Airworthiness Directives; 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, Model MD-10-10F and MD-10-30F Airplanes, and Model MD-11 and MD-11F Airplanes, 40216-40222 [E7-14043]

Download as PDF 40216 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations pwalker on PROD1PC71 with RULES Because of rapid improvements in airplane technology, the applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. These special conditions for the 787 contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. On January 15, 2002, the FAA issued 14 CFR 25.795(a) (Amendment 25–106), which specifies that the flightdeck door of a transport airplane be designed to resist forcible intrusion by unauthorized persons and penetration by small arms fire and fragmentation devices. At the time it was written, the regulation was limited to the flightdeck door to expedite a rapid retrofit of the existing airplanes required by operating rules to have a flightdeck door. In addition to a reinforced flightdeck door, the 787 will have a flightdeck bulkhead which is reinforced to resist intrusion and ballistic penetration. The regulations do not adequately address the certification requirements for such a bulkhead, and appropriate certification standards are necessary. These special conditions require that the reinforced flightdeck bulkhead meet the same standards as those specified in § 25.795(a) for flightdeck doors. These special conditions contain the minimum standards that the Administrator considers necessary to ensure that safety standards are maintained after the aircraft enters into service. On December 21, 2006, the FAA issued a notice of proposed rulemaking that proposes amending § 25.795(a) to require that a flightdeck bulkhead—and any other accessible barrier separating the flightcrew compartment from occupied areas—also be designed to resist intrusion or penetration. The methods of compliance described in the preamble of that notice and associated draft advisory material could be used to show compliance with these special conditions. For the 787, the reinforced bulkhead may be comprised of components such as the walls of adjacent lavatories, galleys, or crew rest areas. Those components are covered by these special conditions. Discussion of Comments Notice of Proposed Special Conditions No. 25–07–08–SC for the 787 was published in the Federal Register on April 12, 2007 (72 FR 18412). One comment was received, from Air Line Pilots Association, International (ALPA). ALPA Comment: ALPA recommended that the requirements of these special VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 conditions apply to future versions of the 787, including possible freighter configurations. FAA Response: These special conditions apply to airplanes that incorporate a reinforced bulkhead. They are not limited to any particular type of operation, nor do they impose operational requirements. Thus, if a future freighter version did incorporate a reinforced bulkhead, these special conditions would apply. These special conditions are adopted as proposed. Issued in Renton, Washington, on July 12, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–14333 Filed 7–23–07; 8:45 am] Applicability [Docket No. FAA–2007–28749; Directorate Identifier 2007–NM–079–AD; Amendment 39–15134; AD 2007–15–05] As discussed above, these special conditions are applicable to the 787. Should Boeing apply at a later date for a change to the type certificate to include another model on the same type certificate incorporating the same novel or unusual design features, these special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features of the 787. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Boeing Model 787–8 airplane. In addition to the requirements of 14 CFR 25.795(a) governing protection of the flightdeck door, the following special conditions apply. I The reinforced bulkhead, including components that comprise the bulkhead, separating the flightcrew compartment from occupied areas must be designed to meet the following standards: It must resist forcible intrusion by unauthorized persons and be capable of withstanding impacts of 300 Joules (221.3 foot-pounds) at critical locations on the bulkhead as well as a 1113 Newton (250 pound) constant tensile load on accessible handholds. It must resist penetration by small arms fire and fragmentation devices to a level equivalent to level IIIa of the National Institute of Justice Standard (NIJ) 0101.04. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; 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, Model MD–10–10F and MD–10–30F Airplanes, and Model MD–11 and MD–11F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all transport category airplanes identified above. This AD requires an inspection to determine if a certain fuel pump housing electrical connector is installed. This AD also requires a revision to the FAA-approved airplane flight manual (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 if applicable. This AD also requires the deactivation of certain fuel tanks or fuel pumps and the installation of placards if applicable. This AD 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. This AD results from a report of two failures of the fuel pump housing electrical connector. 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 lead inside 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 E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations pwalker on PROD1PC71 with RULES explosion and consequent loss of the airplane. DATES: This AD becomes effective August 8, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 8, 2007. On December 5, 2000 (65 FR 69658, November 20, 2000), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in the AD. We must receive comments on this AD by September 24, 2007. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • 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. