[Federal Register: November 28, 2008 (Volume 73, Number 230)]
[Rules and Regulations]
[Page 72323-72326]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28no08-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0910; Directorate Identifier 2008-NM-033-AD;
Amendment 39-15749; AD 2008-24-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
300, A340-500, and A340-600 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an existing 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:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment * * *.
* * * Three additional events of panel loss have been
experienced on in service aircraft already inspected in accordance
with the AD requirements * * *.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 2, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 2,
2009.
ADDRESSES: You may examine the AD docket on the Internet at http://
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 August 26, 2008 (73
FR
[[Page 72324]]
50256) and proposed to supersede AD 2007-08-05, Amendment 39-15022 (72
FR 18563, April 13, 2007). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment.
To avoid potential injuries to persons on ground, Airworthiness
Directive (AD) 2006-0107 [which corresponds with FAA AD 2007-08-05]
mandated a one time detailed visual inspection of the shroud box
bottom panel.
Further to issuance of AD 2006-0107, three additional events of
panel loss have been experienced on in service aircraft already
inspected in accordance with the AD requirements and no findings.
Thus, it has been decided to delete this one time detailed visual
inspection and to mandate a modification which prevents such unsafe
condition. Therefore, the present AD supersedes EASA AD 2006-0107
and mandates the installation of a bolted shroud box bottom panel
instead of blind riveted metallic design.
The modification includes doing all applicable related
investigative and corrective actions. The related investigative action
is an inspection to detect cracks of the shroud box hole. The
corrective action is repairing any cracked shroud box hole. The
applicability of the MCAI has been revised; certain airplanes have been
removed and others added. 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
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 34 products of U.S.
registry. We also estimate that it will take about 20 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 $990
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 $88,060, or $2,590 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 http://
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 removing Amendment 39-15022 (72 FR
18563, April 13, 2007) and adding the following new AD:
2008-24-09 Airbus: Amendment 39-15749. Docket No. FAA-2008-0910;
Directorate Identifier 2008-NM-033-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
2, 2009.
Affected ADs
(b) This AD supersedes AD 2007-08-05, Amendment 39-15022.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of
this AD; certificated in any category.
[[Page 72325]]
Table 1--Applicability
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Except for those
For model-- On which-- airplanes on which--
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(1) A330-200, A330-300, and Airbus Airbus Modification
A340-300 series, all modification 55568 has been done
certified models, all serial 46077 has been in production, or
numbers. embodied in Airbus Mandatory
production. Service Bulletin
A330-57-3100 or
Airbus Mandatory
Service Bulletin
A340-57-4109 has
been embodied in
service.
(2) Airbus A340-500 and A340- None............. Airbus Modification
600 series, all certified 55568 has been
models, all serial numbers. embodied in
production, or
Airbus Mandatory
Service Bulletin
A340-57-5018 has
been embodied in
service.
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Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
An A330 operator reported a shroud box bottom panel missing
during a routine inspection. The same panel detached from an A330
aircraft during take-off, causing damage to the surrounding
structure and to the Trimmable Horizontal Stabilizer (THS) tip
fairing.
The inspection indicated the blind rivets used to attach the
panel worked loose causing fatigue damage with crack propagation
through the fastener line resulting in panel detachment.
To avoid potential injuries to persons on ground, Airworthiness
Directive (AD) 2006-0107 [which corresponds with FAA AD 2007-08-05]
mandated a one time detailed visual inspection of the shroud box
bottom panel.
Further to issuance of AD 2006-0107, three additional events of
panel loss have been experienced on in service aircraft already
inspected in accordance with the AD requirements and no findings.
Thus, it has been decided to delete this one time detailed visual
inspection and to mandate a modification which prevents such unsafe
condition. Therefore, the present AD supersedes EASA AD 2006-0107
and mandates the installation of a bolted shroud box bottom panel
instead of blind riveted metallic design.
The modification includes doing all applicable related
investigative and corrective actions. The related investigative
action is an inspection to detect cracks of the shroud box hole. The
corrective action is repairing any cracked shroud box hole.
New Requirements of This AD: Actions and Compliance
(f) Unless already done: Within 69 months after the effective
date of this AD, modify the shroud box bottom skin panel on both
wings, and do all applicable related investigative and corrective
actions, by accomplishing all the actions in the applicable service
bulletins identified in Table 2 of this AD. Do all applicable
related investigative and corrective actions before further flight.
Table 2--Service Bulletins
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Service Bulletin-- Date--
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin October 1, 2007.
A330-57-3100.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-4109.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-5018.
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FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
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 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 MCAI European Aviation Safety Agency Airworthiness
Directive 2008-0002, dated January 7, 2008, and the service
bulletins identified in Table 2 of this AD for related information.
Material Incorporated by Reference
(i) You must use the service information specified in Table 3 of
this AD 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 SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com.
(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: http://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin-- Date--
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin October 1, 2007.
A330-57-3100.
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-4109.
[[Page 72326]]
Airbus Mandatory Service Bulletin October 1, 2007.
A340-57-5018.
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Issued in Renton, Washington, on November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-27940 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P