
[Federal Register: December 3, 2009 (Volume 74, Number 231)]
[Rules and Regulations]               
[Page 63284-63288]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03de09-3]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1022; Directorate Identifier 2009-NM-163-AD; 
Amendment 39-16078; AD 2008-11-02 R1]
RIN 2120-AA64

 
Airworthiness Directives; Lockheed Model L-1011 Series Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is revising an existing airworthiness directive (AD), 
which applies to all Lockheed Model L-1011 series 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 AD clarifies the intended effect of the AD on spare and 
on-airplane fuel tank system components. 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.

DATES: This AD is effective December 18, 2009.
    On June 25, 2008 (73 FR 29410, May 21, 2008), the Director of the 
Federal

[[Page 63285]]

Register approved the incorporation by reference of a certain 
publication listed in the AD.
    We must receive any comments on this AD by January 19, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Lockheed 
Continued Airworthiness Project Office, Attention Airworthiness, 86 
South Cobb Drive, Marietta, Georgia 30063-0567; telephone 770-494-5444; 
fax 770-494-5445; e-mail ams.portal@lmco.com; Internet http://
www.lockheedmartin.com/ams/tools/TechPubs.html.

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 street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert A. Bosak, Aerospace Engineer, 
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft 
Certification Office, 1701 Columbia Avenue, College Park, Georgia 
30337; telephone (404) 474-5583; fax (404) 474-5606.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 8, 2008, we issued AD 2008-11-02, Amendment 39-15524 (73 FR 
29410, May 21, 2008). That AD applied to all Lockheed Model L-1011 
series airplanes. That AD required 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 required 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 AD resulted from a design review of the fuel tank 
systems. The actions specified in that AD are intended 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.
    Critical design configuration control limitations (CDCCLs) are 
limitation requirements to preserve a critical ignition source 
prevention feature of the fuel tank system design that is necessary to 
prevent the occurrence of an unsafe condition. The purpose of a CDCCL 
is to provide instruction to retain the critical ignition source 
prevention feature during configuration change that may be caused by 
alterations, repairs, or maintenance actions. A CDCCL is not a periodic 
inspection.

Actions Since AD Was Issued

    Since we issued that AD, we have determined that it is necessary to 
clarify the AD's intended effect on spare and on-airplane fuel tank 
system components, regarding the use of maintenance manuals and 
instructions for continued airworthiness.
    Section 91.403(c) of the Federal Aviation Regulations (14 CFR 
91.403(c)) specifies the following:

    No person may operate an aircraft for which a manufacturer's 
maintenance manual or instructions for continued airworthiness has 
been issued that contains an airworthiness limitation section unless 
the mandatory * * * procedures * * * have been complied with.

Some operators have questioned whether existing components affected by 
the new CDCCLs must be reworked. We did not intend for the AD to 
retroactively require rework of components that had been maintained 
using acceptable methods before the effective date of the AD. Owners 
and operators of the affected airplanes therefore are not required to 
rework affected components identified as airworthy or installed on the 
affected airplanes before the required revisions of the FAA-approved 
maintenance program. But once the CDCCLs are incorporated into the FAA-
approved maintenance program, future maintenance actions on components 
must be done in accordance with those CDCCLs.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to revise AD 2008-11-02. This new AD retains the 
requirements of the existing AD, and adds a new note to clarify the 
intended effect of the AD on spare and on-airplane fuel tank system 
components.

Explanation of Additional Changes to AD

    AD 2008-11-02 allowed the use of alternative CDCCLs if they are 
part of a later revision of Lockheed Service Bulletin 093-28-098, 
Revision 1, dated January 22, 2008. That provision has been removed 
from this AD. Allowing the use of ``a later revision'' of a specific 
service document violates Office of the Federal Register regulations 
for approving materials that are incorporated by reference. Affected 
operators, however, may request approval to use an alternative CDCCL 
that is part of a later revision of the referenced service document as 
an alternative method of compliance, under the provisions of paragraph 
(k) of this AD.
    We have revised paragraph (g)(2) of this AD to remove information 
on certain approved methods. Instead we have added Note 3 to this AD to 
specify that guidance on certain CDCCLs can be found in the documents 
identified in Table 1 of this AD. We have re-identified subsequent 
notes accordingly. We have approved the documents in Table 1 of this 
AD. Operators may contact the Manager, Atlanta Aircraft Certification 
Office, for guidance regarding the use of the documents in Table 1 of 
this AD.