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Philip C. Kush, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5263; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion We 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. VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 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. Fuel 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. Other Relevant Rulemaking On 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. We approved 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. On 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 40217 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. On 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. Relevant Service Information We have reviewed the following service bulletins: • Boeing 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. • Boeing Alert Service Bulletin MD11–28A138, Revision 1, dated March 26, 2007, for Model MD–11 and MD– 11F airplanes. Boeing 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. We 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 E:\FR\FM\24JYR1.SGM 24JYR1 40218 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 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. FAA’s Determination and Requirements of This AD The 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 lead inside 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: • Revising 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. • Deactivating certain fuel tanks or fuel pumps, as applicable. • Installing placards on or adjacent to the flight engineer’s fuel control panel or adjacent to display units 1 and 6, as applicable. This 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. pwalker on PROD1PC71 with RULES Differences Between the AD and Boeing Alert Service Bulletin DC10–28A259 The 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 VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 affected electrical connectors on tanks 1, 2, and 3. Differences Between the AD and Boeing Alert Service Bulletin MD11–28A138 The 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 does not 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. The 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. Clarification of Boeing Alert Service Bulletin DC10–28A259 The compliance table for Group 4 airplanes in paragraph 1.E. of Boeing Alert Service Bulletin DC10–28A259 identifies 5 work packages, one of 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. Interim Action We 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 connectors would allow enough time to provide notice and opportunity for prior public comment on the merits of the modification. FAA’s Determination of the Effective Date Since 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. Comments Invited This 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. We will post all comments we receive, without change, to https:// 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 https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://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 in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 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 the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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. We 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. 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: I pwalker on PROD1PC71 with RULES PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2007–15–05 McDonnell Douglas: Amendment 39–15134. Docket No. FAA–2007–28749; Directorate Identifier 2007–NM–079–AD. Effective Date (a) This AD becomes effective August 8, 2007. Affected ADs (b) Accomplishing paragraph (k) or (l) of this AD, as applicable, terminates the requirements of AD 2002–13–10, amendment 39–12798, the requirements of AD 2003–07– 14, amendment 39–13110, and the requirements of paragraph (a) of AD 2000– 22–21, amendment 39–11969. Applicability (c) This AD applies to all 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, Model MD–10–10F and MD–10–30F airplanes, and Model MD– 11 and MD–11F airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report of two failures of the fuel pump housing electrical connectors. 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 lead inside 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. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin References (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable: (1) 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: Boeing Alert Service Bulletin DC10–28A259, dated March 20, 2007; and PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 40219 (2) For Model MD–11 and MD–11F airplanes: Boeing Alert Service Bulletin MD11–28A138, Revision 1, dated March 26, 2007. Inspection To Determine Part Number (P/N) (g) For all airplanes: Within 14 days after the effective date of this AD, inspect the fuel pump housing electrical connector to determine if P/N 60–84355 is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the fuel pump housing electrical connector can be conclusively determined from that review. If P/N 60– 84355 is installed, accomplish the applicable actions specified in paragraphs (h), (i), and (j) of this AD. Airplane Flight Manual (AFM) Revision of Procedures Section (h) For all airplanes equipped with fuel pump housing electrical connector P/N 60– 84355: Within 14 days after the effective date of this AD, insert the applicable Interim Operating Procedures regarding abnormal operations for failure of the fuel pump housing electrical connector into the Procedures section of the FAA-approved AFM, in accordance with Boeing Flight Operations Bulletin DC–10–00–01A, MD–11– 00–03A, and MD–10–00–02A, dated September 20, 2000. Accomplishing the applicable actions specified in paragraph (k) or (l) of this AD, as applicable, terminates the requirements of this paragraph and the corresponding requirements specified in paragraph (i) or (j) of this AD, as applicable. Deactivation of Fuel Tanks and Placard Installation for DC–10/MD–10 Airplanes (i) 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 identified in the applicable service bulletin as Group 1, 2, 3, or 4 airplanes and equipped with fuel pump housing electrical connector P/N 60– 84355: At the applicable time specified in Table 1 of this AD, deactivate the applicable fuel tank(s) and applicable fuel pumps and install a placard at the applicable location specified in Table 1 of this AD, in accordance with the applicable work package of the Accomplishment Instructions of the applicable service bulletin. For the placard installation required by this paragraph, alternative placard location and wording may be used if approved by an appropriate FAA Principal Operations Inspector. Accomplishing the applicable actions specified in paragraph (k) of this AD terminates the corresponding requirements of this paragraph and the AFM revision required by paragraph (h) of this AD. E:\FR\FM\24JYR1.SGM 24JYR1 40220 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations TABLE 1.