[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73925-73930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23901]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23251; Directorate Identifier 2002-NM-20-AD; 
Amendment 39-14413; AD 2005-25-20]
RIN 2120-AA64


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

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A330-300, A340-200, and 
340-300 series airplanes. The existing AD requires repetitive 
inspections to detect cracking of the fuselage skin in the area of the 
VHF2 antenna, and repair if necessary. The existing AD also provides 
for optional terminating action for the repetitive inspections. This 
new AD requires accomplishment of the previously optional terminating 
action, and revises the applicability by removing certain airplanes. 
This AD is prompted by the need to change the applicability of the 
existing AD and to mandate the formerly optional terminating action. We 
are issuing this AD to prevent cracking of the fuselage skin in the 
area of the VHF2 antenna, which could result in depressurization of the 
airplane.

DATES: Effective December 29, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 29, 2005.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 2000).
    We must receive comments on this AD by February 13, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can 
examine this information 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.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This 
docket number is FAA-2005-23251; the directorate identifier for this 
docket is 2002-NM-20-AD.

Examining the Docket

    You can examine the AD docket on the Internet at http://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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: On February 29, 2000, the FAA issued AD 
2000-05-04, amendment 39-11613 (65 FR 12075, March 8, 2000). That AD 
applies to certain Airbus Model A330 and A340 series airplanes and 
requires repetitive inspections to detect cracking of the fuselage skin 
in the area of the VHF2 antenna, and repair if necessary. That AD also 
provides for optional terminating action for the repetitive 
inspections. That action was prompted by issuance of mandatory 
continuing

[[Page 73926]]

airworthiness information by the French civil aviation authority. We 
issued that AD to detect and correct such cracking, which could result 
in depressurization of the airplane.

Actions Since Issuance of Previous Rule

    Since we issued AD 2000-05-04, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, has revised the parallel French airworthiness directives to 
exclude airplanes that have been modified by Airbus Modification 46025, 
46849, or 46900; and to mandate the previously optional terminating 
action.

Explanation of Relevant New Service Information

    Airbus has issued the following service bulletins:

                                                                   Service Information
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         Describes procedures for               Which could be eliminated by the modification specified in--
       Airbus Service Bulletin--           repetitive detailed    --------------------------------------------------------------------------------------
                                             inspections of--           Airbus Service Bulletin--        Revision--                Dated--
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330-53-3094, Revision 03, dated        Model A330-300 series      A330-53-3097                                  02  November 21, 2000.
 February 22, 2001; and Revision 04,     airplanes.
 dated July 23, 2001.
A340-53-4105, Revision 03, dated        Model A340 series          A340-53-4108                                  02  December 6, 2000.
 February 22, 2001, and Revision 04,     airplanes.
 dated July 23, 2001.
--------------------------------------------------------------------------------------------------------------------------------------------------------

The revised service bulletins for the terminating modification are 
essentially the same: They remove certain life limits, but add no new 
procedures. The DGAC classified Service Bulletins A330-53-3097 and 
A340-53-4108 as mandatory and issued French airworthiness directives 
2001-041(B) and 2001-040(B), both dated January 24, 2001, to ensure the 
continued airworthiness of these airplanes in France.
    Airbus has also issued Service Bulletins A330-53-3112 and A340-53-
4124, both dated February 15, 2001, which describe procedures for 
relocating the VHF2 antenna between stringer 51 and stringer 52, away 
from the outlet air flow of the air conditioning packs. These service 
bulletins provide for alternative procedures to those specified in 
Service Bulletins A330-53-3097 and A340-53-4108 to eliminate the need 
for the repetitive inspections. The DGAC has approved Service Bulletins 
A330-53-3112 and A340-53-4124 and considers them optional terminating 
action for the repetitive inspections.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. According to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    For this reason, we are issuing this AD to supersede AD 2000-05-04. 
This AD retains the requirements of the existing AD, requires 
accomplishment of the previously optional terminating action, and adds 
an alternative terminating action. This AD removes certain airplanes 
from the applicability of the existing AD. The actions are required to 
be done in accordance with the service bulletins described previously, 
except as described below.

Additional Changes to AD

    We have made the following additional changes to the AD:
    1. We revised the applicability in this AD by updating the service 
bulletin references to match the applicability of the corresponding 
French airworthiness directives.
    2. The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this new 
AD. Note 1 in this AD defines that inspection.
    3. We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.
    4. Since we issued AD 2000-05-04, the type certificate data sheet 
for affected airplanes has been updated. We have revised the 
applicability of this AD accordingly.

Differences Between AD and Service Bulletins

    The revised service bulletins provide repair procedures for cracks 
up to 14.17 inches. However, no data have been presented that would 
justify the acceptability of the increased crack length. This AD 
requires that operators contact the FAA or DGAC for repair instructions 
of cracks exceeding 9.45 inches.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    The following table provides the estimated costs to comply with 
this AD for any affected airplane that might be imported and placed on 
the U.S. Register in the future.

