[Federal Register Volume 74, Number 144 (Wednesday, July 29, 2009)]
[Rules and Regulations]
[Pages 37523-37527]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-17539]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0211; Directorate Identifier 2008-NM-028-AD; 
Amendment 39-15980 AD 2009-15-17]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:
* * * * *
    [B]ogie beam internal paint has been degraded, leading to a loss 
of cadmium plating and thus allowing development of corrosion 
pitting.
    If not corrected, this situation under higher speed could result 
in the aircraft departing the runway or in the bogie [beam] 
detaching from the aircraft or [main landing] gear collapses, which 
would constitute an unsafe condition.
* * * * *
We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective September 2, 2009.

[[Page 37524]]

    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 2, 
2009.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov 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 FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 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 include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on March 10, 2009 (74 
FR 10199). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    The operator of an A330 aircraft (which has a common bogie beam 
with the A340) has reported a fracture of the RH (right-hand) MLG 
(main landing gear) Bogie Beam whilst turning during low speed taxi 
maneuvers. The bogie [beam] fractured aft of the pivot point and 
remained attached to the sliding tube by the brake torque reaction 
rods. After this RH bogie [beam] failure, the aircraft continued for 
approximately 40 meters on the forks of the sliding member before 
coming to rest on the taxiway without any passenger injury.
    The preliminary investigations revealed that this event was due 
to corrosion pitting occurring on the bore of the bogie beam. 
Investigations are ongoing to determine why bogie beam internal 
paint has been degraded, leading to a loss of cadmium plating and 
thus allowing development of corrosion pitting.
    If not corrected, this situation under higher speed could result 
in the aircraft departing the runway or in the bogie [beam] 
detaching from the aircraft or [main landing] gear collapses, which 
would constitute an unsafe condition.
    To enable early detection and repair of any corrosion of the 
internal surfaces, EASA (European Aviation Safety Agency) AD 2007-
0314 required a one-time inspection on all MLG Bogie Beams except 
Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS.
    The Revision 1 of AD 2007-0314 aimed to clarify the compliance 
time of the inspection and to extend the reporting period.
    The present AD which supersedes the AD 2007-0314R1:

--Takes over the AD 2007-0314R1 requirements and
--Reduces the inspection threshold from 6 to 4.5 years due to 
significant findings on the inspected aircraft.

Required actions include applying protective treatments to the bogie 
beam and corrective actions. Corrective actions include repair of any 
damaged or corroded surfaces or surface treatments, and contacting 
Messier-Dowty for repair instructions and doing the repair. You may 
obtain further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Revise References to the French Export Certificate in the 
NPRM

    Airbus requests that we revise the phrase ``French export 
certificate of airworthiness'' that is specified in paragraphs (f)(2), 
(f)(2)(i), (f)(3), and (f)(3)(i) of the NPRM. Airbus states that there 
is no more ``French'' export airworthiness certificate and states that 
it has been replaced with the EASA export airworthiness certificate.
    We agree to revise paragraphs (f)(2), (f)(2)(i), (f)(3), and 
(f)(3)(i) of this AD for the reason provided by the commenter. We have 
replaced the phrase ``French export certificate of airworthiness'' with 
``French or EASA export certificate of airworthiness.''

Request To Revise Compliance Time Specified in Paragraphs (f)(3)(i) and 
(f)(3)(ii) of the NPRM

    Airbus requests that we revise the compliance time specified in 
paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM to include the 
additional phrase ``or at the next scheduled bogie beam overhaul, 
whichever occurs first.''
    We disagree with revising the compliance time, ``within 18 months 
after the effective date of this AD,'' specified in paragraphs 
(f)(3)(i) and (f)(3)(ii) of this AD to include the additional phrase. 
The requested change would shorten the compliance time for certain 
operators. In developing an appropriate compliance time, we considered 
the safety implications and normal maintenance schedules for timely 
accomplishment of the required actions. We determined that the 
compliance time represents an appropriate interval in which the actions 
required by this AD can be done, in a timely manner within the fleet, 
while still maintaining an adequate level of safety. Operators are 
always permitted to accomplish the requirements of an AD at a time 
earlier than the specified compliance time. If additional data are 
presented that would justify a shorter compliance time, we might 
consider further rulemaking on this issue. We have not revised this AD 
in this regard.

New Relevant Service Information

    Airbus and Messier-Dowty have issued the service information 
described in the following table.

