Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G Airplanes, 41647-41651 [2011-17399]

Download as PDF Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations a request for consent has been submitted, consent shall be deemed to be granted. (e) Expiration by operation of law. Notwithstanding any determination by the Corporation as receiver to withhold consent under this section, the prohibitions described in 12 U.S.C. 5390(c)(13)(C)(i) are no longer applicable 90 days after the appointment of the receiver. (f) Limitations. Any consent granted by the Corporation as receiver under this section shall not act to waive or relinquish any rights granted to the Corporation in any capacity, pursuant to any other applicable law or any agreement or contract, and shall not be construed as waiving, limiting or otherwise affecting the rights or powers of the Corporation as receiver to take any action or to exercise any power not specifically mentioned, including but not limited to any rights, powers or remedies of the receiver regarding transfers taken in contemplation of the covered financial company’s insolvency or with the intent to hinder, delay or defraud the covered financial company or the creditors of such company, or that is a fraudulent transfer under applicable law. (g) Exceptions. (1) This section shall not apply in the case of a contract that is repudiated or disaffirmed by the Corporation as receiver. (2) This section shall not apply to a director or officer liability insurance contract, a financial institution bond, the rights of parties to certain qualified financial contracts pursuant to 12 U.S.C. 5390(c)(8), the rights of parties to netting contracts pursuant to 12 U.S.C. 4401 et seq., or any extension of credit from any Federal reserve bank or the Corporation to any covered financial company or any security interest in the assets of a covered financial company securing any such extension of credit. mstockstill on DSK4VPTVN1PROD with RULES § 380.52 Adequate protection. (a) If the Corporation as receiver determines that it will use, sell, or lease or grant a security interest or other lien against property of the covered financial company that is subject to a security interest of a claimant, the receiver shall provide adequate protection by any of the following means: (1) Making a cash payment or periodic cash payments to the claimant to the extent that the sale, use, or lease of the property or the grant of a security interest or other lien against the property by the Corporation as receiver results in a decrease in the value of such claimant’s security interest in the property; VerDate Mar<15>2010 15:47 Jul 14, 2011 Jkt 223001 (2) Providing to the claimant an additional or replacement lien to the extent that the sale, use, or lease of the property or the grant of a security interest against the property by the Corporation as receiver results in a decrease in the value of the claimant’s security interest in the property; or (3) Providing any other relief that will result in the realization by the claimant of the indubitable equivalent of the claimant’s security interest in the property. (b) Adequate protection of the claimant’s security interest will be presumed if the value of the property is not depreciating or is sufficiently greater than the amount of the claim so that the claimant’s security interest is not impaired. § 380.53 Repudiation of secured contract. To the extent that a contract to which a covered financial company is a party is secured by property of the covered financial company, the repudiation of the contract by the Corporation as receiver shall not be construed as permitting the avoidance of any legally enforceable and perfected security interest in the property, and the security interest shall secure any claim for repudiation damages. By order of the Board of Directors. Dated at Washington, DC, this 6th day of July 2011. Federal Deposit Insurance Corporation. Robert E. Feldman, Executive Secretary. [FR Doc. 2011–17397 Filed 7–14–11; 8:45 am] BILLING CODE 6714–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1305; Directorate Identifier 2010–NM–074–AD; Amendment 39–16749; AD 2011–15–02] RIN 2120–AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all Model 382, 382B, 382E, 382F, and 382G airplanes. That AD currently requires revising the FAA-approved maintenance program by incorporating SUMMARY: PO 00000 Frm 00059 Fmt 4700 Sfmt 4700 41647 new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive fuel system limitations to phase in those inspections, and repair if necessary. This new AD corrects certain part number references, adds an additional inspection area, and for certain airplanes, requires certain actions to be re-accomplished according to revised service information. This AD was prompted by a report of incorrect accomplishment information in the service information cited by the existing AD. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective August 19, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 19, 2011. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 3, 2008 (73 FR 56464, dated September 29, 2008). ADDRESSES: For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, Georgia 30063; telephone 770–494– 5444; fax 770–494–5445; e-mail ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. 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. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building E:\FR\FM\15JYR1.SGM 15JYR1 41648 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Neil Duggan, Aerospace Engineer, Propulsion and Services Branch, ACE– 118A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5576; fax: (404) 474–5606; e-mail: neil.duggan@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede airworthiness directive (AD) 2008–20–01, amendment 39–15680 (73 FR 56464, September 29, 2008). That AD applies to the specified products. The NPRM published in the Federal Register on January 5, 2011 (76 FR 485). That NPRM proposed to continue to require revising the maintenance program by incorporating new airworthiness limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That NPRM also proposed to continue to require the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive fuel system limitations to phase in those inspections, and repair if necessary. That NPRM also proposed to correct certain part number references, add an additional inspection area, and for certain airplanes, require certain actions to be re-accomplished according to revised service information. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment. Request To Revise Cost Estimate Lynden Air Cargo requested that the cost for revising the Instructions for Continued Airworthiness be included in the Costs of Compliance estimate. Lynden Air Cargo stated that there is a significant amount of work-hours associated with revising ‘‘company manuals, job cards, maintenance programs, computerized tracking programs and record keeping documents’’ so that the operator can comply with the requirements of a new AD. Lynden Air Cargo estimated that these actions will take at least 80 workhours for its office staff, and estimated that this cost would affect other operators. Lynden Air Cargo also pointed out that this work load for the office staff will have a greater impact on smaller fleet operators with smaller staff. We agree that a requirement of the new AD will require an update of the maintenance program to incorporate references to revised service information. This action is estimated to take approximately 1 work-hour per airplane. However, we disagree with increasing the estimated work-hours for the time that it takes for writing job cards, tracking programs, or recordkeeping, since those actions are not directly required by this AD. The costs specified by Lynden Air Cargo will not be the same for all operators. The Costs of Compliance estimate has been revised accordingly. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 62 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate per hour is $85. The costs of the new requirements of this AD are as follows: ESTIMATED COSTS FOR NEW ACTIONS Action Work hours Inspection of fuel probes ........ Maintenance program revision Actions necessary for airplanes on which Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006, has been done. 24 1 24 Parts Cost per airplane None ........... None ........... None ........... Number of U.S.-registered airplanes $2,040, per inspection cycle $85 ......................................... $2,040 .................................... 24 24 24 Fleet cost $48,960, per inspection cycle. $2,040. $48,960. The current costs for AD 2008–20–01 are repeated for the convenience of affected operators, as follows: ESTIMATED COSTS FOR ACTIONS REQUIRED BY AD 2008–20–01 mstockstill on DSK4VPTVN1PROD with RULES Action Work hours Maintenance program revision ............................................... Installation of new, improved fuel dump masts ..................... Dry bay zonal inspection, inspection and repair of static ground terminals, marking the wiring for the fuel quantity indicating system, initial inspection of lightning and static bonding jumpers. Installation of GFIs and flame arrestors ................................. Initial inspection of GFIs and flame arrestors ........................ Installation of lightning bonding jumpers ................................ VerDate Mar<15>2010 16:59 Jul 14, 2011 Jkt 223001 PO 00000 Frm 00060 Parts Cost per product Number of U.S.-registered airplanes Fleet cost 1 12 952 $85 $11,308 $80,920 24 24 24 $2,040 $271,392 $1,942,080 120 8 910 Fmt 4700 None ........... $10,288 ....... None ........... $115,000 ..... None ........... $10,000 ....... $125,200 $680 $87,350 24 24 24 $3,004,800 $16,320 $2,096,400 Sfmt 4700 E:\FR\FM\15JYR1.SGM 15JYR1 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41649 ESTIMATED COSTS FOR ACTIONS REQUIRED BY AD 2008–20–01—Continued Action Work hours Sealant application ................................................................. 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. mstockstill on DSK4VPTVN1PROD with RULES 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. 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: VerDate Mar<15>2010 15:47 Jul 14, 2011 Jkt 223001 320 Parts None ........... 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2008–20–01, Amendment 39–15680 (73 FR 56464, September 29, 2008), and adding the following new AD: ■ 2011–15–02 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–16749; Docket No. FAA–2010–1305; Directorate Identifier 2010–NM–074–AD. Effective Date (a) This airworthiness directive (AD) is effective August 19, 2011. Affected ADs (b) This AD supersedes AD 2008–20–01, Amendment 39–15680. Applicability (c) This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (o) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Unsafe Condition (e) This AD results from a design review of the fuel tank systems. The Federal Aviation Administration is issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. PO 00000 Frm 00061 Fmt 4700 Sfmt 4700 Cost per product $27,200 Number of U.S.