Explanation of Further Change to This AD

    We have revised paragraphs (g), (g)(2), (h), (h)(1), and (h)(2), 
Note 4, and Tables 1 and 2 of this AD to remove the term ``the service 
bulletin,'' which is defined in paragraph (f) of this AD. We have 
provided the full service bulletin citation throughout this AD to avoid 
any confusion about which specific service bulletin is being 
referenced. However, we have not removed the ``Service Bulletin 
Reference'' paragraph from this AD. Because this AD revises AD 2008-11-
02, we cannot change paragraph references, which would adversely affect 
compliance. Therefore, we have determined that leaving paragraph (f) of 
this AD unchanged is a less burdensome

[[Page 63286]]

approach for operators, while still adhering to standard drafting 
guidance.

Costs of Compliance

    This revision imposes no additional economic burden. The current 
costs for this AD are repeated for the convenience of affected 
operators, as follows:
    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
----------------------------------------------------------------------------------------------------------------
Maintenance program revision to                4            None            $320              63         $20,160
 incorporate FSLs and CDCCLs....
Removal of auxiliary fuel tank                40            None           3,200               8          25,600
 No. 4, if applicable...........
Modification and inspection of                19            $974           2,494              63         157,122
 the wiring harnesses of the
 fuel level control switch......
Inspection of the airplane fuel              370          18,491          48,091              63       3,029,733
 tanks, vent boxes, and bonding
 jumpers, and the addition of
 bonding jumpers to the fuel/
 vent tube fittings.............
Identification and inspection of               4             336             656              63          41,328
 the FQIS wiring harnesses......
----------------------------------------------------------------------------------------------------------------

FAA's Justification and Determination of the Effective Date

    This revision merely clarifies the intended effect on spare and on-
airplane fuel tank system components, and makes no substantive change 
to the AD's requirements. For this reason, it is found that notice and 
opportunity for prior public comment for this action are unnecessary, 
and good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2009-1022; Directorate Identifier 2009-NM-163-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 the 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 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 part 39 of the Federal Aviation Regulations (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 Amendment 39-15524 (73 FR 
29410, May 21, 2008) and adding the following new AD:

2008-11-02 R1 Lockheed: Amendment 39-16078. Docket No. FAA-2009-
1022; Directorate Identifier 2009-NM-163-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective December 18, 
2009.

Affected ADs

    (b) This AD revises AD 2008-11-02, Amendment 39-15524.

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

[[Page 63287]]

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.

Restatement of Requirements of AD 2008-11-02 With Changes to Compliance 
Method

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 Lockheed Service Bulletin 093-28-098, Revision 1, 
dated January 22, 2008, and the critical design configuration 
control limitations (CDCCLs) specified in paragraph 2.C. of Lockheed 
Service Bulletin 093-28-098, Revision 1, dated January 22, 2008; 
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 Lockheed Service Bulletin 093-28-098, 
Revision 1, dated January 22, 2008, do the applicable actions using 
a method approved in accordance with a method approved by the 
Manager, Atlanta Aircraft Certification Office, FAA.

    Note 3:  Guidance on certain CDCCLs can be found in the 
documents identified in Table 1 of this AD.


