Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes, 38755-38757 [05-13224]
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Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Rules and Regulations
TABLE 3.—THALES AVIONICS SERVICE BULLETINS
Thales Avionics service bulletin—
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)
354–34–051
354–34–053
520–34–014
520–34–015
520–34–016
520–34–017
528–34–006
528–34–007
Revision—
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
...............................................................................................................................................
Inspection and Replacement
(h) Within 6 months after the effective date
of this AD, do an inspection to determine if
the suspect P/Ns and serial number (S/N) of
the Thales Avionics equipment is installed,
in accordance with the Airbus service
bulletin. If any suspect P/N and S/N is found,
within 6 months after the effective date of
this AD, replace the suspect part with a
modified part having a new P/N, in
accordance with the Airbus service bulletin.
Parts Installation
(i) As of the effective date of this AD, no
person may install any Thales Avionics
equipment specified in Table 1 of this AD on
any airplane.
Reporting Requirement
(j) Within 6 months after the effective date
of this AD, submit a report of all P/Ns and
S/N of overhauled equipment found during
the inspection required by paragraph (h) of
this AD to Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; fax
011–33–561934251. Information collection
requirements contained in this AD have been
approved by the Office of Management and
Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C.
3501 et seq.) and have been assigned OMB
Control Number 2120–0056.
Alternative Methods of Compliance
(AMOCs)
(k) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(l) French airworthiness directive F–2004–
037, issued March 17, 2004, also addresses
the subject of this AD.
03
02
04
04
03
03
03
02
Dated—
October 13, 2003.
October 10, 2003.
April 22, 2004.
July 1, 2004.
November 20, 2003.
July 1, 2004.
June 29, 2004.
October 10, 2003.
Material Incorporated by Reference
(m) You must use the service information
listed in Table 4 to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approves the incorporation
by reference of these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of the service
information, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France. To view the AD docket, go to the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
TABLE 4.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Airbus service bulletin
A300–34A0173 ................................................................................................................................................
A300–34A6145 ................................................................................................................................................
A310–34A2178 ................................................................................................................................................
Issued in Renton, Washington, on June 22,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–13143 Filed 7–5–05; 8:45 am]
BILLING CODE 4910–13–U
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19764; Directorate
Identifier 2004–NM–02–AD; Amendment 39–
14182; AD 2005–14–05]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200 and –300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 777–200 and –300 series
airplanes. This AD requires applying an
anti-static conductive coating to the fuel
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16:43 Jul 05, 2005
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PO 00000
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Fmt 4700
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01
01
01
Date
December 18, 2003.
October 17, 2003.
October 17, 2003.
access and thermal anti-icing blowout
doors at the location of the bonding
fasteners on the leading edge of the
wings, and performing a resistance test
on the new coating to ensure correct
ground path resistance. This AD is
prompted by a report that an anti-static
coating was not applied correctly on
doors located within a flammable fluid
leakage zone. We are issuing this AD to
prevent an uncontrollable fire in the
leading edge of the wing, which could
damage critical wing structures and
cause a fuel tank explosion.
This AD becomes effective
August 10, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of August 10, 2005.
DATES:
For service information
identified in this AD, contact Boeing
ADDRESSES:
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06JYR1
38756
Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Rules and Regulations
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19764; the directorate
identifier for this docket is 2004–NM–
02–AD.
FOR FURTHER INFORMATION CONTACT:
Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6500; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing Model 777–
200 and -300 series airplanes. That
action, published in the Federal
Register on December 7, 2004 (69 FR
70574), proposed to require applying an
anti-static conductive coating to the fuel
access and thermal anti-icing blowout
doors at the location of the bonding
fasteners on the leading edge of the
wings, and performing a resistance test
on the new coating to ensure correct
ground path resistance.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Support for the Proposed AD
One commenter, the manufacturer,
supports the proposed AD.
Request To Remove a Service Bulletin
Action To Maintain Certain Coating
Thickness
One commenter concurs with the AD.
However, the commenter states that
Boeing Special Attention Service
Bulletin 777–57–0046, dated September
25, 2003, which is referenced in the
proposed AD as the appropriate source
of service information, specifies an
action to maintain a certain coating
thickness that is impractical to perform.
The commenter states that Note (b) of
Figures 1 and 2 in the Accomplishment
Instructions of the service bulletin
specifies that the conductive coating be
applied at a thickness of 0.0004 to
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16:43 Jul 05, 2005
Jkt 205001
0.0008 inch. The commenter states that
there is no practical method to measure
the thickness and that they have
confirmation from the manufacturer that
the intent of Note (b) is to ensure that
the coating application is continuous.
