[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Proposed Rules]
[Pages 52263-52267]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-20917]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0618; Directorate Identifier 2012-NM-171-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-06-
18, for all Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes) and Model A300 series 
airplanes. AD 2008-06-18 currently requires repetitive inspections for 
any cracking of the wing lower skin panel and associated internal 
support structure, and if necessary, corrective actions such as 
modifying the lower panel inboard of rib 9 aft of the rear spar and 
repairing cracks. Since we issued AD 2008-06-18, we have received a 
report that information from an analysis and fleet survey show a need 
for reduced compliance times and intervals. This proposed AD would 
continue to require the existing requirements, and would reduce some 
compliance times. We are proposing this AD to detect and correct 
cracking, which could lead to reduced structural integrity of the 
airplane.

DATES: We must receive comments on this proposed AD by October 20, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email [email protected]; Internet http://www.airbus.com. You may 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0618; 
Directorate Identifier 2012-NM-171-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On March 7, 2008, we issued AD 2008-06-18, Amendment 39-15430 (73 
FR 14670, March 19, 2008). AD 2008-06-18 requires actions intended to 
address an unsafe condition on all Airbus Model A300 B4-600, B4-600R, 
and F4-600R series airplanes, and Model A300 C4-605R Variant F 
airplanes (collectively called Model A300-600 series airplanes) and 
Model A300 series airplanes.

[[Page 52264]]

    Since we issued AD 2008-06-18, Amendment 39-15430 (73 FR 14670, 
March 19, 2008), we have received a report that information from an 
analysis and fleet survey show a need for reduced compliance times and 
intervals.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0203, dated October 1, 2012 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes) and Model A300 series airplanes. The MCAI states:

    During routine maintenance, cracks were found in the wing bottom 
skin and in the associated internal support structure on an A300 
aeroplane aft of the rear spar and inboard of rib 9. Initially, 
cracks were found in the skin only, starting from a fastener close 
to the forward outboard corner of access panel 575FB/675FB. 
Subsequently, cases were reported of cracks being found in the skin 
support strap and the stiffener.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, EASA issued AD 2006-0282 
[http://ad.easa.europa.eu/ad/2006-0282] [which corresponds with FAA 
AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008)] to 
require repetitive inspections of the wing lower skin panel and 
associated internal support structure aft of the rear spar and 
inboard of rib 9.
    Since that [EASA] AD was issued, the results of a fleet survey 
and updated Fatigue and Damage Tolerance analysis, which were 
performed in order to substantiate the second A300 and A300-600 
Extended Service Goal (ESG2) exercise, revealed that the inspection 
threshold and interval had to be reduced to allow timely detection 
of cracks and the accomplishment of an applicable corrective action.
    Prompted by these findings, Airbus issued Revision 05 of Airbus 
Service Bulletin (SB) A300-57-0177 and Revision 07 of Airbus SB 
A300-57-6029.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2006-0282, which is superseded, but requires 
the accomplishment of those actions within reduced thresholds and 
intervals.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0618.

Relevant Service Information

    Airbus has issued Service Bulletin A300-57-6029, Revision 08, dated 
April 25, 2013. The compliance times for the initial inspections range 
approximately from 160 flight cycles or 270 flight hours, whichever 
occurs first, to 49,300 flight cycles or 98,700 flight hours, whichever 
occurs first, depending on the model and configuration. The repetitive 
intervals range from 30 flight cycles or 40 flight hours, whichever 
occurs first, to 3,800 flight cycles or 7,700 flight hours, whichever 
occurs first, depending on the model and configuration. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Changes to AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 
2008)

    This proposed AD would retain all requirements of AD 2008-06-18, 
Amendment 39-15430 (73 FR 14670, March 19, 2008). Since AD 2008-06-18 
was issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
   Requirement in AD 2008-06-18,
  Amendment 39-15430 (73 FR 14670,    Corresponding requirement in this
           March 19, 2008                        proposed AD
------------------------------------------------------------------------
             paragraph (f)                        paragraph (g)
------------------------------------------------------------------------

    Paragraph (f)(3) of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, 
March 19, 2008), contains a typographical error. That error resulted in 
a reference to paragraph ``(e)(f)(ii)'' of AD 2008-06-18. The correct 
reference is to paragraph (f)(3)(ii) of AD 2008-06-18. Since the AD 
format has been revised and certain paragraphs have been rearranged, 
the reference is now to paragraph (g)(3)(ii) of the proposed AD.

