[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73930-73933]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23900]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22384; Directorate Identifier 2005-NM-131-AD; 
Amendment 39-14412; AD 2005-25-19]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 Series Airplanes, 
Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model 
A310-300 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.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus transport category airplanes. This AD requires 
repetitive eddy current inspections for cracks of the stiffener 
fittings of the fuselage at frame (FR) 12A, and corrective actions if 
necessary. This AD also provides a terminating action for the 
inspections. This AD results from reports of cracks on the upper 
attachment fitting of the stiffener fitting at FR12A. We are issuing 
this AD to prevent failure of the stiffener fittings, which could 
result in the reduced structural integrity of the floor and rods around 
FR 12A.

DATES: This AD becomes effective January 18, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 18, 
2006.

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 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 AD for Model 
A300 B2 series airplanes and Model A300 B4 series airplanes. Contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for 
service information identified in this AD for Model A310-200 series 
airplanes, Model A310-300 series airplanes, and Model A300-600 series 
airplanes.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Airbus 
transport category airplanes. That NPRM was published in the Federal 
Register on September 12, 2005 (70 FR 53739). That NPRM proposed to 
require repetitive eddy current inspections for cracks of the stiffener 
fittings of the fuselage at frame (FR) 12A, and corrective actions if 
necessary. The NPRM also provided a terminating action for the 
inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

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.

[[Page 73931]]

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    This AD will affect about 202 airplanes of U.S. registry. The 
inspection will take between 57 and 64 work hours per airplane, at an 
average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the inspection for U.S. operators is between $748,410 
and $840,320, or between $3,705 and $4,160 per airplane, per inspection 
cycle.

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 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 
adding the following new airworthiness directive (AD):

2005-25-19 Airbus: Amendment 39-14412. Docket No. FAA-2005-22384; 
Directorate Identifier 2005-NM-131-AD.

Effective Date

    (a) This AD becomes effective January 18, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 
airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; 
Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-
622R airplanes; Model A300 C4-605R Variant F airplanes; Model A310-
203, -204, -221, and -222 airplanes; and Model A310-304, -322, -324, 
and -325 airplanes; certificated in any category; except for 
airplanes on which Airbus Modification 12662 has been done in 
production.

Unsafe Condition

    (d) This AD results from reports of cracks on the upper 
attachment fitting of the stiffener fitting at frame (FR) 12A. We 
are issuing this AD to prevent failure of the stiffener fittings, 
which could result in the reduced structural integrity of the floor 
and rods around FR12A.

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.

Inspections

    (f) At the applicable initial inspection threshold specified in 
Table 1 of this AD or within the applicable grace period specified 
in Table 2 of this AD, whichever occurs later: Do an eddy current 
inspection for cracks of the stiffener fittings of the fuselage at 
FR 12A, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-0365, Revision 01 (for Model A300 B2-1A, 
B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, 
and B4-203 airplanes); Airbus Service Bulletin A300-53-6138, 
Revision 01 (for Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes); or Airbus Service Bulletin A310-53-2117, Revision 01 
(for Model A310-203, -204, -221, and -222 airplanes, and Model A310-
304, -322, -324, and -325 airplanes); all dated April 4, 2005; as 
applicable. Repeat the inspection thereafter at intervals not to 
exceed the applicable compliance time specified in Table 1 of this 
AD until the actions specified in paragraph (h) of this AD are done.

                        Table 1.--Compliance Times for Initial and Repetitive Inspections
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                                            Do the initial inspection
     For airplanes identified as--       prior to the accumulation of--  And repeat at intervals not to exceed--
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Configuration 01 in Airbus Service       19,300 total flight cycles....  11,450 flight cycles.
 Bulletin A300-53-0365, Revision 01,
 dated April 4, 2005.
Configuration 02 in Airbus Service       15,500 total flight cycles....  9,200 flight cycles.
 Bulletin A300-53-0365, Revision 01,
 dated April 4, 2005.
Configuration 01 in Airbus Service       19,300 total flight cycles....  11,450 flight cycles.
 Bulletin A300-53-6138, Revision 01,
 dated April 4, 2005.
Configuration 02 in Airbus Service       17,600 total flight cycles....  11,450 flight cycles.
 Bulletin A300-53-6138, Revision 01,
 dated April 4, 2005.
Configuration 03 in Airbus Service       12,700 total flight cycles....  8,000 flight cycles.
 Bulletin A300-53-6138, Revision 01,
 dated April 4, 2005.