The commenter also notes that the
manufacturer plans to delete the
thickness dimension and revise the
wording in Note (b) in the next revision
of the service bulletin.
We agree with the commenter that the
intent of Note (b) of the service bulletin
is to ensure a continuous coating and
that the measured thickness is not
relevant. Although Note (b) specifies
maintaining the thickness of the applied
conductive coating between 0.0004 and
0.0008 inch, we have revised paragraph
(f) of this AD to clarify the
manufacturer’s intent: to apply a
uniform coating to avoid runs, sags, or
wrinkles, and to ensure the anti-static
coating touches the anti-static coating
exposed during surface preparation.
We have coordinated this difference
with the manufacturer. The
manufacturer has informed us that a
revision of the service bulletin that
contains a revised Note (b) is planned
for release. Once the revision has been
issued, under the provisions of
paragraph (g) of this AD, affected
operators may request approval to use
the later revision of the referenced
service bulletin as an alternative method
of compliance.
Request To Reduce the Compliance
Time
One commenter requests that the
compliance time be reduced. The
commenter suggests that the simplicity
and low cost of the task would allow
airlines to perform the task sooner.
We do not agree with the request to
shorten the compliance time. After
considering all the available
information, including the fact that
there have been no reports of in-service
arcing or sparking as a result of the
missing anti-static coating, we
determined that the compliance time, as
proposed, represents an appropriate
interval in which the anti-static coating
can be applied in a timely manner
within the fleet, while still maintaining
an adequate level of safety. In
developing the compliance time for this
AD action, we considered not only the
safety implications of the identified
unsafe condition, but the average
utilization rate of the affected fleet, the
practical aspects of an orderly
modification of the fleet during regular
maintenance periods, the availability of
required parts, and the time necessary
for the rulemaking. However, if
additional data are presented that would
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
justify a shorter compliance time, we
may consider further rulemaking on this
issue. Operators are always permitted to
accomplish the requirements of an AD
at a time earlier than the specified
compliance time.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We have determined that this change
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
This AD will affect about 65 airplanes
worldwide and 18 airplanes of U.S.
registry. The actions will take about 5
work hours per airplane, at an average
labor rate of $65 per work hour. Based
on these figures, the estimated cost of
this AD for U.S. operators is $5,850, or
$325 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
E:\FR\FM\06JYR1.SGM
06JYR1
Federal Register / Vol. 70, No. 128 / Wednesday, July 6, 2005 / Rules and Regulations
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. 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 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2005–14–05 Boeing: Amendment 39–14182.
Docket No. FAA–2004–19764;
Directorate Identifier 2004–NM–02–AD.
Effective Date
(a) This AD becomes effective August 10,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777–
200 and –300 series airplanes, certificated in
any category; as listed in Boeing Special
Attention Service Bulletin 777–57–0046,
dated September 25, 2003.
Unsafe Condition
(d) This AD was prompted by a report that
an anti-static coating was not applied
correctly on doors located within a
flammable fluid leakage zone. We are issuing
this AD to prevent an uncontrollable fire in
the leading edge of the wing, which could
damage critical wing structures and cause a
fuel tank explosion.
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.
Modification and Resistance Test
(f) Within 18 months after the effective
date of this AD, apply an anti-static
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16:43 Jul 05, 2005
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conductive coating to the fuel access and
thermal anti-icing blowout doors at the
location of the bonding fasteners, and
perform a resistance test on the new coating,
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 777–57–0046, dated
September 25, 2003. Where Note (b) of
Figures 1 and 2 of the Accomplishment
Instructions of the service bulletin specifies
to maintain the thickness of the conductive
coating between 0.0004 and 0.0008 inch, this
AD requires applying a uniform coating to
avoid runs, sags, or wrinkles, and to ensure
the anti-static coating touches the anti-static
coating exposed during surface preparation.
(1) If the resistance measured between the
door surface and a fastener located within the
doors’ surrounding support structure is
within the limits specified in the service
bulletin, no further action is required by this
paragraph.
