Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes, 256-260 [E6-22473]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 2 (Thursday, January 4, 2007)]
[Rules and Regulations]
[Pages 256-260]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-22473]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25389; Directorate Identifier 2006-NM-059-AD; 
Amendment 39-14870; AD 2006-26-12]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A330, A340-200, and A340-300 
series airplanes. That AD currently requires repetitive inspections of 
a certain bracket that attaches the flight deck instrument panel to the 
airplane structure; replacement of the bracket with a new, improved 
bracket; and related investigative and corrective actions if necessary. 
This new AD requires replacement of the existing bracket with a 
titanium-reinforced bracket, which ends the repetitive inspections in 
the existing AD. This AD also requires related investigative and 
corrective actions while accomplishing the replacement, and reduces the 
applicability in the existing AD. This AD results from a report of 
cracking damage found on certain brackets that were replaced per the 
requirements in the existing AD. We are issuing this AD to prevent a 
cracked bracket. Failure of this bracket, combined with failure of the 
horizontal beam, could result in collapse of the left part of the 
flight deck instrument panel, and consequent reduced controllability of 
the airplane.

DATES: This AD becomes effective February 8, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 8, 
2007.
    On April 25, 2005 (70 FR 13345, March 21, 2005), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A330-25-3227, including Appendix 01, dated June 17, 
2004; and Airbus Service Bulletin A340-25-4230, including Appendix 01, 
dated June 17, 2004.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

[[Page 257]]

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2005-06-08, amendment 
39-14016 (70 FR 13345, March 21, 2005). The existing AD applies to all 
Airbus Model A330, A340-200, and A340-300 series airplanes. That NPRM 
was published in the Federal Register on July 19, 2006 (71 FR 40942). 
That NPRM proposed to continue to require repetitive inspections of a 
certain bracket that attaches the flight deck instrument panel to the 
airplane structure; replacement of the bracket with a new, improved 
bracket; and related investigative and corrective actions if necessary. 
The NPRM also proposed to add a requirement for replacement of the 
existing bracket with a titanium-reinforced bracket, which would end 
the repetitive inspections in the existing AD. The NPRM also proposed 
to require related investigative and corrective actions while 
accomplishing the replacement, and to reduce the applicability in the 
existing AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Change Applicability

    Airbus suggests that the referenced service bulletins in paragraph 
(k) of the NPRM be added to the applicability in paragraph (c) of the 
NPRM. Airbus states that airplanes modified in service would then be 
excluded from the applicability after the service bulletins are done.
    We disagree with Airbus. The applicability of European Aviation 
Safety Agency (EASA) airworthiness directives 2006-0045 and 2006-0047, 
both dated February 16, 2006, excludes airplanes on which Airbus 
Service Bulletins A330-25-3249 and A340-25-4245, both dated May 3, 
2005, have been accomplished in service. However, we have not excluded 
those airplanes in the applicability of the AD; rather, the AD includes 
a requirement to accomplish the actions specified in those service 
bulletins. This requirement will ensure that the actions specified in 
the service bulletins and required by this AD are accomplished on all 
affected airplanes. Operators must continue to operate the airplane in 
the configuration required by this AD unless an alternative method of 
compliance (AMOC) is approved. We have made no change to the AD in this 
regard.

Request To Clarify Certain Requirements

    Airbus suggests that paragraph (k) of the NPRM refer to Airbus 
(inspection) Service Bulletins A330-25-3227 and A340-25-4230, both 
Revision 01, both dated May 3, 2005, to avoid confusion with Airbus 
(modification) Service Bulletins A330-25-3249 and A340-25-4245, both 
dated May 3, 2005.
    We agree with Airbus. We have changed paragraph (f) of this AD to 
limit the (inspection) service bulletin reference to paragraphs (g), 
(h), and (i) of this AD. In addition, we have changed paragraph (k) of 
this AD to refer to (modification) Airbus Service Bulletins A330-25-
3249 and A340-25-4245, both dated May 3, 2005.
    Airbus also suggests that the description of the related 
investigative and corrective actions specified in parenthesis in 
paragraph (k) be expanded, for clarification, to include the horizontal 
beam.
    We do not agree with Airbus. The description in parenthesis is 
informational only; there is no need to expand it further as the 
description is not meant to be all inclusive. We have made no change to 
the AD in this regard.

