[Federal Register Volume 71, Number 17 (Thursday, January 26, 2006)]
[Proposed Rules]
[Pages 4313-4317]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-972]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 17 / Thursday, January 26, 2006 / 
Proposed Rules  

[[Page 4313]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; and Model 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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede two existing airworthiness 
directives (AD) that apply to certain Airbus Model A300 B2, A300 B4, 
and A300-600 series airplanes. One AD currently requires an inspection 
for cracks of the lower outboard flange of gantry No. 4 in the main 
landing gear (MLG) bay area, and repair if necessary. The other AD 
currently requires, among other actions, repetitive inspections of the 
gantry lower flanges, and repair if necessary. The proposed AD also 
would require new repetitive inspections for cracks in the lower flange 
of certain gantries, and repair if necessary, which would end the 
existing inspection requirements. The proposed AD also would provide 
for optional terminating actions for the new repetitive inspections. 
This proposed AD results from a report of a large fatigue crack along 
the outboard flange of beam No. 4 and a subsequent determination that 
existing inspections are inadequate. We are proposing this AD to detect 
and correct fatigue cracks in the lower flanges of gantries 1 through 5 
inclusive in the MLG bay area, which could result in reduced structural 
integrity of the fuselage, and consequent rapid decompression of the 
airplane.

DATES: We must receive comments on this proposed AD by February 27, 
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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-23690; Directorate Identifier 2004-NM-133-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 
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 the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On December 23, 2003, we issued AD 2003-26-10, amendment 39-13408 
(69 FR 867, January 7, 2004), for certain Airbus Model A300 B2 and B4 
series airplanes, and Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively called 
A300-600 series airplanes). That AD requires a one-time inspection for 
cracking of the lower outboard flange of gantry No. 4 in the main 
landing gear (MLG) bay area, and repair if necessary. That AD resulted 
from a report of cracks found on the lower outboard flange of gantry 
No. 4 in the MLG bay area. We issued that AD to find and fix cracking 
of the lower outboard flange of gantry No. 4, which could result in 
reduced structural integrity of the fuselage, and consequent rapid 
decompression of the airplane.
    On August 31, 2004, we issued AD 2004-18-13, amendment 39-13792 (69 
FR 55329, September 14, 2004), for certain Airbus Model A300 B2 and B4 
series airplanes, and Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622R, C4-605R Variant F, and F4-605R airplanes. For certain airplanes, 
that AD requires a one-time inspection for cracking of the gantry lower 
flanges, and repair if necessary. That AD also requires repetitive 
inspections of the gantry lower flanges; repair if necessary; and 
reinforcement of the left-hand and right-hand gantry. That AD resulted 
from the issuance of mandatory

[[Page 4314]]

continuing airworthiness information by a foreign civil airworthiness 
authority. We issued that AD to detect and correct cracking of the 
gantry lower flanges in the MLG bay area, which could result in 
decompression of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-18-13, we have received a report that, 
during an inspection required by that AD, a large fatigue crack running 
along the outboard flange of beam No. 4 was found. The report also 
indicates that the inspection requirements of ADs 2004-18-13 and 2003-
26-10 do not adequately detect cracks in the lower flange of the left 
and right gantries 1 through 5 inclusive in the MLG bay area. Such 
cracks, if not detected and corrected, could result in reduced 
structural integrity of the fuselage, and consequent rapid 
decompression of the airplane.

Relevant Service Information

    Airbus has issued Revision 01 of Service Bulletins A300-53-0379 
(for Model A300 B2 and B4 series airplanes) and A300-53-6152 (for Model 
A300-600 series airplanes), both dated October 4, 2005. The service 
bulletins describe procedures for doing repetitive ultrasonic 
inspections or high frequency eddy current inspections, including 
rework of the pressure diaphragm, for cracks in the lower flange of the 
left and right gantries 1 through 5 inclusive between FR47 and FR54; 
and repairing any crack. The threshold for the compliance time ranges 
between 1,950 and 54,000 total flight cycles depending on the airplane 
configuration; the grace period is 1,500 flight cycles.
    Accomplishing the actions specified in the service information 
described previously is intended to adequately address the unsafe 
condition. The DGAC mandated that service information and issued French 
airworthiness directive F-2005-091 R1, September 28, 2005, to ensure 
the continued airworthiness of these airplanes in France. The DGAC also 
approved the following service information as optional terminating 
actions for the repetitive ultrasonic and high frequency eddy current 
inspections described previously:
     Airbus Service Bulletins A300-53-0380, dated August 5, 
2005 (for Model A300 B2 and B4 series airplanes), and A300-53-6153, 
dated August 24, 2005 (for Model A300-600 series airplanes). The 
service bulletins describe procedures for reinforcing the flanges of 
the left and right portals 1 through 5 inclusive between FR47 and FR54 
of the landing gear, including a rotating probe inspection for cracks 
of the holes and repair if necessary.
     Airbus Service Bulletins A300-53-0360, dated May 3, 2002 
(for Model A300 B2 and B4 series airplanes), and A300-53-6132, dated 
February 5, 2002 (for Model A300-600 series airplanes). The service 
bulletins describe procedures for reinforcing portals 3, 4, and 5 of 
the plates/skin.

