Airworthiness Directives; Airbus Model A330-200, A330-300, and A340-300 Series Airplanes, 51906-51908 [E8-19720]
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51906
Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
required prior to issuance of the special flight
permit. Before using any approved special
flight permits, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO. Special flight permits
may be permitted provided that the
conditions specified in paragraphs (m)(1),
(m)(2), (m)(3), (m)(4), and (m)(5) of this AD
are met.
(1) Both the right-hand side and left-hand
side of the airplane must have at least one
barrel nut that is not within the suspect batch
(i.e., barrel nut is not identified with a
marking of LH7940T SPS 01). The barrel nuts
that are not within the suspect batch must be
in good working condition (i.e., no cracking
of the barrel nut).
(2) No passengers and no cargo are
onboard.
(3) Airplane must operate in fair weather
conditions with a low risk of turbulence.
(4) Airplane must operate with reduced
airspeed. For further information, contact
Bombardier, Q Series 24 Hour Service
Customer Response Center, at: Telephone 1–
416–375–4000; fax 1–416–375–4539; E-mail:
thd.qseries@aero.bombardier.com.
(5) All of the conditions specified in
paragraphs (m)(1), (m)(2), (m)(3), and (m)(4)
of this AD are on a case-by-case basis.
Contact your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO, for assistance.
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, New York ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN:
Pong Lee, Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516)
228–7324; fax (516) 794–5531. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
pwalker on PROD1PC71 with RULES
Related Information
(o) Canadian airworthiness directive CF–
2008–11R1, dated May 9, 2008, also
addresses the subject of the AD.
Material Incorporated by Reference
(p) You must use Bombardier Alert Service
Bulletin A84–57–19, Revision A, dated
February 6, 2008; or Bombardier Alert
Service Bulletin A84–57–19, Revision B,
dated March 6, 2008; as applicable; to
perform the actions that are required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Bombardier Alert Service Bulletin A84–57–
19, Revision B, dated March 6, 2008, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On February 13, 2008 (73 FR 8187,
February 13, 2008), the Director of the
Federal Register approved the incorporation
by reference of Bombardier Alert Service
VerDate Aug<31>2005
17:07 Sep 05, 2008
Jkt 214001
Bulletin A84–57–19, Revision A, dated
February 6, 2008.
(3) Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19718 Filed 9–5–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0672; Directorate
Identifier 2008–NM–032–AD; Amendment
39–15660; AD 2008–18–03]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, and A340–300
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
During manufacturing of A330/A340
aircraft framework, cracks have been found
on Frame (FR) 12, left (LH) and right (RH)
sides. It has been confirmed that a defect of
the FR12 forming tool press is the root cause
of the cracks.
If undetected such damage could affect,
after propagation, the structural integrity of
the aircraft.
*
*
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 14, 2008.
The Director of the Federal Register
approved the incorporation by reference
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of certain publications listed in this AD
as of October 14, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 24, 2008 (73 FR 35595).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
During manufacturing of A330/A340
aircraft framework, cracks have been found
on Frame (FR) 12, left (LH) and right (RH)
sides. It has been confirmed that a defect of
the FR12 forming tool press is the root cause
of the cracks.
If undetected such damage could affect,
after propagation, the structural integrity of
the aircraft.
In order to permit an early detection and
repair of cracks on FR12, LH and RH sides,
this Airworthiness Directive (AD) mandates a
one time High Frequency Eddy Current
(HFEC) inspection of FR12.
Corrective actions include, for certain
findings, contacting Airbus for repair
instructions and doing the repair;
repairing cracking (i.e., installing a new
splice); and applying new protective
coatings and corrosion inhibitors. You
may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 20 products of U.S. registry. We
also estimate that it will take about 3
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $0 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $4,800, or
$240 per product.
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.
pwalker on PROD1PC71 with RULES
Regulatory Findings
We 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
VerDate Aug<31>2005
17:07 Sep 05, 2008
Jkt 214001
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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 AD:
I
2008–18–03 Airbus: Amendment 39–15660.
Docket No. FAA–2008–0672; Directorate
Identifier 2008–NM–032–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 14, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330–
200, A330–300, and A340–300 series
airplanes; certificated in any category; all
certified models, all manufacturing serial
PO 00000
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51907
numbers (MSN) from MSN 0489 through
0722 inclusive, and MSN 0725, 0726, 0728,
0730, 0732, and 0734.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During manufacturing of A330/A340
aircraft framework, cracks have been found
on Frame (FR) 12, left (LH) and right (RH)
sides. It has been confirmed that a defect of
the FR12 forming tool press is the root cause
of the cracks.