``Contacting the Manufacturer'' Paragraph in This Proposed 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 an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR 
78285, December 26, 2013), we proposed to prevent the 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 the 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 a 
design approval holder (DAH) with State of Design Authority design 
organization approval (DOA), as applicable, to refer to a DAH 
authorized to approve required repairs for the proposed AD.
    One commenter to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) 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

[[Page 52265]]

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 the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this proposed AD to obtain corrective actions 
from a manufacturer, the actions must be accomplished using a method 
approved by the FAA, the European Aviation Safety Agency (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 previously afforded 
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 Airworthiness 
Directive 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.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 162 airplanes of U.S. 
registry.
    The actions that are required by AD 2008-06-18, Amendment 39-15430 
(73 FR 14670, March 19, 2008), and retained in this proposed AD take 
about 2 work-hours per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that are required by AD 2008-06-18 is $170 per product.
    We also estimate that it would take about 2 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $27,540, or $170 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 12 work-hours and require parts costing $10,000, for a cost 
of $11,020 per product. We have no way of determining the number of 
aircraft that might need these actions.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), and 
adding the following new AD:

Airbus: Docket No. FAA-2014-0618; Directorate Identifier 2012-NM-
171-AD.

(a) Comments Due Date

    We must receive comments by October 20, 2014.

[[Page 52266]]

(b) Affected ADs

    This AD replaces AD 2008-06-18, Amendment 39-15430 (73 FR 14670, 
March 19, 2008).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(5) of this AD, certificated in any category, all 
certified models, all serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R and F4-622R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that information from an 
analysis and fleet survey show a need for reduced compliance times 
and intervals. We are issuing this AD to detect and correct 
cracking, which could lead to reduced structural integrity of the 
airplane.

(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 Actions and Compliance Times With Revised Service 
Information

    This paragraph restates the requirements of paragraph (f) of AD 
2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 2008), with 
revised service information. Unless already done, do the following 
actions.
    (1) Except as provided by paragraphs (g)(1)(i), (g)(1)(ii), 
(g)(1)(iii), (g)(1)(iv), and (h) of this AD: At the threshold 
specified in paragraph 1.E.(2) of Airbus Service Bulletin A300-57-
0177, Revision 05, dated March 23, 2007 (for Model A300 series 
airplanes); Airbus Service Bulletin A300-57-6029, Revision 06, dated 
March 23, 2007 (for Model A300-600 series airplanes); or Airbus 
Service Bulletin A300-57-6029, Revision 08, dated April 25, 2013 
(for Model A300-600 series airplanes); as applicable; perform the 
inspection of the wing lower skin panel and associated internal 
support structure aft of the rear spar and inboard of rib 9 and 
apply applicable corrective measures in accordance with Airbus 
Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007 
(for Model A300 series airplanes); or Airbus Service Bulletin A300-
57-6029, Revision 06, dated March 23, 2007 (for Model A300-600 
series airplanes); or Airbus Service Bulletin A300-57-6029, Revision 
08, dated April 25, 2013 (for Model A300-600 series airplanes); as 
applicable. All applicable corrective measures must be done at the 
applicable times specified in paragraph 1.E.(2) and the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-0177, 
Revision 05, dated March 23, 2007 (for Model A300 series airplanes); 
Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 
2007 (for Model A300-600 series airplanes); or Airbus Service 
Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model 
A300-600 series airplanes); as applicable. Accomplishing the 
requirements of paragraph (h) of this AD terminates the requirements 
of this paragraph for Model A300-600 airplanes.
    (i) Where the tables in paragraph 1.E.(2), ``Accomplishment 
Timescale,'' of Airbus Service Bulletin A300-57-0177, Revision 05, 
dated March 23, 2007; A300-57-6029, Revision 06, dated March 23, 
2007; specify a grace period for doing the actions, this AD requires 
that the actions be done within the specified grace period relative 
to April 23, 2008 (the effective date of AD 2008-06-18, Amendment 
39-15430 (73 FR 14670, March 19, 2008)).
    (ii) Where the tables in paragraph 1.E.(2)(e), ``Config 04,'' of 
Airbus Service Bulletin A300-57-0177, Revision 05, dated March 23, 
2007, specify an inspection interval but not an initial threshold, 
this AD requires that the actions be done within the specified 
interval after inspecting in accordance with Table 1A or 1B, as 
applicable, for Configuration 01 airplanes described in the service 
bulletin and thereafter at the inspection interval specified in the 
tables in paragraph 1.E.(2)(e), ``Config 04,'' of Airbus Service 
Bulletin A300-57-0177, Revision 05, dated March 23, 2007.
    (iii) Where the tables in paragraph 1.E.(2)(f), ``Config 05,'' 
of Airbus Service Bulletin A300-57-6029, Revision 06, dated March 
23, 2007, specify an inspection interval but not an initial 
threshold, this AD requires that the actions be done within the 
specified interval after inspecting in accordance with Table 1A, or 
1B, as applicable, for configuration 01 of Airbus Service Bulletin 
A300-57-6029, Revision 06, dated March 23, 2007, and thereafter at 
the inspection interval specified in the tables in paragraph 
1.E.(2)(f), ``Config 05,'' of Airbus Service Bulletin A300-57-6029, 
Revision 06, dated March 23, 2007.
    (iv) All crack lengths specified in Airbus Service Bulletin 
A300-57-0177, Revision 05, dated March 23, 2007; and A300-57-6029, 
Revision 06, dated March 23, 2007, are considered ``not to exceed'' 
lengths.
    (2) Repeat the inspection at the intervals in, and according to 
the instructions defined in, Airbus Service Bulletin A300-57-0177, 
Revision 05, dated March 23, 2007 (for Model A300 series airplanes); 
Airbus Service Bulletin A300-57-6029, Revision 06, dated March 23, 
2007 (for Model A300-600 series airplanes); or Airbus Service 
Bulletin A300-57-6029, Revision 08, dated April 25, 2013 (for Model 
A300-600 series airplanes); as applicable; except where Airbus 
Service Bulletin A300-57-0177, Revision 05, dated March 23, 2007, 
specifies repetitive inspections for cracking if Airbus Service 
Bulletin A300-57-022 has not been embodied, this AD requires doing 
repetitive inspections for cracking if Airbus Service Bulletin A300-
57-0222 (modification 11178H5410) has not been embodied.
    (3) Report to Airbus the first inspection results, whatever they 
may be, at the applicable time specified in paragraph (g)(3)(i) or 
(g)(3)(ii) of this AD.
    (i) If the inspection was done after April 23, 2008 (the 
effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, 
March 19, 2008)), submit the report within 30 days after the 
inspection.
    (ii) If the inspection was accomplished prior to April 23, 2008 
(the effective date of AD 2008-06-18, Amendment 39-15430 (73 FR 
14670, March 19, 2008)), submit the report within 30 days after 
April 23, 2008.

