[Federal Register Volume 79, Number 228 (Wednesday, November 26, 2014)]
[Rules and Regulations]
[Pages 70458-70462]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-27360]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0425; Directorate Identifier 2013-NM-180-AD; 
Amendment 39-18024; AD 2014-23-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2012-06-19 for 
certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-
200 and -300 series airplanes. AD 2012-06-19 required repetitive 
inspections of the main fitting and sliding tube of the nose landing 
gear (NLG) for defects, damage, and cracks; and corrective actions if 
necessary. This new AD requires an inspection of the part number and 
serial number of the NLG main fitting and NLG sliding tube; for 
affected parts, this new AD requires a magnetic particle inspection 
(MPI) for cracks, and flap peening and replacement if necessary. This 
new AD also requires, for certain parts, additional inspections for 
damage and cracking. This new AD also adds airplanes to the 
applicability. This AD was prompted by reports of a cracked main 
fitting and sliding tube during NLG overhaul. We are issuing this AD to 
detect and correct cracks, defects, or damage of the main fitting or 
sliding tube, which could result in consequent NLG collapse.

DATES: This AD becomes effective December 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of April 
30, 2012 (77 FR 22188, April 13, 2012).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0425; 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.

[[Page 70459]]

    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 [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.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-06-19, Amendment 39-17000 (77 FR 22188, 
April 13, 2012). AD 2012-06-19 applied to certain Airbus Model A330-
201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, 
-342, and -343 airplanes; and Model A340-200 and -300 series airplanes. 
The NPRM published in the Federal Register on June 30, 2014 (79 FR 
36666).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0179, dated August 7, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, 
-322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300 
series airplanes. The MCAI states:

    During the overhaul of two different Nose Landing Gear (NLG) 
units, cracks were found on the main fitting of one and the sliding 
tube of the other. Investigations concluded that the cracks 
initiated as a result of residual stress in the parts, following 
damage due to impact during towing incidents.
    A subsequent review of the reported incidents identified a 
specific group of NLG main fittings and sliding tubes that may have 
sustained impact damage as a result of towing incidents.
    This condition, if not detected and corrected could lead to NLG 
collapse.
    To address this potential unsafe condition, EASA issued AD 2010-
0034 [(http://ad.easa.europa.eu/blob/easa_ad_2010_0034_Corrected_superseded.pdf/AD_2010-0034_1) [which 
corresponds to FAA AD 2012-06-19, Amendment 39-17000 (77 FR 22188, 
April 13, 2012)] to require accomplishment of a one-time Magnetic 
Particles Inspection (MPI), followed by repetitive Detailed Visual 
Inspections (DVI) of the main fittings and sliding tubes of the 
affected NLG units identified by Part Number (P/N) and Serial Number 
(S/N) in the Applicability section of that AD and, depending on 
findings, accomplishment of applicable corrective actions.
    Since that [EASA] AD was issued, it has been found necessary to 
address the issue at the level of NLG detail parts and no longer at 
NLG assembly level, as some detail parts have been transferred from 
an aeroplane to another. Airbus revised the applicable Service 
Bulletins (SB), which now list the affected NLG main fittings and 
sliding tubes.
    For the reasons described above, this [EASA] AD retains 
[certain] requirements of EASA AD 2010-0034 which is superseded and 
requires [an inspection of the part number and serial number of the 
NLG main fitting and NLG sliding tube, and for affected parts,] a 
one-time MPI [for cracks], followed by repetitive DVI [for cracking, 
damage to paint, sealant, cadmium, and base metal] of the affected 
NLG main fittings and sliding tubes and, depending on inspection 
results, accomplishment of corrective actions [e.g., flap peening 
and replacing cracked parts]. This AD also extends the applicability 
to A330 freighters.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0425-0002.

Clarification of Service Information References

    We have clarified the service information references in this AD to 
identify the appendices.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
36666, June 30, 2014) and the FAA's response to each comment.

