[Federal Register Volume 75, Number 109 (Tuesday, June 8, 2010)]
[Rules and Regulations]
[Pages 32266-32268]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-13435]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0171; Directorate Identifier 2009-NM-185-AD;
Amendment 39-16329; AD 2010-12-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes;
Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and
Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series
Airplanes); and Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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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 a maintenance check performed by an A310 operator, the
recommended modification of the lower attachment beam of rack 101VU
by accomplishment of Airbus Service Bulletin (SB) A310-53-2076 was
embodied on the aeroplane, leading the operator to find three cracks
on the FR15A crossbeam above the NLG [nose landing gear] box at the
splicing with rack 107VU fitting.
This condition, if not detected and corrected, could degrade the
structural integrity of the crossbeam on NLG FR15A Web attachment
fitting of rack 107VU. Rack 107VU contains major airworthiness
system components whose functioning could be adversely affected by
the loss of the attachment fitting.
As the A300 and A300-600 aeroplanes share this design feature,
they are also affected.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July 13, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 13,
2010.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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 February 25, 2010
(75 FR 8549). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During a maintenance check performed by an A310 operator, the
recommended modification of the lower attachment beam of rack 101VU
by accomplishment of Airbus Service Bulletin (SB) A310-53-2076 was
embodied on the aeroplane, leading the operator to find three cracks
on the FR15A crossbeam above the NLG [nose landing gear] box at the
splicing with rack 107VU fitting.
This condition, if not detected and corrected, could degrade the
structural integrity of the crossbeam on NLG FR15A Web attachment
fitting of rack 107VU. Rack 107VU contains major airworthiness
system components whose functioning could be adversely affected by
the loss of the attachment fitting.
As the A300 and A300-600 aeroplanes share this design feature,
they are also affected.
For the reasons stated above, this AD requires repetitive
inspections for cracks of the crossbeam on NLG FR15A Web face
attachment fitting of rack 107VU and corrective action, depending on
findings.
The corrective actions include contacting Airbus for repair
instructions, and doing the repair if any crack is found. 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 considered the comment received. The commenter, FedEx
Express, supports the NPRM.
Explanation of Change Made to This AD
We have revised the subject header of this AD to identify the
affected airplane models as published in the most recent type
certificate data sheet.
Conclusion
We reviewed the available data, including the comment received, 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 206 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $35,020, or $170 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.
[[Page 32267]]
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 adding the following new AD:
2010-12-08 Airbus: Amendment 39-16329. Docket No. FAA-2010-0171;
Directorate Identifier 2009-NM-185-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 13,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, B2-203, B4-2C, B4-103, B4-203, B4-601, B4-603, B4-620, B4-622,
B4-605R, B4-622R, F4-605R, and F4-622R airplanes; Model C4-605R
Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -
322, -324, and -325 airplanes; certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During a maintenance check performed by an A310 operator, the
recommended modification of the lower attachment beam of rack 101VU
by accomplishment of Airbus Service Bulletin (SB) A310-53-2076 was
embodied on the aeroplane, leading the operator to find three cracks
on the FR15A crossbeam above the NLG [nose landing gear] box at the
splicing with rack 107VU fitting.
This condition, if not detected and corrected, could degrade the
structural integrity of the crossbeam on NLG FR15A Web attachment
fitting of rack 107VU. Rack 107VU contains major airworthiness
system components whose functioning could be adversely affected by
the loss of the attachment fitting.
As the A300 and A300-600 aeroplanes share this design feature,
they are also affected.
For the reasons stated above, this AD requires repetitive
inspections for cracks of the crossbeam on NLG FR15A Web face
attachment fitting of rack 107VU and corrective action, depending on
findings.
The corrective actions include contacting Airbus for repair
instructions, and doing the repair if any crack is found.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Do the following actions.
(1) At the later of the times specified in paragraphs (g)(1)(i)
and (g)(1)(ii) of this AD: Do a detailed inspection for cracks of
the crossbeam on the nose landing gear FR15A Web attachment fitting
of rack 107VU, in accordance with the Accomplishment Instructions in
the applicable service bulletin specified in Table 1 of this AD.
(i) Before the accumulation of 6,600 total flight cycles.
(ii) Within 2,300 flight cycles or 30 months after the effective
date of this AD, whichever occurs first.
(2) Thereafter, at intervals not to exceed 2,300 flight cycles,
repeat the inspection specified in paragraph (g)(1) of this AD.
Table 1--Service Bulletins
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Model Service bulletin Date
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Airbus Model A300 series Airbus Mandatory March 17, 2009.
airplanes. Service Bulletin
A300-53-0388,
including Appendix
01.
Airbus Model 300-600 series Airbus Mandatory March 17, 2009.
airplanes. Service Bulletin
A300-53-6164,
including Appendix
01.
Airbus Model A310 series Airbus Mandatory March 17, 2009.
airplanes. Service Bulletin
A310-53-2131,
including Appendix
01.
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(3) If any crack is found during any inspection required by
paragraphs (g)(1) and (g)(2) of this AD, before further flight
contact Airbus for approved repair instructions and do the repair.
(4) Submit an inspection report of the inspection required by
paragraph (g)(1) of this AD to Airbus Customer Services Directorate,
1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 33 33; fax +33 5 61 93 28 06; e-mail
[email protected]; at the applicable time specified in
paragraph (g)(4)(i) or (g)(4)(ii) of this AD. The report must
include the information specified on the inspection report sheet
provided in Appendix 01 of the applicable service bulletin
identified in Table 1 of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2125; fax (425) 227-1149. Before using any approved AMOC
on any airplane to
[[Page 32268]]
which the AMOC applies, notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI), as appropriate, or
lacking a principal inspector, your local Flight Standards District
Office. The AMOC approval letter must specifically reference this
AD.
(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 (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(i) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0165, dated July 31, 2009, and the service
information specified in Table 1 of this AD, for related
information.
Material Incorporated by Reference
(j) You must use the applicable service information contained in
Table 2 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--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail [email protected];
Internet http://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 2--Material Incorporated by Reference
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Document Date
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Airbus Mandatory Service Bulletin A300- March 17, 2009.
53-0388, including Appendix 01.
Airbus Mandatory Service Bulletin A300- March 17, 2009.
53-6164, including Appendix 01.
Airbus Mandatory Service Bulletin A310- March 17, 2009.
53-2131, including Appendix 01.
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Issued in Renton, Washington, on May 28, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-13435 Filed 6-7-10; 8:45 am]
BILLING CODE 4910-13-P