Request To Remove Part Number

    Airbus recommends removing the reference to titanium-reinforced 
brackets having part number (P/N) F2511305220096, as specified in 
paragraph (k) of the NPRM. Airbus states that referring to a specific 
part number for the replacement brackets may suggest that no other part 
number is acceptable. Airbus adds that, if a new or upgraded part is 
released in the field (illustrated parts catalog), installation of a 
new part number may lead to operator requests for information for the 
difference between the part number specified in the NPRM and any new 
part number. Airbus notes that this information would be technical 
documentation for demonstration of continued conformity to the AD. 
Airbus concludes that recording application of the referenced service 
bulletin should be adapted for compliance with the NPRM.
    We do not agree with Airbus. Replacement of brackets, as specified 
in paragraph (k) of this AD, is to be accomplished in accordance with 
the Accomplishment Instructions of Airbus Service Bulletins A330-25-
3249 and A340-25-4245, both dated May 3, 2005. Each of these service 
bulletins provides instructions for removal of the old bracket and 
installation of the new, reinforced bracket having P/N F2511305220096. 
Any other part number for the bracket, even if upgraded from those in 
the subject service bulletins, will need to be approved as an AMOC to 
paragraph (k) of this AD, in accordance with the requirements in 
paragraph (l) of this AD. We have made no change to the AD in this 
regard.

Request to Publish Service Information/Incorporate by Reference in NPRM

    The Modification and Replacement Parts Association (MARPA) states 
that ADs are based on service information that originates from the type 
certificate holder or its suppliers. MARPA adds that manufacturer's 
service documents are privately authored instruments, generally having 
copyright protection against duplication and distribution. When a 
service document is incorporated by reference into a public document, 
such as an AD, pursuant to 5 U.S.C. 552(a) and 1 CFR part 51, it loses 
its private, protected status and becomes a public document. MARPA 
notes that if a service document is used as a mandatory element of 
compliance it should not simply be referenced, but should be 
incorporated by reference. MARPA believes that public laws, by 
definition, should be public, which means they cannot rely upon private 
writings for compliance. MARPA adds that the legal interpretation of a 
document is a question of law, not of fact; therefore, unless the 
service document is incorporated by reference it cannot be considered. 
MARPA is concerned that failure to incorporate essential service 
information could result in a court decision invalidating the AD.
    MARPA also states that service documents incorporated by reference 
should be made available to the public by publication in the Docket 
Management System (DMS), keyed to the action that incorporates those 
documents. MARPA notes that the stated purpose of the incorporation by 
reference method is brevity, to keep from expanding the Federal 
Register needlessly by publishing documents already in the hands of the 
affected individuals. MARPA adds that, traditionally, ``affected 
individuals'' means aircraft owners and operators, who are generally 
provided service information by the manufacturer. MARPA adds that, a 
new class of affected individuals has emerged, since the majority of 
aircraft maintenance is now performed by specialty shops instead of 
aircraft owners and operators. MARPA notes that this new class