Request to Reference Service Information Instead of Table

    Air France requested that we revise paragraph (g) of the NPRM (79 
FR 36666, June 30, 2014), to replace table 1 to paragraph (g) of the 
NPRM with references to Airbus Service Bulletin A330-32-3233, Revision 
02, including Appendix 01, dated January 27, 2014; and Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated July 
5, 2013. Air France asserted that the main reason for superseding AD 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), is to 
address the issue at the level of NLG detail parts and no longer at the 
NLG assembly level, as some detail parts have been transferred from one 
airplane to another.
    We agree with the commenter that Airbus Service Bulletin A330-32-
3233, Revision 02, including Appendix 01, dated January 27, 2014; and 
Airbus Service Bulletin A340-32-4275, Revision 01, including Appendix 
01, dated July 5, 2013, contain the NLG detail parts (NLG main fitting 
and NLG sliding tube). However, paragraph (g) of this AD is a 
requirement that is retained from AD 2012-06-19, Amendment 39-17000 (77 
FR 22188, April 13, 2012) and only restates the affected parts 
identified in that AD. Paragraphs (i) and (j) of this AD require 
inspecting for affected NLG main fittings and NLG sliding tubes 
identified in the service information and inspecting affected parts for 
cracks. Accomplishing the new requirements specified in paragraph (j) 
of this AD terminates the actions specified in paragraph (g) of this 
AD. Therefore, no changes were made to this AD in this regard.

``Contacting the Manufacturer'' Paragraph in 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.
    We have become 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 the 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, the European Aviation Safety Agency (EASA), or Airbus's

[[Page 70460]]

EASA Design Organization Approval (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.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 36666, June 30, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 36666, June 30, 2014).

Costs of Compliance

    We estimate that this AD affects 92 airplanes of U.S. registry.
    The actions that were required by AD 2012-06-19, Amendment 39-17000 
(77 FR 22188, April 13, 2012), that are retained in this AD take about 
4 work-hours per product, at an average labor rate of $85 per work-
hour. Required parts cost about $0 per product. Based on these figures, 
the estimated cost of the actions that were required by AD 2012-06-19 
is $31,280 per product.
    We also estimate that it will take about 10 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $0 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $78,200, or $850 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 114 work-hours and require parts costing $435,000, for a 
cost of $444,690 per product. We have no way of determining the number 
of aircraft that might need these actions.

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 http://www.regulations.gov/#!docketDetail;D=FAA-2014-0425; 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.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), and 
adding the following new AD:

2014-23-08 Airbus: Amendment 39-18024. Docket No. FAA-2014-0425; 
Directorate Identifier 2013-NM-180-AD.

(a) Effective Date

    This AD becomes effective December 31, 2014.

(b) Affected ADs

    This AD replaces AD 2012-06-19, Amendment 39-17000 (77 FR 22188, 
April 13, 2012).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers.

[[Page 70461]]

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by reports of a cracked nose landing gear 
(NLG) main fitting and sliding tube during NLG overhaul. We are 
issuing this AD to detect and correct cracks, defects, or damage of 
the main fitting or sliding tube, which could result in consequent 
NLG collapse.

