in the stated reason for the revision of that service 
bulletin. We do not agree. Boeing issued Service Bulletin Information 
Notice DC10-53-111 IN 02, dated June 17, 2011, to clarify that fuselage 
317 was not added to the effectivity of Boeing Service Bulletin DC10-
53-111, Revision 7, dated March 16, 2011. No change to this final rule 
is necessary in this regard.

Explanation of Additional Changes Made To This AD

    We have revised certain headings throughout this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the 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 (77 FR 18719, March 28, 2012) for correcting the unsafe condition; 
and

[[Page 59730]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 18719, March 28, 2012).

Costs of Compliance

    We estimate that this AD affects 208 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
----------------------------------------------------------------------------------------------------------------
Installation, inspection, and    Up to 17 work-      Up to $4,169......  Up to $5,614......  Up to $1,167,712.
 resistance measurement           hours x $85 per
 [retained actions from           hour = $1,445.
 existing AD 2009-26-17,
 Amendment 39[dash]16156 (74 FR
 69268, December 31, 2009)].
Installation, inspection, and    Up to 16 work-      Up to $33,230.....  Up to $34,590.....  Up to $7,194,720.
 resistance measurement [new      hours x $85 per
 action].                         hour = $1,360.
----------------------------------------------------------------------------------------------------------------

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, 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) 
2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), and 
adding the following new AD:

2012-19-03 The Boeing Company: Amendment 39-17198; Docket No. FAA-
2012-0327; Directorate Identifier 2011-NM-125-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective November 5, 2012.

(b) Affected ADs

    This AD supersedes AD 2009-26-17, Amendment 39-16156 (74 FR 
69268, December 31, 2009).

(c) Applicability

    This AD applies to The Boeing Company Model DC-10-10, DC-10-10F, 
DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-
10-40F airplanes, and Model MD-10-10F and MD-10-30F airplanes that 
have been converted from Model DC-10 series airplanes; certificated 
in any category; as identified in paragraphs (c)(1) and (c)(2) of 
this AD, as applicable.
    (1) Boeing Service Bulletin DC10-53-109, Revision 8, dated March 
10, 2011 (for airplanes with extended wing-to-fuselage fillets).
    (2) Boeing Service Bulletin DC10-53-111, Revision 7, dated March 
16, 2011 (for airplanes with conventional wing-to-fuselage fillets).

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by fuel system reviews conducted by the 
manufacturer, and our determination that additional actions are 
necessary to address the identified unsafe condition. We are issuing 
this AD to reduce the potential of ignition sources inside fuel 
tanks in the event of a severe lightning strike, which, in 
combination with flammable fuel vapors, could result in fuel tank 
explosions and consequent loss of the airplane.

(f) Compliance

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

(g) Retained Requirements for Installation or Replacement for Certain 
Airplanes, With New Service Information

    This paragraph restates the installation or replacement 
requirements of paragraph (g) of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), with new service information. For 
airplanes with manufacturer's fuselage numbers identified in the 
applicable service bulletin listed in paragraph (g)(1) of this AD: 
Within 7,500 flight hours or 60 months after September 7, 2006 (the 
effective date of AD 2006-16-03, Amendment 39-14703 (71 FR 43962, 
August 3, 2006)), whichever occurs earlier: Install or replace with 
improved parts, as applicable, the bonding straps between the 
metallic frame of the fillet and the wing leading edge ribs, on both 
the left and right sides of the airplane, in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. After 
February 4, 2010 (the effective date of AD 2009-26-17), use the 
applicable service bulletin identified in paragraph (g)(2) or (g)(3) 
of this AD. After the effective date of this AD, use only the 
applicable service bulletin identified in paragraph (g)(3) of this

[[Page 59731]]

AD to do the actions required by this paragraph.
    (1) McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 4, 
dated October 7, 1992 (for airplanes with extended wing-to-fuselage 
fillets); or McDonnell Douglas DC-10 Service Bulletin 53-111, 
Revision 3, dated August 24, 1992 (for airplanes with conventional 
wing-to-fuselage fillets).
    (2) Boeing Service Bulletin DC10-53-109, Revision 7, dated March 
3, 2009 (for airplanes with extended wing-to-fuselage fillets); or 
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009 
(for airplanes with conventional wing-to-fuselage fillets).
    (3) Boeing Service Bulletin DC10-53-109, Revision 8, dated March 
10, 2011 (for airplanes with extended wing-to-fuselage fillets); or 
Boeing Service Bulletin
    DC10-53-111, Revision 7, dated March 16, 2011 (for airplanes 
with conventional wing-to-fuselage fillets).