[[Page 258]]

includes maintenance and repair organizations, component servicing, 
and/or servicing alternatively certified parts under section 21.303 
(``Replacement and modification parts'') of the Federal Aviation 
Regulations (14 CFR 21.303). MARPA notes that the concept of brevity is 
now nearly archaic as documents exist more frequently in electronic 
format than on paper. Therefore, MARPA asks that the service documents 
deemed essential to the accomplishment of the NPRM be incorporated by 
reference into the regulatory instrument and published in DMS.
    We understand MARPA's concern about incorporating by reference 
service information. The Office of the Federal Register (OFR) requires 
that documents that are necessary to accomplish the requirements of the 
AD be incorporated by reference during the final rule phase of 
rulemaking. This final rule incorporates by reference the document 
necessary for the accomplishment of the requirements mandated by this 
AD. Further, we point out that while documents that are incorporated by 
reference do become public information, as noted by the commenter, they 
do not lose their copyright protection. For that reason, we advise the 
public to contact the manufacturer to obtain copies of the referenced 
service information.
    In regard to MARPA's request to post service bulletins on the 
Department of Transportation's DMS, we are currently in the process of 
reviewing issues surrounding the posting of service bulletins on DMS as 
part of an AD docket. Once we have thoroughly examined all aspects of 
this issue and have made a final determination, we will consider 
whether our current practice needs to be revised. No change to the AD 
is necessary in response to these comments.

Requests Regarding Parts Manufacturer Approval (PMA) Parts

    MARPA states that type certificate holders in their service 
documents universally ignore the possible existence of PMA parts. 
According to MARPA, this is especially true with foreign manufacturers 
where the concept may not exist or be implemented in the country of 
origin. MARPA states that frequently the service bulletin upon which an 
AD is based will require the removal of a certain part number and the 
installation of a different part number as a corrective action. MARPA 
states that this practice runs afoul of section 21.303 (``Replacement 
of modification parts'') of the Federal Aviation Regulations (14 CFR 
21.303), which permits the development, certification, and installation 
of alternatively certified parts (PMA). MARPA states that mandating the 
installation of a certain part number to the exclusion of all other 
parts is not a favored general practice. According to MARPA, such 
action has the dual effect of preventing, in some cases, the 
installation of perfectly good parts, while at the same time 
prohibiting the development of new parts permitted under 14 CFR 21.303. 
MARPA states that such a prohibition runs the risk of taking the AD out 
of the realm of safety and into the world of economics since 
prohibiting the development, sale, and use of a perfectly airworthy 
part has nothing to do with safety. MARPA adds that courts could easily 
construe such actions as being outside the statutory basis of the AD 
(safety), and thus unenforceable. MARPA concludes that courts are 
reluctant to find portions of a rule unenforceable since they lack the 
knowledge and authority to rewrite requirements, and are generally 
inclined to void the entire rule.
    In addition, MARPA believes that the practice of requiring an AMOC 
to install a PMA part should be stopped. MARPA states that this is 
somehow tantamount to illogically stating that all PMA parts are 
inherently defective and require an additional layer of approval when 
the original equipment manufacturer (OEM) part is determined to be 
defective. MARPA suspects that FAA personnel who diligently labored to 
certify the PMA part might disagree with such a narrow, OEM slanted 
view. MARPA adds that if the PMA part is defective then it must be 
deemed so in the AD, and not simply implied by a catch-all AMOC 
requirement. MARPA states that it has repeatedly requested that 
language be adopted to trap such defective parts. MARPA suggests that, 
to accomplish this, the Transport Airplane Directorate adopt the 
language used by the Small Airplane Directorate. MARPA adds that this 
action, as written, does not comply with proposed FAA Order 8040.2, 
which requires replacement or installation of certain parts, could have 
replacement parts approved under Federal Aviation Regulation 14 CFR 
21.203, based on a finding of the part being identical.
    MARPA also points out that another AD issued from a Directorate 
other than the Transport Airplane Directorate contains a blanket 
statement that resolves the PMA issue by adding the phrase, ``or FAA-
approved equivalent P/N'' to the part number mandated to be installed. 
MARPA requests that the FAA modify the NPRM to include this language.
    The NPRM did not address PMA parts, as provided in draft FAA Order 
8040.2, because the Order was only a draft that was out for comment at 
the time. After issuance of the NPRM, the Order was revised and issued 
as FAA Order 8040.5 with an effective date of September 29, 2006. FAA 
Order 8040.5 does not address PMA parts in ADs.
    The FAA recognizes the need for standardization of this issue and 
is currently in the process of reviewing issues that address the use of 
PMAs in ADs at the national level. However, the Transport Airplane 
Directorate considers that to delay this particular AD action would be 
inappropriate, since we have determined that an unsafe condition exists 
and that replacement of certain parts must be accomplished to ensure 
continued safety. Therefore, no change has been made to the AD in this 
regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. These changes will neither increase the economic burden on 
any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 24 Model A330 series airplanes of U.S. 
registry.
    The inspections that are required by AD 2005-06-08 and retained in 
this AD take about 1 work hour per airplane, at an average labor rate 
of $80 per work hour. Based on these figures, the estimated cost of the 
currently required actions is $80 per airplane, per inspection cycle.
    The new replacement and investigative actions take about 9 work 
hours per airplane, at an average labor rate of $80 per work hour. 
Required parts will cost about $330 per airplane. Based on these 
figures, the estimated cost of the new actions specified in this AD for 
U.S. operators is $25,200, or $1,050 per airplane.
    There are currently no affected Model A340-200 and -300 series 
airplanes of U.S. registry. However, if one of these airplanes is 
imported and put on the U.S. Register in the future, these cost 
estimates will also apply to those airplanes.

