Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes, 45135-45139 [E9-20994]

Download as PDF Federal Register / Vol. 74, No. 168 / Tuesday, September 1, 2009 / Proposed Rules Issued in Kansas City, Missouri on August 20, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–21057 Filed 8–31–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0186; Directorate Identifier 2007–NM–226–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC– 10A and KDC–10), DC–10–40, DC–10– 40F, MD–10–10F, and MD–10–30F Airplanes mstockstill on DSKH9S0YB1PROD with PROPOSALS AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. SUMMARY: We are revising an earlier proposed airworthiness directive (AD) for certain McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC– 10–30, DC–10–30F (KC–10A and KDC– 10), DC–10–40, DC–10–40F, MD–10– 10F, and MD–10–30F airplanes. That action (the first supplemental NPRM) would have superseded an existing AD that currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. The first supplemental NPRM proposed to add a requirement to reposition or replace two bonding straps for certain airplanes. This action resulted from fuel system reviews conducted by the manufacturer. This second supplemental NPRM would add, for certain airplanes, a bondingresistance check and an inspection to determine correct installation of certain bonding straps, and applicable corrective actions. We are proposing this second supplemental NPRM to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this supplemental NPRM by September 28, 2009. ADDRESSES: You may send comments by any of the following methods: VerDate Nov<24>2008 16:30 Aug 31, 2009 Jkt 217001 • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221 or 425–227–1152. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5262; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0186; Directorate Identifier 2007–NM–226–AD’’ at the beginning of your comments. We specifically invite PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 45135 comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued a notice of proposed rulemaking (NPRM) (the ‘‘first supplemental NPRM’’) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain McDonnell Douglas Model DC– 10–10, DC–10–10F, DC–10–15, DC–10– 30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes. The first supplemental NPRM was published in the Federal Register on November 26, 2008 (73 FR 71957). The first supplemental NPRM would have superseded an existing AD that currently requires installing or replacing with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane. The first supplemental NPRM proposed to add a requirement to reposition or replace two bonding straps for certain airplanes. Actions Since First Supplemental NPRM Was Issued Since we issued the first supplemental NPRM, Boeing has issued Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009; and Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009. We cited Boeing Service Bulletin DC10–53–109, Revision 6, dated July 10, 2008; and Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008; in the first supplemental NPRM. The newly revised service bulletins contain the same procedures as the earlier revisions along with the following changes: • Boeing Service Bulletin DC10–53– 109, Revision 7, dated March 3, 2009, provides instructions to measure the electrical resistance of certain previously installed braided bonding straps and correct any failed resistance checks. The corrective action includes cleaning and installing the braided bonding strap assembly. • Boeing Service Bulletin DC10–53– 111, Revision 6, dated March 3, 2009, incorporates comments from operators E:\FR\FM\01SEP1.SGM 01SEP1 45136 Federal Register / Vol. 74, No. 168 / Tuesday, September 1, 2009 / Proposed Rules to clarify service bulletin instructions, including instructions for Group 1–2 airplanes, Configuration 2, to check the electrical resistance for bonding straps previously installed and correct any failed resistance checks. The corrective action includes cleaning and installing the braided bonding strap assembly. This service bulletin also includes an inspection to determine correct installation of braided bonding straps, and corrective action if necessary, for Group 1–2 airplanes, Configuration 2. The corrective action is repositioning braided bonding straps and replacing fasteners. We have also approved the revised service bulletins as alternative methods of compliance (AMOCs) for the requirements of AD 2006–16–03. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the sole commenter, FedEx Express (FedEx). mstockstill on DSKH9S0YB1PROD with PROPOSALS Support for the NPRM FedEx applauds the FAA’s decision to include ‘‘AMOCs approved previously in accordance with AD 2006–16–03 * * * as AMOCs for the corresponding provisions of this AD.’’ This statement allows FedEx to use its previously obtained AMOC, dated May 24, 2007, for compliance with the bulk of the proposed requirements, without the need for additional FAA approval. Any additional work required by the AD can be incorporated into FedEx’s existing modification program using the AD as approval. Request To Provide Additional Information FedEx requests that the section of the first supplemental NPRM titled ‘‘Actions Since Original NPRM Was Issued’’ include the following statement: ‘‘[Boeing] Service Bulletin DC10–53– 109, Revision 5, now includes an action to reposition two bonding straps by using new bonding straps that are less susceptible to cracking.’’ FedEx notes that while this statement comes directly from the service bulletin section titled ‘‘Reason for Revision,’’ an examination of the changes to Boeing Service Bulletin DC10–53–109, Revision 5, dated March 19, 2008, indicates that the straps in question, which were installed according to McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992, are identical to the straps that replace them in Revision 5, except the replacement straps are 2 inches longer. Revision 6, dated July 10, 2008, of this service bulletin corrects the VerDate Nov<24>2008 16:30 Aug 31, 2009 Jkt 217001 previous statement in the ‘‘Reason’’ section as follows: ‘‘Revision 5 was sent to incorporate engineering released subsequent to Revision 4 of this service bulletin, which replaces an existing braided bonding strap (each side) with a new longer braided bonding strap that is less susceptible to chafing structure.’’ To avoid confusion, FedEx requests that we revise corresponding language in the AD to something similar to the following: ‘‘[Boeing] Service Bulletin DC10–53–109, Revision 5, now includes an action to remove and replace two bonding straps installed via Revision 4 of the service bulletin with longer bonding straps.’’ We acknowledge FedEx’s concern that this language may be confusing. However, the section of the AD preamble referenced by the commenter does not appear in this second supplemental NPRM. In addition, as stated previously, this second supplemental NPRM refers to Revision 7 of Boeing Service Bulletin DC10–53– 109, dated March 3, 2009, which contains the correct information in regard to this issue. Request To Change ‘‘Reason for Revision’’ FedEx requests that we revise the reason for using Boeing Service Bulletin DC10–53–109, Revision 6, dated July 10, 2008, in the first supplemental NPRM to read ‘‘Revision 6 of Service Bulletin DC10–53–109 provides a faster and easier method of replacing the two bonding straps that require replacement per Revision 5, and corrects some part number errors.’’ FedEx also suggests that we revise the reason for using Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008, as noted in the first supplemental NPRM, to read ‘‘In addition to the effectivity correction, Revision 5 of Service Bulletin DC10–53–111 requires the repositioning of two braided bonding straps installed on certain aircraft configuration via Revision 4 and all configurations via Service Bulletin revisions released prior to Revision 4.’’ We acknowledge FedEx’s suggestions that the prior revisions of the service bulletins need to be clarified. However, the section of the AD preamble referenced by the commenter does not appear in this second supplemental NPRM. In addition, this second supplemental NPRM refers to Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009; and Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009; which contain the correct information in regard to this issue. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Request To Revise Paragraph (h) of the First Supplemental NPRM FedEx requests that we revise paragraph (h) of the first supplemental NPRM to indicate that the action is to ‘‘remove two braided bonding straps and install two longer braided bonding straps between the metallic frame of the fillet and the wing leading edge ribs’’ in lieu of ‘‘reposition two bonding straps.’’ We concur with FedEx, and the requested changes in paragraph (h) of the first supplemental NPRM are incorporated in the new reidentified paragraph (i)(1) of this second supplemental NPRM. In addition, FedEx believes that additional work is required for all airplanes previously modified in accordance with McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992. We agree with FedEx’s request to provide clarification. Airplanes that were modified in accordance with McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992, also require an electrical resistance measurement of previously installed braided bonding straps to be in compliance with the proposed requirements of this second supplemental NPRM. Revision 7 of McDonnell Douglas DC–10 Service Bulletin 53–109, dated March 3, 2009, clarifies the additional work required. We have revised paragraph (h) of the first supplemental NPRM (now paragraph (i) of this second supplmenetal NPRM) to specify the additional work required and that the additional work be accomplished in accordance with McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 7, dated March 3, 2009. Request To Clarify Procedures in Service Bulletin DC10–53–111, Revision 5 FedEx notes the following issues in Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008: • In Figure 3, the requirement to remove and install all strap brackets should be removed. Only require a conductivity check of the previously installed strap (with the exception of the single strap that will need to be relocated) with any additional rework based on the results of the conductivity check. Also include the strap to fillet seal and encapsulate with sealant all strap attach points. • The groups and configurations callouts should be revised to distinguish airplanes that did or did not receive metal bonding straps in production and distinguish those on which a previous E:\FR\FM\01SEP1.SGM 01SEP1 Federal Register / Vol. 74, No. 168 / Tuesday, September 1, 2009 / Proposed Rules version of Boeing Service Bulletin DC10–53–111 was or was not done. • The fastener pattern in Figure 1 should be corrected by removing the middle rivet of the three rivets indicated by ‘‘2’’ in the figure and the rivet to the left of those three rivets. This would leave the figure with six evenly spaced rivets on the edge of the stiffener that receives the