AD 2014-20-18

[Federal Register Volume 79, Number 215 (Thursday, November 6, 2014)]
[Rules and Regulations]
[Pages 65879-65885]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-26356]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1064; Directorate Identifier 2012-NM-101-AD; 
Amendment 39-17991; AD 2014-20-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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[[Page 65880]]

SUMMARY: We are superseding Airworthiness Directive (AD) 2005-23-08 for 
certain Airbus Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R airplanes; and Model A300 C4-605R Variant F airplanes. AD 2005-23-
08 required repetitive inspections to detect cracks of certain 
attachment holes, installation of new fasteners, follow-on inspections 
or repair if necessary, and modification of the angle fittings of 
fuselage frame FR47. This new AD adds new repetitive ultrasonic 
inspections for cracks of the center wing box lower panel; and repair 
if necessary. This new AD also removes certain airplanes from the 
applicability. This AD was prompted by reports of cracks found on the 
horizontal flange of the Frame 47 internal corner angle fitting while 
accomplishing the modification required by AD 2005-23-08. We are 
issuing this AD to detect and correct fatigue cracking of the forward 
fitting of fuselage frame FR47, which could result in reduced 
structural integrity of the frame.

DATES: This AD becomes December 11, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 11, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
December 19, 2005 (70 FR 69056, November 14, 2005).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
8, 2002 (67 FR 38193, June 3, 2002).

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-1064; 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--
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; email <a href="/cdn-cgi/l/email-protection#a8c9cbcbc7ddc6dc86c9c1dadfc7dadcc085cdc9dbe8c9c1dacadddb86cbc7c5"><span class="__cf_email__" data-cfemail="5d3c3e3e32283329733c342f2a322f293570383c2e1d3c342f3f282e733e3230">[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.

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 2005-23-08, Amendment 39-14366 (70 FR 69056, 
November 14, 2005). AD 2005-23-08 applied to certain Model A300 B4-601, 
B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R 
airplanes; Model A300 F4-605R airplanes; and Model A300 C4-605R Variant 
F airplanes. The NPRM published in the Federal Register on December 26, 
2013 (78 FR 78285).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0092, dated May 25, 2012; Correction dated 
June 4, 2012 (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:

    Prompted by cracks found on the Frame 47 angle fitting, DGAC 
France published AD 2000-533-328 [<a href="http://ad.easa.europa.eu/ad/F-2000-533-328R1">http://ad.easa.europa.eu/ad/F-2000-533-328R1</a>] to require [a] repetitive inspection programme for 
fuselage frame 47. If not detected and corrected, these cracks could 
affect the structural integrity of the Centre Wing Box (CWB) of the 
aeroplane.
    Subsequent to the publication of a new repetitive inspection 
programme for fuselage frame 47 at certain fasteners of the CWB 
angle fitting, DGAC France issued AD F-2004-159 [<a href="http://ad.easa.europa.eu/ad/F-2004-159">http://ad.easa.europa.eu/ad/F-2004-159</a>] [which corresponds to AD 2005-23-
08, Amendment 39-14366 (70 FR 69056, November 14, 2005)], 
superseding AD 2000-533-328.
    After DGAC France AD F-2004-159 was issued, cracks were 
reportedly found on the horizontal flange of the Frame 47 internal 
corner angle fitting during accomplishment of routine maintenance 
structural inspection and modification in accordance with Airbus SB 
A300-57-6050.
    Prompted by these findings, Airbus reviewed and amended the 
inspection programme for the internal lower angle fitting flange 
(horizontal face). The inspection programme for the lower angle 
fitting web (vertical face) related to SB A300-57-6049 and internal 
lower angle fitting modification programme related to SB A300-57-
6050 remain unchanged.
    For the reasons explained above, this new [EASA] AD retains the 
requirements of DGAC France AD F-2004-159, which is superseded, and 
requires additional repetitive [ultrasonic] inspections [for cracks] 
of the CWB lower panel through the ultrasonic method and, depending 
on findings, [e.g., repair] re-installation of removed fasteners in 
transition fit instead of interference.
    This [EASA] AD has been republished to correct a typographical 
error * * *.