(h) Retained Requirements for Installation or Replacement for Certain 
Other Airplanes, With New Service Information

    This paragraph restates the installation or replacement 
requirements of paragraph (h) of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), with new service information. For 
airplanes with fuselage numbers identified in the applicable service 
bulletin listed in paragraph (g)(2) of this AD that are not also 
identified in the applicable service bulletin listed in paragraph 
(g)(1) of this AD, except for airplanes identified in paragraph (i) 
or (j) of this AD: Within 7,500 flight hours or 60 months, whichever 
occurs first after February 4, 2010 (the effective date of AD 2009-
26-17), install or replace with improved parts, as applicable, the 
bonding straps between the metallic frame of the fillet and the wing 
leading edge ribs, on both the left and right sides of the airplane. 
Do the actions in accordance with the Accomplishment Instructions of 
the applicable service bulletin identified in paragraph (g)(2) or 
(g)(3) of this AD. After the effective date of this AD, use only the 
applicable service bulletin identified in paragraph (g)(3) of this 
AD to do the actions required by this paragraph.

(i) Retained Requirements for Strap Repositioning for Certain 
Airplanes, With New Service Information

    This paragraph restates the strap repositioning requirements of 
paragraph (i) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, 
December 31, 2009), with new service information. For Group 1-4, 
Configuration 3 airplanes, as identified in Boeing Service Bulletin 
DC10-53-109, Revision 7, dated March 3, 2009: Within 7,500 flight 
hours or 60 months after February 4, 2010 (the effective date of AD 
2009-26-17), whichever occurs first, do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD.
    (1) Remove two braided bonding straps and install two longer 
braided bonding straps between the metallic frame of the fillet and 
the wing leading edge ribs, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 7, 
dated March 3, 2009; or Boeing Service Bulletin DC10-53-109, 
Revision 8, dated March 10, 2011. After the effective date of this 
AD, use only Boeing Service Bulletin DC10-53-109, Revision 8, dated 
March 10, 2011, to do the actions required by this paragraph.
    (2) Measure the resistance of the previously installed bonding 
straps and, before further flight, do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 
2009; or Boeing Service Bulletin DC10-53-109, Revision 8, dated 
March 10, 2011. After the effective date of this AD, use only Boeing 
Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011, to 
do the actions required by this paragraph.

(j) Retained Requirements for Inspection and Corrective Action for 
Certain Airplanes, With New Service Information

    This paragraph restates the inspection requirements of paragraph 
(j) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 
2009), with new service information. For Group 1-2, Configuration 2 
airplanes, as identified in Boeing Service Bulletin DC10-53-111, 
Revision 6, dated March 3, 2009: Within 7,500 flight hours or 60 
months after February 4, 2010 (the effective date of AD 2009-26-17), 
whichever occurs first, do the actions specified in paragraphs 
(j)(1) and (j)(2) of this AD.
    (1) Do a general visual inspection to verify correct 
installation of the braided bonding straps (one left-hand wing and 
one right-hand wing) as shown in Sheet 7 in Figure 3 of Boeing 
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009, or 
Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16, 
2011; and, before further flight, do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 
2009, or Boeing Service Bulletin DC10-53-111, Revision 7, dated 
March 16, 2011. After the effective date of this AD, use only Boeing 
Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to 
do the actions required by this paragraph.
    (2) Measure the resistance of the previously installed bonding 
straps and, before further flight, do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 
2009; or Boeing Service Bulletin DC10-53-111, Revision 7, dated 
March 16, 2011. After the effective date of this AD, use only Boeing 
Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to 
do the actions required by this paragraph.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), (i), and (j) this AD, if those actions were 
accomplished before February 4, 2010 (the effective date of AD 2009-
26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009)), using 
Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 
2008; or Boeing Service Bulletin DC10-53-109, Revision 6, dated July 
10, 2008; as applicable; which are not incorporated by reference.

