Airworthiness Directives; Lockheed Model L-1011 Series Airplanes, 63284-63288 [E9-28301]
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Federal Register / Vol. 74, No. 231 / Thursday, December 3, 2009 / Rules and Regulations
provides that the federally insured credit
union will, if the NCUSIF declares a
distribution in the year following the merger
based on the NCUSIF’s equity at the end of
the year of merger, receive a distribution
based on the continuing institution’s insured
shares as of the end of the year of merger.
With regard to distributions declared in the
calendar year of merger but based on the
NCUSIF’s equity from the end of the
preceding year, the institution will receive a
distribution based on its insured shares as of
the end of the preceding year.
i. This formula recognizes that the merging
institution did not contribute to the NCUSIF
equity as of the end of the year preceding the
merger and so no distribution is allotted
against the merging institution’s shares. As
for distributions based on the NCUSIF equity
at the end of the year of merger, this formula
does not include any pro rata reduction for
the merging institution’s contribution. The
Board determined that a pro rata reduction
was unnecessary, given the generally small
relative size of merging institutions to
continuing institutions, and the fact that the
Federal Credit Union Act does not require
any sort of pro rata reduction or other pro
rata calculation with regard to distributions.
C. Conversion from, or termination of,
Federal share insurance.
Paragraph (j)(1) addresses direct insurance
conversions and conversions by merger.
Paragraph (j)(2) addresses liquidations and
insurance termination.
1. Paragraph (j)(1)(i) provides that a
federally insured credit union whose
insurance coverage with the NCUSIF
terminates, including through a conversion
to, or merger into, a nonfederally insured
credit union or a noncredit union entity, will
receive the full amount of its NCUSIF deposit
paid, less any amounts applied to cover
NCUSIF losses that exceed NCUSIF retained
earnings, immediately after the final date on
which any shares of the credit union are
NCUSIF-insured.
i. To illustrate the application of this
paragraph (j)(1)(i), consider the following
hypothetical. Assume Anytown Credit
Union, a credit union with $30 million in
assets, converts from federal to nonfederal
insurance on November 15. Also assume
Anytown Credit Union had $20 million in
insured shares as of the previous December
31, the end of its most recent reporting
period. 12 CFR 741.4(b)(5), (c). The NCUSIF
would return one-percent of $20 million, or
$200,000 to Anytown Credit Union
immediately following the effective date of
its conversion. Note that, if Anytown Credit
Union had reported $50 million or more in
assets on June 30, then June 30 would have
been the end of its most recent reporting
period. Now further assume that, on July 15
of that same year, the NCUSIF had
announced an expense that reduced the
equity ratio from 1.3 to .75, which would
have included a write-off (depletion) of 25%,
or 25 basis points, of the one-percent deposit.
The amount of the deposit returned to
Anytown would be reduced by 25%, from
$200,000 to $150,000. If the NCUSIF had
announced expenses reducing the equity
ratio to .75 after the November 15 conversion
date, this announcement would have no
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effect on Anytown and it would still receive
the full $200,000 from the NCUSIF.
2. Paragraph (j)(1)(ii) provides that a
federally insured credit union whose
insurance coverage with the NCUSIF
terminates, including through a conversion
to, or merger into, a nonfederally insured
credit union or a noncredit union entity, will,
if the NCUSIF declares a distribution at the
end of the calendar year of conversion,
receive a distribution based on the
institution’s insured shares as of the last day
of the most recently ended reporting period
preceding the date of conversion times the
institution’s modified premium/distribution
ratio.
i. To illustrate the application of this
paragraph (j)(1)(ii), again assume Anytown
Credit Union converts to nonfederal
insurance on November 15, and in January of
the following year, the NCUSIF declares a
distribution based on the NCUSIF’s equity
ratio as of December 31. Anytown would
receive a pro rata distribution calculated as
its $20 million in insured shares multiplied
by the modified premium/distribution ratio.
Anytown’s modified premium/distribution
ratio, from the definition in § 741.4(b)(5), is
one minus Anytown’s premium/distribution
ratio, which is one minus the ratio of the full
number of months remaining in the year
divided by twelve, which is one minus (one
divided by twelve), which is eleven divided
by twelve. So Anytown would receive a pro
rata distribution based on $20 million of
insured shares times eleven-twelfths, or
based on about $18.33 million in shares.3
3. Paragraph (j)(1)(iii) provides that a
federally insured credit union whose
insurance coverage with the NCUSIF
terminates, including through a conversion
to, or merger into, a nonfederally insured
credit union or a noncredit union entity, will,
if the NCUSIF assesses a premium in the
calendar year of conversion or merger on or
before the day in which the conversion or
merger is completed, pay a premium based
on the institution’s insured shares as of the
last day of the most recently ended reporting
period preceding the conversion or merger
date times the institution’s modified
premium/distribution ratio. If the institution
has previously paid a premium based on this
same assessment that exceeds this amount,
the institution will receive a refund of the
difference following completion of the
conversion or merger.
i. To illustrate these premium provisions,
again assume Anytown Credit Union is a
credit union with $30 million in assets that
converts from federal to nonfederal insurance
on November 15 of Year One, and that
Anytown Credit Union had $20 million in
insured shares as of the previous December
31 (of Year Zero), the end of its most recent
reporting period. Further assume that NCUA
declares a premium on February 12 of Year
One and invoices the premium on November
15. Since the premium was declared ‘‘on or
before the day in which [Anytown’s]
conversion [was] completed,’’
3 Anytown’s actual distribution would be $18.33
million times the aggregate amount of the
distribution divided by the aggregate amount of all
insured shares at all federally insured credit unions.
