[Federal Register Volume 69, Number 172 (Tuesday, September 7, 2004)]
[Proposed Rules]
[Pages 54063-54067]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20211]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-27-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and 
Model C4-605R Variant F Airplanes (Collectively Called A300-600)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for certain Airbus Model A300 B2 and A300 B4 series 
airplanes; A300 B4-600, B4-600R, and F4-600R series airplanes; and 
Model C4-605R Variant F airplanes (collectively called A300-600). That 
AD currently requires repetitive inspections to detect cracks in Gear 
Rib 5 of the main landing gear (MLG) attachment fittings at the lower 
flange, and repair, if necessary. That AD also requires modification of 
Gear Rib 5 of the MLG attachment fittings, which constitutes 
terminating action for the repetitive inspections. This proposed AD 
would reduce the compliance times for all inspections, and require that 
you do the inspections in accordance with new revisions of the service 
bulletins. This proposed AD is prompted by new service information that 
was issued by the manufacturer and mandated by the French airworthiness 
authority. We are proposing this AD to prevent fatigue cracking of the 
MLG attachment fittings, which could result in reduced structural 
integrity of the airplane.

DATES: We must receive comments on this proposed AD by October 7, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed 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 the service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    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.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-19002; 
Directorate Identifier 2003-NM-27-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed 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 proposed 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 
may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You can examine the AD docket 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.

Discussion

    On February 29, 2000, we issued AD 2000-05-07, amendment 39-11616 
(65 FR 12077, March 8, 2000), for certain Airbus Model A300 and A300-
600 series airplanes. That AD requires repetitive inspections to detect 
cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings 
at the lower flange, and repair, if necessary. That AD also requires 
modification of Gear Rib 5 of the MLG attachment fittings, which 
constitutes terminating action for the repetitive inspections. That AD 
was

[[Page 54064]]

prompted by issuance of mandatory continuing airworthiness information 
by the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France. We issued that AD to 
prevent fatigue cracking of the MLG attachment fittings, which could 
result in reduced structural integrity of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-05-07, Airbus has new service information, 
which the DGAC mandated at reduced compliance times for all 
inspections.

Relevant Service Information

    Airbus has issued the following service bulletins:
     Airbus Service Bulletin A300-57-6087, Revision 04, dated 
February 19, 2002; and Airbus Service Bulletin A300-57-0234, Revision 
05, dated February 19, 2002. The procedures in these revisions are 
essentially the same as those in previous revisions of the service 
bulletin, which were referenced in the AD 2000-05-07 for accomplishment 
of the inspections. However, these new revisions change the compliance 
thresholds and inspection intervals. These revisions also contain 
certain corrections of airplane effectivity.
     Airbus Service Bulletin A300-57-6088, Revision 03, dated 
March 18, 2003; and Airbus Service Bulletin A300-57-0235, Revision 05, 
dated December 3, 2003. The procedures in these revisions are 
essentially the same as those in the previous revisions of the service 
bulletins, which were referenced in the existing AD for accomplishment 
of the modifications. These new revisions of the service bulletins add 
a statement for operators who require assistance with installing 
certain fasteners.
    We have determined that accomplishment of the actions specified in 
the service information will adequately address the unsafe condition. 
The DGAC mandated the service information and issued French 
airworthiness directive 2003-318(B), dated August 30, 2003, to ensure 
the continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed 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. Pursuant 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 AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would supersede AD 2000-
05-07 to continue to require repetitive inspections to detect cracks in 
Gear Rib 5 of the MLG attachment fittings at the lower flange, and 
repair, if necessary; and to continue to require modification of Gear 
Rib 5 of the MLG attachment fittings, which constitutes terminating 
action for the repetitive inspections. This proposed AD would also 
reduce the compliance threshold and repetitive intervals for the 
inspections in the same area. The proposed AD would require you to use 
the service information described previously to perform these actions, 
except as discussed under ``Difference Between the Proposed AD and the 
French Airworthiness Directive,'' and ``Differences Between the 
Proposed AD and the Service Information.''