—REQUIREMENTS FOR MODEL DC–10 AND MODEL MD–10 AIRPLANES Airplanes Compliance time Deactivated fuel tank(s) or fuel pump Placard location Work package Group 1 ............................. Within 90 days after the effective date of this AD. Auxiliary fuel tank .............. Group 2: 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. Group 2: Model MD–10– 10F and MD–10–30F airplanes. Within 90 days after the effective date of this AD. Upper and lower auxiliary fuel tanks. On or adjacent to the flight engineer’s fuel control panel. On or adjacent to the flight engineer’s fuel control panel. Work Package 1—Part 1— Option 1—Aux Fuel Tank (Deactivation). Work Package 1—Option 1—Part 1—Upper and Lower Aux Fuel Tanks (Deactivation) (DC–10/ KDC–10). Within 90 days after the effective date of this AD. Upper and lower auxiliary fuel tanks. Adjacent to display units 1 and 6. Group 3 ............................. Within 90 days after the effective date of this AD. Upper, lower, and aft fuel tanks. On or adjacent to the flight engineer’s fuel control panel. Group 4 ............................. Within 14 days after the effective date of this AD. Fuel pump for aft fuselage tank. On or adjacent to the flight engineer’s fuel control panel. Within 14 days after the effective date of this AD. Fuel pumps for wing tip tanks 1 and 3. On or adjacent to the flight engineer’s fuel control panel. Within 90 days after the effective date of this AD. Upper and lower center wing tanks. On or adjacent to the flight engineer’s fuel control panel. Within 90 days after the effective date of this AD. Fuel pump for forward fuselage tank. On or adjacent to the flight engineer’s fuel control panel. Work Package 1—Option 1—Part 1—Upper and Lower Aux Fuel Tanks (Deactivation) (MD–10). Work Package 1—Option 1—Part 1—Upper, Lower and Aft Aux Fuel Tanks (Deactivation). Work Package 1—Option 1—Part 1—Aft Fuselage Fuel Pump (Deactivation). Work Package 2—Option 1—Part 1—Wing Tip Tank 1 and 3 Pumps (Deactivation). Work Package 1—Option 1—Part 1—Upper and Lower Center Wing Fuel Tanks (Deactivation). Work Package 4—Option 1—Part 1—Fwd Fuselage Fuel Pump (Deactivation). Deactivation of Fuel Tanks and Placard Installation for MD–11/–11F Airplanes (j) For Model MD–11 and MD–11F airplanes identified in the applicable service bulletin as Group 1 and 2 airplanes and equipped with fuel pump housing electrical connector P/N 60–84355: At the applicable time specified in Table 2 of this AD, deactivate the applicable fuel tanks specified in Table 2 of this AD and install a placard adjacent to display units 1 and 6, in accordance with the applicable work package of the Accomplishment Instructions of the applicable service bulletin. For the placard installation required by this paragraph, alternative placard location and wording may be used if approved by an appropriate FAA Principal Operations Inspector. Accomplishing the applicable actions specified in paragraph (l) of this AD terminates the corresponding requirements of this paragraph and the AFM revision required by paragraph (h) of this AD. TABLE 2.—REQUIREMENTS FOR MODEL MD–11 AND MD–11F AIRPLANES Airplanes Compliance time Deactivated fuel tanks Work package Group 1 .......................................... Within 14 days after the effective date of this AD. Not applicable ............................... Within 90 days after the effective date of this AD. Within 90 days after the effective date of this AD. Tail tank ........................................ Within 90 days after the effective date of this AD. Lower auxiliary tank ...................... Within 14 days after the effective date of this AD. Forward auxiliary tank .................. Within 14 days after the effective date of this AD. Not applicable ............................... Within 90 days after the effective date of this AD. Tail tank ........................................ Work Package 1—Option 1—Part 1—Tank 2 (Placards Installation). Work Package 2—Option 1—Part 1—Tail Tank (Deactivation). Work Package 3—Option 1—Part 1—Upper Auxiliary Tank (Placards Installation). Work Package 4—Option 1—Part 1—Lower Auxiliary Tank (Deactivation). Work Package 1—Option 1—Part 1—Forward Auxiliary Tank (Deactivation). Work Package 2—Option 1—Part 1—Tank 2 (Placards Installation). Work Package 3—Option 1—Part 1—Tail Tank (Deactivation). pwalker on PROD1PC71 with RULES Group 2 .......................................... VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 PO 00000 Frm 00006 Fmt 4700 Not applicable ............................... Sfmt 4700 E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations 40221 TABLE 2.—REQUIREMENTS FOR MODEL MD–11 AND MD–11F AIRPLANES—Continued Airplanes Compliance time Deactivated fuel tanks Work package Within 90 days after the effective date of this AD. Not applicable ............................... Within 90 days after the effective date of this AD. Lower auxiliary tank ...................... Work Package 4—Option 1—Part 1—Upper Auxiliary Tank (Placards Installation). Work Package 5—Option 1—Part 1—Lower Auxiliary Tank (Deactivation). Optional Terminating Action for DC–10/MD– 10 Airplanes (k) 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 identified in the applicable service bulletin as Group 1, 2, 3, or 4 airplanes and equipped with fuel pump housing electrical connector P/N 60– 84355: As an option, replace all fuel pump housing electrical connectors, P/N 60–84355, with new, improved electrical connectors, P/ N 60–84355–1, and remove the applicable placards, in accordance with the applicable work package(s) of the Accomplishment Instructions of the applicable service bulletin as specified in Table 3 of this AD. Accomplishing the applicable actions specified in this paragraph terminates the corresponding requirements of paragraph (i) of this AD and the AFM revision required by paragraph (h) of this AD. TABLE 3.—OPTIONAL WORK PACKAGES FOR MODEL DC–10 AND MODEL MD–10 AIRPLANES Airplanes Work package Group 1 ..................................................................................................... Work Package 1—Option 1—Part 2 or Option 2—Aux Fuel Tank (Connector Replacement). Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower Aux Fuel Tanks (DC–10/KDC–10) (Connector Replacement). Group 2: 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. Group 2: Model MD–10–10F and MD–10–30F airplanes ........................ Group 3 ..................................................................................................... Group 4 ..................................................................................................... Optional Terminating Action for MD–11/– 11F Airplanes (l) For Model MD–11 and MD–11F airplanes identified in the applicable service bulletin as Group 1 and 2 airplanes and equipped with fuel pump housing electrical Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower Aux Fuel Tanks (MD–10) (Connector Replacement). Work Package 1—Option 1—Part 2 or Option 2—Upper, Lower and Aft Aux Fuel Tanks (Connector Replacement). Work Package 1—Option 1—Part 2 or Option 2—Aft Fuselage Fuel Pump (Connector Replacement). Work Package 2—Option 1—Part 2 or Option 2—Wing Tip Tanks 1 and 3 (Connector Replacement). Work Package 1—Option 1—Part 2 or Option 2—Upper and Lower Center Wing Fuel Tanks (Connector Replacement). Work Package 4—Option 1—Part 2 or Option 2—Fwd Fuselage Fuel Pump (Connector Replacement). connector P/N 60–84355: As an option, replace all fuel pump housing electrical connectors, P/N 60–84355, with new, improved electrical connectors, P/N 60– 84355–1, and remove the applicable placards, in accordance with the applicable work packages of the Accomplishment Instructions of the applicable service bulletin as specified in Table 4 of this AD. Accomplishing the applicable actions specified in this paragraph terminates the corresponding requirements of paragraph (j) of this AD and the AFM revision required by paragraph (h) of this AD. TABLE 4.—OPTIONAL WORK PACKAGES FOR MODEL MD–11 AND MD–11F AIRPLANES Airplanes Group 1 ................................ pwalker on PROD1PC71 with RULES Group 2 ................................ Work package Work Work Work Work Work Work Work Work Work Package Package Package Package Package Package Package Package Package 1—Option 2—Option 3—Option 4—Option 1—Option 2—Option 3—Option 4—Option 5—Option 1—Part 2 or Option 2—Tank 2 (Connector Replacement). 1—Part 2 or Option 2—Tail Tank (Connector Replacement). 1—Part 2 or Option 2—Upper Auxiliary Tank (Connector Replacement). 1—Part 2 or Option 2—Lower Auxiliary Tank (Connector Replacement). 1—Part 2 or Option 2—Forward Auxiliary Tank (Connector Replacement). 1 Part 2 or Option 2—Tank 2 (Connector Replacement). 1—Part 2 or Option 2—Tail Tank (Connector Replacement). 1—Part 2 or Option 2—Upper Auxiliary Tank (Connector Replacement). 1—Part 2 or Option 2—Lower Auxiliary Tank (Connector Replacement). Parts Installation Terminating Action for AD 2002–13–10 (m) For all airplanes: As of the effective date of this AD, no person may install a fuel pump housing electrical connector, P/N 60– 84355, on any airplane. (n) Replacing all fuel pump housing electrical connectors, P/N 60–84355, with new, improved parts in accordance with paragraph (k) or (l) of this AD, as applicable, terminates the requirements of AD 2002–13– 10. Terminating Action for AD 2003–07–14 VerDate Aug<31>2005 17:17 Jul 23, 2007 Jkt 211001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 (o) Replacing all fuel pump housing electrical connectors, P/N 60–84355, with E:\FR\FM\24JYR1.SGM 24JYR1 40222 Federal Register / Vol. 72, No. 141 / Tuesday, July 24, 2007 / Rules and Regulations new, improved parts in accordance with paragraph (k) of this AD terminates the requirements of AD 2003–07–14. Alternative Methods of Compliance (AMOCs) Terminating Action for Paragraph (a) of AD 2000–22–21 (p) Replacing all fuel pump housing electrical connectors, P/N 60–84355, with new, improved parts in accordance with paragraph (k) or (l) of this AD, as applicable, terminates the requirements of paragraph (a) of AD 2000–22–21. (q)(1) The Manager, Los Angeles Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (r) You must use the service information identified in Table 5 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 5.—MATERIAL INCORPORATED BY REFERENCE Service information Revision level Boeing Alert Service Bulletin DC10–28A259 .......................................... Boeing Alert Service Bulletin MD11–28A138 ......................................... Boeing Flight Operations Bulletin DC–10–00–01A, MD–11–00–03A, and MD–10–00–02A. Original .......................................... 1 ..................................................... Original .......................................... (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin DC10–28A259, dated March 20, 2007; and Boeing Alert Service Bulletin MD11–28A138, Revision 1, dated March 26, 2007; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On December 5, 2000 (65 FR 69658, November 20, 2000), the Director of the Federal Register approved the incorporation by reference of Boeing Flight Operations Bulletin DC–10–00–01A, MD–11–00–03A, and MD–10–00–02A, dated September 20, 2000. (3) Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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 July 13, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–14043 Filed 7–23–07; 8:45 am] pwalker on PROD1PC71 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 17:17 Jul 23, 2007 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27268; Directorate Identifier 2006–NM–190–AD; Amendment 39–15135; AD 2007–15–06] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. This AD becomes effective August 28, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 28, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building, Ground Floor, Room W12–140, 1200 DATES: Jkt 211001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Date March 20, 2007. March 26, 2007. September 20, 2000. New Jersey Avenue, SE., Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 the ground floor of the West Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Airbus Model A318, A319, A320, and A321 airplanes. That NPRM was published in the Federal Register on February 22, 2007 (72 FR 7936). That NPRM proposed to require revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the single comment received. The commenter, Airbus, supports the NPRM. E:\FR\FM\24JYR1.SGM 24JYR1