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,

[[Page 259]]

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 have 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 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14016 (70 FR 13345, March 21, 2005) and by adding 
the following new airworthiness directive (AD):

2006-26-12 Airbus: Amendment 39-14870. Docket No. FAA-2006-25389; 
Directorate Identifier 2006-NM-059-AD.

Effective Date

    (a) This AD becomes effective February 8, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-06-08.

Applicability

    (c) This AD applies to Airbus Model A330, A340-200, and A340-300 
series airplanes; certificated in any category; except airplanes on 
which Airbus Modification 53446 has been incorporated in production.

Unsafe Condition

    (d) This AD results from a report of cracking damage found on 
certain brackets that were replaced to address an unsafe condition. 
We are issuing this AD to prevent a cracked bracket. Failure of this 
bracket, combined with failure of the horizontal beam, could result 
in collapse of the left part of the flight deck instrument panel, 
and consequent reduced controllability of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 2005-06-08

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in paragraphs (g), 
(h), and (i) of this AD, means the Accomplishment Instructions of 
Airbus Service Bulletins A330-25-3227 (for Model A330 series 
airplanes) and A340-25-4230 (for Model A340-200 and -300 series 
airplanes), both Revision 01, both dated May 3, 2005; as applicable. 
Accomplishment before the effective date of this AD of Airbus 
Service Bulletins A330-25-3227 and A340-25-4230, both including 
Appendix 01, both dated June 17, 2004, as applicable, is an 
acceptable means of compliance for paragraphs (g), (h), and (i) of 
this AD.

Initial Inspection

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, perform a detailed inspection of the bracket 
having part number (P/N) F2511012920000, which attaches the flight 
deck instrument panel to airplane structure, in accordance with the 
applicable service bulletin.
    (1) For Model A330 series airplanes: Prior to the accumulation 
of 16,500 total flight cycles, or within 60 days after April 25, 
2005 (the effective date of AD 2005-06-08), whichever is later.
    (2) For Model A340-200 and -300 series airplanes: Prior to the 
accumulation of 9,700 total flight cycles, or within 2,700 flight 
cycles after April 25, 2005, whichever is later.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

No Cracking/Repetitive Inspections

    (h) If no crack is found during the initial inspection required 
by paragraph (g) of this AD: Repeat the inspection thereafter at the 
applicable interval specified in paragraph (h)(1) or (h)(2) of this 
AD, until the replacement specified in paragraph (k) of this AD has 
been accomplished.
    (1) For Model A330 series airplanes: Intervals not to exceed 
13,800 flight cycles.
    (2) For Model A340-200 and -300 series airplanes: Intervals not 
to exceed 7,000 flight cycles.

