Document ID: FAA-2013-0665-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2013-10-31T04:00Z

[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65187-65190]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25130]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0665; Directorate Identifier 2012-NM-082-AD; 
Amendment 39-17634; AD 2013-22-02]
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 adopting a new airworthiness directive (AD) for all 
Airbus Model A330-300 series airplanes and Model A340-200 and -300 
series airplanes. This AD was prompted by reports of corrosion found on 
certain trimmable horizontal stabilizer actuators (THSA), affecting the 
ballscrew lower splines between the tie bar and the screw-jack. This AD 
requires repetitive detailed inspections for corrosion of certain 
THSAs, ballscrew integrity tests if necessary; and replacing any 
affected THSA with a serviceable or new and improved THSA, if 
necessary. We are issuing this AD to detect and correct corrosion of 
the THSAs, which could lead, in the case of ballscrew rupture, to the 
loss of transmission of THSA torque loads from the ballscrew to the 
tie-bar, prompting THSA blowback, and possibly resulting in loss of 
control of the airplane.

DATES: This AD becomes effective December 5, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 5, 
2013.

ADDRESSES: You may examine the AD on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0665 or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.
    For Airbus 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 airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. For Goodrich service information identified in this AD, 
contact Goodrich Corporation, Actuation Systems, Product Support 
Department 13, Avenue de L'Eguillette--Saint-Ouen L'Aumone Boite 
Postale 7186 95056, Cergy Pontoise Cedex, France; fax: 33-1-34326310. 
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 by adding an AD that would apply to the specified products. The 
NPRM published in the Federal Register on August 1, 2013 (78 FR 46543). 
The NPRM proposed to correct an unsafe condition for the specified 
products.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0061R1, dated November 30, 2012 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Some Trimmable Horizontal Stabilizer Actuators (THSA), Part 
Number (P/N) 47147-500, have been found with corrosion, affecting 
the ballscrew lower splines between the tie bar and the screw-jack.
    The results of the technical investigations have identified that 
the corrosion was caused by a combination of:

--Contact/friction between the tie bar and the inner surface of the 
ballscrew leading to the removal of Molykote (corrosion protection) 
at the level of the tie bar splines,
--Humidity ingress initiating surface oxidation starting from areas 
where Molykote is removed, and
--Water retention in THSA lower part leading to corrosion spread out 
and to the creation of a brown deposit (iron oxide).

    The results of the technical investigations have also concluded 
that THSA P/N 47147-500 and P/N 47147-700 ballscrews might be 
affected by this corrosion issue.
    THSA P/N 47147-400 ballscrews might be affected as well, but 
should no longer be in service, and modified into P/N 47147-500, as 
required by EASA AD 2010-0192 and EASA AD 2010-0193 [and as required 
by FAA AD 2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 
2005)].
    This condition, if not detected and corrected, may lead, in case 
of ballscrew rupture, to loss of transmission of THSA torque loads 
from the ballscrew to the tie-bar, prompting THSA blowback, possibly 
resulting in loss of control of the aeroplane.
    To correct this potential unsafe condition, EASA issued AD 2012-
0061 to require repetitive [detailed] visual inspections of the 
ballscrew lower splines of THSA having P/N 47147-500 or P/N 47147-
700 to detect corrosion and, depending on findings [ballscrew 
integrity tests], the accomplishment of applicable corrective 
actions [replacing the affected THSA with a serviceable or improved 
THSA].
    Since that [EASA] AD [2012-0061] was issued, Airbus published 
new Service Bulletin (SB) A330-27-3194 or Airbus SB A340-27-4187 
(Airbus modification 202802), which allow installation in service of 
an improved THSA P/N 47172-530.
    For the reasons described above, this [EASA] AD [2012-0061R1] is 
revised to specify that installation of THSA P/N 47172-530 is an 
alternative (optional) terminating action to the repetitive 
inspections required by this AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0665-0002.

Relevant Service Information

    We have received Airbus Mandatory Service Bulletins A330-27-3179 
and A340-27-4175, both Revision 01, both dated June 13, 2013; which 
specify no additional work. We have updated paragraphs (g), (i), and 
(n) of this final rule to reference this service information. We have 
also added new paragraph (m) to this final rule to allow credit for the 
actions specified in paragraphs (g), (i), and (n) of this final rule, 
if those actions were performed before the effective date of this AD 
using Airbus Mandatory Service Bulletins A330-27-3179, dated February 
14, 2012; or A340-27-4175, dated February 14, 2012. Subsequent 
paragraphs have been re-designated accordingly.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 46543, August 1, 
2013) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the

[[Page 65188]]

public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 46543, August 1, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 46543, August 1, 2013).