Agencies

[Federal Register Volume 72, Number 141 (Tuesday, July 24, 2007)]
[Rules and Regulations]
[Pages 40216-40222]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-14043]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28749; Directorate Identifier 2007-NM-079-AD;
Amendment 39-15134; AD 2007-15-05]
RIN 2120-AA64

Airworthiness Directives; 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, Model MD-10-10F and MD-10-30F Airplanes, and Model MD-11 and
MD-11F Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
transport category airplanes identified above. This AD requires an
inspection to determine if a certain fuel pump housing electrical
connector is installed. This AD also requires a revision to the FAA-
approved airplane flight manual (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
if applicable. This AD also requires the deactivation of certain fuel
tanks or fuel pumps and the installation of placards if applicable.
This AD 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. This AD results from a report of two failures
of the fuel pump housing electrical connector. 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 lead inside 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

[[Page 40217]]

explosion and consequent loss of the airplane.

DATES: This AD becomes effective August 8, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 8,
2007.
On December 5, 2000 (65 FR 69658, November 20, 2000), the Director
of the Federal Register approved the incorporation by reference of a
certain other publication listed in the AD.
We must receive comments on this AD by September 24, 2007.

ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
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.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for service information
identified in this AD.

FOR FURTHER INFORMATION CONTACT: Philip C. Kush, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5263; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Discussion

We 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.
Fuel 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.

Other Relevant Rulemaking

On 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. We approved
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.
On 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.
On 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.

Relevant Service Information

We have reviewed the following service bulletins:
Boeing 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.
Boeing Alert Service Bulletin MD11-28A138, Revision 1,
dated March 26, 2007, for Model MD-11 and MD-11F airplanes.
Boeing 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.
We 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

[[Page 40218]]

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.

FAA's Determination and Requirements of This AD

The 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 lead inside 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:
Revising 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.
Deactivating certain fuel tanks or fuel pumps, as
applicable.
Installing placards on or adjacent to the flight
engineer's fuel control panel or adjacent to display units 1 and 6, as
applicable.
This 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.

Differences Between the AD and Boeing Alert Service Bulletin DC10-
28A259

The 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.

Differences Between the AD and Boeing Alert Service Bulletin MD11-
28A138

The 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 does not 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.
The 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.

Clarification of Boeing Alert Service Bulletin DC10-28A259

The compliance table for Group 4 airplanes in paragraph 1.E. of
Boeing Alert Service Bulletin DC10-28A259 identifies 5 work packages,
one of 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.

Interim Action

We 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.

FAA's Determination of the Effective Date

Since 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.

Comments Invited

This 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.
We will post all comments we receive, without change, to https://
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
https://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at https://
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 in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System receives them.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I,

[[Page 40219]]

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 the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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.
We 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):

2007-15-05 McDonnell Douglas: Amendment 39-15134. Docket No. FAA-
2007-28749; Directorate Identifier 2007-NM-079-AD.

Effective Date

(a) This AD becomes effective August 8, 2007.

Affected ADs

(b) Accomplishing paragraph (k) or (l) of this AD, as
applicable, terminates the requirements of AD 2002-13-10, amendment
39-12798, the requirements of AD 2003-07-14, amendment 39-13110, and
the requirements of paragraph (a) of AD 2000-22-21, amendment 39-
11969.

Applicability

(c) This AD applies to all 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, Model MD-10-10F and MD-10-30F airplanes, and Model
MD-11 and MD-11F airplanes, certificated in any category.

