AD 2009-26-17 Airworthiness Directives; McDonnell Douglas Corporation 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

Models named: DC-10 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to McDonnell Douglas Corporation 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 MD-10-10F and MD-10-30F airplanes that have been converted from Model DC-10 series airplanes; certificated in any category; with manufacturer's fuselage numbers as identified in the applicable service bulletin listed in Table 1 of this AD. Table 1—Applicability Boeing Service Bulletin— Revision— Dated— For airplanes with— DC10-53-109 7 March 3, 2009 Extended wing-to-fuselage fillets. DC10-53-111 6 March 3, 2009 Conventional wing-to-fuselage fillets.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2006-16-03, With New Service Information Installation or Replacement (g) For airplanes with manufacturer's fuselage numbers identified in the applicable service bulletin listed in Table 2 of this AD: Within 7,500 flight hours or 60 months after September 7, 2006 (the effective date of AD 2006-16-03), 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 Table 2 of this AD or Table 1 of this AD. After the effective date of this AD, use the applicable service bulletin identified in Table 1 of this AD. Table 2—Fuselage Numbers Affected by AD 2006-16-03 McDonnell Douglas DC-10 Service Bulletin— Revision— Dated— For airplanes with— 53-109 4 October 7, 1992 Extended wing-to-fuselage fillets. 53-111 3 August 24, 1992 Conventional wing-to-fuselage fillets. New Requirements of This AD Installation or Replacement (h) For airplanes with fuselage numbers not identified in Table 2 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 the effective date of this AD, 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 Table 1 of this AD. Strap Repositioning for Certain Airplanes (i) 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 the effective date of this AD, 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. (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. Inspection and Corrective Action for Certain Airplanes (j) 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 the effective date of this AD, 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, 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. (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. Credit for Actions Accomplished in Accordance With Previous Service Information (k) Actions accomplished before the effective date of this AD according to Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 2008; and Boeing Service Bulletin DC10-53-109, Revision 6, dated July 10, 2008; are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (AMOCs) (l)(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. Send information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5262; fax (562) 627-5210. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) AMOCs approved previously in accordance with AD 2006-16-03 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (m) You must use Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; and Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) 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; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (4) 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on December 17, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-30698 Filed 12-30-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from fuel system reviews conducted by the manufacturer. 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.