installation. It also makes the figure match the work instruction. • The compliance section should be revised so that steps 6 through 13 of Figure 3 of Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008, must be done on all airplanes that have been modified per Figures 1 or 2 of Boeing Service Bulletin DC10– 53–111, Revision 4, dated September 21, 2006. We infer that FedEx wants us to revise this second supplemental NPRM to provide the correct information. We agree. As stated previously, this second supplemental NPRM refers to Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009, which contains the correct information in regard to these issues. Request To Clarify Procedures in Service Bulletin DC10–53–109 FedEx requests the following clarifications of configurations and electrical bonding requirements in Boeing Service Bulletin DC10–53–109, Revision 6, dated July 10, 2008: • Configuration 3 should apply only to airplanes previously accomplished per Boeing Service Bulletin DC10–53– 109, Revision 5, dated March 19, 2008, instead of McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992. • Configurations accomplished in accordance with McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 1, dated August 14, 1981; McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 2, dated October 28, 1983; McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 3, dated November 14, 1986; and McDonnell Douglas DC–10 Service Bulletin 53–109, Revision 4, dated October 7, 1992; should each have their own specific configuration. All previous braided straps are removed and reinstalled using proper electrical bonding procedures. • All references to actions taken for Configuration 3 airplanes should refer to removing braided bonding straps and installing new, longer braided bonding straps. We concur with FedEx’s comments that the proper electrical bonding procedures and/or clarifications be provided in the associated Boeing service bulletins. As stated previously, this second supplemental NPRM now refers to Boeing Service Bulletin DC10– 53–109, Revision 7, dated March 3, 2009, which contains instructions for conductivity checks for all previously installed braided bonding straps, as requested by FedEx. In addition, we note that Configuration 3 applies only to aircraft previously modified per McDonnell Douglas DC–10 Service 45137 Bulletin 53–109, Revision 4, dated October 7, 1992, of this service bulletin, not Boeing Service Bulletin DC10–53– 109, Revision 5, dated March 19, 2008, as FedEx commented. Explanation of Additional Paragraph in the Supplemental NPRM We have added a new paragraph (d) to this supplemental NPRM to provide the Air Transport Association (ATA) of America code. This code is added to make this supplemental NPRM parallel with other new AD actions. We have reidentified subsequent paragraphs accordingly. FAA’s Determination and Proposed Requirements of the Supplemental NPRM We are proposing this second supplemental NPRM because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Certain changes described above expand the scope of the first supplemental NPRM. As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this second supplemental NPRM. Costs of Compliance We estimate that this proposed AD would affect 280 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Work hours Average labor rate per hour Parts Cost per product Number of U.S.-registered airplanes 2–17 ............ $80 Up to $4,169 ................................ Up to $5,529 ................................ 281 mstockstill on DSKH9S0YB1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for VerDate Nov<24>2008 16:30 Aug 31, 2009 Jkt 217001 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Fleet cost Up to $1,553,649. For the reasons discussed above, I certify this proposed 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. E:\FR\FM\01SEP1.SGM 01SEP1 45138 Federal Register / Vol. 74, No. 168 / Tuesday, September 1, 2009 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (b) This AD supersedes AD 2006–16–03. [Amended] 2. The FAA amends § 39.13 by removing amendment 39–14703 (71 FR 43962, August 3, 2006) and adding the following new AD: McDonnell Douglas: Docket No. FAA–2007– 0186; Directorate Identifier 2007–NM– 226–AD. Comments Due Date (a) We must receive comments by September 28, 2009. 1. The authority citation for part 39 continues to read as follows: Affected ADs Applicability (c) This AD applies to McDonnell Douglas Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC– 10), DC–10–40, and DC–10–40F airplanes, and MD–10–10F and MD–10–30F airplanes that have been converted from Model DC–10 series airplanes; certificated in any category; with manufacturer’s fuselage numbers as identified in the applicable service bulletin listed in Table 1 of this AD. TABLE 1—APPLICABILITY Boeing Service Bulletin— Revision— DC10–53–109 .......................................... DC10–53–111 .......................................... Dated— 7 6 Subject For airplanes with— March 3, 2009 ......................................... March 3, 2009 ......................................... Extended wing-to-fuselage fillets. Conventional wing-to-fuselage fillets. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks in the event of a severe lightning strike, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Restatement of Requirements of AD 2006– 16–03 With New Service Information Installation or Replacement (g) For airplanes with manufacturer’s fuselage numbers identified in the applicable service bulletin listed in Table 2 of this AD: Within 7,500 flight hours or 60 months after September 7, 2006 (the effective date of AD 2006–16–03), whichever occurs earlier: Install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD or Table 1 of this AD. After the effective date of this AD, use the applicable service bulletin identified in Table 1 of this AD. TABLE 2—FUSELAGE NUMBERS AFFECTED BY AD 2006–16–03 McDonnell Douglas DC-10 Service Bulletin— Revision— 53-109 ...................................................... 53–111 ..................................................... 4 3 New Requirements of This AD Installation or Replacement mstockstill on DSKH9S0YB1PROD with PROPOSALS Dated— (h) For airplanes with fuselage numbers not identified in Table 2 of this AD except for airplanes identified in paragraph (i) or (j) of this AD: Within 7,500 flight hours or 60 months, whichever occurs first after the effective date of this AD, install or replace with improved parts, as applicable, the bonding straps between the metallic frame of the fillet and the wing leading edge ribs, on both the left and right sides of the airplane, and reposition two bonding straps. Do the actions in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 1 of this AD. For airplanes with— October 7, 1992 ...................................... August 24, 1992 ...................................... Extended wing-to-fuselage fillets. Conventional wing-to-fuselage fillets. 60 months after the effective date of this AD, whichever occurs first, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Remove two braided bonding straps and install two longer braided bonding straps between the metallic frame of the fillet and the wing leading edge ribs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009. (2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009. Strap Repositioning for Certain Airplanes (i) For Group 1–4, Configuration 3 airplanes, as identified in Boeing Service Bulletin DC10–53–109, Revision 7, dated March 3, 2009: Within 7,500 flight hours or Inspection and Corrective Action for Certain Airplanes March 3, 2009: Within 7,500 flight hours or 60 months after the effective date of this AD, whichever occurs first, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) Do a general visual inspection to verify correct installation of the braided bonding strap, and, before further flight, do all applicable corrective actions, in accordance with Accomplishment Instructions of Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009. (2) Measure the resistance of the previously installed bonding straps and, before further flight, do all applicable corrective actions, in accordance with Accomplishment Instructions of Boeing Service Bulletin DC10–53–111, Revision 6, dated March 3, 2009. (j) For Group 1–2, Configuration 2 airplanes, as identified in Boeing Service Bulletin DC10–53–111, Revision 6, dated VerDate Nov<24>2008 16:30 Aug 31, 2009 Jkt 217001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\01SEP1.SGM 01SEP1 Federal Register / Vol. 74, No. 168 / Tuesday, September 1, 2009 / Proposed Rules Credit for Actions Accomplished In Accordance With Previous Service Information (k) Actions accomplished before the effective date of this AD according to Boeing Service Bulletin DC10–53–111, Revision 5, dated March 19, 2008; and Boeing Service Bulletin DC10–53–109, Revision 6, dated July 10, 2008; are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712– 4137; telephone (562) 627–5262; fax (562) 627–5210. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) AMOCs approved previously in accordance with AD 2006–16–03 are approved as AMOCs for the corresponding provisions of this AD. Issued in Renton, Washington, on August 17, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–20994 Filed 8–31–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0763; Directorate Identifier 2007–NM–301–AD] RIN 2120–AA64 mstockstill on DSKH9S0YB1PROD with PROPOSALS Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) VerDate Nov<24>2008 18:00 Aug 31, 2009 Jkt 217001 originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Excessive wear and tear of the backlash remover mechanism has been found several times on Goodrich Part Number (P/N) 23400– 3B and P/N 23400–7 elevator booster control units (BCU), while corrosion has been found on some components in other BCU. The wear and tear may result in a (partly) blocked operation of the elevator system in the normal (hydraulic) mode, while any corrosion may result in deteriorated elevator control when the BCU is in MANUAL mode. * * * * * The unsafe condition is wear and tear, and corrosion of the backlash remover mechanism, which can cause a (partly) blocked operation of the elevator system in the normal (hydraulic) mode and deteriorated elevator control when the BCU is in MANUAL mode, which could result in loss of control of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by October 16, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252– 627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@ stork.com; Internet https:// www.myfokkerfleet.com. For Goodrich service information identified in this proposed AD, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville L6L5Y7, Ontario, Canada; telephone 905–825–1568; e-mail jean.breed@goodrich.com; Internet https://www.goodrich.com/TechPubs. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 45139 Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0763; Directorate Identifier 2007–NM–301–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0032, dated February 17, 2009 (referred to after this as ‘‘the MCAI’’), to correct an E:\FR\FM\01SEP1.SGM 01SEP1

