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)

[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41109-41113]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-11412]



[[Page 41109]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23690; Directorate Identifier 2004-NM-133-AD; 
Amendment 39-14684; AD 2006-15-04]
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: Final rule.

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

SUMMARY: The FAA is superseding 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. This new AD requires new 
repetitive inspections for cracks in the lower flange of certain 
gantries, and repair if necessary, which ends the existing inspection 
requirements. This new AD also provides for optional terminating 
actions for the new repetitive inspections. This 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 issuing 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: This AD becomes effective August 24, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A300-53-0379, Revision 01, 
excluding Appendix 01, dated October 4, 2005; and Airbus Service 
Bulletin A300-53-6152, Revision 01, excluding Appendix 01, dated 
October 4, 2005; listed in the AD as of August 24, 2006.
    On October 19, 2004 (69 FR 55329, September 14, 2004), the Director 
of the Federal Register approved the incorporation by reference of 
Airbus Service Bulletin A300-53-6128, excluding Appendix 01, dated 
March 5, 2001.
    On January 22, 2004 (69 FR 867, January 7, 2004), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
All Operators Telex A300-53A0371, Revision 01, dated September 10, 
2003; and Airbus All Operators Telex A300-53A6145, Revision 01, dated 
September 10, 2003.
    On July 30, 1998 (63 FR 34589, June 25, 1998), the Director of the 
Federal Register approved the incorporation by reference of Airbus All 
Operators Telex (AOT) 53-11, dated October 13, 1997.

ADDRESSES: You may examine the 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., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: 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:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that supersedes AD 2003-26-10, 
amendment 39-13408 (69 FR 867, January 7, 2004), and AD 2004-18-13, 
amendment 39-13792 (69 FR 55329, dated September 14, 2004). The 
existing ADs apply to certain Airbus Model A300 B2 and A300 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 supplemental NPRM was published in the 
Federal Register on May 17, 2006 (71 FR 28615). That supplemental NPRM 
proposed to continue to require 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. That supplemental NPRM also proposed to 
continue to require repetitive inspections of the gantry lower flanges, 
and repair if necessary. In addition, that supplemental NPRM proposed 
to require new repetitive inspections for cracks in the lower flange of 
certain gantries, and repair if necessary, which ends the existing 
inspection requirements. That supplemental NPRM also proposed optional 
terminating actions for the new repetitive inspections. That 
supplemental also revised the original NPRM by including additional 
airplanes that were excluded from the applicability.

Comments

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

Request To Refer to Latest Service Bulletin

    Airbus states that it has issued Service Bulletins A300-53-0360, 
Revision 01, dated May 31, 2006; and A300-53-6132, Revision 01, dated 
June 7, 2006; whose original issues are listed in paragraph (m)(2) of 
the supplemental NPRM.
    We infer that Airbus is requesting that Revision 01 of Service 
Bulletins A300-53-0360 and A300-53-6132 be referred to in paragraph 
(m)(2) of the AD. We agree. We have reviewed Revision 01 of both 
service bulletins. Revision 01 of both service bulletins revises three 
illustrations. The reinforcement procedures in Revision 01 of both 
service bulletins are identical to that in the original issues of the 
service bulletins. No additional work is required for airplanes 
modified in accordance with the original issues of the service 
bulletins. Therefore, we have revised paragraph (m)(2) of this AD to 
refer to Revision 01 of both service bulletins and added a new 
paragraph (p) to the AD (subsequent paragraphs have been redesignated) 
to give credit for accomplishing the original issues of both service 
bulletins.

Explanation of Change Made to the Supplemental NPRM

    Paragraphs (g), (i)(4), and (n) of the supplemental NPRM specify 
making repairs using a method approved by either the FAA or the 
Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its 
delegated agent). The European

[[Page 41110]]

Aviation Safety Agency (EASA) has assumed responsibility for the 
airplane modes that would be subject to this AD. Therefore, we have 
revised those paragraphs of this AD to specify making repairs using a 
method approved by either the FAA, the DGAC (or its delegated agent), 
or the EASA (or its delegated agent).

