Document ID: FAA-2013-0668-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2014-04-16T04:00Z

[Federal Register Volume 79, Number 73 (Wednesday, April 16, 2014)]
[Rules and Regulations]
[Pages 21392-21394]
From the Federal Register Online via the Government Printing 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 account.airworth-eas@airbus.com; 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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                     Labor cost            Parts cost           product         operators
----------------------------------------------------------------------------------------------------------------
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]]

ANM-116-AMOC-REQUESTS@faa.gov. 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 account.airworth-eas@airbus.com; 
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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