Discussion \n\n\tWe have received a report indicating that the fuel pump housing electrical connector, part number (P/N) 60-84355, failed on two McDonnell Douglas MD-11 airplanes. The airplanes had accumulated 3,000 and 3,600 flight hours since installation of the electrical connector in accordance with Boeing Alert Service Bulletin MD11-28A113. The failures were attributed to arcing between the contacts in the potted backside of the electrical connector. Subsequent x-ray inspections of the electrical connectors revealed soldering problems with the connector contacts. Continued arcing following a short circuit of the fuel pump housing electrical connector could damage the conduit that protects the power lead inside the fuel tank. This condition, if not corrected, could create an ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. \n\n\tFuel pump housing electrical connector, P/N 60-84355, has also been installed on McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC- 10) airplanes, Model DC-10-40 and DC-10-40F airplanes, and Model MD-10- 10F and MD-10-30F airplanes, in accordance with Boeing Alert Service Bulletin DC10-28A229. Therefore, all of these models may be subject to the same unsafe condition. \n\nOther Relevant Rulemaking \n\n\tOn November 1, 2000, we issued AD 2000-22-21, amendment 39-11969 (65 FR 69658, November 20, 2000), for all McDonnell Douglas DC-10, MD- 10, and MD-11 series airplanes. That AD requires revising the airplane flight manual (AFM) to ensure that the flightcrew is advised of appropriate procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump electrical connector. For certain airplanes, that AD also requires revising the AFM to prohibit resetting of tripped fuel pump circuit breakers. Weapproved installation of fuel pump housing electrical connector, P/N 60-84355, in accordance with Boeing Alert Service Bulletin DC10-28A229 or MD11- 28A113, as applicable, as an alternative method of compliance (AMOC) for AD 2000-22-21. That AMOC allowed removal of certain interim operating procedures from the Procedures section of the FAA-approved AFM, which is required by paragraph (a) of AD 2000-22-21. This AD reintroduces that requirement, since we have determined that an unsafe condition exists on airplanes equipped with electrical connector P/N 60-84355. \n\n\tOn June 25, 2002, we issued AD 2002-13-10, amendment 39-12798 (67 FR 45053, July 8, 2002), for certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -30F (KC-10A and KDC-10), -40, and -40F airplanes; Model MD-10-10F and -30F airplanes; and Model MD-11 and -11F airplanes. That AD requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/transfer pump connectors; and corrective actions, if necessary. Accomplishing the optional replacement of all electrical connectors in accordance with paragraph (k) or (l) of this AD, as applicable, terminates the requirements of AD 2002-13-10. \n\n\tOn April 4, 2003, we issued AD 2003-07-14, amendment 39-13110 (68 FR 17544, April 10, 2003), for a certain McDonnell Douglas Model DC-10- 30 airplane. That AD requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/transfer pump connectors; and corrective actions, if necessary. Accomplishing the optional replacement of all electrical connectors in accordance with paragraph (k) of this AD terminates the requirements of AD 2003-07-14. \n\nRelevant Service Information \n\n\tWe have reviewed the following service bulletins: \n\n\tBoeing Alert Service Bulletin DC10-28A259, dated March 20, 2007, for Model DC-10-10 and DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, and Model MD-10-10F and MD-10- 30F airplanes. \n\n\tBoeing Alert Service Bulletin MD11-28A138, Revision 1, dated March 26, 2007, for Model MD-11 and MD-11F airplanes. \n\n\tBoeing Alert Service Bulletins DC10-28A259 and MD11-28A138 describe procedures for deactivating certain fuel tanks or fuel pumps, as applicable. The service bulletins also describe procedures for installing a placard on or adjacent to the flight engineer's fuel control panel or adjacent to display units 1 and 6, as applicable. The service bulletins also describe procedures for replacing fuel pump housing electrical connectors, P/N 60-84355, with new, improved electrical connectors, P/N 60-84355-1, and removing the placards after installing the new, improved electrical connectors. \n\n\tWe have also reviewed Boeing Flight Operations Bulletin DC-10-00- 01A, MD-11-00-03A, and MD-10-00-02A, dated September 20, 2000, for Model DC-10-10 and DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes, and Model DC-10- 40 and DC-10-40F airplanes, Model MD-11 and MD-11F airplanes, and Model MD-10-10F and MD-10-30F airplanes. Boeing Flight Operations Bulletin DC-10-00-01A, MD-11-00- 03A, and MD-10-00-02A provides instructions for revising the Procedures section of the FAA-approved AFM by inserting certain Interim Operating Procedures (IOPs). The IOPs advise the flightcrew of proper procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump housing electrical connector. \n\nFAA's Determination and Requirements of This AD \n\n\tThe unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. For this reason, we are issuing this AD to prevent continued arcing following a short circuit of the fuel pump housing electrical connector, which could damage the conduit that protects the power leadinside the fuel tank; this condition could create an ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. This AD requires an inspection to determine if fuel pump housing electrical connector, P/N 60-84355, is installed. If