If undetected such damage could affect,
after propagation, the structural integrity of
the aircraft.
In order to permit an early detection and
repair of cracks on FR12, LH and RH sides,
this Airworthiness Directive (AD) mandates a
one time High Frequency Eddy Current
(HFEC) inspection of FR12.
Corrective actions include, for certain
findings, contacting Airbus for repair
instructions and doing the repair; repairing
cracking (i.e., installing a new splice); and
applying new protective coatings and
corrosion inhibitors.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Prior to the accumulation of 19,500
total flight cycles or within 3 months after
the effective date of this AD, whichever
occurs later: Perform a HFEC inspection at
the LH and RH sides of frame 12, in
accordance with the instructions defined in
Airbus Mandatory Service Bulletin A330–53–
3174 or A340–53–4177, both dated October
10, 2007, as applicable. If no cracking is
found, no further action is required by this
AD. Except as required by paragraph (f)(2) of
this AD, if any cracking is found, before
further flight, do the applicable corrective
actions in accordance with the instructions of
Airbus Mandatory Service Bulletin A330–53–
3174 or A340–53–4177, as applicable.
(2) If any cracking is found that exceeds the
limits specified in Airbus Mandatory Service
Bulletin A330–53–3174 or A340–53–4177,
both dated October 10, 2007, as applicable;
or if any cracking is found during any HFEC
inspection of the cut-out area; before further
flight, contact Airbus for repair instructions
and do the repair.
FAA AD Differences
Note: This AD differs from the MCAI and/
or service information as follows: No
difference.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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: Vladimir
Ulyanov, Aerospace Engineer, International
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51908
Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to European Aviation Safety
Agency (EASA) Airworthiness Directive
2007–0302, dated December 14, 2007; and
Airbus Mandatory Service Bulletins A330–
53–3174 and A340–53–4177, both dated
October 10, 2007; for related information.
Material Incorporated by Reference
pwalker on PROD1PC71 with RULES
(i) You must use Airbus Mandatory Service
Bulletin A330–53–3174, including Appendix
01, dated October 10, 2007; or Airbus
Mandatory Service Bulletin A340–53–4177,
including Appendix 01, dated October 10,
2007; as applicable; to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–19720 Filed 9–5–08; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
17:07 Sep 05, 2008
Jkt 214001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0407; Directorate
Identifier 2008–NM–002–AD; Amendment
39–15662; AD 2008–18–05]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model 717–200 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
McDonnell Douglas Model 717–200
airplanes. This AD requires inspecting
the drive assembly of the aft elevator
standby loop of the elevator standby
cable system for interference between
the clevis and bolt of the bellcrank
assembly, correct orientation of the pullpull cable clevis bolt, and excessive
freeplay of the bellcrank assembly
bearing, and corrective actions if
necessary. This AD also requires
modifying the pull-pull cable clevis in
the drive assembly of the aft elevator
standby loop for certain airplanes. This
AD results from a report of an aborted
takeoff due to a control column
disconnect. We are issuing this AD to
prevent binding of the bolt that connects
the cable 264A clevis to the bellcrank
assembly against the adjacent (upper)
clevis of the pull-pull cable assembly.
This binding condition could result in
slow airplane rotation or a control
column disconnect during takeoff and a
runway excursion if takeoff must be
aborted.
DATES:
This AD is effective October 14,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 14, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846;
Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024).
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
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evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
David Rathfelder, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; telephone (562)
627–5229; fax (562) 627–5210.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain McDonnell Douglas Model 717–
200 airplanes. That NPRM was
published in the Federal Register on
April 7, 2008 (73 FR 18725). That NPRM
proposed to require inspecting the drive
assembly of the aft elevator standby
loop for interference between the clevis
and bolt of the bellcrank assembly,
correct orientation of the pull-pull cable
clevis bolt, and excessive freeplay of the
bellcrank assembly bearing, and
corrective actions if necessary. That
NPRM also proposed to require
modifying the pull-pull cable clevis in
the drive assembly of the aft elevator
standby loop for certain airplanes.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Change Summary Section
for Clarification
Boeing asks that the second sentence
of the Summary section in the NPRM,
which describes what is to be inspected,
be changed as follows: ‘‘This proposed
AD would require inspecting the aft
elevator standby loop drive assembly of
the elevator standby cable system for
interference between the clevis and bolt
of this bellcrank assembly, correct
orientation of the pull-pull cable clevis
bolt, and excessive freeplay of the
bellcrank assembly bearing, and
corrective actions if necessary.’’ Boeing
states that this would more accurately
describe the drive assembly being
inspected since there are two drive
assemblies in the elevator standby cable
system.