(f) Compliance

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

(g) Retained Detailed Inspection and Corrective Actions

    This paragraph restates the requirements of paragraph (g) of AD 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with 
revised service information. For Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes; and Model A340-211, -212, -213, -311, -312, and -313 
airplanes; if fitted with the NLG identified in table 1 to paragraph 
(g) of this AD: Within 900 flight hours after April 30, 2012 (the 
effective date of AD 2012-06-19), do a detailed inspection of the 
NLG main fitting and sliding tube for any cracks, defects, and 
damage of the paint or surface protection, including paint removal 
and cracking of the surface treatment. Before further flight after 
doing the detailed inspection of the NLG, remove the labels, paint, 
surface protection coatings, and cadmium from the NLG main fitting; 
do a detailed inspection for any damage to the surface that will 
impair the magnetic particle inspection (MPI); and, if any defects 
are found, before further flight, remove any defects by polishing. 
Do all actions specified in this paragraph in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (g)(1) or (g)(2) of this AD.
    (1) For Model A330 airplanes: Airbus Mandatory Service Bulletin 
A330-32-3233, dated October 22, 2009; or Airbus Service Bulletin 
A330-32-3233, Revision 02, including Appendix 01, dated January 27, 
2014.
    (2) For Model A340 airplanes: Airbus Mandatory Service Bulletin 
A340-32-4275, dated October 22, 2009; or Airbus Service Bulletin 
A340-32-4275, Revision 01, including Appendix 01, dated July 5, 
2013.

 Table 1 to Paragraph (g) of This AD--Applicable NLG and Serial Numbers
------------------------------------------------------------------------
                          Part No.                            Serial No.
------------------------------------------------------------------------
D23285200..................................................           B2
D23285101-7................................................          B58
D23285101-10...............................................          B75
D23581100-1................................................         B124
D23581100-1................................................         B159
D23581100-7................................................         B386
D23581100-7................................................         B398
D23581100-7................................................         B400
D23581100-7................................................         B403
------------------------------------------------------------------------

(h) Retained Magnetic Particle Inspection

    This paragraph restates the requirements of paragraph (h) of AD 
2012-06-19, Amendment 39-17000 (77 FR 22188, April 13, 2012), with 
revised service information. Before further flight after doing the 
actions required in paragraph (g) of this AD: Do an MPI for cracking 
of the NLG main fitting and sliding tube, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (g)(1) or (g)(2) of this AD.
    (1) If no crack is detected during the MPI required by the 
introductory text of paragraph (h) of this AD: Before further 
flight, flap peen the inspected area where the paint and cadmium has 
been removed, and replace the protective coatings, in accordance 
with the Accomplishment Instructions of the applicable service 
information specified in paragraph (g)(1) or (g)(2) of this AD.
    (2) If any crack is detected during the MPI required by the 
introductory text of paragraph (h) of this AD: Before further 
flight, replace the damaged part with a new or serviceable part, in 
accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraph (g)(1) or (g)(2) of this 
AD.

(i) New Identification of Part and Serial Numbers

    Within 1,000 flight hours after the effective date of this AD, 
identify the part number and serial number of the NLG main fitting 
and NLG sliding tube, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, 
including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable. A review of airplane maintenance 
records is acceptable in lieu of this identification if the part 
number and the serial number of the NLG main fitting and NLG sliding 
tube can be conclusively determined from that review.

(j) New Magnetic Particle Inspection

    If, during the identification required by paragraph (i) of this 
AD, it is determined any NLG main fitting or NLG sliding tube is 
installed and the fitting or tube has a part number and serial 
number listed in Airbus Service Bulletin A330-32-3233, Revision 02, 
including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable: Within 1,000 flight hours after the 
effective date of this AD, do an MPI for cracks of the affected 
parts, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-32-3233, Revision 02, including Appendix 01, 
dated January 27, 2014; or Airbus Service Bulletin A340-32-4275, 
Revision 01, including Appendix 01, dated July 5, 2013; as 
applicable. Accomplishing the MPI required by this paragraph 
terminates the inspections required by paragraphs (g) and (h) of 
this AD.
    (1) If any crack is detected during the MPI required by the 
introductory text of paragraph (j) of this AD: Before further 
flight, replace any cracked part (NLG main fitting and NLG sliding 
tube) with a serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, 
including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable.
    (2) If no crack is detected during the MPI required by the 
introductory text of paragraph (j) of this AD: Before further 
flight, do a flap peening to introduce compressive residual stress 
and corrosion protection, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-32-3233, Revision 02, 
including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable.

