[Federal Register: December 14, 2005 (Volume 70, Number 239)]
[Rules and Regulations]
[Page 73930-73933]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14de05-6]
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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.
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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
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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
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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.
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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