Airworthiness Directives; BAE Systems (Operations) Limited Model ATP Airplanes, 58295-58298 [05-19832]
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Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations
‘‘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
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
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–20–22 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14318. Docket No. FAA–2005–22583;
Directorate Identifier 2002–NM–303–AD.
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(a) This AD becomes effective October 21,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model ATP airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from information
indicating the potential for environmental
damage of the fuselage and wing structure.
We are issuing this AD to detect and correct
such damage, including corrosion, in the
fuselage and wing structure, which could
result in cracking and consequent reduced
structural integrity of the fuselage and wing
structure.
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.
Repetitive Inspections and Corrective
Actions
(f) Within 18 months after the effective
date of this AD, perform detailed inspections
for environmental damage, including but not
limited to corrosion, of the fuselage and wing
structure and any applicable corrective
action in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin ATP–51–001, dated August 14,
2002, except as provided by paragraph (g) of
this AD. Any applicable corrective actions
must be accomplished before further flight.
Thereafter, repeat these inspections at
intervals not to exceed those specified in the
ATP Maintenance Review Board Report and
the Maintenance Planning Document, as
applicable, in accordance with the service
bulletin.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
No Reporting
(h) Although British Aerospace ATP
Service Bulletin ATP–51–001, dated August
14, 2002, specifies reporting inspection
results to the manufacturer, this AD does not
require that action.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(j) None.
Material Incorporated by Reference
(k) You must use BAE Systems
(Operations) Limited Service Bulletin ATP–
51–001, dated August 14, 2002, to perform
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact British Aerospace Regional
Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171, for a copy of
this service information. You may review
copies at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19833 Filed 10–5–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Exception to Service Bulletin Instructions
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Effective Date
58295
14 CFR Part 39
(g) If damage is found that is outside the
limits specified in the structural repair
manual, as referenced in BAE Systems
(Operations) Limited Service Bulletin ATP–
51–001, dated August 14, 2002, and the
service bulletin specifies reporting the details
of the damage to In-Service Engineering and
asking for repair instructions: Before further
flight, repair the damage in accordance with
a method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Civil
Aviation Authority (or its delegated agent).
[Docket No. FAA–2005–22586; Directorate
Identifier 2002–NM–258–AD; Amendment
39–14315; AD 2005–20–19]
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RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited Model
ATP Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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06OCR1
58296
Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations
Final rule; request for
comments.
ACTION:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all BAE
Systems (Operations) Limited Model
ATP airplanes. This AD requires onetime inspections for corrosion of the
engine sub-frame tubes in zone 1 and of
the engine attachment struts in zone 5,
and corrective action if necessary. This
AD results from reports of reduced
thickness in localized areas of the
engine sub-frame tubes due to corrosion,
and reports that corrosion may also exist
in the engine attachment struts in zone
5. We are issuing this AD to prevent
failure of the engine sub-frame tubes or
the engine attachment struts, which
could result in separation of an engine
from the airplane.
DATES: This AD becomes effective
October 21, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 21, 2005.
We must receive comments on this
AD by December 5, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact British Aerospace Regional
Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia
20171, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA),
which is the airworthiness authority for
the United Kingdom, notified us that an
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15:31 Oct 05, 2005
Jkt 208001
unsafe condition may exist on all BAE
Systems (Operations) Limited Model
ATP airplanes. The CAA advises that
there have been reports indicating
reduced thickness in localized areas of
the engine sub-frame tubes due to
corrosion. Such corrosion may also exist
in the engine attachment struts in zone
5. This condition, if not corrected, could
result in failure of the engine sub-frame
tubes or the engine attachment struts,
and consequent separation of an engine
from the airplane.
Relevant Service Information
BAE Systems (Operations) Limited
has issued Service Bulletins ATP–54–18
and ATP–54–19, both dated March 2,
2001. Service Bulletin ATP–54–18
describes procedures for performing an
X-ray (radiographic) inspection for
corrosion of the engine sub-frame tubes
in Zone 1, and doing corrective action
if necessary. Service Bulletin ATP–54–
19 describes procedures for performing
an X-ray (radiographic) inspection for
corrosion of the engine attachment
struts in Zone 5, and doing corrective
action if necessary. If corrosion is found,
the service bulletins specify that the
corrective action is installing a
serviceable component, or contacting
the manufacturer for instructions on
repairing corroded components.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA mandated the
service information and issued British
airworthiness directives 006–03–2001
(mandating Service Bulletin ATP–54–
18) and 007–03–2001 (mandating
Service Bulletin ATP–54–19) to ensure
the continued airworthiness of these
airplanes in the United Kingdom.
