AD 2007-15-05 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

Models named: DC-10-10, DC-10-10F, DC-10-15, DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, MD-11F. Read the applicability below — it usually turns on serial or part numbers too.

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.

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. 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 On or adjacent to the flight engineer's fuel control panel Work Package 1—Part 1—Option 1—Aux Fuel Tank (Deactivation). 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 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 Work Package 1—Option 1—Part 1—Upper and Lower Aux Fuel Tanks (Deactivation) (DC-10/KDC-10). 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 Adjacent to display units 1 and 6 Work Package 1—Option 1—Part 1—Upper and Lower Aux Fuel Tanks (Deactivation) (MD-10). 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 Work Package 1—Option 1—Part 1—Upper, Lower and Aft Aux Fuel Tanks (Deactivation). 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 Work Package 1—Option 1—Part 1—Aft Fuselage Fuel Pump (Deactivation).   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 Work Package 2—Option 1—Part 1—Wing Tip Tank 1 and 3 Pumps (Deactivation).   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 Work Package 1—Option 1—Part 1—Upper and Lower Center Wing Fuel Tanks (Deactivation).   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 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 Work Package 1—Option 1—Part 1—Tank 2 (Placards Installation).   Within 90 days after the effective date of this AD Tail tank Work Package 2—Option 1—Part 1—Tail Tank (Deactivation).   Within 90 days after the effective date of this AD Not applicable Work Package 3—Option 1—Part 1—Upper Auxiliary Tank (Placards Installation).   Within 90 days after the effective date of this AD Lower auxiliary tank Work Package 4—Option 1—Part 1—Lower Auxiliary Tank (Deactivation). Group 2 Within 14 days after the effective date of this AD Forward auxiliary tank Work Package 1—Option 1—Part 1—Forward Auxiliary Tank (Deactivation).   Within 14 days after the effective date of this AD Not applicable Work Package 2—Option 1—Part 1—Tank 2 (Placards Installation).   Within 90 days after the effective date of this AD Tail tank Work Package 3—Option 1—Part 1—Tail Tank (Deactivation).   Within 90 days after the effective date of this AD Not applicable Work Package 4—Option 1—Part 1—Upper Auxiliary Tank (Placards Installation). Within 90 days after the effective date of this AD Lower auxiliary tank 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). 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 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 MD-10-10F and MD-10-30F airplanes Work Package 1—Option 1—Part 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 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 DC10-28A259 Original March 20, 2007. Boeing Alert Service Bulletin MD11-28A138 1 March 26, 2007. Boeing Flight Operations Bulletin DC-10-00-01A, MD-11-00-03A, and MD-10-00-02A Original September 20, 2000. (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: http://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

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.