Unsafe Condition

(d) This AD results from a report of two failures of the fuel
pump housing electrical connectors. 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 lead inside 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.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Service Bulletin References

(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the following service bulletins, as
applicable:
(1) 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: Boeing Alert Service Bulletin DC10-
28A259, dated March 20, 2007; and
(2) For Model MD-11 and MD-11F airplanes: Boeing Alert Service
Bulletin MD11-28A138, Revision 1, dated March 26, 2007.

Inspection To Determine Part Number (P/N)

(g) For all airplanes: Within 14 days after the effective date
of this AD, inspect the fuel pump housing electrical connector to
determine if P/N 60-84355 is installed. A review of airplane
maintenance records is acceptable in lieu of this inspection if the
part number of the fuel pump housing electrical connector can be
conclusively determined from that review. If P/N 60-84355 is
installed, accomplish the applicable actions specified in paragraphs
(h), (i), and (j) of this AD.

Airplane Flight Manual (AFM) Revision of Procedures Section

(h) For all airplanes equipped with fuel pump housing electrical
connector P/N 60-84355: Within 14 days after the effective date of
this AD, insert the applicable Interim Operating Procedures
regarding abnormal operations for failure of the fuel pump housing
electrical connector into the Procedures section of the FAA-approved
AFM, in accordance with Boeing Flight Operations Bulletin DC-10-00-
01A, MD-11-00-03A, and MD-10-00-02A, dated September 20, 2000.
Accomplishing the applicable actions specified in paragraph (k) or
(l) of this AD, as applicable, terminates the requirements of this
paragraph and the corresponding requirements specified in paragraph
(i) or (j) of this AD, as applicable.

Deactivation of Fuel Tanks and Placard Installation for DC-10/MD-10
Airplanes

(i) 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 identified in the applicable service
bulletin as Group 1, 2, 3, or 4 airplanes and equipped with fuel
pump housing electrical connector P/N 60-84355: At the applicable
time specified in Table 1 of this AD, deactivate the applicable fuel
tank(s) and applicable fuel pumps and install a placard at the
applicable location specified in Table 1 of this AD, in accordance
with the applicable work package of the Accomplishment Instructions
of the applicable service bulletin. For the placard installation
required by this paragraph, alternative placard location and wording
may be used if approved by an appropriate FAA Principal Operations
Inspector. Accomplishing the applicable actions specified in
paragraph (k) of this AD terminates the corresponding requirements
of this paragraph and the AFM revision required by paragraph (h) of
this AD.

[[Page 40220]]

Table 1.--Requirements for Model DC-10 and Model MD-10 Airplanes
----------------------------------------------------------------------------------------------------------------
Deactivated fuel
Airplanes Compliance time tank(s) or fuel Placard location Work package
pump
----------------------------------------------------------------------------------------------------------------
Group 1......................... Within 90 days Auxiliary fuel On or adjacent to Work Package 1--
after the tank. the flight Part 1--Option 1--
effective date of engineer's fuel Aux Fuel Tank
this AD. control panel. (Deactivation).
Group 2: Model DC-10-10 and DC- Within 90 days Upper and lower On or adjacent to Work Package 1--
10-10F airplanes, Model DC-10- after the auxiliary fuel the flight Option 1--Part 1--
15 airplanes, Model DC-10-30 effective date of tanks. engineer's fuel Upper and Lower
and DC-10-30F (KC-10A and KDC- this AD. control panel. Aux Fuel Tanks
10) airplanes, and Model DC-10- (Deactivation)
40 and DC-10-40F airplanes. (DC-10/KDC-10).
Group 2: Model MD-10-10F and MD- Within 90 days Upper and lower Adjacent to Work Package 1--
10-30F airplanes. after the auxiliary fuel display units 1 Option 1--Part 1--
effective date of tanks. and 6. Upper and Lower
this AD. Aux Fuel Tanks
(Deactivation)
(MD-10).
Group 3......................... Within 90 days Upper, lower, and On or adjacent to Work Package 1--
after the aft fuel tanks. the flight Option 1--Part 1--
effective date of engineer's fuel Upper, Lower and
this AD. control panel. Aft Aux Fuel
Tanks
(Deactivation).
Group 4......................... Within 14 days Fuel pump for aft On or adjacent to Work Package 1--
after the fuselage tank. the flight Option 1--Part 1--
effective date of engineer's fuel Aft Fuselage Fuel
this AD. control panel. Pump
(Deactivation).
Within 14 days Fuel pumps for On or adjacent to Work Package 2--
after the wing tip tanks 1 the flight Option 1--Part 1--
effective date of and 3. engineer's fuel Wing Tip Tank 1
this AD. control panel. and 3 Pumps
(Deactivation).
Within 90 days Upper and lower On or adjacent to Work Package 1--
after the center wing tanks. the flight Option 1--Part 1--
effective date of engineer's fuel Upper and Lower
this AD. control panel. Center Wing Fuel
Tanks
(Deactivation).
Within 90 days Fuel pump for On or adjacent to Work Package 4--
after the forward fuselage the flight Option 1--Part 1--
effective date of tank. engineer's fuel Fwd Fuselage Fuel
this AD. control panel. Pump
(Deactivation).
----------------------------------------------------------------------------------------------------------------

