[Federal Register: November 6, 2006 (Volume 71, Number 214)]
[Rules and Regulations]
[Page 64881-64884]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06no06-1]
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Rules and Regulations
Federal Register
________________________________________________________________________
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[[Page 64881]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22812; Directorate Identifier 2005-NM-134-AD;
Amendment 39-14811; AD 2006-22-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Airplanes and Model
A340-200 and -300 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 Model A330 airplanes and Model A340-200 and -300 series
airplanes. This AD requires repetitive detailed inspections for
cracking in the aft web of support rib 6 between certain bottom skin
stringers on both wings; high frequency eddy current inspections for
cracking of the attachment holes of the fuel pipes, and repair if
necessary. This AD also provides for an optional modification, which
extends a certain inspection threshold, and mandates, for certain
airplanes, a new modification of support rib 6 on both wings, which
ends the repetitive inspection requirement. This AD results from a
report of significant cracking found in the aft web of support rib 6 on
both wings. We are issuing this AD to prevent cracking in the aft web
of support rib 6, which could result in overloading of adjacent ribs
and the surrounding wing structure and consequent reduced structural
integrity of the wing.
DATES: This AD becomes effective December 11, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 11,
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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for the service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
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 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 would apply to certain
Airbus Model A330 airplanes and Model A340-200 and -300 series
airplanes. That supplemental NPRM was published in the Federal Register
on May 26, 2006 (71 FR 30340). That supplemental NPRM proposed to
require repetitive detailed inspections for cracking in the aft web of
support rib 6 between certain bottom skin stringers on both wings; high
frequency eddy current inspections for cracking of the attachment holes
of the fuel pipes, and repair if necessary. The supplemental NPRM also
provided for an optional modification, which would extend a certain
inspection threshold. For certain airplanes, the supplemental NPRM
proposed to require a new modification of support rib 6 on both wings,
which would end the repetitive inspection requirement. The supplemental
NPRM also proposed to reduce the applicability in the original NPRM.
Comment
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request for Credit for Terminating Modification
The Air Transport Association (ATA), on behalf of its member
Northwest Airlines (NWA), asks that we recognize Airbus Modification
54432 as terminating action for the repetitive inspection requirements
in the supplemental NPRM. NWA states that this modification is being
incorporated by Airbus in production as the ``production solution'' for
the fatigue cracking problems. NWA adds that the modification will be
installed on its Model A330 airplanes delivered with manufacturer's
serial number 0778 and subsequent.
We agree that Airbus Modification 54432 will be terminating action
for the referenced repetitive inspections. However, that modification
is not yet approved by either the European Aviation Safety Agency
(EASA), which is the airworthiness authority for the European Union, or
the FAA. The modification is currently in the approval process with the
EASA. This modification is the production solution that installs a re-
designed rib for production airplanes with a new wing build. Once the
modification is approved, the referenced EASA airworthiness directive
will be revised to include this terminating action. After the
modification is approved and available, operators may request an
alternative method of compliance for installing the modification. We
have not changed the AD in this regard.
Explanation of Change to the Supplemental NPRM
Airbus Service Bulletins A300-57-3085 and A340-57-4093, both
Revision 02, both dated September 29, 2005, were included in the
service information section of the supplemental NPRM as the sources of
service information for accomplishing the inspections. However,
Revision 02 was inadvertently omitted from paragraph (l) of the
supplemental NPRM; we have added Revision 02 to paragraph (l)
accordingly.
[[Page 64882]]
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
This change will neither increase the economic burden on any operator
nor increase the scope of the AD.
Costs of Compliance
This AD affects about 25 airplanes of U.S. registry.
The inspections take about 4 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the inspections for U.S. operators is $8,000, or $320 per
airplane, per inspection cycle.
The modification of support rib 6 on the left-hand wing takes about
38 work hours per airplane, at an average labor rate of $80 per work
hour. Required parts cost about $5,020 per airplane. Based on these
figures, the estimated cost of this modification of the left-hand wing
on U.S. operators is $201,500, or $8,060 per airplane.
The modification of support rib 6 on the right-hand wing takes
about 38 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts cost about $5,020 per airplane. Based on
these figures, the estimated cost of this modification of the right-
hand wing on U.S. operators is $201,500, or $8,060 per airplane.
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):
2006-22-14 Airbus: Amendment 39-14811. Docket No. FAA-2005-22812;
Directorate Identifier 2005-NM-134-AD.
Effective Date
(a) This AD becomes effective December 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330 airplanes and Model
A340-200 and -300 series airplanes, certificated in any category; on
which Airbus Modification 41114 or 44599 was done during production;
except those airplanes on which Airbus Modification 53883 was done
during production.
Unsafe Condition
(d) This AD results from a report of significant cracking found
in the aft web of support rib 6 on both wings. We are issuing this
AD to prevent cracking in the aft web of support rib 6, which could
result in overloading of adjacent ribs and the surrounding wing
structure and consequent reduced structural integrity of the wing.
