[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Proposed Rules]
[Pages 485-489]
From the Federal Register Online via the Government Publishing 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 [email protected]; 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
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Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
airplane airplanes
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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.
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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
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Number of U.S.-
Action Work hours Parts Cost per registered Fleet cost
product airplanes
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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
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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
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Additional source of guidance
Action for accomplishing the action
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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