Difference Between the Proposed AD and the French Airworthiness 
Directive

    The applicability of French airworthiness directive 2003-318(B) 
excludes airplanes that accomplished Airbus Service Bulletin A300-57-
0235 or Airbus Service Bulletin A300-57-6088 in service. However, we 
have not excluded those airplanes in the applicability of this proposed 
AD; rather, this proposed AD includes a requirement to accomplish the 
actions specified in those service bulletins. Such a requirement would 
ensure that the actions specified in the service bulletin and required 
by this proposed AD are accomplished on all affected airplanes. 
Operators must continue to operate the airplane in the configuration 
required by this proposed AD unless an alternative method of compliance 
is approved.

Differences Between the Proposed AD and the Service Information

    Although Airbus Service Bulletin A300-57-6088, Revision 03, 
specifies that the manufacturer may be contacted for disposition of 
certain repairs, this proposed AD would require the repair of those 
conditions to be accomplished in accordance with a method approved 
either by us or by the DGAC (or its delegated agent). In light of the 
type of repair that would be required to address the identified unsafe 
condition, and in consonance with existing bilateral airworthiness 
agreements, we have determined that a repair approved by either us or 
the DGAC (or its delegated agent) would be acceptable for compliance 
with this proposed AD.
    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletins describe procedures 
for submitting certain information to the manufacturer, this proposed 
AD would not require those actions.

Clarification of Inspection Thresholds

    The French airworthiness directive gives repetitive inspection 
thresholds based on the original issue date of that airworthiness 
directive. Due to some procedural differences in the way we express 
compliance times, the thresholds in paragraph (i) of this proposed AD 
are presented in a manner that differs from those in the French 
airworthiness directive. However, the compliance times capture the 
intent of the French airworthiness directive, and ensure that operators 
of all affected airplanes are given sufficient time to accomplish the 
inspections while still ensuring continued operational safety.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 2000-05-07. 
Since AD 2000-05-07 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD as listed in the 
following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2000-05-07             in this  proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
paragraph (e).............................  paragraph (p).
------------------------------------------------------------------------

    We have changed all references to a ``detailed visual inspection'' 
in the existing AD to ``detailed inspection'' in this action.
    We have revised the applicability of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.
    In addition, we have reformatted the existing requirements in 
paragraph (f) of this proposed AD (paragraph (a) of AD 2000-05-07) to 
list service bulletin references in two tables. We included the tables 
for clarity because we added several service bulletin revisions to this 
paragraph.

[[Page 54065]]

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                         Number of
                                                   Average                   Cost per      U.S.-
              Action                 Work hours   labor rate     Parts       airplane    registered   Fleet cost
                                                   per hour                              airplanes
----------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000-           62          $65      $10,270      $14,300          164   $2,345,200
 05-07)...........................
Inspections (new proposed action).            6           65         None          390          164       63,960
----------------------------------------------------------------------------------------------------------------

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing amendment 39-11616 (65 FR 
12077, March 8, 2000) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-
27-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by October 7, 2004.

Affected ADs

    (b) This AD supersedes AD 2000-05-07, amendment 39-11616.

Applicability

    (c) This AD applies to Model A300 B2 and A300 B4 series 
airplanes, as listed in Airbus Service Bulletin A300-57A0234, 
Revision 05, dated February 19, 2002; and Model A300 B4-600, B4-
600R, and F4-600R series airplanes, and Model C4-605R Variant F 
airplanes (collectively called A300-600), as listed in Airbus 
Service Bulletin A300-75A6087, Revision 04, dated February 19, 2002; 
except airplanes on which Airbus Modification 11912 or 11932 has 
been installed; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by new service information that was 
issued by the manufacturer and mandated by the French airworthiness 
authority. We are issuing this AD to prevent fatigue cracking of the 
main landing gear (MLG) attachment fittings, which could result in 
reduced structural integrity 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 the Requirements of AD 2000-05-07

Repetitive Inspections

    (f) Perform a detailed inspection and a high frequency eddy 
current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG 
attachment fittings at the lower flange, in accordance with the 
Accomplishment Instructions of any applicable service bulletin 
listed in Table 1 and Table 2 of this AD, at the time specified in 
paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the 
effective date of AD 2000-05-07, amendment 39-11616), only the 
service bulletins listed in Table 2 of this AD may be used. Repeat 
the inspections thereafter at intervals not to exceed 1,500 flight 
cycles, until paragraph (h), (i), or (k) of this AD is accomplished.