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 30 products of U.S. registry. We also estimate that it takes 
about 6 work-hours per product to comply with the basic requirements of 
this AD. The average labor rate is $85 per work-hour. Based on these 
figures, we estimate the cost of this AD on U.S. operators to be 
$15,300, or $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 13 work-hours and require parts costing up to $722,556 for a 
cost of up to $723,661 per product. We have no way of determining the 
number of products that may 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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0665-0002; 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 AD, the MCAI, 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 adding the following new AD:

2013-22-02 Airbus: Amendment 39-17634. Docket No. FAA-2013-0665; 
Directorate Identifier 2012-NM-082-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 5, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-301, -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.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by reports of corrosion found on certain 
trimmable horizontal stabilizer actuators (THSA), affecting the 
ballscrew lower splines between the tie bar and the screw-jack. We 
are issuing this AD to detect and correct corrosion of the THSAs, 
which could lead, in the case of ballscrew rupture, to loss of 
transmission of THSA torque loads from the ballscrew to the tie-bar, 
prompting THSA blowback, and possibly resulting in loss of control 
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) Repetitive Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD, except as required by paragraphs (h)(1) and (h)(2) of 
this AD: Do a detailed inspection of the gaps between the screw 
shaft and tie rod teeth of any THSA having part numbers (P/N) 47147-
500 and 47147-700, to determine if the corrosion condition is Type 
I, Type II, or Type III, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27-3179, 
Revision 01, dated June 13, 2013 (for Model A330-301, -302, -303, -
321, -322, -323, -341, -342, and -343 airplanes); or A340-27-4175, 
Revision 01, dated June 13, 2013 (for Model A340-211, -212, -213, -
311, -312, and -313 airplanes); and the Accomplishment Instructions 
and flowchart

[[Page 65189]]

following the Accomplishment Instructions of Goodrich Actuation 
Systems Service Bulletin 47147-27-18, dated February 17, 2012. 
Repeat the inspection thereafter at intervals not to exceed 24 
months until the modification specified in paragraph (k) is done.
    (1) For any THSA, which, as of the effective date of this AD, 
has accumulated less than 156 months since its first flight on an 
airplane as THSA P/N 47147-400, or since its first flight after the 
modification specified in the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-27-3052 or A340-27-4059 has been 
done: Do the inspection before the accumulation of 156 months but 
not before the accumulation of 132 months since first flight on an 
airplane as THSA P/N 47147-400, or since the THSA's first flight 
after the modification specified in the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-27-3052 or A340-27-4059 
has been done; or within 3 months after the effective date of this 
AD; whichever occurs later.
    (2) For any THSA, which, as of the effective date of this AD, 
has accumulated 156 months or more since its first flight on an 
airplane as THSA P/N 47147-400, or since its first flight after the 
modification specified in the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-27-3052 or A340-27-4059 has been 
done: Do the inspection within 3 months after the effective date of 
this AD.

(h) Compliance Time Exceptions

    (1) Some THSAs having P/N 47147-500 (and further derivative with 
P/N 47147-700) were originally THSA P/N 47147-400 and were 
subsequently modified in service. In this case, the time accumulated 
by any THSA must be calculated from the first installation on 
airplanes as THSA P/N 47147-400.
    (2) Some THSAs having P/N 47147-500 (and further derivative with 
P/N 47147-700) were originally THSA P/N 47147-200, -210, -213, -300, 
-303, or -350 and were subsequently modified in service as specified 
in the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-27-3052 or A340-27-4059. In this case, the time 
accumulated by any THSA must be calculated from the first flight on 
an airplane after the THSA has been modified as specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3052 or A340-27-4059.