Agencies

[Federal Register Volume 74, Number 168 (Tuesday, September 1, 2009)]
[Proposed Rules]
[Pages 45135-45139]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0186; Directorate Identifier 2007-NM-226-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, 
DC-10-40F, MD-10-10F, and MD-10-30F Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, 
DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-
10F, and MD-10-30F airplanes. That action (the first supplemental NPRM) 
would have superseded an existing AD that currently requires installing 
or replacing with improved parts, as applicable, the bonding straps 
between the metallic frame of the fillet and the wing leading edge 
ribs, on both the left and right sides of the airplane. The first 
supplemental NPRM proposed to add a requirement to reposition or 
replace two bonding straps for certain airplanes. This action resulted 
from fuel system reviews conducted by the manufacturer. This second 
supplemental NPRM would add, for certain airplanes, a bonding-
resistance check and an inspection to determine correct installation of 
certain bonding straps, and applicable corrective actions. We are 
proposing this second supplemental NPRM to reduce the potential of 
ignition sources inside fuel tanks in the event of a severe lightning 
strike, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

DATES: We must receive comments on this supplemental NPRM by September 
28, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at the 
FAA, call 425-227-1221 or 425-227-1152.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5262; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0186; 
Directorate Identifier 2007-NM-226-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued a notice of proposed rulemaking (NPRM) (the ``first 
supplemental NPRM'') to amend 14 CFR part 39 to include an 
airworthiness directive (AD) that would apply to certain McDonnell 
Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-
10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 
airplanes. The first supplemental NPRM was published in the Federal 
Register on November 26, 2008 (73 FR 71957).
    The first supplemental NPRM would have superseded an existing AD 
that currently requires installing or replacing with improved parts, as 
applicable, the bonding straps between the metallic frame of the fillet 
and the wing leading edge ribs, on both the left and right sides of the 
airplane. The first supplemental NPRM proposed to add a requirement to 
reposition or replace two bonding straps for certain airplanes.

Actions Since First Supplemental NPRM Was Issued

    Since we issued the first supplemental NPRM, Boeing has issued 
Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; and 
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009. We cited 
Boeing Service Bulletin DC10-53-109, Revision 6, dated July 10, 2008; 
and Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 
2008; in the first supplemental NPRM. The newly revised service 
bulletins contain the same procedures as the earlier revisions along 
with the following changes:
     Boeing Service Bulletin DC10-53-109, Revision 7, dated 
March 3, 2009, provides instructions to measure the electrical 
resistance of certain previously installed braided bonding straps and 
correct any failed resistance checks. The corrective action includes 
cleaning and installing the braided bonding strap assembly.
     Boeing Service Bulletin DC10-53-111, Revision 6, dated 
March 3, 2009, incorporates comments from operators

[[Page 45136]]

to clarify service bulletin instructions, including instructions for 
Group 1-2 airplanes, Configuration 2, to check the electrical 
resistance for bonding straps previously installed and correct any 
failed resistance checks. The corrective action includes cleaning and 
installing the braided bonding strap assembly. This service bulletin 
also includes an inspection to determine correct installation of 
braided bonding straps, and corrective action if necessary, for Group 
1-2 airplanes, Configuration 2. The corrective action is repositioning 
braided bonding straps and replacing fasteners.
    We have also approved the revised service bulletins as alternative 
methods of compliance (AMOCs) for the requirements of AD 2006-16-03.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the sole commenter, 
FedEx Express (FedEx).

Support for the NPRM

    FedEx applauds the FAA's decision to include ``AMOCs approved 
previously in accordance with AD 2006-16-03 * * * as AMOCs for the 
corresponding provisions of this AD.'' This statement allows FedEx to 
use its previously obtained AMOC, dated May 24, 2007, for compliance 
with the bulk of the proposed requirements, without the need for 
additional FAA approval. Any additional work required by the AD can be 
incorporated into FedEx's existing modification program using the AD as 
approval.

