[Federal Register Volume 71, Number 58 (Monday, March 27, 2006)]
[Proposed Rules]
[Pages 15068-15073]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-4402]


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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 Series 
Airplanes)

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to certain Airbus Model A300 B2 and A300 B4 
series airplanes, and A300-600 series airplanes. The original NPRM 
would have superseded an existing AD that currently requires repetitive 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. The original NPRM proposed to reduce the 
compliance times for all inspections, and require doing the inspections 
in accordance with new revisions of the service bulletins. The original 
NPRM resulted from new service information that was issued by the 
manufacturer and mandated by the French airworthiness authority. This 
new action revises the original NPRM by proposing new repetitive 
inspections of certain areas of the attachment fittings that were 
repaired in accordance with the actions specified in both the existing 
AD and the original NPRM. We are proposing this supplemental NPRM 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 supplemental NPRM by April 21, 
2006.

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 Model A300 B2 and A300 B4 series airplanes, contact Jacques 
Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for 
service information identified in this proposed AD. For Model A300 600 
series airplanes, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, for service information identified in this 
proposed AD.

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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``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 this 
supplemental NPRM. We will consider all comments received by the 
closing date and may amend this supplemental NPRM in light of those 
comments.
    We will post all comments submitted, 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 
that 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 may 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.

Examining the Docket

    You may 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 ADDRESSES. Comments will be available in the 
AD docket shortly after the Docket Management System receives them.

Discussion

    We proposed to amend part 39 of the Federal Aviation Regulations 
(14 CFR part 39) with a notice of proposed rulemaking (the original 
NPRM) for an AD for certain Airbus Model A300 B2 and A300 B4 series 
airplanes; and Model A300-600 series airplanes. The original NPRM 
proposed to supersede AD 2000-05-07, amendment 39-11616 (65 FR 12077, 
March 8, 2000), which applies to certain Airbus Model A300 and A300-600 
series airplanes. The original NPRM was published in the Federal 
Register on September 7, 2004 (69 FR 54063). The original NPRM proposed 
to reduce the compliance times for all inspections required by AD 2000-
05-07, and to require inspections in accordance with new revisions of 
the service bulletins. The original NPRM resulted from new service 
information that was issued by the manufacturer and mandated by the 
French airworthiness authority. We proposed the original NPRM to 
prevent fatigue cracking of the main landing gear (MLG) attachment 
fittings, which could result in reduced structural integrity of the 
airplane.

[[Page 15069]]

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, we have received reports of 
cracks on airplanes that were modified in accordance with Airbus 
Service Bulletin A300-57-0235, Revisions 01 through 05; and Airbus 
Service Bulletin A300-57-6088, Revisions 01 through 04. These service 
bulletins were cited in both the original NPRM and in AD 2000-05-07 as 
the appropriate sources of service information for modifying Gear Rib 5 
of the MLG attachment fittings at the lower flange. The manufacturer 
has indicated that the reported cracks may have existed previously, but 
were probably missed during the installation of the modification 
because of improper inspection during installation, or because not 
enough material was removed during the spotfacing operation. The 
manufacturer has now issued two new service bulletins, described below, 
which provide procedures for inspecting the modified airplanes to 
ensure that the inspection area is crack-free.

Relevant Service Information

    Airbus has issued the service bulletins identified in the following 
table.

                      New Airbus Service Bulletins
------------------------------------------------------------------------
                                    Airbus service
             Model                     bulletin               Date
------------------------------------------------------------------------
A300-600......................  A300-57A6101,           May 20, 2005.
                                 including Appendix 01.
A300 B2 and A300 B4...........  A300-57A0246,           May 20, 2005.
                                 including Appendix 01.
------------------------------------------------------------------------

    The service bulletins describe procedures for doing repetitive 
detailed visual inspections for cracks of the bottom flange and the 
vertical web in the area between the wing rear spar/gear rib 5 
attachment, and the forward reaction-rod pickup lug. On the inboard 
side, this inspection includes inspecting for cracks of the areas 
around all fasteners, particularly at holes 47 and 54. On the outboard 
side, this inspection includes inspecting for cracks of the lower 
flange, the vertical web, and the areas around all fasteners. If any 
crack is found during this inspection, the service bulletins specify 
that operators should measure the length of the crack and contact the 
manufacturer for repair instructions.
    If no crack is found during the detailed visual inspection, the 
service bulletins provide procedures for related investigative and 
corrective actions. The related investigative action is doing a high-
frequency eddy current inspection for cracks of holes 47 and 54. If any 
crack is found, the corrective action is to contact the manufacturer 
for repair instructions. If no crack is found, the corrective action is 
to install new nuts at holes 47 and 54.
    The service bulletins also give instructions for reporting all 
inspection findings, including nil findings, to the manufacturer. The 
service bulletins specify that the detailed visual inspection is to be 
repeated at intervals not to exceed 700 flight cycles. If no crack is 
found during the inspection performed at or above 2,100 flight cycles 
after modifying Gear Rib 5 of the MLG attachment fittings at the lower 
flange, the service bulletins specify that no further action is 
necessary.
    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, mandated the service 
information and issued French airworthiness directive F-2005-113 R1, 
dated July 20, 2005, to ensure the continued airworthiness of these 
airplanes in France.