    The repetitive interval for the new ultrasonic inspection is either 
1,260 flight cycles or 2,720 flight hours, whichever occurs first; or 
1,360 flight cycles or 2,200 flight hours, whichever occurs first; 
depending on average flight time of the airplane. You may examine the 
MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-1064-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (78 
FR 78285, December 26, 2013) and the FAA's response to each comment.

Requests To Remove Requirement To Refer to This AD in Repair Approvals

    Airlines for America, Inc. (A4A), on behalf of seven affected 
member airlines, requested that we revise paragraphs (m)(1), (m)(2), 
and (o)(2) of the NPRM (78 FR 78285, December 26, 2013) to remove the 
requirement to include the AD reference in repair approvals. The 
commenters have made this request because the proposed requirement is 
overly broad and would add significant cost and complexity to their 
operations. The commenters were concerned that this proposed 
requirement would set a precedent for how repairs are approved, and 
could negatively affect all U.S. operators of foreign-manufactured 
airplanes.
    We concur with the commenters' request to remove from this AD the 
requirement that repair approvals must specifically refer to this AD.
    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD. The MCAI or referenced service 
information in an FAA AD often directs the owner/operator to contact 
the manufacturer for corrective actions, such as a repair. Briefly, the 
Airworthy Product paragraph allowed owners/operators to use corrective 
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved 
by the State of Design Authority (or its delegated agent) are 
considered to be FAA-approved.
    In the NPRM (78 FR 78285, December 26, 2013), we proposed to 
prevent the

[[Page 65881]]

use of repairs that were not specifically developed to correct the 
unsafe condition, by requiring that the repair approval provided by the 
State of Design Authority or its delegated agent specifically refer to 
this FAA AD. This change was intended to clarify the method of 
compliance and to provide operators with better visibility of repairs 
that are specifically developed and approved to correct the unsafe 
condition. In addition, we proposed to change the phrase ``its 
delegated agent'' to include ``the Design Approval Holder (DAH) with a 
State of Design Authority's design organization approval (DOA)'' to 
refer to a DAH authorized to approve required repairs for the proposed 
AD.
    One commenter to the NPRM (78 FR 78285, December 26, 2013), United 
Parcel Service (UPS), stated the following: ``The proposed wording, 
being specific to repairs, eliminates the interpretation that Airbus 
messages are acceptable for approving minor deviations (corrective 
actions) needed during accomplishment of an AD mandated Airbus service 
bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed that paragraph and 
retitled it ``Contacting the Manufacturer.'' This paragraph now 
clarifies that for any requirement in this AD to obtain corrective 
actions from a manufacturer, the actions must be accomplished using a 
method approved by the FAA, EASA, or Airbus's EASA DOA.
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility afforded previously 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the AD Implementation 
Aviation Rulemaking Committee to increase flexibility in complying with 
ADs by identifying those actions in manufacturers' service instructions 
that are ``Required for Compliance'' with ADs. We continue to work with 
manufacturers to implement this recommendation. But once we determine 
that an action is required, any deviation from the requirement must be 
approved as an alternative method of compliance.
    Other commenters pointed out that in many cases the foreign 
manufacturer's service bulletin and the foreign authority's MCAI may 
have been issued some time before the FAA AD. Therefore, the DOA may 
have provided U.S. operators with an approved repair, developed with 
full awareness of the unsafe condition, before the FAA AD is issued. 
Under these circumstances, to comply with the FAA AD, the operator 
would be required to go back to the manufacturer's DOA and obtain a new 
approval document, adding time, and expense to the compliance process 
with no safety benefit.
    Based on these comments, we removed from this AD the requirement 
that the DAH-provided repair specifically refer to this AD. Before 
adopting such a requirement in the future, the FAA will coordinate with 
affected DAHs and verify they are prepared to implement means to ensure 
that their repair approvals consider the unsafe condition addressed in 
the AD. Any such requirements will be adopted through the normal AD 
rulemaking process, including notice-and-comment procedures, when 
appropriate.
    We have also decided not to include a generic reference to either 
the ``delegated agent'' or the ``DAH with State of Design Authority 
design organization approval'' for new requirements, but instead we 
will provide the specific delegation approval granted by the State of 
Design Authority for the DAH.

