AD 2017-15-03

[Federal Register Volume 82, Number 139 (Friday, July 21, 2017)]
[Rules and Regulations]
[Pages 33787-33790]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-15119]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9572; Directorate Identifier 2016-NM-151-AD; 
Amendment 39-18963; AD 2017-15-03]
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 superseding Airworthiness Directive (AD) 2014-08-02 
which applied to certain Airbus Model A300 B4-600 and A300 B4-600R 
series airplanes. AD 2014-08-02 required modifying the profile of 
stringer run-outs of both wings, including a high frequency eddy 
current (HFEC) inspection of the fastener holes for defects, and 
repairs if necessary. This new AD retains the actions required by AD 
2014-08-02 and revises the compliance times. This AD was prompted by 
further analysis in the context of widespread fatigue damage (WFD), 
which concluded that shorter compliance times are necessary to meet 
specified requirements to address WFD. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective August 25, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 25, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 
21, 2014 (79 FR 21392, April 16, 2014).

ADDRESSES: For service information identified in this final rule, 
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 <a href="/cdn-cgi/l/email-protection#a6c7c5c5c9d3c8d288c7cfd4d1c9d4d2ce8bc3c7d5e6c7cfd4c4d3d588c5c9cb"><span class="__cf_email__" data-cfemail="204143434f554e540e414952574f5254480d454153604149524255530e434f4d">[email&#160;protected]</span></a>; Internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. 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. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9572.

[[Page 33788]]

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9572; 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 regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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 to supersede AD 2014-08-02, Amendment 39-17826 (79 FR 21392, 
April 16, 2014) (``AD 2014-08-02''). AD 2014-08-02 applied to certain 
Airbus Model A300 B4-600 and A300 B4-600R series airplanes. The NPRM 
published in the Federal Register on March 13, 2017 (82 FR 13405). The 
NPRM was prompted by further analysis in the context of WFD, which 
concluded that a shorter compliance time is necessary to meet specified 
requirements to address WFD. The NPRM proposed to continue to require 
modifying the profile of stringer run-outs of both wings, including a 
high frequency eddy current inspection of the fastener holes for 
defects, and repairs if necessary. The NPRM also proposed to require a 
revised compliance time for these actions. 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 Union, has issued EASA 
Airworthiness Directive 2016-0174, dated August 30, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600 and A300 B4-600R series airplanes. The MCAI states:

    During full-scale fatigue testing, cracks were detected in the 
bottom wing skin stringers at Rib 14. In addition, operators have 
also reported finding cracks in the same area on in-service 
aeroplanes.
    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 was necessary for aeroplanes operating beyond 
the Extended Service Goal 1.
    To address this unsafe condition, Airbus issued Service Bulletin 
(SB) A300-57-6046 Revision 01 to provide modification instructions, 
and EASA issued AD 2013-0008 (later revised) [which corresponds to 
FAA AD 2014-08-02], to require the removal of the stringer end run-
out plate at stringer 19 on the bottom wing skin and a re-profiling 
modification of the stringers 10, 11, 12, 17 and 19.
    Since that [EASA] AD was issued, further analysis in the context 
of Widespread Fatigue Damage (WFD), concluded that a threshold 
reduction is necessary to meet the WFD requirements. Consequently, 
Airbus revised SB A300-57-6046 accordingly (now at Revision 03).
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0008R1, which is superseded, but 
reduces the modification threshold, and introduces a pre-mod High 
Frequency Eddy Current (HFEC) inspection.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9572.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. FedEx Express had no 
objection to the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-57-6046, Revision 03, 
including Appendix 01, dated February 4, 2015. The service information 
describes procedures to modify the profile of stringer run-outs of both 
wings, including a HFEC inspection of the fastener holes for defects, 
and repairs. It also describes new compliance times for completing the 
modifications. This service information is reasonably available because 
the interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 29 airplanes of U.S. registry.
    The actions required by AD 2014-08-02, and retained in this AD, 
take about 63 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts cost about $2,360 per product. Based on 
these figures (accounting for updated work-hour and parts cost 
estimates), the estimated cost of this AD on U.S. operators is $7,715 
per product.
    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 these 
repairs.

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;

[[Page 33789]]

    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.

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 removing Airworthiness Directive (AD) 
2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014), and 
adding the following new AD:

2017-15-03 Airbus: Amendment 39-18963; Docket No. FAA-2016-9572; 
Directorate Identifier 2016-NM-151-AD.

(a) Effective Date

    This AD is effective August 25, 2017.

(b) Affected ADs

    This AD replaces AD 2014-08-02, Amendment 39-17826 (79 FR 21392, 
April 16, 2014) (``AD 2014-08-02'').

(c) Applicability

    This AD applies to Airbus Model A300-B4-601, B4-603, B4-620, and 
B4-622 airplanes, and 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 an evaluation by the design approval 
holder indicating that certain wing skin stringers are subject to 
widespread fatigue damage. 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

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Modification of Rib 14, With Revised Compliance Time and 
Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2014-08-02, with revised compliance times and service information. 
At the time specified in paragraph (g)(1) or (g)(2) of this AD, 
whichever occurs earlier, 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 Service Bulletin A300-57-6046, Revision 02, dated June 21, 
2013; or Revision 03, including Appendix 01, dated February 4, 2015; 
except as required by paragraph (h) of this AD. Do all applicable 
repairs before further flight. As of the effective date of this AD, 
only Airbus Service Bulletin A300-57-6046, Revision 03, including 
Appendix 01, dated February 4, 2015, may be used.
    (1) Before the accumulation of 42,500 total flight cycles, or 
within 2,000 flight cycles after May 21, 2014 (the effective date of 
AD 2014-08-02), whichever occurs later.
    (2) Before the accumulation of 30,000 total flight cycles, or 
within 2,000 flight cycles after the effective date of this AD, 
whichever occurs later.

(h) Retained Exception to the Service Information, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (h) of AD 
2014-08-02, with revised service information.
    (1) 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.
    (2) Where Airbus Service Bulletin A300-57-6046, Revision 03, 
including Appendix 01, dated February 4, 2015, specifies to contact 
Airbus for appropriate action: Before further flight, accomplish 
corrective actions in accordance with the procedures specified in 
paragraph (j)(2) of this AD.

(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 the service information specified in paragraph 
(i)(1), (i)(2), or (i)(3) of this AD.
    (1) Airbus Service Bulletin A300-57-6046, dated January 18, 
1994, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6046, Revision 01, dated 
April 18, 2011, which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A300-57-6046, Revision 02, dated 
June 21, 2013, which was incorporated by reference in AD 2014-08-02.

(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 the attention of 
the person identified in paragraph (k)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#5c65711d1211716d6d6a711d11131f710e190d09190f080f1c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="172e3a56595a3a2626213a565a58543a45524642524443445771767639707861">[email&#160;protected]</span></a>. 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.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0174, dated August 30, 
2016, for related information. This MCAI may be found in the AD 
docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2016-9572.
    (2) For more information about this AD, 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.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(4) and (l)(5) 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.

[[Page 33790]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 25, 2017.
    (i) Airbus Service Bulletin A300-57-6046, Revision 03, including 
Appendix 01, dated February 4, 2015.
    (ii) Reserved.
    (4) 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 <a href="/cdn-cgi/l/email-protection#f49597979b819a80da959d86839b86809cd9919587b4959d86968187da979b99"><span class="__cf_email__" data-cfemail="224341414d574c560c434b50554d50564a0f47435162434b504057510c414d4f">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (5) 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.
    (6) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on July 11, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15119 Filed 7-20-17; 8:45 am]
 BILLING CODE 4910-13-P