Comments

    We have considered the following comments on the original NPRM.

Support for the Proposed AD

    One commenter supports the original NPRM as proposed.

Request To Extend Compliance Time for Modification

    One commenter requests that the compliance time for the proposed 
modification of Gear Rib 5 of the MLG attachment fittings be extended 
from 15 months to 30 months. The commenter states that the request to 
extend the compliance time is justified because the repetitive interval 
has been shortened to 700 flight cycles. According to the commenter, 
the manner in which this crack is expected to grow means that it will 
not reach an un-repairable length during the inspection interval. 
Therefore, the operator states that the time needed to complete the 
modification should be extended to 30 months to fit the heavy 
maintenance schedule for all operators. The commenter considers that 
the adoption of the proposed compliance time of 15 months would require 
operators to schedule special visits to do the repair, at additional 
expense and downtime.
    We do not agree with the commenter's request to extend the 
compliance time from 15 months to 30 months. In developing an 
appropriate compliance time for this action, we considered the urgency 
associated with the subject unsafe condition, and the practical aspect 
of accomplishing the required modification within a period of time that 
corresponds to the normal scheduled maintenance for most affected 
operators. In addition, because operators' schedules vary 
substantially, we cannot accommodate every operator's optimal 
scheduling in each AD. However, according to the provisions of 
paragraph (p) of this supplemental NPRM, we may approve requests to 
adjust the compliance time if the request includes data that prove that 
the new compliance time would provide an acceptable level of safety.
    In addition, based on further evaluation of French airworthiness 
directive 2003-318(B), dated August 20, 2003, we have extended the 
compliance time for the proposed modification of Gear Rib 5 of the MLG 
attachment fittings from 15 months to 16 months. This compliance time 
parallels the compliance time in the French airworthiness directive.

Request To Revise Cost Estimate

    The commenter requests that we revise the cost estimate to between 
82 and 100 work hours for the modification of gear rib 5. The commenter 
states that Airbus Service Bulletin A300-57-6088, Revision 04, dated 
December 3, 2003, includes an estimate of 82 work hours to do this 
modification. The commenter also states that, in its experience, this 
modification takes approximately 100 work hours, depending on the 
difficulty in removing the fasteners. The commenter further states that 
the need to do the modification during special visits will increase the 
cost to operators.
    We partially agree with the commenter's request. After further 
analysis of the service information, we agree that the work hours to do 
the modification as provided in Airbus Service Bulletin A300-57-6088, 
Revision 04, are higher than the work hours in the original NPRM. The 
cost information, below, has been revised to

[[Page 15070]]

indicate this higher amount. We disagree with the request to revise the 
work hours to between 82 and 100 work hours. We consider in our cost 
estimates only the time necessary to perform the specific actions 
actually required by the AD. These figures typically do not include 
incidental costs, such as the time required to gain access and close 
up, planning time, or time necessitated by other administrative 
actions. We have made no further change to this supplemental NPRM 
regarding this issue.

Explanation of Change in Applicability

    We have revised the applicability to identify model designations as 
published in the most recent type certificate data sheet for the 
affected models.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Explanation of Change to Service Bulletin Reference

    We have revised the applicability to correct a reference to Airbus 
Service Bulletin A300-57A6087. This service bulletin was inadvertently 
referred to in the original NPRM as Airbus Service Bulletin A300-
75A6087.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    The changes discussed above expand the scope of the original NPRM; 
therefore, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for public comment on 
this supplemental NPRM.