FAA’s Determination and Requirements
of This AD
This airplane model is manufactured
in the United Kingdom and is type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the CAA has
kept the FAA informed of the situation
described above. We have examined the
CAA’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
prevent failure of the engine sub-frame
tubes or the engine attachment struts,
which could result in separation of an
engine from the airplane. This AD
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requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Differences Among
the AD, British Airworthiness
Directives, and Service Bulletins.’’
Differences Among the AD, British
Airworthiness Directives, and Service
Bulletins
British airworthiness directives 006–
03–2001 and 007–03–2001 specify that
compliance is required no later than
August 31, 2002. We do not use
calendar dates to establish compliance
times in our ADs. In developing an
appropriate compliance time for this
AD, we considered the CAA’s and the
manufacturer’s recommendations, and
the degree of urgency associated with
the subject unsafe condition. In light of
these factors, we find that a compliance
time of 180 days after the effective date
of this AD represents an appropriate
interval of time for affected airplanes to
continue to operate without
compromising safety. This difference
has been coordinated with the CAA.
The service bulletins specify that, in
lieu of replacing a corroded component
with a serviceable component, operators
may contact the manufacturer for
information on the ‘‘serviceability’’ of
corroded components. If any corrosion
is found, this AD requires, before further
flight, replacing the corroded
component with a serviceable
component, or repairing the corroded
component using a method that we or
the CAA (or its delegated agent)
approve. In light of the type of repair
that would be required to address the
unsafe condition, and consistent with
existing bilateral airworthiness
agreements, we have determined that,
for this AD, a repair we or the CAA
approve would be acceptable for
compliance with the repair provision of
this AD.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required actions would take about 7
work hours per airplane, at an average
labor rate of $65 per work hour. Based
on these figures, the estimated cost of
the AD would be $455 per airplane.
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Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2005–22586; Directorate Identifier
2002–NM–258–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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
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15:31 Oct 05, 2005
Jkt 208001
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
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
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58297
2005–20–19 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14315. Docket No. FAA–2005–22586;
Directorate Identifier 2002–NM–258–AD.
Effective Date
(a) This AD becomes effective October 21,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model ATP airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from reports of reduced
thickness in localized areas of the engine
sub-frame tubes due to corrosion, and reports
that corrosion may also exist in the engine
attachment struts in zone 5. The FAA is
issuing this AD to prevent failure of the
engine sub-frame tubes or the engine
attachment struts, which could result in
separation of an engine from 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.
Inspections
(f) Within 180 days after the effective date
of this AD, perform X-ray (radiographic)
inspections for corrosion of the engine subframe tubes in Zone 1 and the engine
attachment struts in Zone 5, in accordance
with the Accomplishment Instructions of
BAE Systems (Operations) Limited Service
Bulletins ATP–54–18 and ATP–54–19, both
dated March 2, 2001. Although the service
bulletins referenced in this AD specify to
submit inspection results to the
manufacturer, this AD does not require that
action.
Corrective Action
(g) If any corrosion is found during the
inspections required by paragraph (f) of this
AD: Before further flight, replace the
corroded component with a serviceable
component, in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletins ATP–54–18 and ATP–54–19, both
dated March 2, 2001; or repair the corroded
component in accordance with a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the Civil
Aviation Authority (or its delegated agent).
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
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58298
Federal Register / Vol. 70, No. 193 / Thursday, October 6, 2005 / Rules and Regulations
FAA Flight Standards Certificate Holding
District Office.
Related Information
(i) British airworthiness directives 006–03–
2001 and 007–03–2001 also address the
subjects of this AD.
Material Incorporated by Reference
(j) You must use BAE Systems (Operations)
Limited Service Bulletin ATP–54–18, dated
March 2, 2001; and BAE Systems
(Operations) Limited Service Bulletin ATP–
54–19, dated March 2, 2001; to perform the
actions that are required by this AD, unless
the AD specifies otherwise. The Director of
the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact British
Aerospace Regional Aircraft American
Support, 13850 Mclearen Road, Herndon,
Virginia 20171, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at 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
September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19832 Filed 10–5–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22587; Directorate
Identifier 2003–NM–266–AD; Amendment
39–14316; AD 2005–20–20]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–301, –321, –322, –341, and –342
Airplanes; and Model A340–200 and
A340–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
Discussion
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–301, –321, –322,
–341, and –342 airplanes; and Model
A340–200 and A340–300 series
airplanes. This AD requires installing
lockplates on the main landing gear
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15:31 Oct 05, 2005
Jkt 208001
(MLG) and center landing gear (CLG)
wheel assemblies, as applicable, to keep
the tie bolts in position in the wheel
assembly in the event of a tie bolt
failure. This AD results from reports of
tie bolts that were broken or missing
from the MLG wheel assembly; in some
cases the wheels have ruptured and
caused damage to other equipment in
the adjacent area. We are issuing this
AD to prevent damage to the wheel
assembly and equipment in the area
adjacent to the MLG and CLG, which
could result in a decrease in braking
function and possible runway over-run.
