
[Federal Register: June 18, 2008 (Volume 73, Number 118)]
[Rules and Regulations]               
[Page 34605-34608]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18jn08-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0637; Directorate Identifier 2008-NM-078-AD; 
Amendment 39-15561; AD 2008-12-17]
RIN 2120-AA64

 
Airworthiness Directives; Lockheed Model L-1011 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Lockheed Model L-1011 series airplanes. That 
AD currently requires an inspection of the fuel level control switch, 
the fuel level control switch wiring harness, and the wiring harness 
conduit for damage, wear or chafing, broken or missing O-rings, or 
indications of electrical arcing. That AD also requires replacement of 
a certain conduit in the fuel level control switch wiring harness, 
installation of electrical sleeving over the fuel level control switch 
wiring harness, and installation of the fuel level control switch that 
has been so modified. This new AD requires an inspection of the fuel 
level control switch, wiring harnesses, and harness conduit for any 
visible damage, wear or chafing, broken or missing O-rings, or 
indications of electrical arcing; an inspection to determine the part 
number of the wiring harness conduit; and corrective actions if 
necessary. This new AD also requires replacing certain sleeving with 
new, improved sleeving over the wiring harness of the fuel level 
control switch. 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.

DATES: This AD becomes effective July 23, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in the AD as of July 
23, 2008.
    On June 1, 2001 (66 FR 21072, April 27, 2001), the Director of the 
Federal Register approved the incorporation by reference of a certain 
service bulletin.

ADDRESSES: For service information identified in this AD, contact 
Lockheed Continued Airworthiness Project Office, Attention: 
Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063-0567.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
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 (telephone 800-647-5527) is the 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: Robert A. Bosak, Aerospace Engineer, 
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft

[[Page 34606]]

Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 
450, Atlanta, Georgia 30349; telephone (770) 703-6094; fax (770) 703-
6097.

SUPPLEMENTARY INFORMATION:

Discussion

    On April 18, 2001, we issued AD 2001-08-21, amendment 39-12198 (66 
FR 21072, April 27, 2001), for all Lockheed Model L-1011 series 
airplanes. That AD requires a general visual inspection of the fuel 
level control switch, the fuel level control switch wiring harness, and 
the wiring harness conduit for damage, wear or chafing, broken or 
missing O-rings, or indications of electrical arcing. That AD also 
requires replacement of a certain conduit in the fuel level control 
switch wiring harness, installation of electrical sleeving over the 
fuel level control switch wiring harness, and installation of the fuel 
level control switch that has been so modified. That AD resulted from a 
design review of the fuel tank systems. We issued that 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. That AD refers to 
the original issue of Lockheed Service Bulletin 093-28-094, dated March 
3, 2000, as the appropriate source of service information for 
accomplishing the actions required by that AD.

Actions Since Existing AD Was Issued

    Since we issued AD 2001-08-21, we issued a notice of proposed 
rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness 
directive (AD) that would apply to all Lockheed Model L-1011 series 
airplanes. That NPRM, Docket No. FAA-2008-0181, was published in the 
Federal Register on February 20, 2008 (73 FR 9235). That NPRM proposed 
to require revising the FAA-approved maintenance program by 
incorporating new airworthiness limitations for fuel tank systems to 
satisfy Special Federal Aviation Regulation No. 88 (``SFAR 88'') 
requirements. That NPRM also proposed to require the accomplishment of 
certain fuel system modifications, the initial inspections of certain 
repetitive fuel system limitations (FSLs) to phase in those 
inspections, and repair if necessary. One of those FSLs involved 
accomplishing the actions specified in Lockheed Service Bulletin 093-
28-094, Revision 1, dated June 23, 2006.
    We gave the public the opportunity to participate in developing 
that NPRM, and we received a comment from ATA Airlines requesting that 
we revise the NPRM by removing the proposed requirement to accomplish 
the FSL specified in Revision 1 of Lockheed Service Bulletin 093-28-
094. The commenter further requested that we instead issue a separate 
rulemaking action to supersede AD 2001-08-21 to require the 
accomplishment of Revision 1 of the service bulletin. As stated in the 
NPRM, AD 2001-08-21 requires the accomplishment of the original issue 
of the service bulletin, but more work is necessary for Revision 1 of 
the service bulletin. The additional work includes replacing any wiring 
harness conduit having part number (P/N) 741652-105 with new conduit 
having P/N 741652-121, removing any braided fiberglass sleeving 
installed in accordance with the original issue of the service 
bulletin, and installing PVC electrical sleeving having P/N PVC-105-2 
over the wiring harness of the fuel level control switch.
    We agree that it is more appropriate to supersede AD 2001-08-21 to 
require the additional work specified in Revision 1 of the service 
bulletin. Therefore, we are issuing this new action to amend 14 CFR 
part 39 to include an AD that supersedes AD 2001-08-21. Further, we 
also removed the proposed requirement to accomplish the FSL specified 
in Revision 1 of the service bulletin from the NPRM, and we issued AD 
2008-11-02, amendment 39-15524 (73 FR 29410, May 21, 2008), on May 8, 
2008, to require all other actions proposed by the NPRM.

