[Federal Register Volume 80, Number 51 (Tuesday, March 17, 2015)]
[Proposed Rules]
[Pages 13799-13803]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05720]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-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) 2008-22-
20, for certain Airbus Model A330-200, A330-300, and A340-300 series 
airplanes. AD 2008-22-20 currently requires repetitive high frequency 
eddy current (HFEC) inspections for cracking, repair if necessary, and 
modification of the upper shell structure of the fuselage. Since we 
issued AD 2008-22-20, we have determined from a fatigue and damage 
tolerance evaluation that the compliance times must be reduced. This 
proposed AD would shorten certain compliance times. We are proposing 
this AD to prevent fatigue cracking of the upper shell structure of the 
fuselage, which could result in reduced structural integrity of the 
airplane.

DATES: We must receive comments on this proposed AD by May 1, 2015.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> 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--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email <a href="/cdn-cgi/l/email-protection#60010912170f121408090e0513134e215353504d21535450200109120215134e030f0d"><span class="__cf_email__" data-cfemail="e7868e95908895938f8e89829494c9a6d4d4d7caa6d4d3d7a7868e95859294c984888a">[email protected]</span></a>; 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 by searching for and locating Docket No. FAA-2015-
0490; 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 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2015-0490; 
Directorate Identifier 2014-NM-018-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 October 20, 2008, we issued AD 2008-22-20, Amendment 39-15717 
(73 FR 66747, November 12, 2008). AD 2008-22-20 requires actions 
intended to address an unsafe condition on certain Airbus Model A330-
200, A330-300, and A340-300 series airplanes.
    Since we issued AD 2008-22-20, Amendment 39-15717 (73 FR 66747, 
November 12, 2008), it has been determined from a fatigue and damage 
tolerance evaluation that the compliance times for certain inspections 
and modification must be reduced.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0012R1, dated January 24, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During fatigue tests (EF3) on the A340-600, damage was found in 
the longitudinal doubler at the Vertical Tail Plane (VTP) attachment 
cut out between Frame (FR) 80 and FR86. This damage occurred between 
58,341 and 72,891 simulated flight cycles (FC).
    Due to the higher Design Service Goal and different design of 
the affected structural area (e.g., doubler thickness) for A330-200/
-300 and A340-300 airplane series, the damage assessment concluded 
that these airplanes may be also potentially affected.
    This condition, if not detected and corrected, could affect the 
structural integrity of the upper shell structure between FR80 and 
FR86.
    Prompted by these findings, EASA issued AD 2007-0284 [(http://ad.easa.europa.eu/blob/easa_ad_2007_0284_superseded.pdf/AD_2007-0284_1)] to require implementation of an inspection programme of 
this structural area using a high frequency eddy current (HFEC) 
method and a modification to improve the upper shell structure.
    Since that [EASA] AD was issued, in the frame of a new fatigue 
and damage tolerance evaluation, taking into account the airplane

[[Page 13800]]

utilisation, the inspection threshold and intervals have been 
reassessed and the conclusion was that the thresholds and intervals 
for inspection, as well as the threshold for modifying the airplane, 
must be reduced.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2007-0284, which is superseded and 
introduces redefined thresholds and intervals.
    This [EASA] AD is revised to clarify that, under some 
conditions, accomplishment of a repair constitutes terminating 
action for the repetitive inspections. One of the outcome of this 
clarification is the deletion of paragraph (5) of this [EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2015-0490.
    Initial compliance time thresholds range from 7,300 flight cycles 
or 47,600 flight hours, and up to 25,400 flight cycles or 76,300 flight 
hours, depending on configuration and range.
    Repetitive compliance time thresholds range from 1,700 flight 
cycles or 11,300 flight hours, and up to 4,500 flight cycles or 13,500 
flight hours, depending on configuration.

Widespread Fatigue Damage

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as 
widespread fatigue damage (WFD). As an airplane ages, WFD will likely 
occur, and will certainly occur if the airplane is operated long enough 
without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.
    <bullet> Airbus Service Bulletin A330-53-3159, Revision 02, dated 
March 29, 2010. The service information describes procedures for a 
modification of the fuselage, which includes inspections (e.g., eddy 
current rotating probe test of fastener holes for cracking, high 
frequency eddy current (HFEC) inspections for cracking of the upper 
shell structure of the fuselage, and checks of the fastener position 
for clearance) and applicable corrective actions (e.g., repair and 
rework).
    <bullet> Airbus Service Bulletin A330-53-3160, Revision 03, dated 
January 6, 2012. The service information describes procedures for 
applicable actions, including an eddy current rotating probe test for 
cracking of the fastener holes and an HFEC inspection for cracks in the 
upper shell of the fuselage (and including checks of the fastener 
position for clearance and applicable corrective actions (e.g., repair 
and rework)), and a modification of the airplane upper shell structure 
of the fuselage between FR80 and FR86.
    <bullet> Airbus Service Bulletin A330-53-3168, Revision 02, dated 
December 21, 2011. The service information describes procedures for a 
HFEC inspection for cracking of the upper shell structure of the 
fuselage between FR80 and FR86.
    <bullet> Airbus Service Bulletin A340-53-4165, Revision 02, dated 
March 29, 2010. The service information describes procedures for a 
modification of the fuselage, which includes inspections (e.g., eddy 
current rotating probe test of fastener holes for cracking, HFEC 
inspections for cracking of the upper shell structure of the fuselage, 
and checks of the fastener position for clearance) and applicable 
corrective actions (e.g., repair and rework).
    <bullet> Airbus Service Bulletin A340-53-4172, Revision 01, dated 
July 8, 2009. The service information describes procedures for 
inspections (e.g., rototest inspections of fastener holes for cracking, 
HFEC inspections for cracking of the upper shell structure of the 
fuselage, and checks of the fastener position for clearance) and 
modification of the airplane upper shell structure between FR80 and 
FR86 (including applicable corrective actions (e.g., repair and 
rework).
    <bullet> Airbus Service Bulletin A340-53-4174, Revision 02, dated 
December 21, 2011. The service information describes procedures for a 
HFEC inspection for cracking of the upper shell structure of the 
fuselage between FR80 and FR86.