                         New Service Information
------------------------------------------------------------------------
      Service Bulletin           Revision                Date
------------------------------------------------------------------------
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A330-32-3225,
 including Appendix 1.
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A340-32-4268,
 including Appendix 1.
Messier-Dowty Service                      1  November 16, 2007.
 Bulletin A33/34-32-271,
 including Appendixes A and
 B.
Messier-Dowty Service                      1  September 22, 2008.
 Bulletin A33/34-32-272,
 including Appendixes A, B,
 C, and D.
------------------------------------------------------------------------

    We referred to earlier revisions of the service bulletins in the 
NPRM, as described in the following table.

                Service Information Specified in the NPRM
------------------------------------------------------------------------
          Service Bulletin                           Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin     November 21, 2007.
 A330-32-3225, including Appendix 01.

[[Page 37525]]

 
Airbus Mandatory Service Bulletin     November 21, 2007.
 A340-32-4268, including Appendix 01.
Messier-Dowty Service Bulletin A33/   September 13, 2007.
 34-32-271, including Appendix A.
Messier-Dowty Service Bulletin A33/   November 16, 2007.
 34-32-272, including Appendixes A,
 B, C, and D.
------------------------------------------------------------------------

    The new service information does not add work for airplanes on 
which the actions specified in the earlier revisions of the service 
bulletins have been accomplished.
    Revision 01 of Airbus Mandatory Service Bulletins A330-32-3225 and 
A340-32-4268 revises references to Messier-Dowty Service Bulletin A33/
34-32-272. We have revised paragraphs (f)(1) and (h) of this AD to 
refer to Revision 01 of Airbus Mandatory Service Bulletins A330-32-3225 
and A340-32-4268. We have also added Airbus Mandatory Service Bulletins 
A330-32-3225 and A340-32-4268, both dated November 21, 2007, to 
paragraph (f)(6) of this AD to give credit for actions done in 
accordance with these service bulletins before the effective date of 
this AD.
    Revision 1 of Messier-Dowty Service Bulletin A33/34-32-271 provides 
a new illustration and updates the procedures. We have revised 
paragraphs (f)(5) and (h) of this AD to refer to Revision 1 of Messier-
Dowty Service Bulletin A33/34-32-271. We have also added Messier-Dowty 
Service Bulletin A33/34-32-271, including Appendix A, dated September 
13, 2007, to paragraph (f)(6) of this AD to give credit for actions 
done in accordance with that service bulletin before the effective date 
of this AD.
    Revision 1 of Messier-Dowty Service Bulletin A33/34-32-272 provides 
new illustrations and updates the procedures. We have revised 
paragraphs (f)(1)(i), (f)(1)(ii), and (h), and Note 1 of this AD to 
refer to Revision 1 of Messier-Dowty Service Bulletin A33/34-32-272. We 
have also added Messier-Dowty Service Bulletin A33/34-32-272, including 
Appendixes A, B, C, and D, dated November 16, 2007, to paragraph (f)(6) 
of this AD to give credit for actions done in accordance with that 
service bulletin before the effective date of this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 29 products of U.S. registry. 
We also estimate that it will take about 22 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $51,040, or $1,760 per product.

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 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); and
    3. 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 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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 37526]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-15-17 Airbus: Amendment 39-15980. Docket No. FAA-2009-0211; 
Directorate Identifier 2008-NM-028-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 2, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-200, A330-300, A340-
200, and A340-300 series airplanes; certificated in any category; 
all certified models; all serial numbers, except those on which 
Airbus modification 54500 has been embodied in production or Airbus 
Service Bulletin A330-32-3212 has been embodied in service.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    The operator of an A330 aircraft (which has a common bogie beam 
with the A340) has reported a fracture of the RH (right-hand) MLG 
(main landing gear) Bogie Beam whilst turning during low speed taxi 
maneuvers. The bogie [beam] fractured aft of the pivot point and 
remained attached to the sliding tube by the brake torque reaction 
rods. After this RH bogie [beam] failure, the aircraft continued for 
approximately 40 meters on the forks of the sliding member before 
coming to rest on the taxiway without any passenger injury.
    The preliminary investigations revealed that this event was due 
to corrosion pitting occurring on the bore of the bogie beam. 
Investigations are ongoing to determine why bogie beam internal 
paint has been degraded, leading to a loss of cadmium plating and 
thus allowing development of corrosion pitting.
    If not corrected, this situation under higher speed could result 
in the aircraft departing the runway or in the bogie [beam] 
detaching from the aircraft or [main landing] gear collapses, which 
would constitute an unsafe condition.
    To enable early detection and repair of any corrosion of the 
internal surfaces, EASA (European Aviation Safety Agency) AD 2007-
0314 required a one-time inspection on all MLG Bogie Beams except 
Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS.
    The Revision 1 of AD 2007-0314 aimed to clarify the compliance 
time of the inspection and to extend the reporting period.
    The present AD which supersedes the AD 2007-0314R1:

--Takes over the AD 2007-0314R1 requirements and
--Reduces the inspection threshold from 6 to 4.5 years due to 
significant findings on the inspected aircraft.