(k) New Detailed Inspection

    Within 900 flight hours after doing the flap peening required by 
paragraph (j)(2) of this AD, do a detailed inspection for damage to 
paint, damage to the sealant around the labels, damage to the 
cadmium or base metal, and for cracking of the affected parts, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, including Appendix 01, dated 
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 
01, including Appendix 01, dated July 5, 2013; as applicable. Repeat 
the inspection thereafter at intervals not to exceed 900 flight 
hours.
    (1) If any damage to the paint, damage to the sealant around the 
labels, or damage to the cadmium or base metal, is detected during 
any detailed inspection required by the introductory text of 
paragraph (k) of this AD; Before further flight, do an MPI for 
cracking of the affected parts, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3233, 
Revision 02, including Appendix 01, dated January 27, 2014; or 
Airbus Service Bulletin A340-32-4275, Revision 01, including 
Appendix 01, dated July 5, 2013; as applicable.
    (2) If any cracking is detected during any inspection required 
by the introductory text of paragraph (k) or paragraph (k)(1) of 
this AD: Before further flight, replace any cracked part with a 
serviceable part, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-32-3233, Revision 02, including 
Appendix 01, dated January 27, 2014; or Airbus Service Bulletin 
A340-32-4275, Revision 01, including Appendix 01, dated July 5, 
2013; as applicable.

(l) Terminating Action

    Replacement of a part as required by paragraph (j)(1) or (k)(2) 
of this AD is terminating action for the repetitive detailed

[[Page 70462]]

inspections required by paragraph (k) of this AD for that part, 
provided that the part number and serial number of the replacement 
part is not listed in Airbus Service Bulletin A330-32-3233, Revision 
02, including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable.

(m) Parts Installation Limitation

    As of the effective date of this AD, installation of an NLG main 
fitting or NLG sliding tube having a part number and serial number 
listed in Airbus Service Bulletin A330-32-3233, Revision 02, 
including Appendix 01, dated January 27, 2014; or Airbus Service 
Bulletin A340-32-4275, Revision 01, including Appendix 01, dated 
July 5, 2013; as applicable; is allowed, provided that the NLG main 
fitting and NLG sliding tube have not accumulated more than 900 
flight hours since the most recent inspection accomplished in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3233, Revision 02, including Appendix 01, dated 
January 27, 2014; or Airbus Service Bulletin A340-32-4275, Revision 
01, including Appendix 01, dated July 5, 2013; as applicable.

(n) Credit for Previous Actions

    This paragraph provides credit for inspections required by 
paragraphs (j) and (k) of this AD and the flap peening required by 
paragraph (j)(2) of this AD, if those actions were performed before 
the effective date of this AD using the applicable service 
information specified in paragraph (n)(1), (n)(2), or (n)(3) of this 
AD.
    (1) Airbus Service Bulletin A330-32-3233, dated October 22, 
2009.
    (2) Airbus Service Bulletin A330-32-3233, Revision 01, dated 
July 5, 2013. This document is not incorporated by reference in this 
AD.
    (3) Airbus Service Bulletin A340-32-4275, dated October 22, 
2009.

(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: [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.
    (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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0179, dated August 7, 2013, for related information. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0425-0002.
    (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 31, 2014.
    (i) Airbus Service Bulletin A330-32-3233, Revision 02, including 
Appendix 01, dated January 27, 2014.
    (ii) Airbus Service Bulletin A340-32-4275, Revision 01, 
including Appendix 01, dated July 5, 2013.
    (4) The following service information was approved for IBR on 
April 30, 2012, (77 FR 22188, April 13, 2012).
    (i) Airbus Service Bulletin A330-32-3233, dated October 22, 
2009.
    (ii) Airbus Service Bulletin A340-32-4275, dated October 22, 
2009.
    (5) 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 [email protected]; 
Internet http://www.airbus.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-27360 Filed 11-25-14; 8:45 am]
BILLING CODE 4910-13-P