                                   Table 1.--Revision 01 of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                                                     Revision
                 Model                       Service bulletin         level                   Date
----------------------------------------------------------------------------------------------------------------
A300-600..............................  A300-57-6087.............           01  March 11, 1998.
A300 B2 and A300 B4...................  A300-57-0234.............           01  March 11, 1998.
----------------------------------------------------------------------------------------------------------------


                                Table 2.--Further Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
               Model                   Service bulletin       Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300-600..........................  A300-57A6087.........  02, including         June 24, 1999.
                                                            Appendix 01.         May 19, 2000.
                                                           03, including         February 19, 2002.
                                                            Appendix 01.
                                                           04, including
                                                            Appendix 01.

[[Page 54066]]

 
A300 B2 and A300 B4...............  A300-57A0234.........  02..................  June 24, 1999.
                                                           03, including         September 2, 1999.
                                                            Appendix 01.         May 19, 2000.
                                                           04, including         February 19, 2002.
                                                            Appendix 01.
                                                           05, including
                                                            Appendix 01.
----------------------------------------------------------------------------------------------------------------

    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, amendment 39-10298): Inspect within 500 flight cycles after 
March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of March 9, 1998: Inspect prior to the accumulation 
of 18,000 total flight cycles, or within 1,500 flight cycles after 
March 9, 1998, whichever occurs later.

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


    Note 2: Accomplishment of the initial detailed and HFEC 
inspections in accordance with Airbus Service Bulletin A300-57A0234 
or A300-57A6087, both dated August 1, 1997, as applicable, is 
considered acceptable for compliance with the initial inspections 
required by paragraph (f) of this AD.

Repair

    (g) If any crack is detected during any inspection required by 
paragraph (f) of this AD, prior to further flight, accomplish the 
requirements of paragraphs (g)(1) or (g)(2) of this AD, as 
applicable.
    (1) If a crack is detected at one hole only, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with the applicable service bulletin in Table 2 of this AD.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its 
delegated agent).

Terminating Modification

    (h) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib 
5 of the MLG attachment fittings at the lower flange in accordance 
with the applicable service bulletin in Table 3 of this AD. After 
the effective date of this AD, only Revision 04 of Airbus Service 
Bulletin A300-57-6088, and Revisions 04 and 05 of Airbus Service 
Bulletin A300-57-0235 may be used. Accomplishment of this 
modification constitutes terminating action for the repetitive 
inspection requirements of this AD.

                            Table 3.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
               Model                   Service bulletin       Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300-600..........................  A300-57-6088.........  01, including         February 1, 1999.
                                                            Appendix 01.         December 3, 2003.
                                                           04..................
A300 B2 and A300 B4...............  A300-57-0235.........  01, including         February, 1, 1999.
                                                            Appendix 01.         March 13, 2003.
                                                           04..................  December 3, 2003.
                                                           05..................
----------------------------------------------------------------------------------------------------------------


    Note 3: Accomplishment of the modification required by paragraph 
(h) of this AD prior to April 12, 2000 (the effective date of AD 
2000-05-07), in accordance with Airbus Service Bulletin A300-57-6088 
or A300-57-0235, both dated August 1, 1998; as applicable; is 
acceptable for compliance with the requirements of that paragraph.

New Requirements of This AD

Repetitive Inspections

    (i) For airplanes on which the modification specified in 
paragraph (h) of this AD has not been done as of the effective date 
of this AD, perform a detailed and a HFEC inspection to detect 
cracks in Gear Rib 5 of the MLG attachment fittings at the lower 
flange, in accordance with the applicable service bulletin in Table 
4 of this AD. Perform the inspections at the applicable time 
specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD. 
Repeat the inspections thereafter at intervals not to exceed 700 
flight cycles until the terminating modification required by 
paragraph (k) of this AD is accomplished. Accomplishment of the 
inspections per paragraph (i) of this AD, terminates the inspection 
requirements of paragraph (f) of this AD.