Request To Revise Costs of Compliance

    One commenter, FedEx, requested assurance that two inspections (the 
rotating probe of the attachment holes of the horizontal flange of the 
internal corner angle fitting, and the ultrasonic inspection of the aft 
bottom panel of the center wing box) specified in the NPRM (78 FR 
78285, December 26, 2013) are to be conducted as two separate 
inspections at two separate thresholds and intervals. FedEx observed 
that both inspections are contained in the same service information, 
and that these two inspections appear to be combined in the Costs of 
Compliance paragraph of the NPRM. FedEx requested that the estimated 
costs be presented separately for the two inspection actions, and added 
that the Costs of Compliance paragraph should specify 4 work-hours for 
the new ultrasonic inspection.
    We agree to clarify the Costs of Compliance paragraph. There are 
two inspection actions (rotating probe and ultrasonic inspections) 
identified in Airbus Service Bulletin A300-57-6086, Revision 05, dated 
January 30, 2012, and these are listed separately in the Costs of 
Compliance paragraph. The second row of the table in the Costs of 
Compliance paragraph should reflect the costs for the rotating probe 
inspections identified in Airbus Service Bulletin A300-57-6086, 
Revision 05, dated January 30, 2012; we have revised the second row of 
the table in the Costs of Compliance paragraph accordingly. We have 
also revised the fourth row of the table in the Costs of Compliance 
paragraph to refer to Airbus Service Bulletin A300-57-6086, Revision 
05, dated January 30, 2012, to reflect costs for the new ultrasonic 
inspection.
    In addition, we agree with FedEx that the ultrasonic inspection 
takes 4 work-hours, as specified in Airbus Service Bulletin A300-57-
6086, Revision 05, dated January 30, 2012. In addition, Airbus Service 
Bulletin A300-57-6086, Revision 05, dated January 30, 2012, specifies 
12 work-hours for access and close procedures. Therefore, we have 
revised the work-hours for the ultrasonic inspection specified in the 
fourth row of the table in the Costs of Compliance paragraph from 35 to 
16 work-hours.

Conclusion

    We reviewed the available data, including the comments 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:

[[Page 65882]]

    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 78285, December 26, 2013) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 78285, December 26, 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 65 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                   Average
            Action                Work hours      labor rate       Parts               Cost per airplane
                                                   per hour
----------------------------------------------------------------------------------------------------------------
Inspection for attachment      13..............          $85  $0.............  $1,105.
 holes on internal angles
 [retained action from AD
 2005-23-08, Amendment 39-
 14366 (70 FR 69056, November
 14, 2005)].
Rotating probe inspections     30..............           85  Between $6,637   Between $9,187 and $21,641 per
 for attachment holes in the                                   and $19,091.     inspection cycle.
 horizontal flange (specified
 in Airbus Service Bulletin
 A300-57-6086, Revision 05,
 dated January 30, 2012)
 [retained action from AD
 2005-23-08, Amendment 39-
 14366 (70 FR 69056, November
 14, 2005)].
Modification [retained action  Between 65 and             85  $3,370.........  Between $8,895 and $34,395.
 from AD 2005-23-08,            365.
 Amendment 39-14366 (70 FR
 69056, November 14, 2005)].
New ultrasonic inspections of  16..............           85  Between $11,750  Between $13,110 and $20,080 per
 the aft bottom panel of the                                   and $18,720.     inspection cycle.
 center wing box (specified
 in Airbus Service Bulletin
 A300-57-6086, Revision 05,
 dated January 30, 2012).
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-1064; 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 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.

[[Page 65883]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005), and 
adding the following new AD:

2014-20-18 Airbus: Amendment 39-17991. Docket No. FAA-2013-1064; 
Directorate Identifier 2012-NM-101-AD.

(a) Effective Date

    This AD becomes effective December 11, 2014.

(b) Affected ADs

    This AD replaces AD 2005-23-08, Amendment 39-14366 (70 FR 69056, 
November 14, 2005).