(l) New Installation and Corrective Actions for Certain Airplanes

    Within 7,500 flight hours or 60 months after the effective date 
of this AD, whichever comes first: Do the applicable actions 
specified in paragraphs (l)(1) through (l)(6) of this AD, as 
applicable.
    (1) For Group 1-4, Configurations 1 and 2 airplanes, as 
identified in Boeing Service Bulletin DC10-53-109, Revision 8, dated 
March 10, 2011, except airplanes that are identified in paragraph 
(g) of this AD: Remove any solid metal bonding straps and install 
seven new braided bonding straps, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin DC10-53-109, 
Revision 8, dated March 10, 2011.
    (2) For Group 1-4, Configurations 1 and 2 airplanes, as 
identified in Boeing Service Bulletin DC10-53-109, Revision 8, dated 
March 10, 2011, that are also identified in paragraph (g) of this 
AD: Remove any solid metal bonding straps not removed during the 
actions required by paragraph (g) of this AD and install a 7th new 
braided bonding strap (paragraph (g) of this AD requires installing 
6 straps), in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 
2011.
    (3) For Group 1-4, Configuration 3 airplanes, as identified in 
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 
2011, except airplanes identified in paragraph (i) of this AD: Do 
the actions specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this 
AD.
    (i) Replace one strap with new braided bonding strap, inspect to 
determine the existence of an installed solid metal bonding strap 
and replace any missing strap and any solid metal bonding strap with 
a new braided bonding strap, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8, 
dated March 10, 2011.
    (ii) Measure the electrical resistance across each bonding joint 
of the six previously-installed braided strap assemblies and verify 
that brackets have an acceptable fillet seal, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8, 
dated March 10, 2011. Do all applicable corrective actions before 
further flight.
    (4) For Group 1-4, Configuration 3 airplanes, as identified in 
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 
2011, that are also identified in paragraph (i) of this AD: Do the 
actions specified in paragraphs (l)(4)(i) and (l)(4)(ii) of this AD.
    (i) Inspect to determine the existence of an installed solid 
metal bonding strap and replace any missing strap and any solid 
metal bonding strap with a new braided bonding strap, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 
DC10-53-109, Revision 8, dated March 10, 2011.

[[Page 59732]]

    (ii) Measure the electrical resistance across each bonding joint 
of the six previously-installed braided strap assemblies and verify 
that brackets have an acceptable fillet seal, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8, 
dated March 10, 2011. Do all applicable corrective actions before 
further flight.
    (5) For Group 1-4, Configuration 4 airplanes, as identified in 
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 
2011: Do the actions specified in paragraphs (l)(5)(i) and 
(l)(5)(ii) of this AD.
    (i) Inspect to determine the existence of an installed solid 
metal bonding strap, and replace any missing strap and any solid 
metal bonding strap with a new braided bonding strap, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 
DC10-53-109, Revision 8, dated March 10, 2011.
    (ii) Measure the electrical resistance across each bonding joint 
of the six previously-installed braided strap assemblies and verify 
that brackets have an acceptable fillet seal, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8, 
dated March 10, 2011. Do all applicable corrective actions before 
further flight.
    (6) For Group 1-4, Configuration 5 airplanes, as identified in 
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10, 
2011: Inspect to determine the existence of an installed solid metal 
bonding strap, and replace any missing strap and any solid metal 
bonding strap with a new braided bonding strap, in accordance with 
the Accomplishment Instructions of Boeing Service Bulletin DC10-53-
109, Revision 8, dated March 10, 2011.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(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 the Related Information 
section 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 previously in accordance with AD 2006-16-03, 
Amendment 39-14703 (71 FR 43962, August 3, 2006), are approved as 
AMOCs for the corresponding provisions of paragraphs (g), (h), (i), 
and (j) of this AD.
    (4) AMOCs approved previously in accordance with AD 2009-26-17, 
Amendment 39-16156 (74 FR 69268, December 31, 2009), are approved as 
AMOCs for the corresponding provisions of paragraphs (g), (h), (i), 
and (j) of this AD.

(n) Related Information

    (1) For more information about this AD, contact Samuel Lee, 
Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; phone: 562-627-5262; fax: 562-627-5210; 
email: Samuel.Lee@faa.gov.
    (2) For service information specified in this AD that is not 
incorporated by reference, contact Boeing Commercial Airplanes, 
Attention: Data & Services Management, 3855 Lakewood Boulevard, MC 
D800-0019, Long Beach, California 90846-0001; telephone 206-544-
5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.

(o) 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 
November 5, 2012.
    (i) Boeing Service Bulletin DC10-53-109, Revision 8, dated March 
10, 2011.
    (ii) Boeing Service Bulletin DC10-53-111, Revision 7, dated 
March 16, 2011.
    (4) The following service information was approved for IBR on 
February 4, 2010 (74 FR 69268, December 31, 2009).
    (i) Boeing Service Bulletin DC10-53-109, Revision 7, dated March 
3, 2009.
    (ii) Boeing Service Bulletin DC10-53-111, Revision 6, dated 
March 3, 2009.
    (5) The following service information was approved for IBR on 
September 7, 2006 (71 FR 43962, August 3, 2006).
    (i) McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 4, 
dated October 7, 1992.
    (ii) McDonnell Douglas DC-10 Service Bulletin 53-111, Revision 
3, dated August 24, 1992.
    (6) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 
Internet https://www.myboeingfleet.
    (7) You may review copies of the 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.
    (8) You may also review copies of the 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: https://www.archives.gov/federal-register/cfr/ibr_locations.html.

    Issued in Renton, Washington, on September 11, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-23049 Filed 9-28-12; 8:45 am]
BILLING CODE 4910-13-P

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