[[Page 73927]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                          Applicable Airbus Service                     Hourly labor     Parts cost
                Action                             Bulletin              Work hours    rate (dollars)     (dollars)       Cost per airplane (dollars)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection............................  A330-53-3094 or A340-53-4105.               6              65   None required  390, per inspection cycle.
Fuselage skin reinforcement...........  A330-53-3097 or A340-53-4108.             107              65               0  6,955.
Antenna relocation....................  A330-53-3112 or A340-53-4124.             109              65           2,850  9,935.
--------------------------------------------------------------------------------------------------------------------------------------------------------

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    Although this is a final rule that was not preceded by notice and 
an opportunity for public comment, we invite you to submit any relevant 
written data, views, or arguments regarding this AD. Send your comments 
to an address listed under ADDRESSES. Include ``Docket No. FAA-2005-
23251; Directorate Identifier 2002-NM-20-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
web site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You can review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you can visit 
http://dms.dot.gov.

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 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 the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); 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. 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 FAA amends Sec.  39.13 by removing amendment 39-11613 (65 FR 
12075, March 8, 2000) and adding the following new airworthiness 
directive (AD):

2005-25-20 Airbus: Amendment 39-14413. Docket No. FAA-2005-23251; 
Directorate Identifier 2002-NM-20-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
29, 2005.

Affected ADs

    (b) This AD supersedes AD 2000-05-04.

Applicability

    (c) This AD applies to the airplanes, certificated in any 
category, listed in Table 1 of this AD.

[[Page 73928]]



                                             Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
                                     Except those modified in accordance with any applicable service information
                                                                    listed below:
                                   ------------------------
              Model--                        Airbus Service Bulletin--                 Or Airbus production
                                                                                          modification--
-----------------------------------
Airbus Model A330-301, -321, -322,  A330-53-3097,          A330-53-3112, dated   46900.
 -323, -341, -342, and -343          Revision 02, dated     February 15, 2001
 airplanes.                          November 21, 2000      (Airbus
                                     (Airbus Modification   Modification 46849).
                                     46025).
Airbus Model A340-211, -212, and -  A340-53-4108,          A340-53-4124, dated   46900.
 213 airplanes, and Airbus Model     Revision 02, dated     February 15, 2001
 A340-311, -312, and -313            December 6, 2000       (Airbus
 airplanes.                          (Airbus Modification   Modification 46849).
                                     46025).
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by the need to change the applicability 
of the existing AD and to mandate the formerly optional terminating 
action. We are issuing this AD to prevent cracking of the fuselage 
skin in the area of the VHF2 antenna, which could result in 
depressurization 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 Requirements of AD 2000-05-04

Detailed Inspection

    (f) At the latest of the times specified in paragraphs (f)(1), 
(f)(2), (f)(3), and (f)(4) of this AD, as applicable: Perform a 
detailed inspection (without removal of the VHF2 antenna) of the 
fuselage skin aft of frame 54, between the airplane centerline and 
stringer 56R in the area of the VHF2 antenna to detect cracks, in 
accordance with Airbus Service Bulletin A330-53-3094, Revision 02, 
dated May 28, 1998, Revision 03, dated February 22, 2001, or 
Revision 04, dated July 23, 2001 (for Model A330 series airplanes); 
or Airbus Service Bulletin A340-53-4105, Revision 02, dated May 25, 
1998, Revision 03, dated February 22, 2001, or Revision 04, dated 
July 23, 2001 (for Model A340 series airplanes). Thereafter, if no 
cracks are detected, repeat the detailed inspection every 36 flight 
hours until accomplishment of the high frequency eddy current (HFEC) 
inspection required by paragraph (g) of this AD.
    (1) Prior to the accumulation of 900 total flight hours.
    (2) Within 1,250 flight hours since accomplishment of the 
interim repair specified by paragraph C.(4) of the Accomplishment 
Instructions of the applicable service bulletin, if the interim 
repair has been accomplished prior to April 12, 2000 (the effective 
date of AD 2000-05-04).
    (3) Within 300 flight hours since the most recent HFEC 
inspection accomplished in accordance with the applicable service 
bulletin, if the most recent HFEC inspection has been accomplished 
prior to April 12, 2000.
    (4) Within 36 flight hours after April 12, 2000.


    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.''