                             Table 4.--Service Bulletins for Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
               Model                   Service bulletin       Revision level                   Date
----------------------------------------------------------------------------------------------------------------
A300-600..........................  A300-57-6087.........  04, including         February 19, 2002.
                                                            Appendix 01.
A300 B2 and A300 B4...............  A300-57-0234.........  05, including         February 19, 2002.
                                                            Appendix 01.
----------------------------------------------------------------------------------------------------------------

    (1) For Models A300 B2 and A300 B4 series airplanes; A300 B4-
600, B4-600R, and F4-600R series airplanes; and Model C4-605R 
Variant F airplanes (collectively called A300-600) that have 
accumulated 18,000 or more total flight cycles as of the effective 
date of this AD: Within 700 flight cycles after the effective date 
of this AD.
    (2) For Model A300 B2 series airplanes that have accumulated 
less than 18,000 total flight cycles as of the effective date of 
this AD: Prior to the accumulation of 18,000 total flight cycles, or 
within 700 flight cycles after the effective date of this AD, 
whichever occurs later.
    (3) For Model A300 B4 series airplanes that have accumulated 
less than 18,000 total flight cycles as of the effective date of 
this AD: Prior to the accumulation of 14,500 total flight cycles, or 
within 700 flight cycles after the effective date of this AD, 
whichever occurs later.
    (4) For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes; and Model C4-605R Variant F airplanes (collectively 
called A300-600) that have accumulated less than

[[Page 54067]]

18,000 total flight cycles as of the effective date of this AD: 
Prior to the accumulation of 11,600 total flight cycles, or within 
700 flight cycles after the effective date of this AD, whichever 
occurs later.

Repair

    (j) If any crack is detected during any inspection required by 
paragraph (i) of this AD, prior to further flight, accomplish the 
requirements of paragraph (j)(1) and (j)(2) of this AD, as 
applicable.
    (1) If a crack is detected at only one hole, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with Airbus Service Bulletin A300-57A0234, Revision 05, including 
Appendix 01, dated February 19, 2002 (for Models A300 B2 and A300 
B4); or A300-57A6087, Revision 04, including Appendix 01, dated 
February 19, 2002 (for Models A300-600); as applicable.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, or the DGAC (or its delegated agent).

Terminating Modification

    (k) For airplanes on which the terminating modification in 
paragraph (h) of this AD has not been accomplished as of the 
effective date of this AD: At the earlier of the times specified in 
paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the 
MLG attachment fittings at the lower flange. Except as provided by 
paragraph letter (l) of this AD, do the modification in accordance 
with the applicable service bulletin in Table 3 of this AD.
    (1) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999, whichever is later.
    (2) Within 15 months after the effective date of this AD.
    (l) Where the applicable service bulletin in paragraph (k) of 
this AD specifies to contact Airbus for modification instructions: 
Prior to further flight, modify in accordance with a method approved 
by the Manager, International Branch, ANM-116, or the DGAC (or its 
delegated agent).
    (m) For airplanes that were modified prior to the effective date 
of this AD in accordance with paragraph (h) of this AD, and on which 
repairs were made prior to the effective date of this AD per 
paragraph (g) of this AD, or on which cracks were found during the 
accomplishment of paragraph (h) of this AD: Within 15 months after 
the effective date of this AD, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116, or the DGAC 
(or its delegated agent).

Actions Accomplished Per Previous Issues of the Service Bulletins

    (n) Actions accomplished before the effective date of this AD 
per the service bulletins listed in Table 5 of this AD, are 
considered acceptable for compliance with the corresponding action 
specified in this AD.

                                 Table 5.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
         Airbus service bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A300-57-0235.............................  02..........................  September 27, 1999.
                                           03, including Appendix 01...  September 5, 2002.
A300-57A6087.............................  Original Issue..............  August 1, 1997.
A300-57-6088.............................  02..........................  September 5, 2000.
                                           03..........................  March 13, 2003.
----------------------------------------------------------------------------------------------------------------

No Reporting Requirements

    (o) Although the service bulletins A300-57A0234, A30057-0235, 
A300-57A6087, and A300-57-6088 specify to submit certain information 
to the manufacturer, this AD does not include such a requirement.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, International Branch, ANM-116, FAA, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Alternative methods of compliance, approved previously per 
AD 2000-05-07, amendment 39-11616, are approved as alternative 
methods of compliance with this AD.

Related Information

    (q) French airworthiness directive 2003-318(B), dated August 20, 
2003, also addresses the subject of this AD.

    Issued in Renton, Washington, on August 26, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-20211 Filed 9-3-04; 8:45 am]
BILLING CODE 4910-13-P