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 
Sec.  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.
    This proposed AD would supersede ADs 2003-26-10 and 2004-18-13 and 
retain certain requirements of AD 2003-26-10 and all requirements of AD 
2004-18-13. This proposed AD also would require accomplishing the 
actions specified in Airbus Service Bulletins A300-53-0379 and A300-53-
6152 described previously and would provide for optional terminating 
actions specified in the remaining service information described 
previously, except as discussed under ``Difference Between the Proposed 
AD and Service Information.''

Difference Between the Proposed AD and Service Information

    The service information specifies 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.

Change to Existing AD

    Since ADs 2003-26-10 and 2004-18-13 were 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 in
       Requirement in AD 2003-26-10               this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
-------------------------------------------
       Requirement in AD 2004-18-13         Corresponding requirement in
                                                   this proposed AD
-------------------------------------------
Paragraph (a).............................  Paragraph (h).
Paragraph (b).............................  Paragraph (i).
Paragraph (c).............................  Paragraph (j).
------------------------------------------------------------------------

Costs of Compliance

    This proposed AD would affect about 165 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this proposed AD. Not all actions must be completed on all 
airplanes.

                                                          Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                   Number of U.S.-
              Action                  Work hours     Average labor           Parts            Cost per airplane      registered          Fleet cost
                                                     rate per hour                                                    airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
One-time inspection (required by                 1             $65  None..................  $65..................              23  $1,495.
 AD 2003-26-10).
One-time inspection (required by                 4              65  None..................  260..................              43  11,180.
 AD 2004-18-13).

[[Page 4315]]

 
Repetitive inspections (required                12              65  None..................  780, per inspection                78  60,840, per
 by AD 2004-18-13).                                                                          cycle.                                 inspection cycle.
Repetitive inspections (new                     16              65  None..................  1,040, per inspection              78  81,120, per
 proposed actions).                                                                          cycle.                                 inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                  Number of U.S.-
       Optional action            Work hours     Average labor       Parts           Cost per       registered
                                                 rate per hour                       airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in     807............             $65  Between $87,100  Between                      23
 Airbus Service Bulletin A300-                                   and $121,560     $139,555 and
 53-0380, dated August 5,                                        depending on     $174,015
 2005.                                                           kit purchased.   depending on
                                                                                  airplane
                                                                                  configuration.
Reinforcement specified in     807............              65  Between $82,460  Between                     120
 Airbus Service Bulletin A300-                                   and $87,070      $134,915 and
 53-6153, dated August 24,                                       depending on     $139,525
 2005.                                                           kit purchased.   depending on
                                                                                  airplane
                                                                                  configuration.
Reinforcement specified in     Between 24 and               65  Between $250     Between $1,810               23
 Airbus Service Bulletin A300-  128 depending                    and $1,000       and $9,320
 53-0360, dated May 3, 2002.    on airplane                      depending on     depending on
                                configuration.                   kit purchased.   airplane
                                                                                  configuration.
Reinforcement specified in     109............              65  Between $260     Between $7,345              120
 Airbus Service Bulletin A300-                                   and $950         and $8,035
 53-6132, dated February 5,                                      depending on     depending on
 2002.                                                           kit purchased.   airplane
                                                                                  configuration.
----------------------------------------------------------------------------------------------------------------

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 proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792 
(69 FR 55329, September 14, 2004) and adding the following new 
airworthiness directive (AD):

Airbus: Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-
133-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
27, 2006.

Affected ADs

    (b) This AD supersedes ADs 2003-26-10 and 2004-18-13.

Applicability

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

[[Page 4316]]



                         Table 1.--Applicability
------------------------------------------------------------------------
                                          Except for those airplanes on
       Affected Airbus airplanes                     which--
------------------------------------------------------------------------
(1) All Model A300 B2-1A, B2-1C, B2K-    None.
 3C, and B2-203 airplanes.
(2) All Model A300 B4-2C, B4-103, and    None.
 B4-203 airplanes.
(3) Model A300 B4-601, B4-603, B4-620,   Airbus Modification 12169 has
 and B4-622 airplanes.                    been incorporated in
                                          production.
(4) Model A300 B4-605R and B4-622R       Airbus Modification 12169 has
 airplanes.                               been incorporated in
                                          production.
(5) Model A300 F4-605R and F4-622R       Airbus Modification 12169 has
 airplanes.                               been incorporated in
                                          production.
(6) Model A300 C4-605R Variant F         Airbus Modification 12169 has
 airplanes.                               been incorporated in
                                          production.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report of a large fatigue crack along 
the outboard flange of beam No. 4. We are issuing this AD to detect 
and correct fatigue cracks in the lower flanges of the left and 
right gantries 1 through 5 inclusive in the main landing gear (MLG) 
bay area, which could result in reduced structural integrity of the 
fuselage, and consequent rapid decompression 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 2003-26-10