Request To Provide Additional Information

    FedEx requests that the section of the first supplemental NPRM 
titled ``Actions Since Original NPRM Was Issued'' include the following 
statement: ``[Boeing] Service Bulletin DC10-53-109, Revision 5, now 
includes an action to reposition two bonding straps by using new 
bonding straps that are less susceptible to cracking.'' FedEx notes 
that while this statement comes directly from the service bulletin 
section titled ``Reason for Revision,'' an examination of the changes 
to Boeing Service Bulletin DC10-53-109, Revision 5, dated March 19, 
2008, indicates that the straps in question, which were installed 
according to McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 
4, dated October 7, 1992, are identical to the straps that replace them 
in Revision 5, except the replacement straps are 2 inches longer. 
Revision 6, dated July 10, 2008, of this service bulletin corrects the 
previous statement in the ``Reason'' section as follows: ``Revision 5 
was sent to incorporate engineering released subsequent to Revision 4 
of this service bulletin, which replaces an existing braided bonding 
strap (each side) with a new longer braided bonding strap that is less 
susceptible to chafing structure.''
    To avoid confusion, FedEx requests that we revise corresponding 
language in the AD to something similar to the following: ``[Boeing] 
Service Bulletin DC10-53-109, Revision 5, now includes an action to 
remove and replace two bonding straps installed via Revision 4 of the 
service bulletin with longer bonding straps.''
    We acknowledge FedEx's concern that this language may be confusing. 
However, the section of the AD preamble referenced by the commenter 
does not appear in this second supplemental NPRM. In addition, as 
stated previously, this second supplemental NPRM refers to Revision 7 
of Boeing Service Bulletin DC10-53-109, dated March 3, 2009, which 
contains the correct information in regard to this issue.

Request To Change ``Reason for Revision''

    FedEx requests that we revise the reason for using Boeing Service 
Bulletin DC10-53-109, Revision 6, dated July 10, 2008, in the first 
supplemental NPRM to read ``Revision 6 of Service Bulletin DC10-53-109 
provides a faster and easier method of replacing the two bonding straps 
that require replacement per Revision 5, and corrects some part number 
errors.'' FedEx also suggests that we revise the reason for using 
Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 2008, 
as noted in the first supplemental NPRM, to read ``In addition to the 
effectivity correction, Revision 5 of Service Bulletin DC10-53-111 
requires the repositioning of two braided bonding straps installed on 
certain aircraft configuration via Revision 4 and all configurations 
via Service Bulletin revisions released prior to Revision 4.''
    We acknowledge FedEx's suggestions that the prior revisions of the 
service bulletins need to be clarified. However, the section of the AD 
preamble referenced by the commenter does not appear in this second 
supplemental NPRM. In addition, this second supplemental NPRM refers to 
Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; 
and Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 
2009; which contain the correct information in regard to this issue.

Request To Revise Paragraph (h) of the First Supplemental NPRM

    FedEx requests that we revise paragraph (h) of the first 
supplemental NPRM to indicate that the action is to ``remove two 
braided bonding straps and install two longer braided bonding straps 
between the metallic frame of the fillet and the wing leading edge 
ribs'' in lieu of ``reposition two bonding straps.''
    We concur with FedEx, and the requested changes in paragraph (h) of 
the first supplemental NPRM are incorporated in the new reidentified 
paragraph (i)(1) of this second supplemental NPRM.
    In addition, FedEx believes that additional work is required for 
all airplanes previously modified in accordance with McDonnell Douglas 
DC-10 Service Bulletin 53-109, Revision 4, dated October 7, 1992.
    We agree with FedEx's request to provide clarification. Airplanes 
that were modified in accordance with McDonnell Douglas DC-10 Service 
Bulletin 53-109, Revision 4, dated October 7, 1992, also require an 
electrical resistance measurement of previously installed braided 
bonding straps to be in compliance with the proposed requirements of 
this second supplemental NPRM. Revision 7 of McDonnell Douglas DC-10 
Service Bulletin 53-109, dated March 3, 2009, clarifies the additional 
work required. We have revised paragraph (h) of the first supplemental 
NPRM (now paragraph (i) of this second supplmenetal NPRM) to specify 
the additional work required and that the additional work be 
accomplished in accordance with McDonnell Douglas DC-10 Service 
Bulletin 53-109, Revision 7, dated March 3, 2009.