DATES: Effective October 21, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 21, 2005.
We must receive comments on this
AD by December 5, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-Wide Rulemaking Web
Site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist on certain Airbus Model A330–
301, –321, –322, –341, and –342
airplanes that are equipped with
Messier-Goodrich main landing gear
(MLG) wheel assemblies, part number
(P/N) 3–1509–2; and Model A340–200
and A340–300 series airplanes that are
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equipped with center landing gear
(CLG) and MLG wheel assemblies, P/N
3–1509–2. The DGAC advises that
operators of Model A330 series
airplanes fitted with the affected wheel
assemblies reported tie bolts that were
broken or missing from the MLG wheel
assemblies. Investigations indicated that
the tie bolts ruptured due to fatigue
failure and subsequently migrated out of
the tie bolt hole. As a consequence, in
some cases the failed tie bolt caught on
the brake unit and ruptured a wheel.
This condition, if not corrected, could
cause damage to the wheel assembly
and equipment in the area adjacent to
the MLG and CLG, which could result
in a decrease in braking function and
possible runway over-run.
Relevant Service Information
Airbus has issued Service Bulletin
A330–32–3167, dated August 12, 2003
(for Model A330–301, –321, –322, and
–342 airplanes); and Service Bulletin
A340–32–4206, dated August 12, 2003
(for Model A340–211 and –212
airplanes; and Model A340–300 series
airplanes). The service bulletins
describe procedures for modifying the
MLG and CLG, as applicable, by
installing lockplates on the wheel
assembly to keep the tie bolts in
position in the wheel assembly in the
event of a tie bolt failure.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. The DGAC mandated the
service information and issued French
airworthiness directives 2003–392(B)
and 2003–393(B), both dated October
29, 2003, to ensure the continued
airworthiness of these airplanes in
France.
The service bulletins refer to
Goodrich-Messier Service Bulletin 3–
1509–32–5, dated August 12, 2003, as
an additional source of service
information for installing the lockplates.
FAA’s Determination and Requirements
of This AD
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the DGAC has
kept the FAA informed of the situation
described above. We have examined the
DGAC’s findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
E:\FR\FM\06OCR1.SGM
06OCR1
]]>Agencies
[Federal Register Volume 70, Number 193 (Thursday, October 6, 2005)]
[Rules and Regulations]
[Pages 58295-58298]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19832]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22586; Directorate Identifier 2002-NM-258-AD;
Amendment 39-14315; AD 2005-20-19]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited Model
ATP Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 58296]]
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
BAE Systems (Operations) Limited Model ATP airplanes. This AD requires
one-time inspections for corrosion of the engine sub-frame tubes in
zone 1 and of the engine attachment struts in zone 5, and corrective
action if necessary. This AD results from reports of reduced thickness
in localized areas of the engine sub-frame tubes due to corrosion, and
reports that corrosion may also exist in the engine attachment struts
in zone 5. We are issuing this AD to prevent failure of the engine sub-
frame tubes or the engine attachment struts, which could result in
separation of an engine from the airplane.
DATES: This AD becomes effective October 21, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 21,
2005.
We must receive comments on this AD by December 5, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact British Aerospace Regional Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia 20171, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified us that an unsafe condition
may exist on all BAE Systems (Operations) Limited Model ATP airplanes.
The CAA advises that there have been reports indicating reduced
thickness in localized areas of the engine sub-frame tubes due to
corrosion. Such corrosion may also exist in the engine attachment
struts in zone 5. This condition, if not corrected, could result in
failure of the engine sub-frame tubes or the engine attachment struts,
and consequent separation of an engine from the airplane.