One-Time Inspection

    (f) For airplanes on which Airbus Modification 10147 has not 
been done: At the later of the times specified in paragraphs (f)(1) 
and (f)(2) of this AD: Do a one-time detailed inspection for 
cracking of the lower outboard flange of gantry No. 4 in the main 
landing gear bay area per paragraph 4.2.1 of Airbus All Operators 
Telex (AOT) A300-53A0371, Revision 01 (for Model A300 B2 and B4 
series airplanes); or AOT A300-53A6145, Revision 01 (for Model A300-
600 series airplanes); both dated September 10, 2003; as applicable.
    (1) Before the accumulation of 8,000 total flight cycles since 
the date of issuance of the original Airworthiness Certificate or 
the date of issuance of the Export Certificate of Airworthiness, 
whichever is first.
    (2) Within 30 days after January 22, 2004 (the effective date AD 
2003-26-10).


    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.''

Repair

    (g) Repair any cracking found during the inspection required by 
paragraph (f) of this AD before further flight, per a method 
approved by either the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the Direction Generale de 
l'Aviation Civile (or its delegated agent).

Restatement of Requirements of AD 2004-18-13

One-time Inspection and Corrective Action

    (h) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, 
and Model A300 B4-2C, B4-103, and B4-203 airplanes, on which Airbus 
Modification 3474 has been done: Prior to the accumulation of 16,300 
total flight cycles, or within 500 flight cycles after July 30, 1998 
(the effective date of AD 98-13-37), whichever occurs later, perform 
a one-time ultrasonic inspection for cracking of the gantry lower 
flanges in the MLG bay area, in accordance with Airbus AOT 53-11, 
dated October 13, 1997.
    (1) If any cracking is detected, prior to further flight, repair 
in accordance with the AOT.
    (2) If no cracking is detected, no further action is required by 
this paragraph.

Repetitive Inspections and Corrective Actions

    (i) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4-
605R Variant F airplanes, and F4-605R airplanes, on which Airbus 
Modification 12169 has not been done in production: Perform the 
requirements of paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of 
this AD, in accordance with Airbus Service Bulletin A300-53-6128, 
dated March 5, 2001.
    (1) At the later of the times specified in paragraphs (i)(1)(i) 
and (i)(1)(ii) of this AD, perform initial ultrasonic inspections or 
high-frequency eddy current inspections for cracks of the lower 
flanges of gantries 3, 4, and 5 between fuselage frames FR47 and 
FR54, in accordance with the Accomplishment Instructions, including 
the Synoptic Chart contained in Figure 2, sheets 1 through 5 
inclusive, of the service bulletin.
    (i) In accordance with the thresholds specified in the Synoptic 
Chart contained in Figure 2, sheets 1 through 5 inclusive, of the 
service bulletin; or
    (ii) Within 200 flight cycles after October 19, 2004 (the 
effective date AD 2004-18-13).
    (2) Perform repetitive ultrasonic inspections or high-frequency 
eddy current inspections for cracks of the lower flanges of gantries 
3, 4, and 5 between fuselage frames FR47 and FR54, in accordance 
with the thresholds and Accomplishment Instructions, including the 
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, 
of the service bulletin.
    (3) Perform repairs and reinforcements, in accordance with the 
thresholds and the Accomplishment Instructions, including the 
Synoptic Chart contained in Figure 2, sheets 1 through 5 inclusive, 
of the service bulletin, except as specified in paragraph (i)(4) of 
this AD.
    (4) If a new crack is found during any action required by 
paragraph (i)(1), (i)(2) or (i)(3) of this AD and the Synoptic Chart 
contained in Figure 2, sheets 1 through 5 inclusive, of the service 
bulletin specifies to contact Airbus for appropriate action: Prior 
to further flight, repair per a method approved by the Manager, 
International Branch, ANM-116, or the Direction Generale de 
l'Aviation Civile (DGAC) (or its delegated agent).

Credit for Inspections Accomplished in Accordance With AOT

    (j) Any inspection accomplished before October 19, 2004, in 
accordance with Airbus AOT 53-11, dated October 13, 1997, is 
acceptable for compliance with the corresponding inspection 
specified in paragraph (i)(1) of this AD, for that inspection area 
only. Operators must do the applicable inspections in paragraph 
(i)(1) of this AD for the remaining inspection areas.