High Frequency Eddy Current Inspection

    (g) Perform an HFEC inspection to detect cracks of the fuselage 
skin aft of frame 54, between the airplane centerline and stringer 
56R in the area of the VHF2 antenna, in accordance with Airbus 
Service Bulletin A330-53-3094, Revision 02, dated May 28, 1998, 
Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 
2001; or Service Bulletin A340-53-4105, Revision 02, dated May 25, 
1998, Revision 03, dated February 22, 2001, or Revision 04, dated 
July 23, 2001; at the applicable time specified by paragraph (g)(1) 
or (g)(2) of this AD. Accomplishment of this inspection terminates 
the requirements of paragraph (f) of this AD.
    (1) For airplanes on which the interim repair specified by 
paragraph C.(4) of the Accomplishment Instructions of the applicable 
service bulletin has not been accomplished before April 12, 2000: 
Prior to the accumulation of 900 total flight hours on the airplane, 
or within 500 flight hours after April 12, 2000, whichever occurs 
later. Thereafter, accomplish the follow-on actions of paragraph (h) 
or (i) of this AD, as applicable.
    (2) For airplanes on which the interim repair specified by 
paragraph C.(4) of the Accomplishment Instructions of the applicable 
service bulletin has been accomplished before April 12, 2000: Within 
1,250 flight hours after accomplishment of the interim repair, or 
within 500 flight hours after April 12, 2000, whichever occurs 
later.

Repetitive Inspections

    (h) If no crack is detected during the HFEC inspection required 
by paragraph (g) of this AD, accomplish the repetitive inspections 
required by paragraph (h)(1) or (h)(2) of this AD, as applicable, 
until the terminating action required by paragraph (k) of this AD 
has been done.
    (1) For airplanes on which the interim repair specified by 
paragraph C.(4) of the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3094, Revision 02, dated May 28, 1998, Revision 03, 
dated February 22, 2001, or Revision 04, dated July 23, 2001; or 
Service Bulletin A340-53-4105, Revision 02, dated May 25, 1998, 
Revision 03, dated February 22, 2001, or Revision 04, dated July 23, 
2001; has not been accomplished before April 12, 2000: Accomplish 
the actions specified by paragraphs (h)(1)(i) and (h)(1)(ii) of this 
AD.
    (i) Repeat the HFEC inspection specified by paragraph (g) at 
intervals not to exceed 500 flight hours.
    (ii) Within 300 flight hours after each HFEC inspection required 
by this AD: Perform a detailed inspection (without removal of the 
VHF2 antenna) of the fuselage skin aft of frame 54, between the 
airplane centerline and stringer 56R in the area of the VHF2 antenna 
to detect cracks, in accordance with the applicable service 
bulletin. Thereafter, if no cracks are detected, repeat the detailed 
inspection at intervals not to exceed 36 flight hours until 
accomplishment of the next HFEC inspection required by paragraph 
(h)(1)(i) of this AD.
    (2) For airplanes on which the interim repair specified by 
paragraph C.(4) of the Accomplishment Instructions of the applicable 
service bulletin has been accomplished before April 12, 2000: Repeat 
the HFEC inspection specified by paragraph (g) of this AD at 
intervals not to exceed 1,250 flight hours.

Corrective Actions

    (i) If any crack is detected during any inspection required by 
paragraph (k), (l), or (m) of this AD, and the interim repair 
specified by paragraph C.(4) of the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 
1998, Revision 03, dated February 22, 2001, or Revision 04, dated 
July 23, 2001; or Service Bulletin A340-53-4105, Revision 02, dated 
May 25, 1998, Revision 03, dated February 22, 2001, or Revision 04, 
dated July 23, 2001; has not been accomplished: Prior to further 
flight, accomplish the actions specified by paragraph (i)(1) or 
(i)(2) of this AD, as applicable.
    (1) If only one crack is detected and that crack is 9.45 inches 
or less, and is within the limits specified by the applicable 
service bulletin: Install the interim repair specified in paragraph 
C.(4) of the Accomplishment Instructions of the applicable service 
bulletin. Thereafter, repeat the HFEC inspection specified by 
paragraph (g) of this AD at intervals not to exceed 1,250 flight

[[Page 73929]]

hours, until the terminating action required by paragraph (k) of 
this AD has been done.


    Note 2: The interim repair referenced by this AD consists of 
cutting out the cracked portion of the fuselage skin, and installing 
a filler plate in the skin cutout, two doublers, and shims, as 
described in paragraph C.(4) of the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 
1998, Revision 03, dated February 22, 2001, or Revision 04, dated 
July 23, 2001 (for Model A330 series airplanes); or Airbus Service 
Bulletin A340-53-4105, Revision 02, dated May 25, 1998, Revision 03, 
dated February 22, 2001, or Revision 04, dated July 23, 2001 (for 
Model A340 series airplanes).


    Note 3: Accomplishment of the interim repair in accordance with 
paragraph 4.3 of Airbus Industrie All Operator Telex (AOT) 53-10, 
dated September 24, 1997, is acceptable for compliance with the 
requirements of paragraph (i)(1) of this AD.