Required actions include applying protective treatments to the bogie 
beam and corrective actions. Corrective actions include repair of 
any damaged or corroded surfaces or surface treatments, and 
contacting Messier-Dowty for repair instructions and doing the 
repair.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) At the applicable compliance time specified in paragraph 
(f)(2) or (f)(3) of this AD: Clean the internal bore and perform a 
detailed visual inspection of internal surfaces of the MLG bogie 
beam (right-hand and left-hand) for any damage to the protective 
treatments or any corrosion, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-32-3225 or 
A340-32-4268, both Revision 01, both dated October 30, 2008; as 
applicable.
    (i) If no damage and corrosion is found, before further flight, 
apply the protective treatments of the bogie beam, in accordance 
with the Accomplishment Instructions of Messier-Dowty Service 
Bulletin A33/34-32-272, Revision 1, including Appendixes A, B, C, 
and D, dated September 22, 2008.
    (ii) If any damage or corrosion is found, before further flight, 
do all applicable corrective actions and apply the protective 
treatments of the bogie beam, in accordance with the Accomplishment 
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, 
Revision 1, including Appendixes A, B, C, and D, dated September 22, 
2008.
    (2) For airplanes with 54 months or less time-in-service since 
the date of issuance of the original French airworthiness 
certificate or the date of issuance of the original French or EASA 
export certificate of airworthiness as of the effective date of this 
AD: At the latest of the applicable times specified in paragraphs 
(f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, do the actions 
required by paragraph (f)(1) of this AD.
    (i) Not before 54 months since the date of issuance of the 
original French airworthiness certificate or the date of issuance of 
the original French or EASA export certificate of airworthiness, but 
no later than 72 months since the date of issuance of the original 
French airworthiness certificate or the date of issuance of the 
original French or EASA export certificate of airworthiness.
    (ii) Not before 54 months since the installation of a new bogie 
beam in-service before the effective date of this AD, but no later 
than 72 months since the installation of a new bogie beam in-service 
before the effective date of this AD.
    (iii) Not before 54 months since the last overhaul of a bogie 
beam before the effective date of this AD, but no later than 72 
months since the last overhaul of a bogie beam before the effective 
date of this AD.
    (3) For airplanes with more than 54 months time-in-service since 
the date of issuance of the original French airworthiness 
certificate or the date of issuance of the original French or EASA 
export certificate of airworthiness as of the effective date of this 
AD: At the applicable time specified in paragraph (f)(3)(i), 
(f)(3)(ii), f)(3)(iii), (f)(3)(iv), or (f)(3)(v) of this AD, do the 
actions required by paragraph (f)(1) of this AD.
    (i) For airplanes on which the bogie beam has not been replaced 
or overhauled since the date of issuance of the original French 
airworthiness certificate or the date of issuance of the original 
French or EASA export certificate of airworthiness as of the 
effective date of this AD: Within 18 months after the effective date 
of this AD.
    (ii) For airplanes on which the bogie beam has been replaced in-
service with a new bogie beam and the new bogie beam has more than 
54 months time-in-service as of the effective date of this AD: 
Within 18 months after the effective date of this AD.
    (iii) For airplanes on which the bogie beam has been replaced 
in-service with a new bogie beam and the new bogie beam has 54 
months or less time-in-service as of the effective date of this AD: 
Not before 54 months since the installation of a new bogie beam in-
service before the effective date of this AD, but no later than 72 
months since the installation of a new bogie beam in-service before 
the effective date of this AD.
    (iv) For airplanes on which the bogie beam has been overhauled 
and the overhauled bogie beam has more than 54 months time-in-
service as of the effective date of this AD: Within 18 months after 
the effective date of this AD, or at the next scheduled bogie beam 
overhaul, whichever occurs first.
    (v) For airplanes on which the bogie beam has been overhauled 
and the overhauled bogie beam has 54 months or less time-in-service 
as of the effective date of this AD: Not before 54 months since the 
last overhaul of a bogie beam before the effective date of this AD, 
but no later than 72 months since the last overhaul of a bogie beam 
before the effective date of this AD.
    (4) Within 30 days after accomplishment of the inspection 
required by paragraph (f)(1) of this AD or within 30 days after the 
effective date of this AD, whichever occurs later, report the 
results, including no findings, to Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; e-mail <a href="/cdn-cgi/l/email-protection#b9d8d0cbced6cbcdd1d0d7dccaca97f88a8a8994f88a8d89f9d8d0cbdbccca97dad6d4"><span class="__cf_email__" data-cfemail="1d7c746f6a726f69757473786e6e335c2e2e2d305c2e292d5d7c746f7f686e337e7270">[email protected]</span></a>.
    (5) Actions accomplished in accordance with Messier-Dowty 
Service Bulletin A33/34-32-271, Revision 1, including Appendixes A 
and B, dated November 16, 2007, are considered acceptable for 
compliance with the corresponding requirements of this AD.
    (6) Actions accomplished before the effective date of this AD in 
accordance with the service bulletins specified in Table 1 of this 
AD are considered acceptable for compliance with the corresponding 
requirements of this AD.