-registered airplanes 24 Fleet cost $652,800 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 2008–20– 01, WITH NEW SERVICE INFORMATION: Maintenance Program Revision (g) Before December 16, 2008, revise the maintenance program to incorporate the fuel system limitations (FSLs) and the critical design configuration control limitations (CDCCLs) specified in the Accomplishment Instructions of the Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008; except as provided by paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and except that the modifications and initial inspections specified in table 1 of this AD must be done at the compliance time specified in paragraph (h) of this AD. (1) For the CDCCLs specified in paragraphs 2.C.(3)(e), 2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 2.C.(7)(h), and 2.C.(8) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008, do the applicable actions in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006; or Revision 4, dated September 18, 2008. After the effective date of this AD, use only Revision 4. (2) Where paragraph 2.C.(1)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008, specifies to change the maintenance program to indicate that repetitive inspections of the lightning and static bonding jumpers must be done in accordance with Lockheed Service Bulletin 382–28–21, instead do the repetitive inspections in accordance with Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006; or Revision 4, dated September 18, 2008. After the effective date of this AD, use only Revision 4. (3) Where Lockheed Service Bulletin 382– 28–22, Revision 3, dated March 28, 2008, specifies to inspect, this AD requires doing a general visual inspection. Note 2: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, E:\FR\FM\15JYR1.SGM 15JYR1 41650 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations ladders, or platforms may be required to gain proximity to the area being checked.’’ Fuel System Modifications, Initial Inspections, and Repair if Necessary (h) Within 36 months after November 3, 2008 (the effective date of AD 2008–20–01), do the applicable actions specified in table 1 of this AD, and repair any discrepancy before further flight, in accordance with the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. TABLE 1—MODIFICATIONS AND INITIAL INSPECTIONS Action Additional source of guidance for accomplishing the action For airplanes having any serial number prior to 4962: Install new, improved fuel dump masts in accordance with paragraph 2.C.(1)(d) of the Accomplishment Instructions of Lockheed Service Bulletin 382– 28–22, Revision 3, dated March 28, 2008. Mark the fuel quantity indicating system (FQIS) wires in accordance with paragraphs 2.C.(1)(a)2, 2.C.(4)(b), and 2.C.(4)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Do the dry bay zonal inspection and inspect the static ground terminals of the fuel system plumbing in accordance with paragraph 2.C.(1)(a) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Install ground fault interrupters (GFIs) and flame arrestors for protection of the fuel system in accordance with paragraphs 2.C.(1)(b) and 2.C.(7)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Inspect the GFIs for protection of the fuel system in accordance with paragraph 2.C.(1)(b)1 of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Install the lightning bonding jumpers (straps) in accordance with paragraphs 2.C.(1)(c) and 2.C.(6)(a) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Inspect the lightning and static bonding jumpers (straps) in accordance with paragraphs 2.C.(1)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Apply a certain sealant to the interior of the main wing fuel tanks; and apply a certain sealant to the all external fuel tank nose caps, mid sections, and tail sections; as applicable; in accordance with paragraphs 2.C.(1)(e)1, 2.C.(1)(e)3, and 2.C.(7)(i)1 of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. No Alternative Inspections, Inspection Intervals, or CDCCLs (i) After accomplishing the actions specified in paragraphs (g) and (h) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used unless the inspections, intervals, or CDCCLs are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (o) of this AD. No Reporting Requirement mstockstill on DSK4VPTVN1PROD with RULES (j) Although Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006, specifies to notify Lockheed of any discrepancies found during inspection, this AD does not require that action. NEW REQUIREMENTS OF THIS AD: Incorrect Steps in a Service Bulletin (k) Where the last two bulleted steps of paragraphs 2.C.(2)(b)5 and 2.C.(2)(c)3 of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008, specify that the GFI FAILURE and GROUND FAULT DETECTED lights illuminate for 2 seconds, this AD does not require those steps. VerDate Mar<15>2010 15:47 Jul 14, 2011 Jkt 223001 Lockheed Service Bulletin 382–28–9, dated May 13, 1983. Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008. Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008. Lockheed Service Bulletin 382–28–20, Revision 11, dated April 20, 2010. Paragraph 2.C.(2) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. Lockheed Service Bulletin 382–28–21, Revision 4, dated January 6, 2010. Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008. Lockheed Service Bulletin 382–28–24, Revision 1, dated November 5, 2007, including the Errata Notice, dated January 7, 2008. Additional Inspection Area (l) For airplanes on which Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006, has not been done: Where table 1 of this AD specifies to do the dry bay zonal inspection, do an inspection of the fuel probes as part of the dry bay zonal inspections, in accordance with the service information specified in paragraph (h) of this AD for the dry bay zonal inspections. Do the inspections at the time specified in paragraph (h) of this AD, or within 9 months after the effective date of this AD, whichever occurs later. Actions for Airplanes on Which a Previous Issue of Lockheed Service Bulletin 382–28– 19 Was Done (m) For airplanes on which any action was done in accordance with Lockheed Service Bulletin 382–28–19, Revision 3, dated November 30, 2006: Within the compliance time specified in paragraph (h) of this AD, or within 9 months after the effective date of this AD, whichever occurs later, do the actions required by paragraphs (m)(1) through (m)(4) of this AD and repair any discrepancy before further flight, in accordance with Accomplishment Instructions of Lockheed Service Bulletin PO 00000 Frm 00062 Fmt 4700 Sfmt 4700 382–28–19, Revision 4, dated September 18, 2008. Although Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008, specifies to notify Lockheed of any discrepancies found during inspection, this AD does not require that action. (1) Inspect the fuel probes as part of the zonal inspections of the dry bay areas and other areas. (2) Inspect generator feeder and control wire bundles for correct separation from other wires in the wing leading edge and fuselage areas, and for correct separation from fuel tank boundaries in the wing leading edge area. (3) Inspect for correct spot-tying of certain wire bundles that are within 2 to 12 inches of hot equipment or wires with flameresistant lacing braid, or, for wiring in powerplant areas, with fiberglass braid. (4) Inspect for use of the correct shielding specification and separation of the FQIS wiring in certain locations from alternating current (AC) power wires. Credit for Actions Accomplished in Accordance With Previous Service Information (n) Actions done before the effective date of this AD in accordance with Lockheed E:\FR\FM\15JYR1.SGM 15JYR1 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Service Bulletin 382–28–20, Revision 8, dated October 13, 2009; Revision 9, dated December 14, 2009; or Revision 10, dated March 18, 2010; are acceptable for compliance with the requirements of paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, Atlanta 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) AMOCs approved for AD 2008–20–01 are approved as AMOCs for this AD. mstockstill on DSK4VPTVN1PROD with RULES Related Information (p) For more information about this AD, contact Neil Duggan, Aerospace Engineer, Propulsion and Services Branch, ACE–118A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474–5576; fax: (404) 474–5606; e-mail: neil.duggan@faa.gov. Material Incorporated by Reference (q) You must use Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008; or Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Lockheed Service Bulletin 382–28–19, Revision 4, dated September 18, 2008, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Lockheed Service Bulletin 382– 28–22, Revision 3, dated March 28, 2008, on November 3, 2008 (73 FR 56464, September 29, 2008). (3) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, Georgia 30063; telephone 770–494– 5444; fax 770–494–5445; e-mail ams.portal@lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. (4) You may review copies of the service information at the FAA, 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. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this VerDate Mar<15>2010 15:47 Jul 14, 2011 Jkt 223001 Issued in Renton, Washington, on July 1, 2011. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–17399 Filed 7–14–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0217; Directorate Identifier 2010–NM–165–AD; Amendment 39–16748; AD 2011–15–01] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD–88 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a detailed inspection to detect distress and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs = 52.267; repetitive inspections for cracking in the front spar cap forward flanges of the vertical stabilizer, and either the aft flanges or side skins; repetitive inspections for loose and missing fasteners; and related investigative and corrective actions if necessary. This AD was prompted by reports of cracked vertical stabilizer skin, a severed front spar cap, elongated fastener holes at the leading edge of the vertical stabilizer, and a cracked front spar web and front spar cap bolt holes in the vertical stabilizer. We are issuing this AD to detect and correct such cracking damage, which could result in the structure being unable to support limit load, and could lead to the loss of the vertical stabilizer. DATES: This AD is effective August 19, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 19, 2011. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 SUMMARY: PO 00000 Frm 00063 Fmt 4700 Sfmt 4700 41651 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. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: 562– 627–5233; fax: 562–627–5210; e-mail: Roger.Durbin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM published in the Federal Register on March 14, 2011 (76 FR 13543). That NPRM proposed to require a detailed inspection to detect distress and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs = 52.267; repetitive inspections for cracking in the front spar cap forward flanges of the vertical stabilizer, and either the aft flanges or side skins; repetitive inspections for loose and missing fasteners; and related investigative and corrective actions if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to each comment. E:\FR\FM\15JYR1.SGM 15JYR1