that electrical connector is installed, this AD requires the following additional actions: \n\n\tRevising the Procedures section of the FAA-approved AFM to advise the flightcrew of the appropriate procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump housing electrical connector. \n\n\tDeactivating certain fuel tanks or fuel pumps, as applicable. \n\n\tInstalling placards on or adjacent to the flight engineer's fuel control panel or adjacent to display units 1 and 6, as applicable. \n\n\tThis AD also allows the optional replacement of the fuel pump housing electrical connectors with new, improved parts, which would terminate the AFM revisions, deactivation of certain fuel tanks and fuel pumps, and placard installation. \n\nDifferences Between the AD and Boeing Alert Service Bulletin DC10- 28A259 \n\n\tThe Accomplishment Instructions of Boeing Alert Service Bulletin DC10-28A259 is divided into work packages for airplanes identified as Groups 1, 2, 3, 4, and 5. This AD does not require any action for Group 5 airplanes. Also, this AD does not require accomplishing Work Package 2 for Groups 1, 2, and 3 airplanes and does not require accomplishing Work Package 5 for Group 4 airplanes; these work packages describe procedures for replacing the affected electrical connectors on tanks 1, 2, and 3. \n\nDifferences Between the AD and Boeing Alert Service Bulletin MD11- 28A138 \n\n\tThe Accomplishment Instructions of Boeing Alert Service Bulletin MD11-28A138 is divided into work packages for airplanes identified as Groups 1 and 2. This AD does not require accomplishing Work Package 5 for Group 1 airplanes and doesnot require accomplishing Work Package 6 for Group 2 airplanes; these work packages describe procedures for replacing the affected electrical connectors on main tanks 1 and 3. \n\n\tThe compliance tables in paragraph 1.E. of Boeing Alert Service Bulletin MD11-28A138 recommend a compliance time of 10 days for accomplishing the following actions: (1) Work Package 1--Option 1--Part 1--Tank 2 (Placards Installation) for Group 1 airplanes, (2) Work Package 1--Option 1--Part 1--Forward Auxiliary Tank (Deactivation) for Group 2 airplanes, and (3) Work Package 2--Option 1--Part 1--Tank 2 (Placards Installation) for Group 2 airplanes. This AD, however, would require accomplishing those actions within 14 days after the effective date of this AD. We have coordinated this difference with Boeing. \n\nClarification of Boeing Alert Service Bulletin DC10-28A259 \n\n\tThe compliance table for Group 4 airplanes in paragraph 1.E. of Boeing Alert Service Bulletin DC10-28A259 identifies 5 work packages, oneof which is "Work Package 3--Upper and Lower Center Wing Tanks.'' However, the procedures for Work Package 3 are described under the headings, "Work Package 1--Option 1--Part 1--Upper and Lower Center Wing Fuel Tanks (Deactivation)'' and "Work Package 1--Option 1--Part 2 or Option 2--Upper and Lower Center Wing Fuel Tank (Connector Replacement)'' in the Accomplishment Instructions of the service bulletin. In this AD, we have referenced the headings for Work Package 3 exactly as they appear in the Accomplishment Instructions of the service bulletin. \n\nInterim Action \n\n\tWe consider this AD interim action. We are currently considering requiring replacement of all affected electrical connectors, which will constitute terminating action for the AFM revisions, deactivation of certain fuel tanks and fuel pumps, and placard installation required by this AD action. However, the planned compliance time for the replacement of all affected connectors would allow enough time to provide notice and opportunity for prior public comment on the merits of the modification. \n\nFAA's Determination of the Effective Date \n\n\tSince an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists to make this AD effective in less than 30 days. \n\nComments Invited \n\n\tThis AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include "Docket No. FAA-2007- 28749; Directorate Identifier 2007-NM-079-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. \n\n\tWe will post all comments we receive, without change, to http:// dms.dot.gov , including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov. \n\nExamining the Docket \n\n\tYou may examine the AD docket on the Internet at http:// dms.dot.gov , or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on ground floor of the West Building at the DOT street address stated inthe ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. \n\nAuthority for This Rulemaking \n\n\tTitle 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. \n\n\tWe 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. \n\nRegulatory Findings \n\n\tWe 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. \n\n\tFor the reasons discussed above, I certify that the regulation: \n\n\t1. Is not a "significant regulatory action'' under Executive Order 12866; \n\n\t2. Is not a "significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and \n\n\t3. 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. \n\n\tWe prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. \n\nList of Subjects in 14 CFR Part 39 \n\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. \n\nAdoption of the Amendment \n\nAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n 1. The authority citation for part 39 continues to read as follows: \n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\nSec. 39.13 (Amended) \n\n2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by adding the following new airworthiness directive (AD):