(2) If the resistance measured between the
door surface and a fastener located within the
doors’ surrounding support structure is
outside the limits specified in the service
bulletin, before further flight, repeat the
actions as required by paragraph (f) of this
AD up to five times, as applicable. If the
results of the fifth test exceed the limits
specified in the service bulletin, before
further flight, contact the Manager, Seattle
Aircraft Certification Office (ACO), FAA, for
disposition of repairs.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(h) You must use Boeing Special Attention
Service Bulletin 777–57–0046, dated
September 25, 2003, to perform the actions
that are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register approves the incorporation
by reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207. To
view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the 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 June 24,
2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–13224 Filed 7–5–05; 8:45 am]
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Part 35
[Docket No. PL05–11–000]
Policy Statement Regarding Evaluation
of Independent Ownership and
Operation of Transmission
Issued June 27, 2005.
Federal Energy Regulatory
Commission, DOE.
ACTION: Policy statement.
AGENCY:
SUMMARY: The Federal Energy
Regulatory Commission (Commission) is
adopting this Policy Statement to clarify
the ownership structures that could
qualify for passive ownership in regards
to independent ownership and
operation.
Effective Date: The Policy
Statement will become effective
immediately.
DATES:
FOR FURTHER INFORMATION CONTACT:
Sebastian Tiger (Technical Information),
Office of Market Oversight and
Investigations, Federal Energy
Regulatory Commission, 888 First
Street, NE., Washington, DC 20426,
(202) 502–6079.
Andre Goodson (Legal Information),
Office of the General Counsel, Federal
Energy Regulatory Commission, 888
First Street, NE., Washington, DC
20426, (202) 502–8560.
SUPPLEMENTARY INFORMATION:
Before Commissioners: Pat Wood, III,
Chairman; Nora Mead Brownell, Joseph T.
Kelliher, and Suedeen G. Kelly.
I. Introduction
1. The Commission is issuing this
Policy Statement to provide clarity and
remove barriers to the formation of
independent transmission companies.
Specifically, the Policy Statement
clarifies that the Commission would be
willing to accept proposals from
independent transmission companies
(ITCs) which have market participants
as passive minority equity owners. On
various occasions, the Commission has
allowed innovative rate treatments both
to facilitate the creation of ITCs and to
stimulate investment in transmission
infrastructure by ITCs.1
1 These incentive proposals include: enhanced
returns on equity, within the zone of
reasonableness; hypothetical or imputed capital
structures; recovery of deferred income tax
liabilities; cost deferrals; Construction Work in
Progress (CWIP) in rate base; accelerated book
depreciation; and expensing of pre-certification
Continued
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 70, Number 128 (Wednesday, July 6, 2005)]
[Rules and Regulations]
[Pages 38755-38757]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13224]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19764; Directorate Identifier 2004-NM-02-AD;
Amendment 39-14182; AD 2005-14-05]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 777-200 and -300 series airplanes. This AD
requires applying an anti-static conductive coating to the fuel access
and thermal anti-icing blowout doors at the location of the bonding
fasteners on the leading edge of the wings, and performing a resistance
test on the new coating to ensure correct ground path resistance. This
AD is prompted by a report that an anti-static coating was not applied
correctly on doors located within a flammable fluid leakage zone. We
are issuing this AD to prevent an uncontrollable fire in the leading
edge of the wing, which could damage critical wing structures and cause
a fuel tank explosion.
DATES: This AD becomes effective August 10, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of August
10, 2005.
ADDRESSES: For service information identified in this AD, contact
Boeing
[[Page 38756]]
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2004-19764; the directorate
identifier for this docket is 2004-NM-02-AD.
FOR FURTHER INFORMATION CONTACT: Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6500; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Boeing Model 777-200 and -300 series airplanes.
That action, published in the Federal Register on December 7, 2004 (69
FR 70574), proposed to require applying an anti-static conductive
coating to the fuel access and thermal anti-icing blowout doors at the
location of the bonding fasteners on the leading edge of the wings, and
performing a resistance test on the new coating to ensure correct
ground path resistance.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Support for the Proposed AD
One commenter, the manufacturer, supports the proposed AD.
Request To Remove a Service Bulletin Action To Maintain Certain Coating
Thickness
One commenter concurs with the AD. However, the commenter states
that Boeing Special Attention Service Bulletin 777-57-0046, dated
September 25, 2003, which is referenced in the proposed AD as the
appropriate source of service information, specifies an action to
maintain a certain coating thickness that is impractical to perform.
The commenter states that Note (b) of Figures 1 and 2 in the
Accomplishment Instructions of the service bulletin specifies that the
conductive coating be applied at a thickness of 0.0004 to 0.0008 inch.
