Document ID: FAA-2010-1305-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Lockheed Martin Corp./Lockheed Martin Aeronautics Co, Model 382, 382B, 382E, 382F, and 382G Airplanes
Posted Date: 2011-01-05T05:00Z

[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Proposed Rules]
[Pages 485-489]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33335]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1305; Directorate Identifier 2010-NM-074-AD]
RIN 2120-AA64

Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Model 382, 382B, 382E, 382F, and 
382G airplanes. The existing 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 proposed AD would 
correct certain part number references, add an additional inspection 
area, and for certain airplanes, require certain actions to be re-
accomplished according to revised service information. This proposed AD 
results from a report of incorrect accomplishment information in the 
service information cited by the existing AD. We are proposing 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: We must receive comments on this proposed AD by February 22, 
2011.

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 proposed AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-
5445; e-mail ams.portal@lmco.com; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.html. You may review copies 
of the referenced 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.

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 proposed 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: Neil Duggan, Aerospace Engineer, 
Propulsion and Services Branch, ACE-118A, FAA, Atlanta Aircraft 
Certification Office, 1701 Columbia Avenue, College Park, GA 30337; 
telephone (404) 474-5576; fax (404) 474-5606.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the

[[Page 486]]

ADDRESSES section. Include ``Docket No. FAA-2010-1305; Directorate 
Identifier 2010-NM-074-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
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 proposed AD.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    On September 11, 2008, we issued AD 2008-20-01, amendment 39-15680 
(73 FR 56464, September 29, 2008), for all Model 382, 382B, 382E, 382F, 
and 382G airplanes. That AD requires revising the 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. That AD resulted from a design review of the fuel tank 
systems. We issued that 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2008-20-01, we received information from the 
manufacturer that Lockheed Service Bulletin 382-28-21, Revision 2, 
dated November 20, 2006 (referenced in AD 2008-20-01 as a source of 
additional guidance), contained an error in referencing certain part 
numbers for tube, fuel tank, and bulkhead joint jumpers. The part 
numbers as referenced in Revision 2 of that service bulletin do not 
exist. The manufacturer has published Lockheed Service Bulletin 382-28-
21, Revision 4, dated January 6, 2010, to provide the correct part 
number references. We have revised Table 1 of this AD accordingly.
    We have also received information from the manufacturer that the 
last two bulleted steps of paragraphs 2.C.(2)(b)5 and 2.C.(2)(c)3 of 
Lockheed Service Bulletin 382-28-22, Revision 3, dated March 28, 2008, 
contain an error. Those steps specify that the GFI FAILURE and GROUND 
FAULT DETECTED lights illuminate for 2 seconds. An alternate means of 
compliance (AMOC) for AD 2008-20-01 was issued to disregard those 
steps. The manufacturer has advised that it is planning to publish a 
revision to Lockheed Service Bulletin 382-28-22, Revision 3, dated 
March 28, 2008. However, we have determined that delaying this action 
until after the release of this planned revision is not warranted, 
since sufficient notice of the error in Lockheed Service Bulletin 382-
28-22, Revision 3, dated March 28, 2008, exists.

Relevant Service Information

    We have also reviewed Lockheed Service Bulletin 382-28-19, Revision 
4, dated September 18, 2008. That service bulletin describes procedures 
that are similar to those in Lockheed Service Bulletin 382-28-19, 
Revision 3, dated November 30, 2006 (which was referenced in AD 2008-
20-01 as a source of additional guidance). However, Revision 4 of 
Lockheed Service Bulletin 382-28-19 specifies an additional inspection 
area (fuel probes) for the dry bay and other areas and revises actions. 
Revision 4 of that service bulletin also specifies that for airplanes 
on which the actions described in Revision 3 of Lockheed Service 
Bulletin 382-28-19 are done, it is necessary to do the additional 
action of inspecting the fuel probes when doing the zonal inspection of 
the dry bay areas and other areas and re-accomplish certain inspections 
of certain fuel system electrical wires (such as ensuring that 
generator wire bundles are separated from fuel tank boundaries, certain 
wire bundles are spot tied with certain lacing braid, and that the fuel 
quantity indication system (FQIS) wiring in certain locations is routed 
separately from AC power wires and is shielded using the correct 
standard).
    We have also reviewed Lockheed Service Bulletin 382-28-20, Revision 
11, dated April 20, 2010. That service bulletin describes procedures 
that are similar to Lockheed Service Bulletin 382-28-20, Revision 5, 
dated June 19, 2008 (which was referenced as a source of guidance in AD 
2008-20-01), for installing ground fault interrupters (GFIs) and flame 
arrestors for protection of the fuel system.