Agencies

[Federal Register Volume 76, Number 136 (Friday, July 15, 2011)]
[Rules and Regulations]
[Pages 41647-41651]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-17399]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1305; Directorate Identifier 2010-NM-074-AD; 
Amendment 39-16749; AD 2011-15-02]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Model 382, 382B, 382E, 382F, and 382G airplanes. That AD 
currently requires revising the FAA-approved maintenance program by 
incorporating new airworthiness limitations for fuel tank systems to 
satisfy Special Federal Aviation Regulation No. 88 requirements. That 
AD also requires the accomplishment of certain fuel system 
modifications, the initial inspections of certain repetitive fuel 
system limitations to phase in those inspections, and repair if 
necessary. This new AD corrects certain part number references, adds an 
additional inspection area, and for certain airplanes, requires certain 
actions to be re-accomplished according to revised service information. 
This AD was prompted by a report of incorrect accomplishment 
information in the service information cited by the existing AD. We are 
issuing this AD to prevent the potential for ignition sources inside 
fuel tanks caused by latent failures, alterations, repairs, or 
maintenance actions, which, in combination with flammable fuel vapors, 
could result in a fuel tank explosion and consequent loss of the 
airplane.

DATES: This AD is effective August 19, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of August 19, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 3, 2008 (73 FR 56464, dated September 29, 2008).

ADDRESSES: For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-
5445; e-mail ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html. 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.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building

[[Page 41648]]

Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 
20590.

FOR FURTHER INFORMATION CONTACT: Neil Duggan, Aerospace Engineer, 
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft 
Certification Office, 1701 Columbia Avenue, College Park, GA 30337; 
phone: (404) 474-5576; fax: (404) 474-5606; e-mail: 
neil.duggan@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede airworthiness directive (AD) 2008-20-01, amendment 
39-15680 (73 FR 56464, September 29, 2008). That AD applies to the 
specified products. The NPRM published in the Federal Register on 
January 5, 2011 (76 FR 485). That NPRM proposed to continue to require 
revising the maintenance program by incorporating new airworthiness 
limitations for fuel tank systems to satisfy Special Federal Aviation 
Regulation No. 88 requirements. That NPRM also proposed to continue to 
require the accomplishment of certain fuel system modifications, the 
initial inspections of certain repetitive fuel system limitations to 
phase in those inspections, and repair if necessary. That NPRM also 
proposed to correct certain part number references, add an additional 
inspection area, and for certain airplanes, require certain actions to 
be re-accomplished according to revised service information.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the proposal 
and the FAA's response to the comment.

Request To Revise Cost Estimate

    Lynden Air Cargo requested that the cost for revising the 
Instructions for Continued Airworthiness be included in the Costs of 
Compliance estimate. Lynden Air Cargo stated that there is a 
significant amount of work-hours associated with revising ``company 
manuals, job cards, maintenance programs, computerized tracking 
programs and record keeping documents'' so that the operator can comply 
with the requirements of a new AD. Lynden Air Cargo estimated that 
these actions will take at least 80 work-hours for its office staff, 
and estimated that this cost would affect other operators. Lynden Air 
Cargo also pointed out that this work load for the office staff will 
have a greater impact on smaller fleet operators with smaller staff.
    We agree that a requirement of the new AD will require an update of 
the maintenance program to incorporate references to revised service 
information. This action is estimated to take approximately 1 work-hour 
per airplane. However, we disagree with increasing the estimated work-
hours for the time that it takes for writing job cards, tracking 
programs, or record-keeping, since those actions are not directly 
required by this AD. The costs specified by Lynden Air Cargo will not 
be the same for all operators. The Costs of Compliance estimate has 
been revised accordingly.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    There are about 62 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD. The average labor rate per hour 
is $85. The costs of the new requirements of this AD are as follows:

                                         Estimated Costs for New Actions
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
           Action               Work hours          Parts           Cost per       registered       Fleet cost
                                                                    airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Inspection of fuel probes...              24  None............  $2,040, per                  24  $48,960, per
                                                                 inspection                       inspection
                                                                 cycle.                           cycle.
Maintenance program revision               1  None............  $85............              24  $2,040.
Actions necessary for                     24  None............  $2,040.........              24  $48,960.
 airplanes on which Lockheed
 Service Bulletin 382-28-19,
 Revision 3, dated November
 30, 2006, has been done.
----------------------------------------------------------------------------------------------------------------

    The current costs for AD 2008-20-01 are repeated for the 
convenience of affected operators, as follows:

                              Estimated Costs for Actions Required by AD 2008-20-01
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action               Work hours          Parts           Cost per       registered      Fleet cost
                                                                      product        airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision.               1  None.............             $85              24          $2,040
Installation of new, improved              12  $10,288..........         $11,308              24        $271,392
 fuel dump masts.
Dry bay zonal inspection,                 952  None.............         $80,920              24      $1,942,080
 inspection and repair of
 static ground terminals,
 marking the wiring for the
 fuel quantity indicating
 system, initial inspection
 of lightning and static
 bonding jumpers.
Installation of GFIs and                  120  $115,000.........        $125,200              24      $3,004,800
 flame arrestors.
Initial inspection of GFIs                  8  None.............            $680              24         $16,320
 and flame arrestors.
Installation of lightning                 910  $10,000..........         $87,350              24      $2,096,400
 bonding jumpers.

[[Page 41649]]

 
Sealant application..........             320  None.............         $27,200              24        $652,800
----------------------------------------------------------------------------------------------------------------

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 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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:

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 FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2008-20-01, Amendment 39-15680 (73 FR 56464, September 29, 2008), and 
adding the following new AD:

2011-15-02 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-16749; Docket No. FAA-2010-1305; Directorate 
Identifier 2010-NM-074-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective August 19, 
2011.

Affected ADs

    (b) This AD supersedes AD 2008-20-01, Amendment 39-15680.

Applicability

    (c) This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes, certificated in any category.

    Note 1:  This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (o) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

    (e) This AD results from a design review of the fuel tank 
systems. The Federal Aviation Administration is issuing this AD to 
prevent the potential for ignition sources inside fuel tanks caused 
by latent failures, alterations, repairs, or maintenance actions, 
which, in combination with flammable fuel vapors, could result in a 
fuel tank explosion 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 2008-20-01, WITH NEW SERVICE 
INFORMATION:

Maintenance Program Revision

    (g) Before December 16, 2008, revise the maintenance program to 
incorporate the fuel system limitations (FSLs) and the critical 
design configuration control limitations (CDCCLs) specified in the 
Accomplishment Instructions of the Lockheed Service Bulletin 382-28-
22, Revision 3, dated March 28, 2008; except as provided by 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and except that 
the modifications and initial inspections specified in table 1 of 
this AD must be done at the compliance time specified in paragraph 
(h) of this AD.
    (1) For the CDCCLs specified in paragraphs 2.C.(3)(e), 
2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 2.C.(7)(h), and 2.C.(8) of the 
Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, 
Revision 3, dated March 28, 2008, do the applicable actions in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 382-28-19, Revision 3, dated November 30, 2006; or Revision 
4, dated September 18, 2008. After the effective date of this AD, 
use only Revision 4.
    (2) Where paragraph 2.C.(1)(c) of the Accomplishment 
Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, 
dated March 28, 2008, specifies to change the maintenance program to 
indicate that repetitive inspections of the lightning and static 
bonding jumpers must be done in accordance with Lockheed Service 
Bulletin 382-28-21, instead do the repetitive inspections in 
accordance with Lockheed Service Bulletin 382-28-19, Revision 3, 
dated November 30, 2006; or Revision 4, dated September 18, 2008. 
After the effective date of this AD, use only Revision 4.
    (3) Where Lockheed Service Bulletin 382-28-22, Revision 3, dated 
March 28, 2008, specifies to inspect, this AD requires doing a 
general visual inspection.