Difference Between the Supplemental NPRM and Airbus Service Bulletins 
A300-57A0246 and A300-57A6101

    Airbus Service Bulletins A300-57A0246 and A300-57A6101 specify to 
contact the manufacturer for instructions on how to repair certain 
conditions, but this proposed AD would require repairing those 
conditions using a method that we or the DGAC (or its delegated agent) 
approve. In light of the type of repair that would be required to 
address the unsafe condition, and consistent with existing bilateral 
airworthiness agreements, we have determined that, for this proposed 
AD, a repair we or the DGAC approve would be acceptable for compliance 
with this proposed AD.

Clarification of Inspection Terminology

    In this supplemental NPRM, the ``detailed visual inspection'' 
specified in the Airbus service bulletins and in the French 
airworthiness directives, is referred to as a ``detailed inspection.'' 
We have included the definition for a detailed inspection in a note in 
the supplemental NPRM.

Explanation of Reporting Requirement

    This proposed AD also specifies that operators report to the 
manufacturer any positive findings of cracks during the post-
modification inspections. These inspection reports will help determine 
the extent of the cracking in the affected fleet. Based on the results 
of these reports, we may determine that further corrective action is 
warranted.

Costs of Compliance

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                            Number of U.S.-
                  Action                      Work hours     Average labor       Parts         Cost per       registered             Fleet cost
                                                             rate per hour                     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000-05-07)..              70             $65         $10,270         $14,820             164  $2,430,480
Pre-modification inspections (new proposed               6              65            None             390             164  $63,960, per inspection
 action), per inspection cycle.                                                                                              cycle.
Post-modification inspections (new                       2              65            None             130             164  $21,320, per inspection
 proposed action), per inspection cycle.                                                                                     cycle.
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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 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 supplemental NPRM 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, Safety.

[[Page 15071]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

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

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 21, 
2006.

Affected ADs

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

Applicability

    (c) This AD applies to Model A300 B2-1A, B2-1C, B2K-3C, B2-203, 
B4-2C, B4-103, and B4-203 airplanes, as identified in Airbus Service 
Bulletin A300-57A0234, Revision 05, dated February 19, 2002; and 
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-
605R, F4-622R, and C4-605R Varian F airplanes, as identified in 
Airbus Service Bulletin A300-57A6087, 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), 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
----------------------------------------------------------------------------------------------------------------
                Model                  Airbus service bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,   A300-57-6087...........  01.....................  March 11, 1998.
 B4-605R, B4-622R, F4-605R, F4-622R,
 and A300 C4-605R Variant F airplanes.
A300 B2 and A300 B4 series airplanes.  A300-57-0234...........  01.....................  March 11, 1998.
----------------------------------------------------------------------------------------------------------------


                                Table 2.--further revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                Model                  Airbus service bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,   A300-57A6087...........  02, including Appendix   June 24, 1999.
 B4-605R, B4-622R, F4-605R, F4-622R,                             01.                     May 19, 2000.
 and A300 C4-605R Variant F airplanes.                          03, including Appendix   February 19, 2002.
                                                                 01.
                                                                04, including Appendix
                                                                 01.
A300 B2 and A300 B4 series airplanes.  A300-57A0234...........  02, including Appendix   June 24, 1999.
                                                                 01.
                                                                03, including Appendix   September 2, 1999.
                                                                 01.
                                                                04, including Appendix   May 19, 2000.
                                                                 01.
                                                                05, including Appendix   February 19, 2002.
                                                                 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 5, 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 Accomplishment Instructions of 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, Transport Airplane Directorate, FAA, or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (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 Accomplishment Instructions of the applicable service 
bulletin in Table 3 of this AD. After the effective date of this AD, 
only Revision 04 of Airbus

[[Page 15072]]

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 paragraphs (f) and (i) of this AD.

                            Table 3.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                Model                  Airbus service bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,   A300-57-6088...........  01, including Appendix   February 1, 1999.
 B4-605R, B4-622R, F4-605R, F4-622R,                             01.                     September 5, 2002.
 and A300 C4-605R Variant F airplanes.                          02.....................  December 3, 2003.
                                                                04.....................
A300 B2 and A300 B4..................  A300-57-0235...........  01, including Appendix   February, 1, 1999.
                                                                 01.
                                                                03.....................  September 5, 2002.
                                                                04.....................  March 13, 2003.
                                                                05.....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------


    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 5, 1998; as applicable; is 
acceptable for compliance with the requirements of that paragraph.