Relevant Service Information
BAE Systems (Operations) Limited has issued Service Bulletins ATP-
54-18 and ATP-54-19, both dated March 2, 2001. Service Bulletin ATP-54-
18 describes procedures for performing an X-ray (radiographic)
inspection for corrosion of the engine sub-frame tubes in Zone 1, and
doing corrective action if necessary. Service Bulletin ATP-54-19
describes procedures for performing an X-ray (radiographic) inspection
for corrosion of the engine attachment struts in Zone 5, and doing
corrective action if necessary. If corrosion is found, the service
bulletins specify that the corrective action is installing a
serviceable component, or contacting the manufacturer for instructions
on repairing corroded components.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA mandated
the service information and issued British airworthiness directives
006-03-2001 (mandating Service Bulletin ATP-54-18) and 007-03-2001
(mandating Service Bulletin ATP-54-19) to ensure the continued
airworthiness of these airplanes in the United Kingdom.
FAA's Determination and Requirements of This AD
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. We have examined the CAA's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to prevent failure of the engine
sub-frame tubes or the engine attachment struts, which could result in
separation of an engine from the airplane. This AD requires
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Among the
AD, British Airworthiness Directives, and Service Bulletins.''
Differences Among the AD, British Airworthiness Directives, and Service
Bulletins
British airworthiness directives 006-03-2001 and 007-03-2001
specify that compliance is required no later than August 31, 2002. We
do not use calendar dates to establish compliance times in our ADs. In
developing an appropriate compliance time for this AD, we considered
the CAA's and the manufacturer's recommendations, and the degree of
urgency associated with the subject unsafe condition. In light of these
factors, we find that a compliance time of 180 days after the effective
date of this AD represents an appropriate interval of time for affected
airplanes to continue to operate without compromising safety. This
difference has been coordinated with the CAA.
The service bulletins specify that, in lieu of replacing a corroded
component with a serviceable component, operators may contact the
manufacturer for information on the ``serviceability'' of corroded
components. If any corrosion is found, this AD requires, before further
flight, replacing the corroded component with a serviceable component,
or repairing the corroded component using a method that we or the CAA
(or its delegated agent) approve. In light of the type of repair that
would be required to address the unsafe condition, and consistent with
existing bilateral airworthiness agreements, we have determined that,
for this AD, a repair we or the CAA approve would be acceptable for
compliance with the repair provision of this AD.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required actions would take about 7 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the AD would be $455 per airplane.
[[Page 58297]]
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
22586; Directorate Identifier 2002-NM-258-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-20-19 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-14315. Docket No. FAA-
2005-22586; Directorate Identifier 2002-NM-258-AD.
Effective Date
(a) This AD becomes effective October 21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model ATP airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from reports of reduced thickness in
localized areas of the engine sub-frame tubes due to corrosion, and
reports that corrosion may also exist in the engine attachment
struts in zone 5. The FAA is issuing this AD to prevent failure of
the engine sub-frame tubes or the engine attachment struts, which
could result in separation of an engine from 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.
Inspections
(f) Within 180 days after the effective date of this AD, perform
X-ray (radiographic) inspections for corrosion of the engine sub-
frame tubes in Zone 1 and the engine attachment struts in Zone 5, in
accordance with the Accomplishment Instructions of BAE Systems
(Operations) Limited Service Bulletins ATP-54-18 and ATP-54-19, both
dated March 2, 2001. Although the service bulletins referenced in
this AD specify to submit inspection results to the manufacturer,
this AD does not require that action.
Corrective Action
(g) If any corrosion is found during the inspections required by
paragraph (f) of this AD: Before further flight, replace the
corroded component with a serviceable component, in accordance with
the Accomplishment Instructions of BAE Systems (Operations) Limited
Service Bulletins ATP-54-18 and ATP-54-19, both dated March 2, 2001;
or repair the corroded component in accordance with a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the Civil Aviation Authority
(or its delegated agent).
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the
[[Page 58298]]
FAA Flight Standards Certificate Holding District Office.
Related Information
(i) British airworthiness directives 006-03-2001 and 007-03-2001
also address the subjects of this AD.
Material Incorporated by Reference
(j) You must use BAE Systems (Operations) Limited Service
Bulletin ATP-54-18, dated March 2, 2001; and BAE Systems
(Operations) Limited Service Bulletin ATP-54-19, dated March 2,
2001; to perform the actions that are required by this AD, unless
the AD specifies otherwise. The Director of the Federal Register
approved the incorporation by reference of these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact British
Aerospace Regional Aircraft American Support, 13850 Mclearen Road,
Herndon, Virginia 20171, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at 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 September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19832 Filed 10-5-05; 8:45 am]
BILLING CODE 4910-13-P