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.

[[Page 13801]]

Differences Between This Proposed AD and the MCAI or Service 
Information

    Unlike the procedures described in the service information, this 
proposed AD would not permit further flight if cracks are detected in 
the upper shell structure. We have determined that, because of the 
safety implications and consequences associated with that cracking, any 
cracked upper shell structure must be repaired before further flight. 
This difference has been coordinated with the EASA and Airbus.

Explanation of Compliance Time for Modification

    The compliance time for the modification specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is modified before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 26 airplanes of U.S. 
registry. We also estimate that it would take about 208 work-hours per 
product to comply with the basic requirements (inspection and 
modification) of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $28,360 per product. Based 
on these figures, we estimate the cost of this proposed AD on U.S. 
operators to be $1,197,040, or $46,040 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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) 
2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-
018-AD.

(a) Comments Due Date

    We must receive comments by May 1, 2015.

(b) Affected ADs

    This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747, 
November 12, 2008).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343; and 
Model A340-311, -312, and -313 airplanes; certificated in any 
category; all manufacturer serial numbers on which Airbus 
Modification 44205 has been embodied in production, except those on 
which Airbus Modification 52974 or 53223 has been embodied in 
production.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by the results of a fatigue and damage 
tolerance evaluation that concluded existing compliance times must 
be reduced. We are issuing this AD to prevent fatigue cracking of 
the upper shell structure of the fuselage, which could result in 
reduced structural integrity of the airplane.

(f) Compliance

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

(g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except 
Model A340-300 Weight Variant (WV) 027 Airplanes

    For Model A330-300 and A340-300 airplanes, except Model A340-300 
WV 027 airplanes: At the applicable time specified in paragraph 
(g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) 
inspection for cracking of the upper shell structure between frame 
(FR) 80 and FR86, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 
21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, 
dated December 21, 2011; as applicable. Repeat the inspection 
thereafter at the applicable time specified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable.
    (1) For airplanes that, as of the effective date of this AD, 
have not been inspected in accordance with Airbus Service Bulletin 
A330-53-3168; or Airbus Service Bulletin A340-53-4174; as 
applicable: Inspect at the later of the times specified in 
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) Before reaching the applicable threshold specified in 
paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-
3168, Revision 02, dated December 21, 2011; or Airbus Service 
Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as 
applicable for airplane model, configuration, and utilization, since 
the airplane's first flight.
    (ii) Within the threshold defined in paragraph 1.E, 
``COMPLIANCE,'' of Airbus

[[Page 13802]]

Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; 
or Airbus Service Bulletin A340-53-4174, Revision 01, dated February 
15, 2008; as applicable for airplane model, configuration, and 
utilization since the airplane's first flight; or within 12 months 
after the effective date of this AD; whichever occurs first.
    (2) For airplanes that, as of the effective date of this AD, 
have been inspected in accordance with Airbus Service Bulletin A330-
53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: 
Inspect at the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD.
    (i) Within the applicable interval specified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
02, dated December 21, 2011; or Airbus Service Bulletin A340-53-
4174, Revision 02, dated December 21, 2011; as applicable; to be 
counted from the last inspection.
    (ii) Within 12 months after the effective date of this AD 
without exceeding the intervals defined in paragraph 1.E, 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 
01, dated February 15, 2008; or Airbus Service Bulletin A340-53-
4174, Revision 01, dated February 15, 2008; as applicable for 
airplane model, configuration, and utilization to be counted from 
the last inspection.

(h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes, 
Except Model A340-300 WV 027 Airplanes

    If any crack is detected during any HFEC inspection required by 
the introductory text to paragraph (g) of this AD: 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). Accomplishment of a repair for a 
specific area, as required by this paragraph, is terminating action 
for the repetitive HFEC inspections required by the introductory 
text to paragraph (g) of this AD, as applicable, for that specific 
repaired area only. The need and definition of subsequent repetitive 
inspections (if any) for that specific repaired area will be defined 
in the applicable repair 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).