Relevant Service Information

    We have reviewed Revision 1 of Lockheed Service Bulletin 093-28-
094. That service bulletin describes the following procedures:
     Inspecting the fuel level control switch, wiring harness, 
and wiring harness conduit for any visible damage, wear or chafing, 
broken or missing O-rings, or indications of electrical arcing.
     Verifying the part number of the wiring harness conduit.
     Removing any braided fiberglass sleeving installed in 
accordance with the original issue of the service bulletin, and 
installing PVC electrical sleeving having P/N PVC-105-2 over the wiring 
harness of the fuel level control switch.
     Doing corrective actions if necessary.
    The corrective actions include replacing the fuel level control 
switch with a new part if any visible damage, wear or chafing, broken 
or missing O-ring, or indication of electrical arcing is found; and 
replacing any wiring harness conduit having P/N 741652-103 or -105 with 
new conduit having P/N 741652-121.
    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 2001-08-21 and would retain the requirements of the 
existing AD. This AD would also require the following actions:
     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 O-rings, or indications of 
electrical arcing, and corrective action as applicable.
     An inspection to determine the part number of the wiring 
harness conduit, and corrective action as applicable.
     Replacement of any braided fiberglass sleeving with PVC 
electrical sleeving over the wiring harness of the fuel level control 
switch.
     A revision to the FAA-approved maintenance program to 
incorporate repetitive general visual inspections of the fuel level 
control switch, wiring harness, and wiring harness conduit for any 
visible damage, wear or chafing, broken or missing O-rings, or 
indications of electrical arcing.
    This AD allows accomplishing the revision to the FAA-approved 
maintenance program in accordance with later revisions of Lockheed 
Service Bulletin 093-28-094 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 093-28-094, 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 093-28-
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 2001-08-21. Since AD 2001-
08-21 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 2001-08-21                   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 2001-08-21)....
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

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-12198 (66 FR 21072, April 27, 2001) and by adding 
the following new airworthiness directive (AD):

2008-12-17 Lockheed: Amendment 39-15561. Docket No. FAA-2008-0637; 
Directorate Identifier 2008-NM-078-AD.

Effective Date

    (a) This AD becomes effective July 23, 2008.

Affected ADs

    (b) This AD supersedes AD 2001-08-21.

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) 
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 2001-08-21

Inspection, Replacement, and Installation

    (f) Within 18 months after June 1, 2001 (the effective date of 
AD 2001-08-21): 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 O-rings, or indications of electrical 
arcing, in accordance with the Accomplishment Instructions in 
Lockheed Service Bulletin 093-28-094, 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 drop-light, 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 093-28-094, 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 97590-103 is installed, replace the 
conduit with one having P/N 97590-121, 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 O-rings, 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 093-28-094, 
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 FAA-approved 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 093-28-094,    and wiring harness conduit
                                                              Revision 1, dated       for any visible damage,
                                                              June 23, 2006.          wear or chafing, broken or
                                                                                      missing O-rings, or
                                                                                      indications of electrical
                                                                                      arcing, in accordance with
                                                                                      Lockheed Service Bulletin
                                                                                      093-28-094, 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 093-28-094, 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 093-28-094, 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 093-28-094, dated 
March 3, 2000; or Lockheed Service Bulletin 093-28-094, 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 093-28-094, 
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 093-28-094, dated March 3, 2000.
    (3) Contact Lockheed Continued Airworthiness Project Office, 
Attention: Airworthiness, 86 South Cobb Drive, Marietta, Georgia 
30063-0567, 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 202-741-6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 5, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-13277 Filed 6-17-08; 8:45 am]

BILLING CODE 4910-13-P