    Note 2: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands,

[[Page 41650]]

ladders, or platforms may be required to gain proximity to the area 
being checked.''

Fuel System Modifications, Initial Inspections, and Repair if Necessary

    (h) Within 36 months after November 3, 2008 (the effective date 
of AD 2008-20-01), do the applicable actions specified in table 1 of 
this AD, and repair any discrepancy before further flight, in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 382-28-22, Revision 3, dated March 28, 2008.

             Table 1--Modifications and Initial Inspections
------------------------------------------------------------------------
                                          Additional source of guidance
                 Action                    for accomplishing the action
------------------------------------------------------------------------
For airplanes having any serial number   Lockheed Service Bulletin 382-
 prior to 4962: Install new, improved     28-9, dated May 13, 1983.
 fuel dump masts in accordance with
 paragraph 2.C.(1)(d) of the
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Mark the fuel quantity indicating        Lockheed Service Bulletin 382-
 system (FQIS) wires in accordance with   28-19, Revision 4, dated
 paragraphs 2.C.(1)(a)2, 2.C.(4)(b),      September 18, 2008.
 and 2.C.(4)(c) of the Accomplishment
 Instructions of Lockheed Service
 Bulletin 382-28-22, Revision 3, dated
 March 28, 2008.
Do the dry bay zonal inspection and      Lockheed Service Bulletin 382-
 inspect the static ground terminals of   28-19, Revision 4, dated
 the fuel system plumbing in accordance   September 18, 2008.
 with paragraph 2.C.(1)(a) of the
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Install ground fault interrupters        Lockheed Service Bulletin 382-
 (GFIs) and flame arrestors for           28-20, Revision 11, dated
 protection of the fuel system in         April 20, 2010.
 accordance with paragraphs 2.C.(1)(b)
 and 2.C.(7)(c) of the Accomplishment
 Instructions of Lockheed Service
 Bulletin 382-28-22, Revision 3, dated
 March 28, 2008.
Inspect the GFIs for protection of the   Paragraph 2.C.(2) of the
 fuel system in accordance with           Accomplishment Instructions of
 paragraph 2.C.(1)(b)1 of the             Lockheed Service Bulletin 382-
 Accomplishment Instructions of           28-22, Revision 3, dated March
 Lockheed Service Bulletin 382-28-22,     28, 2008.
 Revision 3, dated March 28, 2008.
Install the lightning bonding jumpers    Lockheed Service Bulletin 382-
 (straps) in accordance with paragraphs   28-21, Revision 4, dated
 2.C.(1)(c) and 2.C.(6)(a) of the         January 6, 2010.
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Inspect the lightning and static         Lockheed Service Bulletin 382-
 bonding jumpers (straps) in accordance   28-19, Revision 4, dated
 with paragraphs 2.C.(1)(c) of the        September 18, 2008.
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Apply a certain sealant to the interior  Lockheed Service Bulletin 382-
 of the main wing fuel tanks; and apply   28-24, Revision 1, dated
 a certain sealant to the all external    November 5, 2007, including
 fuel tank nose caps, mid sections, and   the Errata Notice, dated
 tail sections; as applicable; in         January 7, 2008.
 accordance with paragraphs
 2.C.(1)(e)1, 2.C.(1)(e)3, and
 2.C.(7)(i)1 of the Accomplishment
 Instructions of Lockheed Service
 Bulletin 382-28-22, Revision 3, dated
 March 28, 2008.
------------------------------------------------------------------------

No Alternative Inspections, Inspection Intervals, or CDCCLs

    (i) After accomplishing the actions specified in paragraphs (g) 
and (h) of this AD, no alternative inspections, inspection 
intervals, or CDCCLs may be used unless the inspections, intervals, 
or CDCCLs are approved as an alternative method of compliance in 
accordance with the procedures specified in paragraph (o) of this 
AD.