(c) Applicability

    This AD applies to Airbus Model B4-603, B4-620, and B4-622 
airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-
605R airplanes; and Model A300 C4-605R Variant F airplanes; 
certificated in any category; except airplanes on which Airbus 
Modification 12171 or 12249 has been embodied in production, or on 
which Airbus Service Bulletin A300-57-6069 has been embodied in 
service.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Reason

    This AD was prompted by reports of cracks found on the 
horizontal flange of the Frame 47 internal corner angle fitting 
while accomplishing the modification required by AD 2005-23-08, 
Amendment 39-14366 (70 FR 69056, November 14, 2005). We are issuing 
this AD to detect and correct fatigue cracking of the forward 
fitting of fuselage frame FR47, which could result in reduced 
structural integrity of the frame.

(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) Retained Inspections for Attachment Holes on the Internal Angles of 
the Wing Center Box, and Corrective Action

    This paragraph restates the requirements of paragraphs (f), (g), 
and (h) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 
14, 2005), with revised service information. Perform a rotating 
probe inspection to detect cracking of the applicable attachment 
holes on the left and right internal angles of the wing center box 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6049, Revision 06, dated July 15, 2004; or Airbus 
Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006. 
Do the inspection at the applicable time specified by paragraph 
1.E.(2), Accomplishment Timescale, of Airbus Service Bulletin A300-
57-6049, Revision 06, dated July 15, 2004; except as required by 
paragraph (j) of this AD. Repeat the rotating probe inspection 
specified in this paragraph thereafter at intervals not to exceed 
the applicable interval specified in Airbus Service Bulletin A300-
57-6049, Revision 06, dated July 15, 2004, except that all touch-
and-go landings must be counted in determining the total number of 
flight cycles between consecutive inspections. As of the effective 
date of this AD, only Airbus Service Bulletin A300-57-6049, Revision 
07, dated December 22, 2006, may be used to accomplish the actions 
required by this paragraph.
    (1) If no cracking is found during any inspection required by 
paragraph (g) of this AD: Prior to further flight, install new 
fasteners in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15, 
2004; or Airbus Service Bulletin A300-57-6049, Revision 07, dated 
December 22, 2006. As of the effective date of this AD, only Airbus 
Service Bulletin A300-57-6049, Revision 07, dated December 22, 2006, 
may be used to accomplish the actions required by this paragraph.
    (2) If any cracking is found during any inspection required by 
paragraph (g) of this AD: Prior to further flight, perform 
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and 
installing new or oversize fasteners), in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049, 
Revision 06, dated July 15, 2004; or Airbus Service Bulletin A300-
57-6049, Revision 07, dated December 22, 2006; except as required by 
paragraph (k) of this AD. As of the effective date of this AD, only 
Airbus Service Bulletin A300-57-6049, Revision 07, dated December 
22, 2006, may be used to accomplish the actions required by this 
paragraph.

(h) Retained Inspections for Attachment Holes in the Horizontal Flange 
of the Internal Corner Angle Fitting of Fuselage Frame FR47, and 
Corrective Action

    This paragraph restates the requirements of paragraphs (i), (j), 
and (k) of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 
14, 2005), with revised service information. Perform a rotating 
probe inspection to detect cracking of the applicable attachment 
holes in the horizontal flange of the internal corner angle fitting 
of fuselage frame FR47, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002; or Airbus Service Bulletin A300-57-6086, 
Revision 05, dated January 30, 2012. Do the inspection at the 
applicable time specified in paragraph 1.E., Compliance, of Airbus 
Service Bulletin A300-57-6086, Revision 01, dated April 2, 2002, 
except as provided by paragraph (j) of this AD; or within 1,500 
flight cycles after July 8, 2002 (the effective date of AD 2002-11-
04, Amendment 39-12765 (67 FR 38193, June 3, 2002)); whichever 
occurs later. Repeat the rotating probe inspection specified in this 
paragraph thereafter at intervals not to exceed the applicable 
interval specified in Airbus Service Bulletin A300-57-6086, dated 
June 6, 2000, except that all touch-and-go landings must be counted 
in determining the total number of flight cycles between consecutive 
inspections. As of the effective date of this AD, only Airbus 
Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, 
may be used to accomplish the actions required by this paragraph.
    (1) If no cracking is found during any inspection required by 
paragraph (h) of this AD: Prior to further flight, install new 
fasteners in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2, 
2002; or Airbus Service Bulletin A300-57-6086, Revision 05, dated 
January 30, 2012. As of the effective date of this AD, only Airbus 
Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, 
may be used to accomplish the actions required by this paragraph.
    (2) If any cracking is found during any inspection required by 
paragraph (h) of this AD: Prior to further flight, perform 
applicable corrective actions (including inspecting hole T if any 
cracking is found at hole G, reaming the holes, and installing 
oversize fasteners), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01, 
dated April 2, 2002; or Airbus Service Bulletin A300-57-6086, 
Revision 05, dated January 30, 2012; except as required by paragraph 
(k) of this AD. As of the effective date of this AD, only Airbus 
Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, 
may be used to accomplish the actions required by this paragraph.

