Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition.

FAA's Findings

During the SFAR 88 safety assessment, Lockheed concluded that no operator had installed auxiliary fuel tank No. 4, in accordance with Lockheed Service Bulletin 09328089, on Model L10113853 series airplanes. Thus, safety assessments for the auxiliary fuel tank, including the electrical equipment involved with the modification, did not need to be analyzed to show compliance with SFAR 88. Since Lockheed has not provided the service information required under SFAR 88 that could lead the FAA to make a finding of compliance, and there is a possibility that there may be unreported installations of the modification, we must mandate the removal of auxiliary fuel tank.

If an operator does not wish to remove the auxiliary fuel tank, we will consider requests for alternative methods of compliance (AMOCs). The most likely requests would be to allow continued use of the tank by showing compliance
[[Page 9237]]
with SFAR 88. This would involve obtaining STCs and developing design and maintenance procedures to address all identified safety issues. FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require revising the FAAapproved maintenance program to incorporate the FSLs and CDCCLs specified in Lockheed Service Bulletin 09328098. This proposed AD would also require the accomplishment of certain fuel system modifications, the initial inspections of certain repetitive FSLs to phase in those inspections, and repair if necessary. Differences Between the Proposed AD and Service Bulletin

Lockheed Service Bulletin 09328098 specifies to revise the operator's maintenance program to incorporate Revision 7 of Lockheed Service Bulletin 09328062 and Revision 1 of Lockheed Service Bulletin 09328093. However, this proposed AD would not require those actions, since Lockheed Service Bulletins 09328062 and 09328093 are mandated by other ADs. AD 992412, amendment 3911436 (64 FR 66756, November 30, 1999), mandated Revision 1 of Lockheed Service Bulletin 09328093. AD 802504, amendment 393983 (45 FR 79011, November 28, 1980), mandated Revision 1 of Lockheed Service Bulletin 09328062, but this proposed AD would not require accomplishing Revision 7 of the service bulletin since both Revisions 1 and 7 adequately address the unsafe condition.

Where Lockheed Service Bulletin 09328098 specifies to inspect, this proposed AD would require a general visual inspection. We have included Note 2 in this proposed AD to define this type of inspection.

Although Lockheed Service Bulletins 09328094, 09328095, 09328 096, and 09328097 describe procedures for notifying Lockheed of any discrepancies found during inspection or any evidence of damage or wire replacement, this proposed AD would not require those actions. Explanation of Compliance Time

In most ADs, we adopt a compliance time allowing a specified amount of time after the AD's effective date. In this case, however, the FAA has already issued regulations that require operators to revise their maintenance/inspection programs to address fuel tank safety issues. The compliance date for these regulations is December 16, 2008. To provide for efficient and coordinated implementation of these regulations and this proposed AD, we are using that same compliance date in this proposed AD.

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 hour, for U.S. operators to comply with this proposed AD.
Estimated Costs Number of Work Cost per U.S. Action hours Parts airplane registered Fleet cost airplanes Maintenance program revision to 4 None................. $320 63 $20,160 incorporate FSLs and CDCCLs.
Removal of auxiliary fuel tank No. 4, 40 None................. 3,200 8 25,600 if applicable.
Modification and inspection of the 19 $974................. 2,494 63 157,122 wiring harnesses of the fuel level
control switch.
Inspection of the airplane fuel tanks, 370 $18,491.............. 48,091 63 3,029,733 vent boxes, and bonding jumpers, and
the addition of bonding jumpers to the
fuel/vent tube fittings.
Inspection of the wiring harnesses of 2 $41,785.............. 41,945 63 2,642,535 the No. 1 and No. 3 engine tank valves.
Identification and inspection of the 4 $336................. 656 63 41,328 FQIS wiring harnesses.

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 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 that the 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.

We prepared a regulatory evaluation of the estimated costs to comply with this proposed 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, 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 39AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows: [[Page 9238]]

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

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by adding the following new airworthiness directive (AD):
Lockheed: Docket No. FAA20080181; Directorate Identifier 2007NM 180AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 21, 2008.
Affected ADs
(b) None.
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) 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 09328098, Revision 1, dated January 22, 2008.
Maintenance Program Revision
(g) Before December 16, 2008, revise the FAAapproved
maintenance program to incorporate the fuel system limitations (FSLs) specified in paragraph 2.B. 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) and (g)(2) 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 Overhauling and repairing the Manual 282403, Revision 14, electricallyoperated fuel dated May 15, 2000. boost pumps. 2.C.(2)(d)................................... Lockheed L1011 Service Keeping the electrical conduit Information Letter 2812, dated for the electricallyoperated March 17, 1998. fuel boost pumps open and unplugged at the wing rear spar. 2.C.(15)(a).................................. Lockheed Drawing 1527514, Installing the fuel tank Revision D, dated November 11, valves, auxiliary power unit 1981. pump, sight gages, 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) Before December 16, 2008, do the applicable FSLs specified in paragraphs 2.B.(1)(b), 2.B.(1)(d), 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.

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 Refers to Lockheed Service paragraph Bulletin For 2.B.(1)(b)................................... 09328089, Revision 3, dated Removing auxiliary fuel tank October 4, 2006 (or later). No. 4, if applicable. 2.B.(1)(d)................................... 09328094, Revision 1, dated Modifying the wiring harnesses June 23, 2006 (or later). of the fuel level control switch; repetitively inspecting the fuel level control switch, wiring harness, and harness conduit for any visible damage, wear or chafing, broken or missing Orings, or indications of electrical arcing; and replacing the fuel level control switch assembly with a new assembly if any damage or evidence of chafing to the wiring is found. [[Page 9239]]
2.B.(1)(e)................................... 09328095, dated September 13, Repetitively inspecting the 2006 (or later). airplane fuel tanks and vent boxes for cleanliness and evidence of deteriorated or damaged fuel/vent tubes and components; repetitively 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 repetitively inspecting the bonding jumpers on the fuel/vent tube fittings. 2.B.(1)(f)................................... 09328096, Revision 2, dated Repetitively inspecting the June 23, 2006 (or later). 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)................................... 09328097, dated August 3, 2006 Identifying the wiring (or later). harnesses for the fuel quantity indicator system (FQIS); repetitively 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 09328094, Revision 1, dated June 23, 2006; Lockheed Service Bulletin 09328095, dated September 13, 2006; Lockheed Service Bulletin 09328096, Revision 2, dated June 23, 2006; and Lockheed Service Bulletin 09328097, 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.

Issued in Renton, Washington, on February 11, 2008. Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E82996 Filed 21908; 8:45 am]
BILLING CODE 491013P

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