Request To Clarify Procedures in Service Bulletin DC10-53-111, Revision 
5

    FedEx notes the following issues in Boeing Service Bulletin DC10-
53-111, Revision 5, dated March 19, 2008:
     In Figure 3, the requirement to remove and install all 
strap brackets should be removed. Only require a conductivity check of 
the previously installed strap (with the exception of the single strap 
that will need to be relocated) with any additional rework based on the 
results of the conductivity check. Also include the strap to fillet 
seal and encapsulate with sealant all strap attach points.
     The groups and configurations callouts should be revised 
to distinguish airplanes that did or did not receive metal bonding 
straps in production and distinguish those on which a previous

[[Page 45137]]

version of Boeing Service Bulletin DC10-53-111 was or was not done.
     The fastener pattern in Figure 1 should be corrected by 
removing the middle rivet of the three rivets indicated by ``2'' in the 
figure and the rivet to the left of those three rivets. This would 
leave the figure with six evenly spaced rivets on the edge of the 
stiffener that receives the installation. It also makes the figure 
match the work instruction.
     The compliance section should be revised so that steps 6 
through 13 of Figure 3 of Boeing Service Bulletin DC10-53-111, Revision 
5, dated March 19, 2008, must be done on all airplanes that have been 
modified per Figures 1 or 2 of Boeing Service Bulletin DC10-53-111, 
Revision 4, dated September 21, 2006.
    We infer that FedEx wants us to revise this second supplemental 
NPRM to provide the correct information. We agree. As stated 
previously, this second supplemental NPRM refers to Boeing Service 
Bulletin DC10-53-111, Revision 6, dated March 3, 2009, which contains 
the correct information in regard to these issues.

Request To Clarify Procedures in Service Bulletin DC10-53-109

    FedEx requests the following clarifications of configurations and 
electrical bonding requirements in Boeing Service Bulletin DC10-53-109, 
Revision 6, dated July 10, 2008:
     Configuration 3 should apply only to airplanes previously 
accomplished per Boeing Service Bulletin DC10-53-109, Revision 5, dated 
March 19, 2008, instead of McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 4, dated October 7, 1992.
     Configurations accomplished in accordance with McDonnell 
Douglas DC-10 Service Bulletin 53-109, Revision 1, dated August 14, 
1981; McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 2, 
dated October 28, 1983; McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 3, dated November 14, 1986; and McDonnell Douglas DC-10 
Service Bulletin 53-109, Revision 4, dated October 7, 1992; should each 
have their own specific configuration.
    All previous braided straps are removed and reinstalled using 
proper electrical bonding procedures.
     All references to actions taken for Configuration 3 
airplanes should refer to removing braided bonding straps and 
installing new, longer braided bonding straps.
    We concur with FedEx's comments that the proper electrical bonding 
procedures and/or clarifications be provided in the associated Boeing 
service bulletins. As stated previously, this second supplemental NPRM 
now refers to Boeing Service Bulletin DC10-53-109, Revision 7, dated 
March 3, 2009, which contains instructions for conductivity checks for 
all previously installed braided bonding straps, as requested by FedEx. 
In addition, we note that Configuration 3 applies only to aircraft 
previously modified per McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 4, dated October 7, 1992, of this service bulletin, not 
Boeing Service Bulletin DC10-53-109, Revision 5, dated March 19, 2008, 
as FedEx commented.

Explanation of Additional Paragraph in the Supplemental NPRM

    We have added a new paragraph (d) to this supplemental NPRM to 
provide the Air Transport Association (ATA) of America code. This code 
is added to make this supplemental NPRM parallel with other new AD 
actions. We have reidentified subsequent paragraphs accordingly.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    We are proposing this second supplemental NPRM because we evaluated 
all pertinent information and determined an unsafe condition exists and 
is likely to exist or develop on other products of the same type 
design. Certain changes described above expand the scope of the first 
supplemental NPRM. As a result, we have determined that it is necessary 
to reopen the comment period to provide additional opportunity for the 
public to comment on this second supplemental NPRM.

Costs of Compliance

    We estimate that this proposed AD would affect 280 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                     Number of U.S.-
   Work hours      Average labor        Parts           Cost per        registered            Fleet cost
                   rate per hour                        product         airplanes
----------------------------------------------------------------------------------------------------------------
2-17............             $80   Up to $4,169...  Up to $5,529...             281   Up to $1,553,649.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

[[Page 45138]]

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:


    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-14703 (71 FR 
43962, August 3, 2006) and adding the following new AD:

McDonnell Douglas: Docket No. FAA-2007-0186; Directorate Identifier 
2007-NM-226-AD.

Comments Due Date

    (a) We must receive comments by September 28, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-16-03.

Applicability

    (c) This AD applies to McDonnell Douglas Model DC-10-10, DC-10-
10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, 
and DC-10-40F airplanes, and MD-10-10F and MD-10-30F airplanes that 
have been converted from Model DC-10 series airplanes; certificated 
in any category; with manufacturer's fuselage numbers as identified 
in the applicable service bulletin listed in Table 1 of this AD.