New Requirements of This AD

New Repetitive Inspections

    (i) For airplanes on which the modification specified in 
paragraph (h) or (k) of this AD has not been done as of the 
effective date of this AD, perform a detailed and an HFEC inspection 
to detect cracks of the lower flange of Gear Rib 5 of the MLG at 
holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the 
applicable service bulletin listed 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                  Airbus service bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,   A300-57A6087...........  04, including Appendix   February 19, 2002.
 B4-605R, B4-622R, F4-605R, F4-622R,                             01.
 and C4-605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- A300-57A0234...........  05, including Appendix   February 19, 2002.
 2C, B4-103, and B4-203 airplanes.                               01.
----------------------------------------------------------------------------------------------------------------

    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes; A300 B4-600, B4-600R, and F4-600R series 
airplanes; and Model C4-605R Variant F airplanes 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 B2-1A, B2-1C, B2K-3C, and B2-203 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 B4-2C, B4-103, and B4-203 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 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes that have 
accumulated less than 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.

Crack 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 Model A300 B2-1A, B2-1C, 
B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-
57A6087, Revision 04, including Appendix 01, dated February 19, 2002 
(for Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R airplanes); 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 before 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 5 of this AD. This 
action terminates the repetitive inspections requirements of 
paragraphs (f) and (i) 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 16 months after the effective date of this AD.

[[Page 15073]]



                            Table 5.--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                Model                  Airbus service bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,   A300-57-6088...........  04.....................  December 3, 2003.
 B4-605R, B4-622R, F4-605R, F4-622R,
 and C4-605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- A300-57-0235...........  04.....................  March 13, 2003.
 2C, B4-103, and B4-203 airplanes.                              05.....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------

    (l) Where the applicable service bulletin in paragraph (k) of 
this AD specifies to contact Airbus for modification instructions; 
or if there is a previously installed repair at any of the affected 
fastener holes; or if a crack is found when accomplishing the 
modification: 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).

Post-Modification Inspections

    (m) Within 700 flight cycles after doing the modification in 
accordance with paragraph (h), (k), or (l) of this AD, or within 6 
months after the effective date of this AD, whichever occurs later, 
except as provided by paragraph (o) of this AD: Do a detailed and an 
HFEC inspection for cracks at holes 47 and 54 in the lower flange of 
Gear Rib 5, and do all related investigative and corrective actions 
before further flight by doing all the actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-57A0246, 
including Appendix 01, dated May 20, 2005; or Airbus Service 
Bulletin A300-57A6101, including Appendix 01, dated May 20, 2005; as 
applicable. Where the applicable service bulletin specifies to 
contact Airbus for repair 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). 
Repeat the inspection and related investigative and corrective 
actions thereafter at intervals not to exceed 700 flight cycles. If 
no crack is detected during the repeat inspection performed at or 
above 2,100 flight cycles after doing the modification in accordance 
with paragraph (h), (k), or (l) of this AD, then no further 
inspection is required. Except, at least one inspection is required 
after the accumulation of 2,100 flight cycles after installing the 
modification in accordance with paragraph (h) or (k) of this AD.

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 6 of this AD, are 
considered acceptable for compliance with the corresponding action 
specified in this AD.

             Table 6.--Previous Issues of Service Bulletins
------------------------------------------------------------------------
   Airbus service bulletin       Revision level             Date
------------------------------------------------------------------------
A300-57-0235................  02, including         September 27, 1999.
                               Appendix 01.
                              03..................  September 5, 2002.
A300-57-6088................  02..................  September 5, 2000.
                              03..................  March 13, 2003.
------------------------------------------------------------------------

Reporting

    (o)(1) Although Airbus Service Bulletins A300-57A0234, A300-57-
0235, A300-57A6087, A300-57-6088, A300-57A0246, and A300-57A6101, 
specify to submit certain information to the manufacturer, this AD 
does not include such a requirement, except as provided by paragraph 
(o)(2) of this AD.
    (2) Where Airbus Service Bulletins A300-57A0246 and A300-
57A6101, both dated May 20, 2005, specify to submit a report of 
positive and negative findings of the post-modification inspection 
required by paragraph (m) of this AD, within 30 days after the 
effective date of this AD, submit a report only of the positive 
findings of post-modification inspections to Airbus, Customer 
Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. The report must include the inspection results, a 
description of any discrepancies found, the airplane serial number, 
and the number of landings and flight hours on the airplane. Under 
the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 
3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance (AMOCs)

    (p)(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 Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs, approved previously per AD 2000-05-07, are approved 
as AMOCs with this AD.

Related Information

    (q) French airworthiness directives 2003-318(B), dated August 
20, 2003; and F-2005-113 R1, dated July 20, 2005; also address the 
subject of this AD.

    Issued in Renton, Washington, on March 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-4402 Filed 3-24-06; 8:45 am]
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