FAA's Determination and Requirements of the Proposed 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 proposing this AD, which 
would supersede AD 2008-20-01 and would retain the requirements of the 
existing AD. This

[[Page 487]]

proposed AD would also require certain actions to be re-accomplished 
according to revised service information described previously, except 
as discussed under ``Difference Between the Proposed AD and the Service 
Information.''

Difference Between the Proposed AD and the Service Information

    Although Lockheed Service Bulletin 382-28-19, Revision 4, dated 
September 18, 2008, describes procedures for notifying Lockheed of any 
discrepancies found during inspection, this proposed AD would not 
require that action.

Explanation of Change to This AD

    We have removed the ``Service Bulletin Reference'' paragraph from 
this NPRM. That paragraph was identified as paragraph (f) in AD 2008-
20-01. Instead, we have provided the full service bulletin citations 
throughout this NPRM.

Explanation of Change to Applicability

    We have revised the NPRM to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.

Costs of Compliance

    There are about 62 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
per hour is $85. The costs of the new requirements of this proposed AD 
are as follows:

                                         Estimated Costs for New Actions
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
            Action              Work hours        Parts            Cost per        registered       Fleet cost
                                                                   airplane         airplanes
----------------------------------------------------------------------------------------------------------------
Inspection of fuel probes....           24  None.............  $2,040, per                   24  $48,960, per
                                                                inspection                        inspection
                                                                cycle.                            cycle.
Actions necessary for                   24  None.............  $2,040..........              24  $48,960.
 airplanes on which Lockheed
 Service Bulletin 382-28-19,
 Revision 3, dated November
 30, 2006, has been done.
----------------------------------------------------------------------------------------------------------------

    The current costs for this proposed AD are repeated for the 
convenience of affected operators, as follows:

                              Estimated Costs for Actions Required by AD 2008-20-01
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
             Action                 Work hours         Parts         Cost per       registered      Fleet cost
                                                                      product        airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision....               1            None             $85              24          $2,040
Installation of new, improved                 12         $10,288          11,308              24         271,392
 fuel dump masts................
Dry bay zonal inspection,                    952            None          80,920              24       1,942,080
 inspection and repair of static
 ground terminals, marking the
 wiring for the fuel quantity
 indicating system, initial
 inspection of lightning and
 static bonding jumpers.........
Installation of GFIs and flame               120         115,000         125,200              24       3,004,800
 arrestors......................
Initial inspection of GFIs and                 8            None             680              24          16,320
 flame arrestors................
Installation of lightning                    910          10,000          87,350              24       2,096,400
 bonding jumpers................
Sealant application.............             320            None          27,200              24         652,800
----------------------------------------------------------------------------------------------------------------

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.

[[Page 488]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 39--AIRWORTHINESS 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 FAA amends Sec.  39.13 by removing amendment 39-15680 (73 FR 
56464, September 29, 2008) and adding the following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2010-1305; Directorate Identifier 2010-NM-074-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
22, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-20-01, Amendment 39-15680.

Applicability

    (c) This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
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 according 
to paragraph (o) 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.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

    (e) This AD results from a design review of the fuel tank 
systems. The Federal Aviation Administration is 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

    (f) 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 2008-20-01, With New Service 
Information