(h) New Requirement of This AD: New Compliance Times for Model A300-600 
Airplanes

    For Model A300-600 airplanes, do the actions specified in 
paragraphs (h)(1) through (h)(3) of this AD at the applicable times 
specified in those paragraphs.
    (1) Except as provided by paragraphs (h)(1)(i) and (h)(1)(ii) of 
this AD: Within the compliance times specified in Airbus Service 
Bulletin A300-57-6029, Revision 08, dated April 25, 2013, perform 
the inspection of the wing lower skin panels and associated internal 
support structures aft of the rear spar and inboard of rib 9, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6029, Revision 08, dated April 25, 2013. 
Thereafter, repeat these inspections at intervals specified in 
Airbus Service Bulletin A300-57-6029, Revision 08, dated April 25, 
2013. Accomplishment of the actions required by this paragraph 
terminates the requirements of paragraph (g) of this AD for Model 
A300-600 airplanes.
    (i) Where the tables in paragraph 1.E.(2), ``Accomplishment 
Timescale,'' of Airbus Service Bulletin A300-57-6029, Revision 08, 
dated April 25, 2013, specify a grace period for doing the actions 
for airplanes that have exceeded the thresholds, this AD requires, 
for all airplanes, that the actions be done within the specified 
grace period after the effective date of this AD or before the 
specified thresholds, whichever occurs later.
    (ii) Where Airbus Service Bulletin A300-57-6029, Revision 08, 
dated April 25, 2013, specifies to ``contact Airbus'' before further 
flight, this AD requires repairing using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA); and accomplishing 
those actions before further flight. If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (2) If, during any inspection as required by paragraph (h)(1) of 
this AD, discrepancies are detected, before next flight, accomplish 
the applicable corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6029, 
Revision 08, dated April 25, 2013.
    (3) Corrective actions, as required by paragraph (h)(2) of this 
AD, do not constitute terminating action for the repetitive 
inspection requirements of paragraph (h)(1) of this AD.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD,

[[Page 52267]]

if those actions were performed before April 23, 2008 (the effective 
date of AD 2008-06-18, Amendment 39-15430 (73 FR 14670, March 19, 
2008)), using the applicable service information identified in 
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD, which are not 
incorporated by reference by this AD.
    (i) Airbus Service Bulletin A300-57-0177, Revision 03, dated May 
29, 2006.
    (ii) Airbus Service Bulletin A300-57-0177, Revision 04, dated 
January 5, 2007.
    (iii) Airbus Service Bulletin A300-57-6029, Revision 04, dated 
May 29, 2006.
    (iv) Airbus Service Bulletin A300-57-6029, Revision 05, dated 
October 23, 2006.
    (2) This paragraph provides credit for actions required by 
paragraph (g) or (h) of this AD, if those actions were performed 
before the effective date of this AD, using Airbus Service Bulletin 
A300-57-6029, Revision 07, dated June 6, 2011, which is not 
incorporated by reference by 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: [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. AMOCs 
approved previously for AD 2008-06-18, Amendment 39-15430 (73 FR 
14670, March 19, 2008) are considered acceptable for this AD.
    (2) Contacting the Manufacturer: 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0203, dated October 1, 2012, for related information. This MCAI may 
be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2014-0618.
    (2) 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 service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on August 23, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-20917 Filed 9-2-14; 8:45 am]
BILLING CODE 4910-13-P