No Reporting Requirement

    (j) Although Lockheed Service Bulletin 382-28-19, Revision 3, 
dated November 30, 2006, specifies to notify Lockheed of any 
discrepancies found during inspection, this AD does not require that 
action.

NEW REQUIREMENTS OF THIS AD:

Incorrect Steps in a Service Bulletin

    (k) Where the last two bulleted steps of paragraphs 2.C.(2)(b)5 
and 2.C.(2)(c)3 of Lockheed Service Bulletin 382-28-22, Revision 3, 
dated March 28, 2008, specify that the GFI FAILURE and GROUND FAULT 
DETECTED lights illuminate for 2 seconds, this AD does not require 
those steps.

Additional Inspection Area

    (l) For airplanes on which Lockheed Service Bulletin 382-28-19, 
Revision 3, dated November 30, 2006, has not been done: Where table 
1 of this AD specifies to do the dry bay zonal inspection, do an 
inspection of the fuel probes as part of the dry bay zonal 
inspections, in accordance with the service information specified in 
paragraph (h) of this AD for the dry bay zonal inspections. Do the 
inspections at the time specified in paragraph (h) of this AD, or 
within 9 months after the effective date of this AD, whichever 
occurs later.

Actions for Airplanes on Which a Previous Issue of Lockheed Service 
Bulletin 382-28-19 Was Done

    (m) For airplanes on which any action was done in accordance 
with Lockheed Service Bulletin 382-28-19, Revision 3, dated November 
30, 2006: Within the compliance time specified in paragraph (h) of 
this AD, or within 9 months after the effective date of this AD, 
whichever occurs later, do the actions required by paragraphs (m)(1) 
through (m)(4) of this AD and repair any discrepancy before further 
flight, in accordance with Accomplishment Instructions of Lockheed 
Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. 
Although Lockheed Service Bulletin 382-28-19, Revision 4, dated 
September 18, 2008, specifies to notify Lockheed of any 
discrepancies found during inspection, this AD does not require that 
action.
    (1) Inspect the fuel probes as part of the zonal inspections of 
the dry bay areas and other areas.
    (2) Inspect generator feeder and control wire bundles for 
correct separation from other wires in the wing leading edge and 
fuselage areas, and for correct separation from fuel tank boundaries 
in the wing leading edge area.
    (3) Inspect for correct spot-tying of certain wire bundles that 
are within 2 to 12 inches of hot equipment or wires with flame-
resistant lacing braid, or, for wiring in powerplant areas, with 
fiberglass braid.
    (4) Inspect for use of the correct shielding specification and 
separation of the FQIS wiring in certain locations from alternating 
current (AC) power wires.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (n) Actions done before the effective date of this AD in 
accordance with Lockheed

[[Page 41651]]

Service Bulletin 382-28-20, Revision 8, dated October 13, 2009; 
Revision 9, dated December 14, 2009; or Revision 10, dated March 18, 
2010; are acceptable for compliance with the requirements of 
paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Atlanta 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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) AMOCs approved for AD 2008-20-01 are approved as AMOCs for 
this AD.

Related Information

    (p) For more information about this AD, contact Neil Duggan, 
Aerospace Engineer, Propulsion and Services Branch, ACE-118A, FAA, 
Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College 
Park, GA 30337; phone: (404) 474-5576; fax: (404) 474-5606; e-mail: 
neil.duggan@faa.gov.

Material Incorporated by Reference

    (q) You must use Lockheed Service Bulletin 382-28-19, Revision 
4, dated September 18, 2008; or Lockheed Service Bulletin 382-28-22, 
Revision 3, dated March 28, 2008; as applicable; to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Lockheed Service Bulletin 382-28-19, 
Revision 4, dated September 18, 2008, under 5 U.S.C. 552(a) and 1 
CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Lockheed Service Bulletin 382-28-22, 
Revision 3, dated March 28, 2008, on November 3, 2008 (73 FR 56464, 
September 29, 2008).
    (3) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-
5445; e-mail ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html.
    (4) You may review copies of the service information at the FAA, 
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.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 1, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-17399 Filed 7-14-11; 8:45 am]
BILLING CODE 4910-13-P
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