[Federal Register Volume 79, Number 73 (Wednesday, April 16, 2014)]
[Rules and Regulations]
[Pages 21392-21394]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-08455]
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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;
Amendment 39-17826; AD 2014-08-02]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 certain
Airbus Model A300 B4-600 and A300 B4-600R series airplanes. This AD was
prompted by reports of cracks found in certain bottom wing skin
stringers during full-scale fatigue testing and in service. This AD
requires modifying the profile of stringer run-outs of both wings,
including a high frequency eddy current inspection of the fastener
holes for defects and, if necessary, repairs. We are issuing this AD to
prevent cracking in the bottom wing skin stringers, which could result
in reduced structural integrity of the wings.
DATES: This AD becomes effective May 21, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 21,
2014.
ADDRESSES: You may examine the AD on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0668; or in person at the
Docket 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.
For service information identified in this 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 view this 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.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A300
B4-600 and A300 B4-600R series airplanes. The NPRM published in the
Federal Register on August 1, 2013 (78 FR 46536). The NPRM was prompted
by reports of cracks found in the bottom wing skin stringers at rib 14
during full-scale fatigue testing and in service. The NPRM proposed to
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 repairs if necessary. We are issuing
this AD to prevent cracking in the bottom wing skin stringers, which
could result in reduced structural integrity of the wings.
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, if necessary,
repairs. You may examine the MCAI in the AD docket on the Internet at
http://www.regulations.gov/#!documentDetail;D=FAA-2013-0668-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the NPRM (78 FR
46536, August 1, 2013) and the FAA's response to the comment.
Request To Refer to New Service Information
UPS requested that the source of work instructions for
accomplishing the proposed actions be revised to Airbus Mandatory
Service Bulletin A300-57-6046, Revision 02, dated June 21, 2013. UPS
noted that the NPRM (78 FR 46536, August 1, 2013) referenced Airbus
Mandatory Service Bulletin A300-57-6046, Revision 01, dated April 18,
2011, as the source of work instructions.
We agree. We have revised paragraph (g) of this final rule to refer
to Airbus Mandatory Service Bulletin A300-57-6046, Revision 02, dated
June 21, 2013, instead. We have revised paragraph (i) of this AD to
also identify Airbus Mandatory Service Bulletin A300-57-6046, Revision
01, dated April 18, 2011, as an acceptable source of instructions if
those actions are accomplished before the effective date of this AD.
Additional Change
We have revised paragraph (g) of this final rule to clarify when
the applicable repairs are required to be done.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 46536, August 1, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 46536, August 1, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 29 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 21393]]
Estimated Costs
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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 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 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 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);
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.
Examining the AD Docket
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0668-0002; 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 MCAI, 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.
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:
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 airworthiness
directive (AD):
2014-08-02 Airbus: Amendment 39-17826. Docket No. FAA-2013-0668;
Directorate Identifier 2013-NM-017-AD.
(a) Effective Date
This AD becomes effective May 21, 2014.
(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 02, dated June 21, 2013,
except as required by paragraph (h) of this AD. Do all applicable
repairs before further flight.
(h) Exception to the Service Information
Where Airbus Mandatory Service Bulletin A300-57-6046, Revision
02, dated June 21, 2013, specifies to contact Airbus for repair
instructions, 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; or Airbus Mandatory Service Bulletin A300-57-6046,
Revision 01, dated April 18, 2011 (which are not incorporated by
reference in this AD).
(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. 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: 9-
[[Page 21394]]
[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) EASA Airworthiness Directive 2013-0008R1, dated January 22,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0668-0002.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the addresses specified
in paragraphs (l)(3) and (l)(4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A300-57-6046, Revision 02,
dated June 21, 2013.
(ii) Reserved.
(3) For service information identified in this 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.
(4) You may view 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.
(5) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 2, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08455 Filed 4-15-14; 8:45 am]
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