Maintenance Program Revision

    (g) Before December 16, 2008, revise the maintenance program to 
incorporate the fuel system limitations (FSLs) and the critical 
design configuration control limitations (CDCCLs) specified in the 
Accomplishment Instructions of the Lockheed Service Bulletin 382-28-
22, Revision 3, dated March 28, 2008; except as provided by 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and except that 
the modifications and initial inspections specified in Table 1 of 
this AD must be done at the compliance time specified in paragraph 
(h) of this AD.
    (1) For the CDCCLs specified in paragraphs 2.C.(3)(e), 
2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 2.C.(7)(h), and 2.C.(8) of the 
Accomplishment Instructions of Lockheed Service Bulletin 382-28-22, 
Revision 3, dated March 28, 2008, do the applicable actions in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 382-28-19, Revision 3, dated November 30, 2006; or Revision 
4, dated September 18, 2008. After the effective date of this AD, 
use only Revision 4.
    (2) Where paragraph 2.C.(1)(c) of the Accomplishment 
Instructions of Lockheed Service Bulletin 382-28-22, Revision 3, 
dated March 28, 2008, specifies to change the maintenance program to 
indicate that repetitive inspections of the lightning and static 
bonding jumpers must be done in accordance with Lockheed Service 
Bulletin 382-28-21, instead do the repetitive inspections in 
accordance with Lockheed Service Bulletin 382-28-19, Revision 3, 
dated November 30, 2006; or Revision 4, dated September 18, 2008. 
After the effective date of this AD, use only Revision 4.
    (3) Where Lockheed Service Bulletin 382-28-22, Revision 3, dated 
March 28, 2008, specifies to inspect, this AD requires 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.''

Fuel System Modifications, Initial Inspections, and Repair If Necessary

    (h) Within 36 months after November 3, 2008 (the effective date 
of AD 2008-20-01), do the applicable actions specified in Table 1 of 
this AD, and repair any discrepancy before further flight, in 
accordance with the Accomplishment Instructions of Lockheed Service 
Bulletin 382-28-22, Revision 3, dated March 28, 2008.

             Table 1--Modifications and Initial Inspections
------------------------------------------------------------------------
                                          Additional source of guidance
                 Action                    for accomplishing the action
------------------------------------------------------------------------
For airplanes having any serial number   Lockheed Service Bulletin 382-
 prior to 4962: Install new, improved     28-9, dated May 13, 1983.
 fuel dump masts in accordance with
 paragraph 2.C.(1)(d) of the
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Mark the fuel quantity indicating        Lockheed Service Bulletin 382-
 system (FQIS) wires in accordance with   28-19, Revision 4, dated
 paragraphs 2.C.(1)(a)2, 2.C.(4)(b),      September 18, 2008.
 and 2.C.(4)(c) of the Accomplishment
 Instructions of Lockheed Service
 Bulletin 382-28-22, Revision 3, dated
 March 28, 2008.
Do the dry bay zonal inspection and      Lockheed Service Bulletin 382-
 inspect the static ground terminals of   28-19, Revision 4, dated
 the fuel system plumbing in accordance   September 18, 2008.
 with paragraph 2.C.(1)(a) of the
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Install ground fault interrupters        Lockheed Service Bulletin 382-
 (GFIs) and flame arrestors for           28-20, Revision 11, dated
 protection of the fuel system in         April 20, 2010.
 accordance with paragraphs 2.C.(1)(b)
 and 2.C.(7)(c) of the Accomplishment
 Instructions of Lockheed Service
 Bulletin 382-28-22, Revision 3, dated
 March 28, 2008.

[[Page 489]]

 
Inspect the GFIs for protection of the   Paragraph 2.C.(2) of the
 fuel system in accordance with           Accomplishment Instructions of
 paragraph 2.C.(1)(b)1 of the             Lockheed Service Bulletin 382-
 Accomplishment Instructions of           28-22, Revision 3, dated March
 Lockheed Service Bulletin 382-28-22,     28, 2008.
 Revision 3, dated March 28, 2008.
Install the lightning bonding jumpers    Lockheed Service Bulletin 382-
 (straps) in accordance with paragraphs   28-21, Revision 4, dated
 2.C.(1)(c) and 2.C.(6)(a) of the         January 6, 2010.
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Inspect the lightning and static         Lockheed Service Bulletin 382-
 bonding jumpers (straps) in accordance   28-19, Revision 4, dated
 with paragraphs 2.C.(1)(c) of the        September 18, 2008.
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
Apply a certain sealant to the interior  Lockheed Service Bulletin 382-
 of the main wing fuel tanks; and apply   28-24, Revision 1, dated
 a certain sealant to all external fuel   November 5, 2007, including
 tank nose caps, mid sections, and tail   the Errata Notice, dated
 sections; as applicable; in accordance   January 7, 2008.
 with paragraphs 2.C.(1)(e)1,
 2.C.(1)(e)3, and 2.C.(7)(i)1 of the
 Accomplishment Instructions of
 Lockheed Service Bulletin 382-28-22,
 Revision 3, dated March 28, 2008.
------------------------------------------------------------------------