Conclusion

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

Costs of Compliance

    This AD will affect about 165 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this 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 AD                  1             $80  None......................  $80......................              23  $1,840.
 2003-26-10).
One-time inspection (required by AD                  4              80  None......................  $320.....................              43  $13,760.
 2004-18-13).
Repetitive inspections (required by AD              12              80  None......................  $960, per inspection                   78  $74,880, per inspection cycle.
 2004-18-13).                                                                                        cycle.
Repetitive inspections (new proposed                16              80  None......................  $1,280, per inspection                 78  $99,840, per inspection cycle.
 actions).                                                                                           cycle.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                      Number of
                                                     Average                           Cost per         U.S.-
        Optional action             Work hours      labor rate        Parts            airplane       registered
                                                     per hour                                         airplanes
----------------------------------------------------------------------------------------------------------------
Reinforcement specified in      807..............          $80  Between $87,100    Between $151,660           23
 Airbus Service Bulletin A300-                                   and $121,560       and $186,120
 53-0380, dated August 5, 2005.                                  depending on kit   depending on
                                                                 purchased.         airplane
                                                                                    configuration.
Reinforcement specified in      807..............           80  Between $82,460    Between $147,020          120
 Airbus Service Bulletin A300-                                   and $87,070        and $151,630
 53-6153, dated August 24,                                       depending on kit   depending on
 2005.                                                           purchased.         airplane
                                                                                    configuration.
Reinforcement specified in      Between 24 and              80  Between $250 and   Between $2,170             23
 Airbus Service Bulletin A300-   128 depending on                $1,000 depending   and $11,240
 53-0360, Revision 01, dated     airplane                        on kit purchased.  depending on
 May 31, 2002.                   configuration.                                     airplane
                                                                                    configuration.
Reinforcement specified in      109..............           80  Between $260 and   Between $8,980            120
 Airbus Service Bulletin A300-                                   $950 depending     and $9,670
 53-6132, Revision 01, dated                                     on kit purchased.  depending on
 June 7, 2006.                                                                      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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities

[[Page 41111]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendments 39-13408 (69 FR 867, January 7, 2004) and 39-13792 
(69 FR 55329, September 14, 2004, and by adding the following new 
airworthiness directive (AD):

2006-15-04 Airbus: Amendment 39-14684. Docket No. FAA-2006-23690; 
Directorate Identifier 2004-NM-133-AD.

Effective Date

    (a) This AD becomes effective August 24, 2006.
    (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.

                         Table 1.--Applicability
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
                        Affected Airbus Airplanes
 
(1) All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes.
(2) All Model A300 B4-2C, B4-103, and B4-203 airplanes.
(3) All Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(4) All Model A300 B4-605R and B4-622R airplanes.
(5) All Model A300 F4-605R and F4-622R airplanes.
(6) All Model A300 C4-605R Variant F airplanes.
------------------------------------------------------------------------

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 MLG 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; the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or the European Aviation Safety Agency (EASA) (or its 
delegate 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 (HFEC) 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; the DGAC (or its delegated agent); or 
the European Aviation Safety Agency (EASA) (or its delegate 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

[[Page 41112]]

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 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.

                       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 Termianting 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, Revision   (c)(2) of this AD
                                                                 01, dated May 31,        inclusive.
                                                                 2006, except as
                                                                 provided by paragraph
                                                                 (n) of this AD.
                                                                Airbus Service Bulletin  Paragraphs (c)(3)
                                                                 A300-53-6132, Revision   through (c)(6) of this
                                                                 01, dated June 7,        AD inclusive.
                                                                 2006, 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; the DGAC (or its delegated agent); or 
the European Aviation Safety Agency (EASA) (or its delegate 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.
    (p) Accomplishing the reinforcement before the effective date of 
this AD in accordance with Airbus Service Bulletin A300-53-0360, 
dated May 3, 2002; and Airbus Service Bulletin A300-53-6132, dated 
February 5, 2002; is acceptable for compliance with the 
corresponding requirements of paragraph (m)(2) of this AD.

No Inspection Report

    (q) 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)

    (r)(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

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

Material Incorporated by Reference

    (t) You must use the applicable service bulletins identified in 
Table 4 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents in Table 5 of this AD in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On October 19, 2004 (69 FR 55329, September 14, 2004), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A300-53-6128, excluding 
Appendix 01, dated March 5, 2001.
    (3) On January 22, 2004 (69 FR 867, January 7, 2004), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus All Operators Telex A300-53A0371, Revision 01, 
dated September 10, 2003; and Airbus All Operators Telex A300-
53A6145, Revision 01, dated September 10, 2003.
    (4) On July 30, 1998 (63 FR 34589, June 25, 1998), the Director 
of the Federal Register approved the incorporation by reference of

[[Page 41113]]

Airbus All Operators Telex (AOT) 53-11, dated October 13, 1997.
    (5) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

                                Table 4.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Airbus All Operators Telex A300-53A0371.  01.........................  September 10, 2003.
Airbus All Operators Telex A300-53A6145.  01.........................  September 10, 2003.
Airbus All Operators Telex (AOT) 53-11..  Original...................  October 13, 1997.
Airbus Service Bulletin A300-53-0379,     01.........................  October 4, 2005.
 excluding Appendix 01.
Airbus Service Bulletin A300-53-6128,     Original...................  March 5, 2001.
 excluding Appendix 01.
Airbus Service Bulletin A300-53-6152,     01.........................  October 4, 2005.
 excluding Appendix 01.
----------------------------------------------------------------------------------------------------------------


                                Table 5.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-53-0379,     01.........................  October 4, 2005.
 excluding Appendix 01.
Airbus Service Bulletin A300-53-6152,     01.........................  October 4, 2005.
 excluding Appendix 01.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on July 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-11412 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P

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