[Federal Register: November 14, 2005 (Volume 70, Number 218)]
[Rules and Regulations]
[Page 69056-69059]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14no05-8]
[[Page 69056]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22110; Directorate Identifier 2004-NM-205-AD;
Amendment 39-14366; AD 2005-23-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600 and A300 B4-
600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Airbus Model A300 B4-600 and A300 B4-600R
series airplanes, and all Model A300 F4-605R airplanes. That AD
currently requires repetitive inspections to detect cracks of certain
attachment holes, installation of new fasteners, follow-on inspections
or repair if necessary, and modification of the angle fittings of
fuselage frame FR47. This new AD revises certain inspection thresholds
and intervals. This new AD also adds inspections to detect cracks of
additional attachment holes. This AD results from reports of cracks
found before the inspection thresholds in the existing AD and cracks
found in nearby areas not inspected by the existing AD. We are issuing
this AD to prevent fatigue cracking of the forward fitting of fuselage
frame FR47, which could result in reduced structural integrity of the
frame.
DATES: This AD becomes effective December 19, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 19,
2005.
On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of the
Federal Register approved the incorporation by reference of Airbus
Service Bulletin A300-57-6086, dated June 6, 2000.
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: 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 supersedes AD 2002-11-04, amendment
39-12765 (67 FR 38193, June 3, 2002). The existing AD applies to all
Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all
Model A300 F4-605R airplanes. That NPRM was published in the Federal
Register on August 16, 2005 (70 FR 48085). That NPRM proposed to
continue to require repetitive inspections to detect cracks of certain
attachment holes, installation of new fasteners, follow-on inspections
or repair if necessary, and modification of the angle fittings of
fuselage frame FR47. That NPRM also proposed to revise certain
inspection thresholds and intervals and add inspections to detect
cracks of additional attachment holes.
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 NPRM.
Request To Clarify Inspection in Paragraph (k)
One commenter, the manufacturer, requests that we clarify the
inspection specified in paragraph (k) of the NPRM. The commenter states
that the inspection of hole T is not required if ``any cracking is
found'' but is required only if cracking is found at hole G.
We agree with the commenter that the inspection of hole T is
required only if cracking is found at hole G. As specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002 (which is referenced as the
appropriate source of service information for accomplishing the
required actions for certain airplanes), the inspection of hole T is
applicable only if cracking is found at hole G. For clarity, we have
revised paragraph (k) of the final rule.
Clarification of Service Bulletin References
We have revised certain references to the service bulletins for
clarity. We have clarified that the actions specified in paragraphs (j)
and (k) of the final rule are done in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002. We have also clarified that the
modifications specified in paragraph (l) of the final rule are done in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6050, Revision 03, dated May 31, 2001.
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.
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
The following table provides the estimated costs for U.S. operators
to comply with this AD. This AD will affect about 74 airplanes of U.S.
registry.
[[Page 69057]]
Estimated Costs
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Average
Action Work hours labor rate Parts Cost per airplane Fleet cost
per hour
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Inspection per Airbus Service 13 $65 $0 $845............. $62,530, per
Bulletin A300-57-6049. inspection
cycle.
Inspection per Airbus Service 30 65 6,637-19,091 $8,587-$21,041, $635,438-$1,557,0
Bulletin A300-57-6086. per inspection 34, per
cycle. inspection
cycle.
Modification per Airbus Service 65-365 65 3,370 $7,595-$27,095... $562,030-$2,005,0
Bulletin A300-57-6050. 30.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this 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
removing amendment 39-12765 (67 FR 38193, June 3, 2002) and by adding
the following new airworthiness directive (AD):
2005-23-08 Airbus: Amendment 39-14366. Docket No. FAA-2005-22110;
Directorate Identifier 2004-NM-205-AD.
Effective Date
(a) This AD becomes effective December 19, 2005.
Affected ADs
(b) This AD supersedes AD 2002-11-04.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes;
Model A300 F4-605R airplanes; and Model A300 C4-605R Variant F
airplanes; certificated in any category; except airplanes on which
Airbus Modification 12171 or 12249 has been accomplished or on which
Airbus Service Bulletin A300-57-6069 has been accomplished.
Unsafe Condition
(d) This AD was prompted by reports of cracks found before the
inspection thresholds in the existing AD and cracks found in nearby
areas not inspected by the existing AD. We are issuing this AD to
prevent fatigue cracking of the forward fitting of fuselage frame
FR47, which could result in reduced structural integrity of the
frame.
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 for Attachment Holes on the Internal Angles of the Wing
Center Box, and Corrective Action
(f) Perform a rotating probe inspection to detect cracking of
the applicable attachment holes on the left and right internal
angles of the wing center box in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6049, Revision 06,
dated July 15, 2004. Do the inspection at the applicable time
specified by paragraph 1.E.(2), Accomplishment Timescale, of
Revision 06 of the service bulletin, except as required by paragraph
(m) of this AD. Repeat the rotating probe inspection specified in
this paragraph thereafter at intervals not to exceed the applicable
interval specified in Revision 06 of the service bulletin, except
that all touch-and-go landings must be counted in determining the
total number of flight cycles between consecutive inspections.
(g) If no cracking is found during any inspection required by
paragraph (f) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6049, Revision 06, dated July 15,
2004.