[[Page 37527]]



                   Table 1--Credit Service Information
------------------------------------------------------------------------
          Service Bulletin                           Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin     November 21, 2007.
 A330-32-3225.
Airbus Mandatory Service Bulletin     November 21, 2007.
 A340-32-4268.
Messier-Dowty Service Bulletin A33/   September 13, 2007.
 34-32-271, including Appendix A.
Messier-Dowty Service Bulletin A33/   November 16, 2007.
 34-32-272, including Appendixes A,
 B, C, and D.
------------------------------------------------------------------------

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: The MCAI specifies repair and corrective actions in 
accordance with Airbus Mandatory Service Bulletin A330-32-3225 or 
A340-32-4268, both dated November 21, 2007; however, these Airbus 
service bulletins do not describe those actions. Paragraphs 
(f)(1)(i) and (f)(1)(ii) of this AD specify repair and corrective 
actions in accordance with Messier-Dowty Service Bulletin A33/34-32-
272, Revision 1, including Appendixes A, B, C, and D, dated 
September 22, 2008.

Other FAA AD Provisions

    (g) 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. Send information to ATTN: 
Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office.
    (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: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to EASA Airworthiness Directive 2008-0093, dated May 
20, 2008, and the service bulletins specified in Table 2 of this AD, 
for related information.

                      Table 2--Service Information
------------------------------------------------------------------------
      Service Bulletin           Revision                Date
------------------------------------------------------------------------
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A330-32-3225,
 including Appendix 1.
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A340-32-4268,
 including Appendix 1.
Messier-Dowty Service                      1  November 16, 2007.
 Bulletin A33/34-32-271,
 including Appendixes A and
 B.
Messier-Dowty Service                      1  September 22, 2008.
 Bulletin A33/34-32-272,
 including Appendixes A, B,
 C, and D.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the service information contained in Table 3 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

               Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
      Service Bulletin           Revision                Date
------------------------------------------------------------------------
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A330-32-3225,
 including Appendix 1.
Airbus Mandatory Service                  01  October 30, 2008.
 Bulletin A340-32-4268,
 including Appendix 1.
Messier-Dowty Service                      1  November 16, 2007.
 Bulletin A33/34-32-271,
 including Appendixes A and
 B.
Messier-Dowty Service                      1  September 22, 2008.
 Bulletin A33/34-32-272,
 including Appendixes A, B,
 C, and D.
------------------------------------------------------------------------

(Pages identified as ``intentionally blank'' in the Messier-Dowty 
service bulletins identified in Table 3 of this AD are at the 
revision level and date specified in Table 3 for those documents.)
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For Airbus service information identified in this AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail 
<a href="/cdn-cgi/l/email-protection#fe9f978c89918c8a9697909b8d8dd0bfcdcdced3bfcdcacebe9f978c9c8b8dd09d9193"><span class="__cf_email__" data-cfemail="e1808893968e939589888f849292cfa0d2d2d1cca0d2d5d1a1808893839492cf828e8c">[email protected]</span></a>; Internet http://www.airbus.com. 
For Messier-Dowty service information identified in this AD, contact 
Messier Services Americas, Customer Support Center, 45360 Severn 
Way, Sterling, Virginia 20166-8910; telephone 703-450-8233; fax 703-
404-1621; Internet https://techpubs.services.messier-dowty.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-17539 Filed 7-28-09; 8:45 am]
BILLING CODE 4910-13-P


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