                                             Table 1--Applicability
----------------------------------------------------------------------------------------------------------------
       Boeing Service  Bulletin--           Revision--              Dated--              For airplanes with--
----------------------------------------------------------------------------------------------------------------
DC10-53-109.............................               7  March 3, 2009.............  Extended wing-to-fuselage
                                                                                       fillets.
DC10-53-111.............................               6  March 3, 2009.............  Conventional wing-to-
                                                                                       fuselage fillets.
----------------------------------------------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to reduce the potential of 
ignition sources inside fuel tanks in the event of a severe 
lightning strike, which, in combination with flammable fuel vapors, 
could result in fuel tank explosions and consequent loss of the 
airplane.

Compliance

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

Restatement of Requirements of AD 2006-16-03 With New Service 
Information

Installation or Replacement

    (g) For airplanes with manufacturer's fuselage numbers 
identified in the applicable service bulletin listed in Table 2 of 
this AD: Within 7,500 flight hours or 60 months after September 7, 
2006 (the effective date of AD 2006-16-03), whichever occurs 
earlier: Install or replace with improved parts, as applicable, the 
bonding straps between the metallic frame of the fillet and the wing 
leading edge ribs, on both the left and right sides of the airplane, 
in accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in Table 2 of this AD or Table 1 of this 
AD. After the effective date of this AD, use the applicable service 
bulletin identified in Table 1 of this AD.

                               Table 2--Fuselage Numbers Affected by AD 2006-16-03
----------------------------------------------------------------------------------------------------------------
  McDonnell Douglas DC[dash]10 Service
               Bulletin--                   Revision--              Dated--              For airplanes with--
----------------------------------------------------------------------------------------------------------------
53[dash]109.............................               4  October 7, 1992...........  Extended wing-to-fuselage
                                                                                       fillets.
53-111..................................               3  August 24, 1992...........  Conventional wing-to-
                                                                                       fuselage fillets.
----------------------------------------------------------------------------------------------------------------

New Requirements of This AD

Installation or Replacement

    (h) For airplanes with fuselage numbers not identified in Table 
2 of this AD except for airplanes identified in paragraph (i) or (j) 
of this AD: Within 7,500 flight hours or 60 months, whichever occurs 
first after the effective date of this AD, install or replace with 
improved parts, as applicable, the bonding straps between the 
metallic frame of the fillet and the wing leading edge ribs, on both 
the left and right sides of the airplane, and reposition two bonding 
straps. Do the actions in accordance with the Accomplishment 
Instructions of the applicable service bulletin identified in Table 
1 of this AD.

Strap Repositioning for Certain Airplanes

    (i) For Group 1-4, Configuration 3 airplanes, as identified in 
Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 
2009: Within 7,500 flight hours or 60 months after the effective 
date of this AD, whichever occurs first, do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD.
    (1) Remove two braided bonding straps and install two longer 
braided bonding straps between the metallic frame of the fillet and 
the wing leading edge ribs, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-109, Revision 7, 
dated March 3, 2009.
    (2) Measure the resistance of the previously installed bonding 
straps and, before further flight, do all applicable corrective 
actions in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009.

Inspection and Corrective Action for Certain Airplanes

    (j) For Group 1-2, Configuration 2 airplanes, as identified in 
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 
2009: Within 7,500 flight hours or 60 months after the effective 
date of this AD, whichever occurs first, do the actions specified in 
paragraphs (j)(1) and (j)(2) of this AD.
    (1) Do a general visual inspection to verify correct 
installation of the braided bonding strap, and, before further 
flight, do all applicable corrective actions, in accordance with 
Accomplishment Instructions of Boeing Service Bulletin DC10-53-111, 
Revision 6, dated March 3, 2009.
    (2) Measure the resistance of the previously installed bonding 
straps and, before further flight, do all applicable corrective 
actions, in accordance with Accomplishment Instructions of Boeing 
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009.

[[Page 45139]]

Credit for Actions Accomplished In Accordance With Previous Service 
Information

    (k) Actions accomplished before the effective date of this AD 
according to Boeing Service Bulletin DC10-53-111, Revision 5, dated 
March 19, 2008; and Boeing Service Bulletin DC10-53-109, Revision 6, 
dated July 10, 2008; are considered acceptable for compliance with 
the corresponding action specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion 
Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5262; fax (562) 627-5210.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 2006-16-03 
are approved as AMOCs for the corresponding provisions of this AD.

    Issued in Renton, Washington, on August 17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20994 Filed 8-31-09; 8:45 am]
BILLING CODE 4910-13-P
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