Crack Found/Replacement and Repetitive Inspections

    (i) If any crack is found during any inspection required by 
paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1) 
and (i)(2) of this AD, except as provided by paragraph (j) of this 
AD, until accomplishment of the replacement required by paragraph 
(k) of this AD.
    (1) Before further flight: Replace the cracked bracket with a 
new, improved bracket having P/N F2511012920095, in accordance with 
the service bulletin.
    (2) Repeat the inspection of the replaced bracket as required by 
paragraph (g) of this AD, at the time specified in paragraph 
(i)(2)(i) or (i)(2)(ii) of this AD. Then, do repetitive inspections 
or replace the bracket as specified in paragraph (h) or (i) of this 
AD, as applicable.
    (i) For Model A330 series airplanes: Within 16,500 flight cycles 
after replacing the bracket.
    (ii) For Model A340-200 and -300 series airplanes: Within 9,700 
flight cycles after replacing the bracket.
    (j) If both flanges of a bracket are found broken during any 
inspection required by this AD: Before further flight, replace the 
bracket as specified in paragraph (i) of this AD and perform any 
applicable related investigative and corrective actions (which may 
include inspections for damage to surrounding structure caused by 
the broken bracket, and corrective actions for any damage that is 
found), in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent).

New Requirements of This AD

Replacement of Brackets/Investigative and Corrective Actions

    (k) Except as required by paragraph (i)(1) of this AD: Within 72 
months after the effective date of this AD, replace existing 
brackets having P/N F2511012920000 or P/N

[[Page 260]]

F2511012920095 with titanium-reinforced brackets having P/N 
F2511305220096; and perform any related investigative and corrective 
actions (which may include detailed inspections for cracking of the 
bracket or damage to surrounding structure caused by a broken 
bracket, and applicable corrective actions for any damage that is 
found); in accordance with the Accomplishment Instructions of Airbus 
Service Bulletins A330-25-3249 and A340-25-4245, excluding Appendix 
01, both dated May 3, 2005, as applicable. If any crack is found, 
before further flight, repair in accordance with the applicable 
service bulletin. Replacement of the affected bracket with a 
titanium-reinforced bracket having P/N F2511305220096 ends the 
repetitive inspections required by paragraph (h) or (i) of this AD. 
Although the service bulletins specify to submit certain information 
to the manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (m) EASA airworthiness directives 2006-0045 and 2006-0047, both 
dated February 16, 2006, also address the subject of this AD.

Material Incorporated by Reference

    (n) You must use the applicable service bulletin specified in 
Table 1 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of the service bulletins specified in 
Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.
    (2) On April 25, 2005 (70 FR 13345, March 21, 2005), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A330-25-3227, including 
Appendix 01, dated June 17, 2004; and Airbus Service Bulletin A340-
25-4230, including Appendix 01, dated June 17, 2004.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at https://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

            Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
     Airbus service bulletin        Revision level           Date
------------------------------------------------------------------------
A330-25-3227, including Appendix  Original..........  June 17, 2004.
 01.
A330-25-3227, excluding Appendix  01................  May 3, 2005.
 01.
A330-25-3249....................  Original..........  May 3, 2005.
A340-25-4230, including Appendix  Original..........  June 17, 2004.
 01.
A340-25-4230, excluding Appendix  01................  May 3, 2005.
 01.
A340-25-4245....................  Original..........  May 3, 2005.
------------------------------------------------------------------------


            Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
     Airbus service bulletin        Revision level           Date
------------------------------------------------------------------------
A330-25-3227, excluding Appendix  01................  May 3, 2005.
 01.
A330-25-3249....................  Original..........  May 3, 2005.
A340-25-4230, excluding Appendix  01................  May 3, 2005.
 01.
A340-25-4245....................  Original..........  May 3, 2005.
------------------------------------------------------------------------


    Issued in Renton, Washington, on December 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-22473 Filed 1-3-07; 8:45 am]
BILLING CODE 4910-13-P