The corrective actions include replacing the fuel level control switch with a new part if any visible damage, wear or chafing, broken or missing Oring, or indication of electrical arcing is found; and replacing any wiring harness conduit having P/N 741652103 or 105 with new conduit having P/N 741652121.

The service bulletin also describes procedures for notifying Lockheed of any discrepancies found during the inspection, and revising the airplane records and maintenance planning documents to repeat the inspection at intervals not to exceed 120 months.

FAA's Determination and Requirements of the AD

We have evaluated all pertinent information and identified an unsafe condition that is likely to develop on other airplanes of the same type design. For this reason, we are issuing this AD, which would supersede AD 20010821 and would retain the requirements of the existing AD. This AD would also require the following actions:

This AD allows accomplishing the revision to the FAAapproved maintenance program in accordance with later revisions of Lockheed Service Bulletin 09328094 as an acceptable method of compliance if they are approved by the Manager, Atlanta Aircraft Certification Office, FAA.

Difference Between This AD and Service Bulletin

Although Lockheed Service Bulletin 09328094, Revision 1, describes procedures for notifying Lockheed of any discrepancies found during the inspection, this AD does not require that action. Clarification of Inspection Terminology

The ``inspection'' specified in Lockheed Service Bulletin 09328 094, Revision 1, is referred to as a ``general visual inspection'' in this AD. We have included the definition for a general visual inspection in a note in this AD.

Change to Existing AD

This AD retains all requirements of AD 20010821. Since AD 2001 0821 was issued, the AD format has been revised, and certain paragraphs have
[[Page 34607]]
been rearranged. As a result, the corresponding paragraph identifiers have changed in this AD, as listed in the following table:
Revised Paragraph Identifiers
Corresponding requirement in Requirement in AD 20010821 this AD paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).

Costs of Compliance

There are about 108 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs, at an average labor rate of $80 per work hour, for U.S. operators to comply with this AD.
Estimated Costs Number of U.S. Action Work hours Parts Cost per registered Fleet cost airplane airplanes Inspection of fuel level control 19 $200 $1,720 63 $108,360 switch and installation of
braided fiberglass sleeving
(required by AD 20010821)....
Inspection of fuel level control 3 41,785 42,025 63 2,647,575 switch and installation of PVC
sleeving (new action)..........
Maintenance program revision to 1 None 80 63 5,040 incorporate repetitive
inspection (new action)........

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); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39AIRWORTHINESS 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by removing amendment 3912198 (66 FR 21072, April 27, 2001) and by adding the following new airworthiness directive (AD):
20081217 Lockheed: Amendment 3915561. Docket No. FAA20080637; Directorate Identifier 2008NM078AD.
Effective Date
(a) This AD becomes effective July 23, 2008.
Affected ADs
(b) This AD supersedes AD 20010821.
Applicability
(c) This AD applies to all Lockheed Model L1011 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) according to paragraph (l) 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 chafing of the fuel level control switch wiring harness, which could cause arcing and result in a fire in the fuel tank.
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.
Restatement of Requirements of AD 20010821
Inspection, Replacement, and Installation
(f) Within 18 months after June 1, 2001 (the effective date of AD 20010821): Verify the part number (P/N) of the wiring harness conduit and perform a general visual inspection of the fuel level control switch, the fuel level control switch wiring harness, and the wiring harness conduit to detect any visible damage, any wear or chafing, broken or missing Orings, or indications of electrical arcing, in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 09328094, dated March 3, 2000; or Revision 1, dated June 23, 2006.

Note 2: For the purposes of this AD, a general visual inspection is defined as: ``A visual examination of an interior or exterior [[Page 34608]]
area, installation, or assembly to detect obvious damage, failure, or irregularity. 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.''
(g) Prior to further flight after accomplishment of the requirements in paragraph (f) of this AD, accomplish the actions specified in paragraphs (g)(1) and (g)(2), as applicable, in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 09328094, dated March 3, 2000; or Revision 1, dated June 23, 2006.
(1) Install sleeving over each fuel level control switch wiring harness and install the modified fuel level control switch. (2) If a conduit with P/N 97590103 is installed, replace the conduit with one having P/N 97590121, install sleeving over each fuel level control switch wiring harness, and install the modified fuel level control switch.
New Requirements of This AD
New Inspections, Replacement, and Corrective Actions
(h) Within 60 months after the effective date of this AD: Do a general visual inspection of the fuel level control switch, wiring harness, and wiring harness conduit for any visible damage, wear or chafing, broken or missing Orings, or indications of electrical arcing; do an inspection to determine the part number of the wiring harness conduit; replace any braided fiberglass sleeving with PVC electrical sleeving over the wiring harness of the fuel level control switch; and do all applicable corrective actions; by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Lockheed Service Bulletin 09328094, Revision 1, dated June 23, 2006. The corrective actions must be done before further flight after doing the inspections.
Maintenance Program Revision
(i) Concurrently with accomplishing the actions specified in paragraph (h) of this AD: Revise the FAAapproved maintenance program to incorporate the information specified in Table 1 of this AD.
Table 1.Fuel System Limitation for Fuel Level Control Switch Task Repetitive Interval Applicability Description Airworthiness limitation 120 months............ All airplanes modified General visual inspection instruction (ALI). in accordance with of the fuel level control Lockheed Service switch, wiring harness, Bulletin 09328094, and wiring harness conduit Revision 1, dated for any visible damage, June 23, 2006. wear or chafing, broken or missing Orings, or indications of electrical arcing, in accordance with Lockheed Service Bulletin 09328094, Revision 1, dated June 23, 2006. No Alternative Inspections or Inspection Intervals
(j) After accomplishing the action specified in paragraph (i) of this AD, no alternative inspections or inspection intervals may be used unless the inspections or intervals are part of a later revision of Lockheed Service Bulletin 09328094, Revision 1, dated June 23, 2006, that is approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA; or unless the inspections or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (l) of this AD.
No Reporting Requirement
(k) Although Lockheed Service Bulletin 09328094, Revision 1, dated June 23, 2006, specifies notifying Lockheed of any
discrepancies found during the inspection, this AD does not require that action.
Alternative Methods of Compliance (AMOCs)
(l)(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
(m) You must use Lockheed Service Bulletin 09328094, dated March 3, 2000; or Lockheed Service Bulletin 09328094, Revision 1, dated June 23, 2006; as applicable; to perform the actions that are 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 09328094, Revision 1, dated June 23, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On June 1, 2001 (66 FR 21072, April 27, 2001), the Director of the Federal Register approved the incorporation by reference of Lockheed Service Bulletin 09328094, dated March 3, 2000.
(3) Contact Lockheed Continued Airworthiness Project Office, Attention: Airworthiness, 86 South Cobb Drive, Marietta, Georgia 300630567, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 2027416030, or go to: http:// www.archives.gov/federalregister/cfr/ibrlocations.html.

Issued in Renton, Washington, on June 5, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E813277 Filed 61708; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Robert A. Bosak, Aerospace Engineer, Propulsion and Services Branch, ACE118A, FAA, Atlanta Aircraft [[Page 34606]]
Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone (770) 7036094; fax (770) 703 6097.