We agree that the description in the
Summary section of the AD should be
clarified. Therefore, we have changed
the Summary section and all other
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]]>Agencies
[Federal Register Volume 73, Number 174 (Monday, September 8, 2008)]
[Rules and Regulations]
[Pages 51906-51908]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-19720]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0672; Directorate Identifier 2008-NM-032-AD;
Amendment 39-15660; AD 2008-18-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, and
A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
During manufacturing of A330/A340 aircraft framework, cracks
have been found on Frame (FR) 12, left (LH) and right (RH) sides. It
has been confirmed that a defect of the FR12 forming tool press is
the root cause of the cracks.
If undetected such damage could affect, after propagation, the
structural integrity of the aircraft.
* * * * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 14, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 14,
2008.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 24, 2008 (73 FR
35595). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During manufacturing of A330/A340 aircraft framework, cracks
have been found on Frame (FR) 12, left (LH) and right (RH) sides. It
has been confirmed that a defect of the FR12 forming tool press is
the root cause of the cracks.
If undetected such damage could affect, after propagation, the
structural integrity of the aircraft.
In order to permit an early detection and repair of cracks on
FR12, LH and RH sides, this Airworthiness Directive (AD) mandates a
one time High Frequency Eddy Current (HFEC) inspection of FR12.
Corrective actions include, for certain findings, contacting Airbus for
repair instructions and doing the repair; repairing cracking (i.e.,
installing a new splice); and applying new protective coatings and
corrosion inhibitors. You may obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
[[Page 51907]]
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 20 products of U.S.
registry. We also estimate that it will take about 3 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts will cost about $0 per
product. Where the service information lists required parts costs that
are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $4,800, or $240 per product.
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 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 this AD:
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 AD:
2008-18-03 Airbus: Amendment 39-15660. Docket No. FAA-2008-0672;
Directorate Identifier 2008-NM-032-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
14, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-200, A330-300, and
A340-300 series airplanes; certificated in any category; all
certified models, all manufacturing serial numbers (MSN) from MSN
0489 through 0722 inclusive, and MSN 0725, 0726, 0728, 0730, 0732,
and 0734.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During manufacturing of A330/A340 aircraft framework, cracks
have been found on Frame (FR) 12, left (LH) and right (RH) sides. It
has been confirmed that a defect of the FR12 forming tool press is
the root cause of the cracks.
If undetected such damage could affect, after propagation, the
structural integrity of the aircraft.
In order to permit an early detection and repair of cracks on
FR12, LH and RH sides, this Airworthiness Directive (AD) mandates a
one time High Frequency Eddy Current (HFEC) inspection of FR12.
Corrective actions include, for certain findings, contacting Airbus
for repair instructions and doing the repair; repairing cracking
(i.e., installing a new splice); and applying new protective
coatings and corrosion inhibitors.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Prior to the accumulation of 19,500 total flight cycles or
within 3 months after the effective date of this AD, whichever
occurs later: Perform a HFEC inspection at the LH and RH sides of
frame 12, in accordance with the instructions defined in Airbus
Mandatory Service Bulletin A330-53-3174 or A340-53-4177, both dated
October 10, 2007, as applicable. If no cracking is found, no further
action is required by this AD. Except as required by paragraph
(f)(2) of this AD, if any cracking is found, before further flight,
do the applicable corrective actions in accordance with the
instructions of Airbus Mandatory Service Bulletin A330-53-3174 or
A340-53-4177, as applicable.
(2) If any cracking is found that exceeds the limits specified
in Airbus Mandatory Service Bulletin A330-53-3174 or A340-53-4177,
both dated October 10, 2007, as applicable; or if any cracking is
found during any HFEC inspection of the cut-out area; before further
flight, contact Airbus for repair instructions and do the repair.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No difference.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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:
Vladimir Ulyanov, Aerospace Engineer, International
[[Page 51908]]
Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-
1138; fax (425) 227-1149. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to European Aviation Safety Agency (EASA)
Airworthiness Directive 2007-0302, dated December 14, 2007; and
Airbus Mandatory Service Bulletins A330-53-3174 and A340-53-4177,
both dated October 10, 2007; for related information.
Material Incorporated by Reference
(i) You must use Airbus Mandatory Service Bulletin A330-53-3174,
including Appendix 01, dated October 10, 2007; or Airbus Mandatory
Service Bulletin A340-53-4177, including Appendix 01, dated October
10, 2007; as applicable; to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-
locations.html.
Issued in Renton, Washington, on August 18, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-19720 Filed 9-5-08; 8:45 am]
BILLING CODE 4910-13-P