The commenter states that there is no practical method to measure the
thickness and that they have confirmation from the manufacturer that
the intent of Note (b) is to ensure that the coating application is
continuous. The commenter also notes that the manufacturer plans to
delete the thickness dimension and revise the wording in Note (b) in
the next revision of the service bulletin.
We agree with the commenter that the intent of Note (b) of the
service bulletin is to ensure a continuous coating and that the
measured thickness is not relevant. Although Note (b) specifies
maintaining the thickness of the applied conductive coating between
0.0004 and 0.0008 inch, we have revised paragraph (f) of this AD to
clarify the manufacturer's intent: to apply a uniform coating to avoid
runs, sags, or wrinkles, and to ensure the anti-static coating touches
the anti-static coating exposed during surface preparation.
We have coordinated this difference with the manufacturer. The
manufacturer has informed us that a revision of the service bulletin
that contains a revised Note (b) is planned for release. Once the
revision has been issued, under the provisions of paragraph (g) of this
AD, affected operators may request approval to use the later revision
of the referenced service bulletin as an alternative method of
compliance.
Request To Reduce the Compliance Time
One commenter requests that the compliance time be reduced. The
commenter suggests that the simplicity and low cost of the task would
allow airlines to perform the task sooner.
We do not agree with the request to shorten the compliance time.
After considering all the available information, including the fact
that there have been no reports of in-service arcing or sparking as a
result of the missing anti-static coating, we determined that the
compliance time, as proposed, represents an appropriate interval in
which the anti-static coating can be applied in a timely manner within
the fleet, while still maintaining an adequate level of safety. In
developing the compliance time for this AD action, we considered not
only the safety implications of the identified unsafe condition, but
the average utilization rate of the affected fleet, the practical
aspects of an orderly modification of the fleet during regular
maintenance periods, the availability of required parts, and the time
necessary for the rulemaking. However, if additional data are presented
that would justify a shorter compliance time, we may consider further
rulemaking on this issue. Operators are always permitted to accomplish
the requirements of an AD at a time earlier than the specified
compliance time.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD will affect about 65 airplanes worldwide and 18 airplanes
of U.S. registry. The actions will take about 5 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of this AD for U.S. operators is $5,850, or
$325 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
[[Page 38757]]
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-14-05 Boeing: Amendment 39-14182. Docket No. FAA-2004-19764;
Directorate Identifier 2004-NM-02-AD.
Effective Date
(a) This AD becomes effective August 10, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777-200 and -300 series
airplanes, certificated in any category; as listed in Boeing Special
Attention Service Bulletin 777-57-0046, dated September 25, 2003.
Unsafe Condition
(d) This AD was prompted by a report that an anti-static coating
was not applied correctly on doors located within a flammable fluid
leakage zone. We are issuing this AD to prevent an uncontrollable
fire in the leading edge of the wing, which could damage critical
wing structures and cause a fuel tank explosion.
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.
Modification and Resistance Test
(f) Within 18 months after the effective date of this AD, apply
an anti-static conductive coating to the fuel access and thermal
anti-icing blowout doors at the location of the bonding fasteners,
and perform a resistance test on the new coating, in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-57-0046, dated September 25, 2003. Where Note (b) of
Figures 1 and 2 of the Accomplishment Instructions of the service
bulletin specifies to maintain the thickness of the conductive
coating between 0.0004 and 0.0008 inch, this AD requires applying a
uniform coating to avoid runs, sags, or wrinkles, and to ensure the
anti-static coating touches the anti-static coating exposed during
surface preparation.
(1) If the resistance measured between the door surface and a
fastener located within the doors' surrounding support structure is
within the limits specified in the service bulletin, no further
action is required by this paragraph.
(2) If the resistance measured between the door surface and a
fastener located within the doors' surrounding support structure is
outside the limits specified in the service bulletin, before further
flight, repeat the actions as required by paragraph (f) of this AD
up to five times, as applicable. If the results of the fifth test
exceed the limits specified in the service bulletin, before further
flight, contact the Manager, Seattle Aircraft Certification Office
(ACO), FAA, for disposition of repairs.
Alternative Methods of Compliance (AMOCs)
(g) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
Material Incorporated by Reference
(h) You must use Boeing Special Attention Service Bulletin 777-
57-0046, dated September 25, 2003, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approves the incorporation by reference of
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
To get copies of the service information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view
the AD docket, go to the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at the
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 June 24, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-13224 Filed 7-5-05; 8:45 am]
BILLING CODE 4910-13-P