(i) Ballscrew Integrity Test and Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
it is determined that a THSA has Type II or Type III corrosion: 
Before further flight, do a ballscrew integrity test, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-27-3179, Revision 01, dated June 13, 2013 (for Model 
A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes); or A340-27-4175, Revision 01, dated June 13, 2013 (for 
Model A340-211, -212, -213, -311, -312, and -313 airplanes).
    (1) For THSAs having Type II or Type III corrosion, and on which 
the results of the ballscrew integrity test were not correct, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-27-3179, Revision 01, dated June 13, 2013 (for 
Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes); or A340-27-4175, Revision 01, dated June 13, 2013 (for 
Model A340-211, -212, -213, -311, -312, and -313 airplanes): Before 
further flight, replace the affected THSA with a new or serviceable 
THSA, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-27-3179, Revision 01, dated June 13, 
2013 (for Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes); or A340-27-4175, Revision 01, dated June 13, 
2013 (for Model A340-211, -212, -213, -311, -312, and -313 
airplanes).
    (2) For THSAs having Type III corrosion, and on which the 
results of the ballscrew integrity test are correct, as specified in 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3179, Revision 01, dated June 13, 2013 (for Model A330-301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes); or 
A340-27-4175, Revision 01, dated June 13, 2013 (for Model A340-211, 
-212, -213, -311, -312, and -313 airplanes): Within 10 days after 
the most recent inspection, replace the THSA with a new or 
serviceable THSA, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-27-3179, Revision 01, 
dated June 13, 2013 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4175, Revision 01, 
dated June 13, 2013 (for Model A340-211, -212, -213, -311, -312, and 
-313 airplanes).
    (3) For THSAs having Type II corrosion, and on which the results 
of the ballscrew integrity test are correct: Within 24 months or 
4,400 flight cycles after the most recent inspection, whichever 
occurs first, replace the THSA with a new or serviceable THSA, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-27-3179, Revision 01, dated June 13, 2013 (for 
Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes); or A340-27-4175, Revision 01, dated June 13, 2013 (for 
Model A340-211, -212, -213, -311, -312, and -313 airplanes).

(j) Replacement of a THSA Is Not Terminating Action

    Replacement of a THSA with a THSA having P/N 47147-500 or 47147-
700 does not constitute a terminating action for the repetitive 
inspections required by paragraph (g) of this AD.

(k) Optional Terminating Modification

    (1) Replacing any THSA having P/N 47147-500 with a new improved 
THSA having P/N 47172-300 (Airbus modification 200238), in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3182 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4178 (for Model 
A340-211, -212, -213, -311, -312, and -313 airplanes); both dated 
February 14, 2012; terminates the repetitive inspections required by 
paragraph (g) of this AD.
    (2) Replacing any THSA having P/N 47147-700 with a new improved 
THSA having P/N 47172-530 (Airbus modification 202802), in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3194 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4187 (for Model 
A340-211, -212, -213, -311, -312, and -313 airplanes); both dated 
October 8, 2012; terminates the repetitive inspections required by 
paragraph (g) of this AD.

(l) Parts Installation Limitation

    As of the effective date of this AD, no person may install a 
THSA, P/N 47147-500 or P/N 47147-700, on any airplane, unless the 
THSA is classified as Type I (no corrosion), in accordance with the 
criteria defined in Goodrich Actuation Systems Service Bulletin 
47147-27-18, dated February 17, 2012; and thereafter inspected in 
accordance with the requirements of paragraph (g) of this AD and any 
applicable actions required by paragraph (i) of this AD are 
accomplished.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraphs (g), (i), and (n) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A330-27-3179, dated February 14, 2012, 
which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the actions specified in 
paragraphs (g), (i), and (n) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A340-27-4175, dated February 14, 2012, 
which is not incorporated by reference in this AD.

(n) Reporting

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g) of this AD to Airbus, at 
the applicable time specified in paragraph (n)(1) or (n)(2) of this 
AD, using Appendix 01 of Airbus Mandatory Service Bulletin A330-27-
3179, Revision 01, dated June 13, 2013 (for Model A330-301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes); or A340-27-
4175, Revision 01, dated June 13, 2013 (for Model A340-211, -212, -
213, -311, -312, and -313 airplanes).
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your

[[Page 65190]]

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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0061R1, dated November 30, 
2012, for related information. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0665-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (q)(3) and (q)(4) 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.
    (i) Airbus Mandatory Service Bulletin A330-27-3179, Including 
Appendix 01, Revision 01, dated June 13, 2013.
    (ii) Airbus Service Bulletin A330-27-3182, dated February 14, 
2012.
    (iii) Airbus Service Bulletin A330-27-3194, dated October 8, 
2012.
    (iv) Airbus Mandatory Service Bulletin A340-27-4175, including 
Appendix 01, Revision 01, dated June 13, 2013.
    (v) Airbus Service Bulletin A340-27-4178, dated February 14, 
2012.
    (vi) Airbus Service Bulletin A340-27-4187, dated October 8, 
2012.
    (vii) Goodrich Actuation Systems Service Bulletin 47147-27-18, 
dated February 17, 2012.
    (3) For Airbus 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 airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. For Goodrich Actuation Systems 
service information identified in this AD, contact Goodrich 
Corporation, Actuation Systems, Product Support Department 13, 
Avenue de L'Eguillette--Saint-Ouen L'Aumone Boite Postale 7186 
95056, Cergy Pontoise Cedex, France; fax: 33-1-34326310.
    (4) You may review copies of the 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.
    (5) 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 October 15, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25130 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P