[Federal Register Volume 78, Number 148 (Thursday, August 1, 2013)]
[Proposed Rules]
[Pages 46536-46538]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18556]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0668; Directorate Identifier 2013-NM-017-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A300 B4-600 and A300 B4-600R series airplanes.
This proposed AD was prompted by reports of cracks found in the bottom
wing skin stringers at rib 14 during full-scale fatigue testing and in
service. This proposed AD would require modifying the profile of
stringer run-outs at rib 14 of both wings, including a high frequency
eddy current inspection of the fastener holes for defects and repair if
necessary. We are proposing this AD to prevent cracking in the bottom
wing skin stringers, which could result in reduced structural integrity
of the wings.
DATES: We must receive comments on this proposed AD by September 16,
2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [email protected]; Internet http://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
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 this proposed AD, 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.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0668;
Directorate Identifier 2013-NM-017-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0008R1, dated January 22, 2013 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
During full-scale fatigue testing, cracks were detected in the
bottom wing skin stringers at rib 14. In addition, A300 aeroplane
operators have also reported finding cracks in the same area.
This condition, if not detected and corrected, could impair the
structural integrity of the wings.
Additional analysis results showed that the improved design of
the stringer run-out is necessary for aeroplanes operating beyond
the ESG 1 [extended service goal 1: 42,500 flight cycles].
For the reasons described above, this [EASA] AD requires the
removal of the stringer end run-out plate at stringer 19 on the
bottom wing skin and the re-profiling modification of the stringers
10, 11, 12, 17 and 19.
* * * * *
The modification also includes doing a high frequency eddy current
inspection of the fastener holes for defects and repair if necessary.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-57-6046, Revision
01, dated April 18, 2011. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe
[[Page 46537]]
condition exists and is likely to exist or develop on other products of
the same type design.
Differences Between This Proposed AD and the MCAI or Service
Information
Although Airbus Mandatory Service Bulletin A300-57-6046, Revision
01, dated April 18, 2011, specifies to contact the manufacturer for
instructions to repair certain conditions, this proposed AD would
require repairing those conditions using a method approved by either
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA (or its delegated agent).
Costs of Compliance
We estimate that this proposed AD affects 29 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Modification of the profile of 60 work-hours x $85 None............... $5,100 $147,900
stringer run-outs. per hour = $5,100.
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We have received no definitive data that would enable us to provide
cost estimates for any on-condition actions specified in this proposed
AD. We have no way of determining the number of aircraft that might
need this repair.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Airbus: Docket No. FAA-2013-0668; Directorate Identifier 2013-NM-
017-AD.
(a) Comments Due Date
We must receive comments by September 16, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and
B4-622 airplanes; and Airbus Model A300 B4-605R and B4-622R
airplanes; certificated in any category, except airplanes on which
Airbus Modification 10324 or 10325 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks found in the bottom
wing skin stringers at rib 14 during full-scale fatigue testing and
in service. We are issuing this AD to prevent cracking in the bottom
wing skin stringers, which could result in reduced structural
integrity of the wings.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Modification of Rib 14
Before the accumulation of 42,500 total flight cycles, or within
2,000 flight cycles after the effective date of this AD, whichever
occurs later, modify the profile of stringer run-outs at rib 14 of
both wings, including a high frequency eddy current inspection of
the fastener holes for defects and all applicable repairs, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A300-57-6046, Revision 01, dated April 18, 2011,
except as required by paragraph (h) of this AD.
(h) Exception to the Service Information
Where Airbus Mandatory Service Bulletin A300-57-6046, Revision
01, dated April 18, 2011, specifies to report defects to Airbus,
this AD requires contacting the Manager, ANM-116, International
Branch, Transport Airplane Directorate, FAA, or the European
Aviation Safety Agency (EASA) (or its delegated agent) for repair
instructions and doing those repairs before further flight.
(i) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A300-57-6046, dated
January 18, 1994 (which is not incorporated by reference).
(j) Other FAA AD Provisions
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.
[[Page 46538]]
In accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the International Branch, send it
to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
Information may be emailed to: [email protected].
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) Airworthiness
Directive 2013-0008R1, dated January 22, 2013, for related
information.
(2) For service information identified in this AD that is not
incorporated by reference, contact Airbus SAS, Airworthiness
Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email
[email protected]; Internet http://www.airbus.com. You
may review copies of this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
Issued in Renton, Washington, on July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18556 Filed 7-31-13; 8:45 am]
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