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Fmt 4700
Sfmt 4700
§ 741.4(j)(1)(iii) applies. Anytown would
then pay a premium based on $20 million (its
‘‘insured shares as of the last day of the most
recently ended reporting period preceding
the conversion or merger date’’) times eleventwelfths (its ‘‘modified premium/distribution
ratio’’), or based on about $18.33 million.
Note that NCUA might have already have
invoiced Anytown for the premium
sometime between February 12 and
Anytown’s merger on November 15. If so,
Anytown will likely receive a refund of some
of this earlier premium, as provided in the
last sentence of § 741.1(j)(1)(iii), since it may
have overpaid the earlier premium.
[FR Doc. E9–28218 Filed 12–2–09; 8:45 am]
BILLING CODE 7535–01–P
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.
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
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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
https://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 https://
www.lockheedmartin.com/ams/tools/
TechPubs.html.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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:
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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
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16:15 Dec 02, 2009
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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.
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63285
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 reidentified 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
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Federal Register / Vol. 74, No. 231 / Thursday, December 3, 2009 / Rules and Regulations
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
Action
Work hours
Maintenance program revision to incorporate FSLs and
CDCCLs ...........................................................................
Removal of auxiliary fuel tank No. 4, if applicable ..............
Modification and inspection of the wiring harnesses of the
fuel level control switch ....................................................
Inspection of the airplane fuel tanks, vent boxes, and
bonding jumpers, and the addition of bonding jumpers
to the fuel/vent tube fittings ..............................................
Identification and inspection of the FQIS wiring harnesses
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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 https://
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
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Parts
None
None
$320
3,200
63
8
$20,160
25,600
19
$974
2,494
63
157,122
370
4
18,491
336
48,091
656
63
63
3,029,733
41,328
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
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
1. The authority citation for part 39
continues to read as follows:
■
Regulatory Findings
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
Frm 00016
Fleet cost
4
40
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.
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Number of
U.S.-registered
airplanes
Cost per
airplane
Fmt 4700
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§ 39.13
[Amended]
2. The FAA amends § 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
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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
63287
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,
dated January 22, 2008, in
paragraph—
Guidance can be found in—
For—
2.C.(2)(d) ..............................
Hamilton Sundstrand Overhaul Manual 28–24–03, Revision 14, dated May 15, 2000.
Lockheed L–1011 Service Information Letter 28–12,
dated March 17, 1998.
2.C.(15)(a) ............................
Lockheed Drawing 1527514, Revision D, dated September 26, 1981.
Overhauling and repairing the electrically operated fuel
boost pumps.
Keeping the electrical conduit for the electrically operated fuel boost pumps open and unplugged at the
wing rear spar.
Installing the fuel tank valves, auxiliary power unit
pump, sight gauges, fuel quantity indicating system
tank units, over-wing filler cap adapter ring, boost
pump mounting plate, and access doors for the boost
pump, vent box, vent valve, and fuel level control
switch.
2.C.(2)(c) ..............................
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
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The FSL identified in
Lockheed Service Bulletin
093–28–098, Revision 1,
dated January 22, 2008, in
paragraph—
Refers to Lockheed Service Bulletin—
For—
2.B.(1)(b) ..............................
093–28–089, Revision 3, dated October 4, 2006 ...........
Removing auxiliary fuel tank No. 4, if applicable.
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TABLE 2—ADDITIONAL SOURCES OF GUIDANCE FOR CERTAIN FSLS—Continued
The FSL identified in
Lockheed Service Bulletin
093–28–098, Revision 1,
dated January 22, 2008, in
paragraph—
Refers to Lockheed Service Bulletin—
For—
2.B.(1)(e) ..............................
093–28–095, dated September 13, 2006 .......................
2.B.(1)(f) ...............................
093–28–096, Revision 2, dated June 23, 2006 ..............
2.B.(1)(g) ..............................
093–28–097, dated August 3, 2006 ...............................
Inspecting the 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.
Inspecting the wiring harnesses of the No. 1 and No. 3
engine tank valves for evidence of damage and fuel
contamination; replacing any damaged wire with new
wire; and repairing or replacing any contaminated
wires as applicable.
Identifying the 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
jlentini on DSKJ8SOYB1PROD with RULES
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 FAAapproved 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,
VerDate Nov<24>2008
16:15 Dec 02, 2009
Jkt 220001
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 https://
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
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
to: https://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
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 38
[Docket No. RM05–5–013; Order No. 676–
E]
Standards for Business Practices and
Communication Protocols for Public
Utilities
Issued November 24, 2009.
AGENCY: Federal Energy Regulatory
Commission, DOE.
ACTION: Final rule.
SUMMARY: The Federal Energy
Regulatory Commission (Commission) is
revising its regulations to incorporate by
reference in its regulations at 18 CFR
38.2 the latest version (Version 002.1) of
certain business practice standards
adopted by the Wholesale Electric
Quadrant of the North American Energy
Standards Board (NAESB). NAESB’s
Version 002.1 Standards include
standards adopted by NAESB in
response to Order Nos. 890, 890–A, and
E:\FR\FM\03DER1.SGM
03DER1
]]>Agencies
[Federal Register Volume 74, Number 231 (Thursday, December 3, 2009)]
[Rules and Regulations]
[Pages 63284-63288]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28301]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 https://www.lockheedmartin.com/ams/tools/TechPubs.html.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 https://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 https://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: https://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