              Table 1--Approved Methods for Certain CDCCLs
------------------------------------------------------------------------
 For the CDCCL identified in
  Lockheed Service Bulletin
   093-28-098, Revision 1,       Guidance can be            For--
 dated January 22, 2008, in        found in--
         paragraph--
------------------------------------------------------------------------
2.C.(2)(c)..................  Hamilton Sundstrand   Overhauling and
                               Overhaul Manual 28-   repairing the
                               24-03, Revision 14,   electrically
                               dated May 15, 2000.   operated fuel boost
                                                     pumps.
2.C.(2)(d)..................  Lockheed L-1011       Keeping the
                               Service Information   electrical conduit
                               Letter 28-12, dated   for the
                               March 17, 1998.       electrically
                                                     operated fuel boost
                                                     pumps open and
                                                     unplugged at the
                                                     wing rear spar.
2.C.(15)(a).................  Lockheed Drawing      Installing the fuel
                               1527514, Revision     tank valves,
                               D, dated September    auxiliary power
                               26, 1981.             unit pump, sight
                                                     gauges, fuel
                                                     quantity indicating
                                                     system tank units,
                                                     over[dash]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 
Lockheed Service Bulletin 093-28-098, Revision 1, dated January 22, 
2008, and repair any discrepancy, in accordance with Lockheed 
Service Bulletin 093-28-098, Revision 1, dated January 22, 2008. Any 
repair must be done before further flight.
    (1) For the FSL identified in paragraph 2.B.(1)(b) of Lockheed 
Service Bulletin 093-28-098, Revision 1, dated January 22, 2008, 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 Lockheed Service Bulletin 093-28-098, 
Revision 1, dated January 22, 2008, do the applicable FSLs within 60 
months after June 25, 2008 (the effective date AD 2008-11-02).

    Note 4:  Lockheed Service Bulletin 093-28-098, Revision 1, dated 
January 22, 2008, refers to the service information listed in Table 
2 of this AD as additional sources of guidance for doing the FSLs 
and repair.


        Table 2--Additional Sources of Guidance for Certain FSLs
------------------------------------------------------------------------
    The FSL identified in
  Lockheed Service Bulletin
   093-28-098, Revision 1,     Refers to Lockheed           For--
 dated January 22, 2008, in    Service Bulletin--
         paragraph--
------------------------------------------------------------------------
2.B.(1)(b)..................  093-28-089, Revision  Removing auxiliary
                               3, dated October 4,   fuel tank No. 4, if
                               2006.                 applicable.

[[Page 63288]]


2.B.(1)(e)..................  093-28-095, dated     Inspecting the
                               September 13, 2006.   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  Inspecting the
                               2, dated June 23,     wiring harnesses of
                               2006.                 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     Identifying the
                               August 3, 2006.       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 approved as an AMOC in accordance with the procedures 
specified in paragraph (k) of this AD.

New Information

Explanation of CDCCL Requirements

    Note 5: Notwithstanding any other maintenance or operational 
requirements, components that have been identified as airworthy or 
installed on the affected airplanes before the revision of the FAA-
approved maintenance program, as required by paragraph (g) of this 
AD, do not need to be reworked in accordance with the CDCCLs. 
However, once the FAA-approved maintenance program has been revised, 
future maintenance actions on these components must be done in 
accordance with the CDCCLs.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Atlanta Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: 
Robert Bosak, Aerospace Engineer, Propulsion Branch, ACE-118A, FAA, 
Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College 
Park, GA 30337; telephone (404) 474-5583; fax (404) 474-5606.
    (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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.

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 previously approved the 
incorporation by reference of this service information on June 25, 
2008 (73 FR 29410 May 21, 2008).
    (2) For service information identified in this AD, contact 
Lockheed Continued Airworthiness Project Office, Attention 
Airworthiness, 86 South Cobb Drive, Marietta, Georgia 30063-0567; 
telephone 770-494-5444; fax 770-494-5445; e-mail 
ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/
tools/TechPubs.html.
    (3) You may review copies of the 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 or 425-227-1152.
    (4) 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 NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on October 26, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-28301 Filed 12-2-09; 8:45 am]

BILLING CODE 4910-13-P