(h) If any cracking is found during any inspection required by
paragraph (f) of this AD: Prior to further flight, perform
applicable corrective actions (including reaming, drilling, drill-
stopping holes, chamfering, performing follow-on inspections, and
installing new or oversize fasteners) in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6049,
Revision 06, dated July 15, 2004, except as required by paragraph
(n) of this AD.
Inspections for Attachment Holes in the Horizontal Flange of the
Internal Corner Angle Fitting of Fuselage Frame FR47, and Corrective
Action
(i) Perform a rotating probe inspection to detect cracking of
the applicable attachment holes in the horizontal flange of the
internal corner angle fitting of fuselage frame FR47, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-57-6086, Revision 01, dated April 2, 2002. Do the inspection at
the applicable time specified in paragraph 1.E., Compliance, of
Airbus Service Bulletin A300-57-6086,
[[Page 69058]]
Revision 01, dated April 2, 2002, except as provided by paragraph
(m) of this AD; or within 1,500 flight cycles after July 8, 2002
(the effective date of AD 2002-11-04, amendment 39-12765); whichever
occurs later. Repeat the rotating probe inspection specified in this
paragraph thereafter at intervals not to exceed the applicable
interval specified in Airbus Service Bulletin A300-57-6086, dated
June 6, 2000, except that all touch-and-go landings must be counted
in determining the total number of flight cycles between consecutive
inspections.
(j) If no cracking is found during any inspection required by
paragraph (i) of this AD: Prior to further flight, install new
fasteners in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-57-6086, Revision 01, dated April 2,
2002.
(k) If any cracking is found during any inspection required by
paragraph (i) of this AD: Prior to further flight, perform
applicable corrective actions (including inspecting hole T if any
cracking is found at hole G, reaming the holes, and installing
oversize fasteners) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6086, Revision 01,
dated April 2, 2002, except as required by paragraph (n) of this AD.
Modification of Angle Fittings of the Wing Center Box
(l) Modify the left and right internal angle fittings of the
wing center box. The modification includes performing a rotating
probe inspection to detect cracking, repairing cracks, cold
expanding holes, and installing medium interference fitting bolts.
Perform the modification in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6050, Revision 03,
dated May 31, 2001; and at the applicable time specified by
paragraph 1.B.(4), Accomplishment Timescale, of Airbus Service
Bulletin A300-57-6050, Revision 03, dated May 31, 2001; except as
required by paragraphs (m) and (n) of this AD.
Exceptions to Specifications in Service Bulletins
(m) Where the service bulletins specified in paragraphs (f),
(i), and (l) of this AD specify a grace period relative to receipt
of the service bulletin, this AD requires compliance within the
applicable grace period following the effective date of this AD, if
the threshold has been exceeded.
(n) If any crack is detected during any inspection required by
this AD, and the applicable service bulletin specifies to contact
the manufacturer for disposition of certain corrective actions:
Prior to further flight, repair in accordance with a method approved
by either the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC) (or its delegated agent).
Actions Accomplished According to Previous Issue of Service Bulletins
(o) Actions accomplished prior to the effective date of this AD
in accordance with Airbus Service Bulletin A300-57-6086, dated June
6, 2000, are acceptable for compliance with the requirements of
paragraph (i) of this AD.
(p) Modifications accomplished prior to the effective date of
this AD in accordance with Airbus Service Bulletin A300-57-6050,
Revision 02, dated February 10, 2000; are acceptable for compliance
with the requirements of paragraph (l) of this AD.
No Reporting Requirement
(q) Although Airbus Service Bulletin A300-57-6049, Revision 06,
dated July 15, 2004; and Airbus Service Bulletin A300-57-6086,
Revision 01, dated April 2, 2002; 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, 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 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously according to AD 2002-11-04, are
not approved as AMOCs with this AD.
Related Information
(s) French airworthiness directive F-2004-159, dated September
29, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(t) You must use the service bulletins listed in Table 1 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 service bulletins listed in Table
2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of
the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
(3) 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 1.--All Material Incorporated by Reference
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Airbus service bulletin Revision level Date
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A300-57-6049, excluding Appendix 06.............. July 15, 2004.
01.
A300-57-6050.................... 03.............. May 31, 2001.
A300-57-6086.................... Original........ June 6, 2000.
A300-57-6086.................... 01.............. April 2, 2002.
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Table 2.--New Material Incorporated by Reference
------------------------------------------------------------------------
Airbus service bulletin Revision level Date
------------------------------------------------------------------------
A300-57-6049, excluding Appendix 06.............. July 15, 2004.
01.
A300-57-6050.................... 03.............. May 31, 2001.
A300-57-6086.................... 01.............. April 2, 2002.
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Airbus Service Bulletin A300-57-6050, Revision 03, dated May 31,
2001, contains the following effective pages:
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Revision level
Page number shown on page Date shown on page
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1, 4, 10A-11, 75-76.......... 03............ May 31, 2001.
2, 8-9, 17-32, 41-42, 57-58, 02............ February 10, 2000.
61-63, 77.
3, 5-7, 10, 12, 33-34, 37-38, 01............ May 31, 1999.
47, 59-60.
13-16, 35-36, 39-40, 43-46, Original...... September 9, 1994.
48-56, 64-74.
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[[Page 69059]]
Issued in Renton, Washington, on October 31, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22216 Filed 11-10-05; 8:45 am]
BILLING CODE 4910-13-P