(i) Retained Modification of Angle Fittings of the Wing Center Box

    This paragraph restates the requirements of paragraph (l) of AD 
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). 
Modify the left and right internal angle fittings of the wing center 
box. The modification includes performing a rotating probe 
inspection to detect cracking, repairing cracks, cold expanding 
holes, and installing medium interference fitting bolts. Perform the 
modification in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31, 
2001; and at the applicable time specified by paragraph 1.B.(4), 
Accomplishment Timescale, of Airbus Service Bulletin A300-57-6050, 
Revision 03, dated May 31, 2001; except as required by paragraphs 
(j) and (k) of this AD.

(j) Retained Compliance Time Exception to Service Information Specified 
in Paragraphs (g), (h), and (i) of This AD

    This paragraph restates the requirements of paragraph (m) of AD 
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). 
Where the service information specified in paragraphs (g), (h), and 
(i) of this AD specify a grace period relative to receipt of the 
service bulletin, this AD requires compliance within the applicable 
grace period following December 19, 2005 (the effective date of AD 
2005-23-08), if the threshold has been exceeded.

[[Page 65884]]

(k) Retained Corrective Action Exception to Service Information 
Specified in Paragraphs (g), (h), and (i) of This AD

    This paragraph restates the requirements of paragraph (n) of AD 
2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005). If 
any crack is detected during any inspection required by paragraph 
(g), (h), or (i) of this AD, and the applicable service information 
specifies to contact the manufacturer for disposition of certain 
corrective actions: Prior to further flight, repair in accordance 
with a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).

(l) Credit for Previous Actions

    (1) This paragraph restates the credit provided by paragraph (o) 
of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 
2005): This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before 
December 19, 2005 (the effective date of AD 2005-23-08), using 
Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
    (2) This paragraph restates the credit provided by paragraph (p) 
of AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 
2005): This paragraph provides credit for the modification required 
by paragraph (i) of this AD, if the modification was performed 
before December 19, 2005 (the effective date of AD 2005-23-08), 
using Airbus Service Bulletin A300-57-6050, Revision 02, dated 
February 10, 2000.

(m) New Requirements of This AD: Repetitive Ultrasonic Inspections and 
Corrective Action

    (1) For airplanes on which Airbus Service Bulletin A300-57-6050, 
Revision 03, dated May 31, 2001, has not been done, or on which 
Airbus Modification 10155 has been done: Perform an ultrasonic 
inspection for cracking of the left- and right-hand aft bottom panel 
of the center wing box (CWB), in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6086, Revision 05, 
dated January 30, 2012. Do the inspection at the later of the times 
specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. If any 
cracking is found, before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat 
the inspection thereafter at intervals not to exceed the applicable 
interval specified in paragraph 1.E.(2), Accomplishment Timescale, 
of Airbus Service Bulletin A300-57-6086, Revision 05, dated January 
30, 2012.
    (i) Within 13,400 flight cycles or 34,600 flight hours after the 
first flight of the airplane, whichever occurs first.
    (ii) Within 650 flight cycles or 8 months after the effective 
date of this AD, whichever occurs first.
    (2) For airplanes on which Airbus Service Bulletin A300-57-6050, 
Revision 03, dated May 31, 2001, has been done: Perform an 
ultrasonic inspection for cracking of the left- and right-hand aft 
bottom panel of the center wing box (CWB), in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086, 
Revision 05, dated January 30, 2012. Do the inspection at the later 
of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of 
this AD. If any cracking is found, before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA). Repeat the inspection thereafter at intervals not to exceed 
the applicable interval specified in paragraph 1.E.(2), 
Accomplishment Timescale, of Airbus Service Bulletin A300-57-6086, 
Revision 05, dated January 30, 2012.
    (i) Within 13,400 flight cycles or 34,600 flight hours after 
accomplishing Airbus Service Bulletin A300-57-6050, whichever occurs 
first.
    (ii) Within 650 flight cycles or 8 months after the effective 
date of this AD, whichever occurs first.