    (2) If any crack is detected that is longer than 9.45 inches, or 
is outside the limits specified by the service bulletin, or if more 
than one crack is detected: Repair in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC) (or its delegated agent).
    (j) If any crack is detected during any inspection required by 
paragraph (f), (g), or (h) of this AD, and the interim repair 
specified by paragraph C.(4) of the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3094, Revision 02, dated May 28, 
1998, Revision 03, dated February 22, 2001, or Revision 04, dated 
July 23, 2001; or Airbus Service Bulletin A340-53-4105, Revision 02, 
dated May 25, 1998, Revision 03, dated February 22, 2001, or 
Revision 04, dated July 23, 2001; has been accomplished: Prior to 
further flight, repair in accordance with a method approved by the 
Manager, International Branch, ANM-116; or the DGAC (or its 
delegated agent).

New Requirements of This AD

Terminating Action

    (k) Within 18 months after the effective date of this AD: Do the 
actions specified in either paragraph (k)(1) or (k)(2). 
Accomplishment of either action terminates the repetitive 
inspections required by paragraphs (f), (g), (h) and (i)(1) of this 
AD.
    (1) Reinforce the fuselage skin between FR54 and FR55 in the 
area of the VHF2 antenna, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3097, Revision 02, 
dated November 21, 2000 (for Model A330 series airplanes); or A340-
53-4108, Revision 02, dated December 6, 2000 (for Model A340 series 
airplanes); as applicable.
    (2) Relocate the VHF2 antenna between stringer 51 and stringer 
52, in accordance with Airbus Service Bulletin A330-53-3112 (for 
Model A330 series airplanes) or A340-53-4124 (for Model A340 series 
airplanes), both dated February 15, 2001; as applicable.
    (l) Work done before the effective date of this AD in accordance 
with an applicable source listed in Table 2 of this AD is acceptable 
for compliance with the corresponding requirements of paragraph (k) 
of this AD.

                                     Table 2.--Credit for Prior Modification
----------------------------------------------------------------------------------------------------------------
              Model                  Service information             Revision                     Date
----------------------------------------------------------------------------------------------------------------
A330-300........................  Airbus Service Bulletin   Original.................  July 29, 1998.
                                   A330-53-3097.
A330-300, A340..................  Airbus production                         (done in production)
                                   Modification 46025.
A340............................  Airbus Service Bulletin   Original.................  July 31, 1998.
                                   A340-53-4108.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance

    (m)(1) In accordance with 14 CFR 39.19, the Manager, 
International Branch, ANM-116, is authorized to approve alternative 
methods of compliance for this AD.
    (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

    (n) The subject of this AD is addressed in French airworthiness 
directives 2001-040(B) and 2001-041(B), both dated January 24, 2001.

Material Incorporated by Reference

    (o) Unless otherwise specified in this AD, the actions must be 
done in accordance with the service information listed in Table 3 of 
this AD, as applicable.

                                  Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus Service Bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A330-53-3094.............................  02..........................  May 28, 1998.
A330-53-3094.............................  03..........................  February 22, 2001.
A330-53-3094.............................  04..........................  July 23, 2001.
A330-53-3097.............................  02..........................  November 21, 2000.
A330-53-3112.............................  Original....................  February 15, 2001.
A340-53-4105.............................  02..........................  May 25, 1998.
A340-53-4105.............................  03..........................  February 22, 2001.
A340-53-4105.............................  04..........................  July 23, 2001.
A340-53-4108.............................  02..........................  December 6, 2000.
A340-53-4124.............................  Original....................  February 15, 2001.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of the service information 
listed in Table 4 of this AD is approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.

                               Table 4.--Material Newly Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus Service Bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A330-53-3094.............................  03..........................  February 22, 2001.
A330-53-3094.............................  04..........................  July 23, 2001.
A330-53-3097.............................  02..........................  November 21, 2000.
A330-53-3112.............................  Original....................  February 15, 2001.

[[Page 73930]]

 
A340-53-4105.............................  03..........................  February 22, 2001.
A340-53-4105.............................  04..........................  July 23, 2001.
A340-53-4108.............................  02..........................  December 6, 2000.
A340-53-4124.............................  Original....................  February 15, 2001.
----------------------------------------------------------------------------------------------------------------

    (2) The incorporation by reference of the service information 
listed in Table 5 of this AD was approved previously by the Director 
of the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 
2000).

         Table 5.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
                                  Revision
    Airbus Service Bulletin        level                 Date
------------------------------------------------------------------------
A330-53-3094..................           02  May 28, 1998.
A340-53-4105..................           02  May 25, 1998.
------------------------------------------------------------------------

    (3) Copies may be obtained from Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or 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 December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23901 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P