2008-11-02: Fuel tank systems

2008-11-02 Lockheed: Amendment 39-15524. Docket No. FAA-2008-0181; Directorate Identifier 2007-NM-180-AD. Effective Date (a) This airworthiness directive (AD) is effective June 25, 2008. Affected ADs (b) None. Applicability (c) This AD applies to all Lockheed Model L-1011 series 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 (AMOC) in accordance with paragraph (k) 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. Unsafe Condition (d) This AD results from a design review of the fuel tank systems. 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. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) The term "service bulletin," as used in this AD, means the Accomplishment Instructions of Lockheed Service Bulletin 093-28-098, Revision 1, dated January 22, 2008. Maintenance Program Revision (g) Before December 16, 2008, revise the FAA-approved maintenance program to incorporate the fuel system limitations (FSLs) specified in paragraphs 2.B.(1)(b), 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin, and the critical design configuration control limitations (CDCCLs) specified in paragraph 2.C. of the service bulletin; except as provided by paragraphs (g)(1), (g)(2), and (h) of this AD. (1) Where the FSLs specify to inspect, this AD would require 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, ladders, or platforms may be required to gain proximity to the area being checked." (2) For the CDCCLs specified in paragraphs 2.C.(2)(c), 2.C.(2)(d), and 2.C.(15)(a) of the service bulletin, do the applicable actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD. The applicable service information listed in Table 1 of this AD is one approved method. Table 1.--Approved Methods for Certain CDCCLs For the CDCCL identified in the service bulletin in paragraph - One Approved Method is - For - 2.C.(2)(c) Hamilton Sundstrand Overhaul Manual 28-24-03, Revision 14, dated May 15, 2000 Overhauling and repairing the electrically-operated fuel boost pumps. 2.C.(2)(d) Lockheed L-1011 Service Information Letter 28-12, dated March 17, 1998 Keeping the electrical conduit for the electrically-operated fuel boost pumps open and unplugged at the wing rear spar. 2.C.(15)(a) Lockheed Drawing 1527514, Revision D, dated September 26, 1981 Installing the fuel tank valves, auxiliary power unit pump, sight gauges, fuel quantity indicating system tank units, over-wing filler cap adapter ring, boost pump mounting plate, and access doors for the boost pump, vent box, vent valve, and fuel level control switch. Initial Accomplishment of FSLs and Repair if Necessary (h) At the applicable compliance time specified in paragraph (h)(1) or (h)(2) of this AD, do the applicable FSLs specified in paragraphs 2.B.(1)(b), 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin and repair any discrepancy, in accordance with the service bulletin. Any repair must be done before further flight. (1) For the FSL identified in paragraph 2.B.(1)(b) of the service bulletin, do the FSL before December 16, 2008. (2) For the FSLs identified in paragraphs 2.B.(1)(e), 2.B.(1)(f), and 2.B.(1)(g) of the service bulletin, do the applicable FSLs within 60 months after the effective date of this AD. Note 3: The service bulletin refers to the service information listed in Table 2 of this AD as additional sources of service information for doing the FSLs and repair. Table 2.--Additional Sources of Service Information for Certain FSLs The FSL identified in the service bulletin in paragraph - Refers to Lockheed Service Bulletin - For - 2.B.(1)(b) 093-28-089, Revision 3, dated October 4, 2006 (or later) Removing auxiliary fuel tank No. 4, if applicable. 2.B.(1)(e) 093-28-095, dated September 13, 2006 (or later) Inspecting the airplane fuel tanks and vent boxes for cleanliness and evidence of deteriorated or damaged fuel/vent tubes and components; inspecting bonding jumpers for proper installation, corrosion, frayed or broken strands, and the condition of the environmental sealing or bonding clamps and hardware; correcting any discrepant conditions; adding bonding jumpers to the fuel/vent tube fittings; and inspecting the bonding jumpers on the fuel/vent tube fittings. 2.B.(1)(f) 093-28-096, Revision 2, dated June 23,2006 (or later) Inspecting the wiring harnesses of the No. 1 and No. 3 engine tank valves for evidence of damage and fuel contamination; replacing any damaged wire with new wire; and repairing or replacing any contaminated wires as applicable. 2.B.(1)(g) 093-28-097, dated August 3, 2006 (or later) Identifying the wiring harnesses for the fuel quantity indicator system (FQIS); inspecting the FQIS wiring harnesses for any visible damage, wear, chafing, or indications of electrical arcing; and replacing or repairing any damaged wires as applicable. No Reporting Requirement (i) Although Lockheed Service Bulletin 093-28-095, dated September 13, 2006; Lockheed Service Bulletin 093-28-096, Revision 2, dated June 23, 2006; and Lockheed Service Bulletin 093-28-097, dated August 3, 2006; specify to notify Lockheed of any discrepancies found during inspection or any evidence of damage or wire replacement, this AD does not require that action. No Alternative Inspections, Inspection Intervals, or CDCCLs (j) 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 part of a later revision of the service bulletin that is approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA; or unless the inspections, intervals, or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (k) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Atlanta ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (l) You must use Lockheed Service Bulletin 093-28-098, Revision 1, dated January 22, 2008, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Lockheed Continued Airworthiness Project Office, Attention: Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063-0567. (3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_ regulations/ibr_locations.html.