No Alternative Inspections, Inspection Intervals, or CDCCLs

    (i) 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 alternative method of compliance in 
accordance with the procedures specified in paragraph (k) of this 
AD.

No Reporting Requirement

    (j) Although Lockheed Service Bulletin 382-28-19, Revision 3, 
dated November 30, 2006, specifies to notify Lockheed of any 
discrepancies found during inspection, this AD does not require that 
action.

New Requirements of This AD

Incorrect Steps in a Service Bulletin

    (k) Where the last two bulleted steps of paragraphs 2.C.(2)(b)5 
and 2.C.(2)(c)3 of Lockheed Service Bulletin 382-28-22, Revision 3, 
dated March 28, 2008, specify that the GFI FAILURE and GROUND FAULT 
DETECTED lights illuminate for 2 seconds, this AD does not require 
those steps.

Additional Inspection Area

    (l) For airplanes on which Lockheed Service Bulletin 382-28-19, 
Revision 3, dated November 30, 2006, has not been done: Where Table 
1 of this AD specifies to do the dry bay zonal inspection, do an 
inspection of the fuel probes as part of the dry bay zonal 
inspections, in accordance with the service information specified in 
paragraph (h) of this AD for the dry bay zonal inspections. Do the 
inspections at the time specified in paragraph (h) of this AD, or 
within 9 months after the effective date of this AD, whichever 
occurs later.

Actions for Airplanes on Which a Previous Issue of Lockheed Service 
Bulletin 382-28-19 Was Done

    (m) For airplanes on which any action was done in accordance 
with Lockheed Service Bulletin 382-28-19, Revision 3, dated November 
30, 2006: Within the compliance time specified in paragraph (h) of 
this AD, or within 9 months after the effective date of this AD, 
whichever occurs later, do the actions required by paragraphs (m)(1) 
through (m)(4) of this AD and repair any discrepancy before further 
flight, in accordance with Accomplishment Instructions of Lockheed 
Service Bulletin 382-28-19, Revision 4, dated September 18, 2008. 
Although Lockheed Service Bulletin 382-28-19, Revision 4, dated 
September 18, 2008, specifies to notify Lockheed of any 
discrepancies found during inspection, this AD does not require that 
action.
    (1) Inspect the fuel probes as part of the zonal inspections of 
the dry bay areas and other areas.
    (2) Inspect generator feeder and control wire bundles for 
correct separation from other wires in the wing leading edge and 
fuselage areas, and for correct separation from fuel tank boundaries 
in the wing leading edge area.
    (3) Inspect for correct spot-tying of certain wire bundles that 
are within 2 to 12 inches of hot equipment or wires with flame-
resistant lacing braid, or, for wiring in powerplant areas, with 
fiberglass braid.
    (4) Inspect for use of the correct shielding specification and 
separation of the FQIS wiring in certain locations from AC power 
wires.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (n) Actions done before the effective date of this AD in 
accordance with Lockheed Service Bulletin 382-28-20, Revision 8, 
dated October 13, 2009; Revision 9, dated December 14, 2009; or 
Revision 10, dated March 18, 2010; is acceptable for compliance with 
the requirements of paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, Atlanta Aircraft Certification Office (ACO), 
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: Neil Duggan, Aerospace Engineer, Propulsion and Services 
Branch, ACE-118A, FAA, Atlanta ACO, 1701 Columbia Avenue, College 
Park, GA 30337; telephone (404) 474-5576; 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.
    (3) AMOCs approved for AD 2008-20-01 are approved as AMOCs for 
this AD.

    Issued in Renton, Washington, on December 27, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-33335 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P