(n) New Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (m) of this AD to the Design 
Approval Holder, at the applicable time specified in paragraph 
(n)(1) or (n)(2) of this AD. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, and the number of flight cycles and flight hours on 
the airplane. The inspection report form in Appendix 01 of Airbus 
Service Bulletin A300-57-6086, Revision 05, dated January 30, 2012, 
may be used.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) 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.

(o) 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: <a href="/cdn-cgi/l/email-protection#dbe2f69a9596f6eaeaedf69a969498f6899e8a8e9e888f889bbdbabaf5bcb4ad"><span class="__cf_email__" data-cfemail="c7feea86898aeaf6f6f1ea868a8884ea958296928294939487a1a6a6e9a0a8b1">[email&#160;protected]</span></a>.
    (i) 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.
    (ii) AMOCs approved previously in accordance with AD 2005-23-08, 
Amendment 39-14366 (70 FR 69056, November 14, 2005), are approved as 
AMOCs for the corresponding provision of this AD.
    (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 the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) 2012-0092, dated May 25, 2012; Correction dated June 4, 2012; 
for related information. You may examine the MCAI in the AD docket 
on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-10640002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(5) and (q)(6) of this AD.

(q) 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.
    (3) The following service information was approved for IBR on 
December 11, 2014.
    (i) Airbus Service Bulletin A300-57-6049, Revision 07, dated 
December 22, 2006.
    (ii) Airbus Service Bulletin A300-57-6086, Revision 05, dated 
January 30, 2012.
    (4) The following service information was approved for IBR on 
December 19, 2005 (70 FR 69056, November 14, 2005).
    (i) Airbus Service Bulletin A300-57-6049, excluding Appendix 01, 
Revision 06, dated July 15, 2004.

[[Page 65885]]

    (ii) Airbus Service Bulletin A300-57-6050, Revision 03, dated 
May 31, 2001. This document contains the effective pages specified 
in paragraphs (q)(4)(ii)(A), (q)(4)(ii)(B), (q)(4)(ii)(C), and 
(q)(4)(ii)(D) of this AD.
    (A) Pages 1, 4, 10A through 11, 75, and 76 are identified as 
Revision 03, dated May 31, 2001.
    (B) Pages 2, 8, 9, 17 through 32, 41, 42, 57, 58, 61 through 63, 
and 77 are identified as Revision 02, dated February 10, 2000.
    (C) Pages 3, 5 through 7, 10, 12, 33, 34, 37, 38, 47, 59, and 60 
are identified as Revision 01, dated May 31, 1999.
    (D) Pages 13 through 16, 35, 36, 39, 40, 43 through 46, 48 
through 56, and 64 through 74 are identified as original, dated 
September 9, 1994.
    (iii) Airbus Service Bulletin A300-57-6086, Revision 01, dated 
April 2, 2002.
    (5) The following service information was approved for IBR on 
July 8, 2002 (67 FR 38193, June 3, 2002).
    (i) Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
    (ii) Reserved.
    (6) 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; email <a href="/cdn-cgi/l/email-protection#bddcdeded2c8d3c993dcd4cfcad2cfc9d590d8dccefddcd4cfdfc8ce93ded2d0"><span class="__cf_email__" data-cfemail="8eefedede1fbe0faa0efe7fcf9e1fcfae6a3ebeffdceefe7fcecfbfda0ede1e3">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (7) 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.
    (8) 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 September 24, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26356 Filed 11-5-14; 8:45 am]
BILLING CODE 4910-13-P