[[Page 73932]]

 
Configuration 04 in Airbus Service       10,200 total flight cycles....  6,400 flight cycles.
 Bulletin A300-53-6138, Revision 01,
 dated April 4, 2005.
Configuration 01 in Airbus Service       19,300 total flight cycles....  11,450 flight cycles.
 Bulletin A310-53-2117, Revision 01,
 dated April 4, 2005.
Configuration 02 in Airbus Service       17,600 total flight cycles....  11,450 flight cycles.
 Bulletin A310-53-2117, Revision 01,
 dated April 4, 2005.
Configuration 03 in Airbus Service       12,700 total flight cycles....  8,000 flight cycles.
 Bulletin A310-53-2117, Revision 01,
 dated April 4, 2005.
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            Table 2.--Grace Period for the Initial Inspection
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              For Airbus Model--                   Grace period is--
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A300 B2-1A, B2-1C, B2K-3C, and B2-203          Within 2,500 flight
 airplanes.                                     cycles after the
                                                effective date of this
                                                AD.
A300 B4-2C, B4-103, and B4-203 airplanes;      Within 2,000 flight
 A300 B4-601, B4-603, B4-620, and B4-622        cycles after the
 airplanes; A300 B4-605R and B4-622R            effective date of this
 airplanes; A300 F4-605R and F4-622R            AD.
 airplanes; A300 C4-605R Variant F airplanes;
 A310-203, -204, -221, and -222 airplanes;
 and A310-304, -322, -324, and -325 airplanes.
------------------------------------------------------------------------

Corrective Action

    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD, before further flight, do the replacement 
and installation specified in paragraph (h) of this AD.

Terminating Action

    (h) Replacing the existing fitting on FR12A with a FR12A 
crossbeam and installing a new web between FR12A and FR13 at 
stringer 26 in accordance with Airbus Service Bulletin A300-53-0364, 
Revision 02, dated September 24, 2004 (for Model A300 B2-1A, B2-1C, 
B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-
203 airplanes); Airbus Service Bulletin A300-53-6137, Revision 03, 
dated April 4, 2005 (for Model A300 B4-601, B4-603, B4-620, and B4-
622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 
F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes); or Airbus Service Bulletin A310-53-2116, Revision 02, 
dated September 24, 2004 (for Model A310-203, -204, -221, and -222 
airplanes, and Model A310-304, -322, -324, and -325 airplanes); as 
applicable; and except as required by paragraph (i) of this AD; 
constitutes terminating action for the requirements of this AD.
    (i) Where the service bulletins specify to contact the 
manufacturer for certain information, before further flight, do the 
terminating action according to a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the DGAC (or its delegated agent).

Actions Accomplished According to Previous Issue of Service Bulletin

    (j) Actions accomplished before the effective date of this AD 
according to the Airbus service bulletins specified in Table 3 of 
this AD are considered acceptable for compliance with the 
corresponding actions specified in this AD.

                                 Table 3.--Previous Issues of Service Bulletins
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         Airbus Service Bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A300-53-0364.............................  Original....................  December 1, 2003.
A300-53-0364.............................  01..........................  May 5, 2004.
A300-53-0365.............................  Original....................  December 1, 2003.
A300-53-6137.............................  Original....................  December 1, 2003.
A300-53-6137.............................  01..........................  May 5, 2004.
A300-53-6137.............................  02..........................  September 24, 2004.
A300-53-6138.............................  Original....................  December 1, 2003.
A310-53-2116.............................  Original....................  December 1, 2003.
A310-53-2116.............................  01..........................  May 5, 2004.
A310-53-2117.............................  Original....................  December 1, 2003.
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No Reporting Required

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

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 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

    (m) French airworthiness directive F-2005-084, dated May 25, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (n) You must use the service information listed in Table 4 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise. The Director of the Federal Register 
approved the incorporation by reference of these documents in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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

[[Page 73933]]

in this AD for Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes; and Airbus Model A300 B4-2C, B4-103, and B4-203 
airplanes. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, for service information identified in this AD 
for Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; 
Airbus Model A300 B4-605R and B4-622R airplanes; Airbus Model A300 
F4-605R and F4-622R airplanes; Airbus Model A300 C4-605R Variant F 
airplanes; Model A310-203, -204, -221, and -222 airplanes; and 
Airbus Model A310-304, -322, -324, and -325 airplanes. 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.--Material Incorporated by Reference
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                                 Revision
    Airbus Service Bulletin        level                Date
------------------------------------------------------------------------
A300-53-0364..................          02  September 24, 2004.
A300-53-0365, excluding                 01  April 4, 2005.
 Appendix 01.
A300-53-6137..................          03  April 4, 2005.
A300-53-6138, excluding                 01  April 4, 2005.
 Appendix 01.
A310-53-2116..................          02  September 24, 2004.
A310-53-2117, excluding                 01  April 4, 2005.
 Appendix 01.
------------------------------------------------------------------------


    Issued in Renton, Washington, on December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23900 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P