Deactivation of Fuel Tanks and Placard Installation for MD-11/-11F
Airplanes

(j) For Model MD-11 and MD-11F airplanes identified in the
applicable service bulletin as Group 1 and 2 airplanes and equipped
with fuel pump housing electrical connector P/N 60-84355: At the
applicable time specified in Table 2 of this AD, deactivate the
applicable fuel tanks specified in Table 2 of this AD and install a
placard adjacent to display units 1 and 6, in accordance with the
applicable work package of the Accomplishment Instructions of the
applicable service bulletin. For the placard installation required
by this paragraph, alternative placard location and wording may be
used if approved by an appropriate FAA Principal Operations
Inspector. Accomplishing the applicable actions specified in
paragraph (l) of this AD terminates the corresponding requirements
of this paragraph and the AFM revision required by paragraph (h) of
this AD.

Table 2.--Requirements for Model MD-11 and MD-11F Airplanes
----------------------------------------------------------------------------------------------------------------
Airplanes Compliance time Deactivated fuel tanks Work package
----------------------------------------------------------------------------------------------------------------
Group 1.............................. Within 14 days after Not applicable......... Work Package 1--Option
the effective date of 1--Part 1--Tank 2
this AD. (Placards
Installation).
Within 90 days after Tail tank.............. Work Package 2--Option
the effective date of 1--Part 1--Tail Tank
this AD. (Deactivation).
Within 90 days after Not applicable......... Work Package 3--Option
the effective date of 1--Part 1--Upper
this AD. Auxiliary Tank
(Placards
Installation).
Within 90 days after Lower auxiliary tank... Work Package 4--Option
the effective date of 1--Part 1--Lower
this AD. Auxiliary Tank
(Deactivation).
Group 2.............................. Within 14 days after Forward auxiliary tank. Work Package 1--Option
the effective date of 1--Part 1--Forward
this AD. Auxiliary Tank
(Deactivation).
Within 14 days after Not applicable......... Work Package 2--Option
the effective date of 1--Part 1--Tank 2
this AD. (Placards
Installation).
Within 90 days after Tail tank.............. Work Package 3--Option
the effective date of 1--Part 1--Tail Tank
this AD. (Deactivation).

[[Page 40221]]

Within 90 days after Not applicable......... Work Package 4--Option
the effective date of 1--Part 1--Upper
this AD. Auxiliary Tank
(Placards
Installation).
Within 90 days after Lower auxiliary tank... Work Package 5--Option
the effective date of 1--Part 1--Lower
this AD. Auxiliary Tank
(Deactivation).
----------------------------------------------------------------------------------------------------------------

Optional Terminating Action for DC-10/MD-10 Airplanes

(k) 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 identified in the applicable service
bulletin as Group 1, 2, 3, or 4 airplanes and equipped with fuel
pump housing electrical connector P/N 60-84355: As an option,
replace all fuel pump housing electrical connectors, P/N 60-84355,
with new, improved electrical connectors, P/N 60-84355-1, and remove
the applicable placards, in accordance with the applicable work
package(s) of the Accomplishment Instructions of the applicable
service bulletin as specified in Table 3 of this AD. Accomplishing
the applicable actions specified in this paragraph terminates the
corresponding requirements of paragraph (i) of this AD and the AFM
revision required by paragraph (h) of this AD.

Table 3.--Optional Work Packages for Model DC-10 and Model MD-10
Airplanes
------------------------------------------------------------------------
Airplanes Work package
------------------------------------------------------------------------
Group 1................................ Work Package 1--Option 1--Part
2 or Option 2--Aux Fuel Tank
(Connector Replacement).
Group 2: Model DC-10-10 and DC-10-10F Work Package 1--Option 1--Part
airplanes, Model DC-10-15 airplanes, 2 or Option 2--Upper and Lower
Model DC-10-30 and DC-10-30F (KC-10A Aux Fuel Tanks (DC-10/KDC-10)
and KDC-10) airplanes, and Model DC-10- (Connector Replacement).
40 and DC-10-40F airplanes.
Group 2: Model MD-10-10F and MD-10-30F Work Package 1--Option 1--Part
airplanes. 2 or Option 2--Upper and Lower
Aux Fuel Tanks (MD-10)
(Connector Replacement).
Group 3................................ Work Package 1--Option 1--Part
2 or Option 2--Upper, Lower
and Aft Aux Fuel Tanks
(Connector Replacement).
Group 4................................ Work Package 1--Option 1--Part
2 or Option 2--Aft Fuselage
Fuel Pump (Connector
Replacement).
Work Package 2--Option 1--Part
2 or Option 2--Wing Tip Tanks
1 and 3 (Connector
Replacement).
Work Package 1--Option 1--Part
2 or Option 2--Upper and Lower
Center Wing Fuel Tanks
(Connector Replacement).
Work Package 4--Option 1--Part
2 or Option 2--Fwd Fuselage
Fuel Pump (Connector
Replacement).
------------------------------------------------------------------------