(i) Optional Terminating Action

    For Airbus Model A330-300 and A340-300 airplanes, except Model 
A340-300 WV 027 airplanes: Modification, which includes inspections 
and applicable corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, 
Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-
53-4165, Revision 02, dated March 29, 2010; as applicable; 
terminates the repetitive HFEC inspections required by the 
introductory text to paragraph (g) of this AD, except where Airbus 
Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or 
Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 
2010; as applicable; specifies to contact the manufacturer, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA 
DOA.

(j) Inspection and Modification for Airbus Model A330-200 Airplanes

    (1) Within the compliance times specified in paragraph (j)(1)(i) 
or (j)(1)(ii) of this AD, whichever occurs later: Do all applicable 
actions, including an eddy current rotating probe test and an HFEC 
inspection for cracks, and modify the airplane upper shell structure 
between FR80 and FR86; in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, 
dated January 6, 2012.
    (i) Within the compliance times identified in paragraph 1.E., 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 
03, dated January 6, 2012, as applicable for airplane configuration 
and utilization since the airplane's first flight.
    (ii) Within 12 months after the effective date of this AD 
without exceeding the threshold, defined in paragraph 1.E, 
``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 
02, dated March 29, 2010, since the airplane's first flight.

(k) Inspection and Modification for Airbus Model A340-300 Airplanes, 
Only WV 027

    For Model A340-300 airplanes, WV 027 only: Before the 
accumulation of 14,200 total flight cycles from the airplane's first 
flight, do all applicable inspections and modify the airplane upper 
shell structure between FR80 and FR86; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, 
Revision 01, dated July 8, 2009.

(l) Corrective Action for Airbus Model A330-200 Airplanes; and Model 
A340-300 Airplanes, Only WV 027

    If any crack is detected during the inspection required by 
paragraph (j) or (k) of this AD, before further flight, repair using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; 
concurrently with modification required by paragraph (j) or (k) of 
this AD.

(m) Definition of ``Threshold'' and ``Interval''

    (1) For the purposes of this AD, the term ``Threshold,'' as used 
in paragraph 1.E., ``COMPLIANCE,'' of the service information 
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD 
means the total flight cycles or flight hours accumulated since the 
airplane's first flight.
    (2) For the purposes of this AD, the term ``Interval'' as used 
in paragraph 1.E., ``COMPLIANCE,'' of the service information 
specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD 
means the total flight cycles or flight hours accumulated since the 
last inspection, as applicable.
    (i) Airbus Service Bulletin A330-53-3168, dated September 19, 
2007.
    (ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated 
February 15, 2008.
    (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated 
December 21, 2011.
    (iv) Airbus Service Bulletin A340-53-4174, dated September 19, 
2007.
    (v) Airbus Service Bulletin A340-53-4174, Revision 01, dated 
February 15, 2008.
    (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated 
December 21, 2011.

(n) Credit for Previous Actions

    (1) For Model A330-300 and A340-300 airplanes, except Model 
A340-300 WV 027 airplanes: This paragraph provides credit for the 
modification specified in paragraph (i) of this AD, if those actions 
were performed before the effective date of this AD using the 
service information identified in paragraph (n)(1)(i), (n)(1)(ii), 
(n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service 
information is not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A330-53-3159, dated September 19, 
2007.
    (ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated 
June 15, 2009.
    (iii) Airbus Service Bulletin A340-53-4165, dated September 19, 
2007.
    (iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated 
June 17, 2009.
    (2) For Model A330-200 airplanes: This paragraph provides credit 
for the inspection and modification required by paragraph (j) of 
this AD, if those actions were performed before the effective date 
of this AD using the service information identified in paragraph 
(n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as applicable. 
This service information is not incorporated by reference in this 
AD.
    (i) Airbus Service Bulletin A330-53-3160, dated July 9, 2007.
    (ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated 
April 28, 2009.
    (iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated 
March 29, 2010.
    (3) For Model A340-300 airplanes, WV 027 only: This paragraph 
provides credit for the inspection and modification required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A340-53-
4172, dated July 10, 2007, which is not incorporated by reference in 
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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425- 227-1149. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#734a5e323d3e5e4242455e323e3c305e2136222636202720331512125d141c05"><span class="__cf_email__" data-cfemail="bb8296faf5f6968a8a8d96faf6f4f896e9feeaeefee8efe8fbdddada95dcd4cd">[email protected]</span></a>. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal

[[Page 13803]]

inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0012R1, dated January 24, 
2014, 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-2015-0490.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#12737b60657d60667a7b7c7761613c532121223f5321262252737b607067613c717d7f"><span class="__cf_email__" data-cfemail="1c7d756e6b736e68747572796f6f325d2f2f2c315d2f282c5c7d756e7e696f327f7371">[email protected]</span></a>; 
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 March 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05720 Filed 3-16-15; 8:45 am]
 BILLING CODE 4910-13-P


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