New Requirements of This AD

Repetitive Inspections

    (k) At the later of the applicable times specified in the 
``Threshold (FC)'' and ``Grace Period'' columns of Tables 1 and 2 in 
paragraph 1.E of the applicable service bulletin in Table 2 of this 
AD: Do an ultrasonic inspection or high frequency eddy current 
(HFEC) inspection, including rework of the pressure diaphragm, for 
cracks in the lower flanges of the left and right gantries 1 through 
5 inclusive between FR47 and FR54, in accordance with the 
Accomplishment Instructions of the applicable service bulletin in 
Table 2 of this AD. Repeat the inspection at the applicable times 
specified in the ``Interval (FC)'' column of Tables 1 and 2 in 
paragraph 1.E of the applicable service bulletin in Table 2 of this 
AD. Accomplishment of the initial inspection ends the inspections 
required by paragraphs (f), (h), and (i) of this AD.

[[Page 4317]]



                       Table 2.--Service Bulletins
------------------------------------------------------------------------
       Airbus service bulletin--          For airplanes identified in--
------------------------------------------------------------------------
(1) A300-53-0379, Revision 01, dated     Paragraphs (c)(1) and (c)(2) of
 October 4, 2005.                         this AD inclusive.
(2) A300-53-6152, Revision 01, dated     Paragraphs (c)(3) through
 October 4, 2005.                         (c)(6) of this AD inclusive.
------------------------------------------------------------------------

Corrective Action

    (l) If any crack is detected during any ultrasonic or HFEC 
inspection required by paragraph (k) of this AD, before further 
flight, repair the crack in accordance with the Accomplishment 
Instructions of the applicable service bulletin in Table 2 of this 
AD, except as provided by paragraph (n) of this AD.

Optional Terminating Actions

    (m) Accomplishment of the actions specified in Table 3 of this 
AD ends the repetitive inspections required by paragraph (k) of this 
AD.

                                     Table 3.--Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
                                                                    By doing all the
                                                                 actions in accordance        For airplanes
  Before or at the same time with--          Reinforce--        with the accomplishment      identified in--
                                                                    instructions of--
----------------------------------------------------------------------------------------------------------------
(1) The actions required by paragraph  The flanges of the left  Airbus Service Bulletin  Paragraphs (c)(1) and
 (k) of this AD and the action          and right portals 1      A300-53-0380, dated      (c)(2) of this AD
 specified in paragraph (m)(2) of       through 5 inclusive      August 5, 2005, except   inclusive.
 this AD.                               between FR47 and FR54    as provided by
                                        of the landing gear,     paragraph (n) of this
                                        including a rotating     AD.
                                        probe inspection for
                                        cracks of holes and
                                        repair if necessary.
                                                                Airbus Service Bulletin  Paragraphs (c)(3)
                                                                 A300-53-6153, dated      through (c)(6) of this
                                                                 August 24, 2005,         AD inclusive.
                                                                 except as provided by
                                                                 paragraph (n) of this
                                                                 AD.
(2) The actions required by paragraph  Portals 3, 4, and 5 of   Airbus Service Bulletin  Paragraphs (c)(1) and
 (k) of this AD.                        the plates/skin.         A300-53-0360, dated      (c)(2) of this AD
                                                                 May 3, 2002, except as   inclusive.
                                                                 provided by paragraph
                                                                 (n) of this AD.
                                                                Airbus Service Bulletin  Paragraphs (c)(3)
                                                                 A300-53-6132, dated      through (c)(6) of this
                                                                 February 5, 2002,        AD inclusive.
                                                                 except as provided by
                                                                 paragraph (n) of this
                                                                 AD.
----------------------------------------------------------------------------------------------------------------

Repair of Certain Cracks

    (n) Where the applicable service bulletin recommends contacting 
Airbus for appropriate action: Before further flight, repair the 
crack in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

Credit for Original Service Bulletins

    (o) Accomplishing the inspections and repair before the 
effective date of this AD in accordance with Airbus Service Bulletin 
A300-53-0379, dated May 9, 2005; or Airbus Service Bulletin A300-53-
6152, dated May 9, 2005; as applicable; is acceptable for compliance 
with the corresponding requirements of paragraphs (k) and (l) of 
this AD.

No Inspection Report

    (p) Although the service bulletins in this AD specify to submit 
certain information to the manufacturer, this AD does not include 
that requirement.

Alternative Methods of Compliance (AMOCs)

    (q)(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.

Related Information

    (r) French airworthiness directive F-2005-091 R1, issued 
September 28, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on January 19, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-972 Filed 1-25-06; 8:45 am]
BILLING CODE 4910-13-P