Optional Terminating Action for MD-11/-11F Airplanes

(l) For Model MD-11 and MD-11F airplanes identified in the
applicable service bulletin as Group 1 and 2 airplanes and equipped
with fuel pump housing electrical connector P/N 60-84355: As an
option, replace all fuel pump housing electrical connectors, P/N 60-
84355, with new, improved electrical connectors, P/N 60-84355-1, and
remove the applicable placards, in accordance with the applicable
work packages of the Accomplishment Instructions of the applicable
service bulletin as specified in Table 4 of this AD. Accomplishing
the applicable actions specified in this paragraph terminates the
corresponding requirements of paragraph (j) of this AD and the AFM
revision required by paragraph (h) of this AD.

Table 4.--Optional Work Packages for Model MD-11 and MD-11F Airplanes
------------------------------------------------------------------------
Airplanes Work package
------------------------------------------------------------------------
Group 1...................... Work Package 1--Option 1--Part 2 or
Option 2--Tank 2 (Connector
Replacement).
Work Package 2--Option 1--Part 2 or
Option 2--Tail Tank (Connector
Replacement).
Work Package 3--Option 1--Part 2 or
Option 2--Upper Auxiliary Tank
(Connector Replacement).
Work Package 4--Option 1--Part 2 or
Option 2--Lower Auxiliary Tank
(Connector Replacement).
Group 2...................... Work Package 1--Option 1--Part 2 or
Option 2--Forward Auxiliary Tank
(Connector Replacement).
Work Package 2--Option 1 Part 2 or Option
2--Tank 2 (Connector Replacement).
Work Package 3--Option 1--Part 2 or
Option 2--Tail Tank (Connector
Replacement).
Work Package 4--Option 1--Part 2 or
Option 2--Upper Auxiliary Tank
(Connector Replacement).
Work Package 5--Option 1--Part 2 or
Option 2--Lower Auxiliary Tank
(Connector Replacement).
------------------------------------------------------------------------

Parts Installation

(m) For all airplanes: As of the effective date of this AD, no
person may install a fuel pump housing electrical connector, P/N 60-
84355, on any airplane.

Terminating Action for AD 2002-13-10

(n) Replacing all fuel pump housing electrical connectors, P/N
60-84355, with new, improved parts in accordance with paragraph (k)
or (l) of this AD, as applicable, terminates the requirements of AD
2002-13-10.

Terminating Action for AD 2003-07-14

(o) Replacing all fuel pump housing electrical connectors, P/N
60-84355, with

[[Page 40222]]

new, improved parts in accordance with paragraph (k) of this AD
terminates the requirements of AD 2003-07-14.

Terminating Action for Paragraph (a) of AD 2000-22-21

(p) Replacing all fuel pump housing electrical connectors, P/N
60-84355, with new, improved parts in accordance with paragraph (k)
or (l) of this AD, as applicable, terminates the requirements of
paragraph (a) of AD 2000-22-21.

Alternative Methods of Compliance (AMOCs)

(q)(1) The Manager, Los Angeles Aircraft Certification Office,
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.

Material Incorporated by Reference

(r) You must use the service information identified in Table 5
of this AD to perform the actions that are required by this AD,
unless the AD specifies otherwise.

Table 5.--Material Incorporated by Reference
------------------------------------------------------------------------
Service information Revision level Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin Original.......... March 20, 2007.
DC10-28A259.
Boeing Alert Service Bulletin 1................. March 26, 2007.
MD11-28A138.
Boeing Flight Operations Original.......... September 20,
Bulletin DC-10-00-01A, MD-11-00- 2000.
03A, and MD-10-00-02A.
------------------------------------------------------------------------

(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin DC10-
28A259, dated March 20, 2007; and Boeing Alert Service Bulletin
MD11-28A138, Revision 1, dated March 26, 2007; in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On December 5, 2000 (65 FR 69658, November 20, 2000), the
Director of the Federal Register approved the incorporation by
reference of Boeing Flight Operations Bulletin DC-10-00-01A, MD-11-
00-03A, and MD-10-00-02A, dated September 20, 2000.
(3) Contact Boeing Commercial Airplanes, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention:
Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of
this service information. You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or 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 July 13, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-14043 Filed 7-23-07; 8:45 am]
BILLING CODE 4910-13-P

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