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.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(f) For Model A330 series airplanes on which Airbus Modification
53882 was not done during production: At the applicable time
specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD, perform
a detailed inspection for cracking in the aft web of support rib 6
between bottom skin stringers 18 and 20 on both wings, and high
frequency eddy current inspections for cracking of the attachment
holes of the fuel pipe and fuel pipe mounting, by doing all the
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-57-3085, Revision 02, dated September 29,
2005. If no crack is found during the initial inspections, repeat
the inspections thereafter at intervals not to exceed 8,000 flight
cycles or 25,000 flight hours, whichever is first, until the
terminating action specified in paragraph (n) of this AD is done. If
any crack is found during any inspection, repair as specified in
paragraph (k) of this AD, or before further flight do the
terminating action specified in paragraph (n) of this AD.
(1) For airplanes that have accumulated 7,999 or fewer total
flight cycles, and 24,999 or fewer total flight hours, as of the
effective date of this AD: Do the inspections at the later of the
times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or
25,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total
flight cycles, but fewer than 10,000 total flight cycles; or 25,000
or more total flight hours, but fewer than 30,000 total flight
hours; as of the effective date of this AD: Do the inspections at
the later of the times specified in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
30,000 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total
flight cycles or 30,000 or more total flight hours as of the
effective
[[Page 64883]]
date of this AD: Do the inspections within 3 months after the
effective date of this AD.
(g) For Model A330 series airplanes on which Airbus Modification
53882 was done during production or on which Airbus Service Bulletin
A330-57-3087, dated February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform the applicable
inspections required by paragraph (f) of this AD at the earliest of
the initial inspection thresholds specified in Figure 4, Sheet 1,
``Inspection Flow Chart'' of Airbus Service Bulletin A330-57-3085,
Revision 02, dated September 29, 2005; or within 6 months after the
effective date of this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this AD at the time
specified in paragraph (f) of this AD, until the terminating action
specified in paragraph (n) of this AD is done.
(h) For Model A340 series airplanes on which Airbus Modification
53882 was not done during production: Perform the inspections
required by paragraph (f) of this AD at the applicable time
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Perform
the inspections by doing all the actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-57-4093,
Revision 02, dated September 29, 2005. Repeat the inspections
thereafter at intervals not to exceed 8,000 flight cycles or 30,200
flight hours, whichever is first, until the terminating action
specified in paragraph (n) of this AD is done.
(1) For airplanes that have accumulated 7,999 or fewer total
flight cycles, and 30,199 or fewer total flight hours, as of the
effective date of this AD: Do the inspections at the later of the
times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Before the accumulation of 8,000 total flight cycles or
30,200 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(2) For airplanes that have accumulated 8,000 or more total
flight cycles, but fewer than 10,000 total flight cycles; or 30,200
or more total flight cycles, but fewer than 43,700 total flight
hours, as of the effective date of this AD: Do the inspections at
the later of the times specified in paragraphs (h)(2)(i) and
(h)(2)(ii) of this AD.
(i) Before the accumulation of 10,000 total flight cycles or
43,700 total flight hours, whichever is first.
(ii) Within 8 months after the effective date of this AD.
(3) For airplanes that have accumulated 10,000 or more total
flight cycles or 43,700 or more total flight hours as of the
effective date of this AD: Do the inspections within 3 months after
the effective date of this AD.
(i) For Model A340 series airplanes on which Airbus Modification
53882 was done during production or on which Airbus Service Bulletin
A340-57-4095, dated February 15, 2005, or Revision 01, dated
September 22, 2005, has been done: Perform the applicable
inspections required by paragraph (f) of this AD at the earliest of
the initial inspection thresholds specified in Figure 4, Sheet 1,
``Inspection Flow Chart'' of Airbus Service Bulletin A340-57-4093,
Revision 02, dated September 29, 2005; or within 6 months after the
effective date of this AD, whichever is later. Repeat the
inspections required by paragraph (f) of this AD at the time
specified in paragraph (h) of this AD, until the terminating action
specified in paragraph (n) of this AD is done.
Inspections Accomplished According to Previous Issue of Service
Bulletins
(j) Inspections accomplished before the effective date of this
AD according to Airbus All Operator Telex A330-57A3085 or A340-
57A4093, each dated December 15, 2004; or Airbus Service Bulletin
A330-57-3085 or A340-57-4093, each Revision 01, each dated March 25,
2005; are considered acceptable for compliance with the
corresponding inspections specified in this AD.
Repair
(k) If any cracking is found during any inspection required by
this AD: Before further flight, either repair and get a schedule for
subsequent inspections, according to a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent); or accomplish the terminating action specified
in paragraph (n) of this AD.
Optional Modification
(l) Accomplishing the modification of the fuel pipe connector
and the fastener holes of support rib 6 on both wings by doing all
the actions specified in the Accomplishment Instructions of Airbus
Service Bulletin A330-57-3087 or A340-57-4095, each dated February
15, 2005, or Revision 01, each dated September 22, 2005, as
applicable, extends the interval for the next inspection to the
applicable post-modification inspection threshold specified in
Figure 4, Sheet 1, ``Inspection Flow Chart'' of Airbus Service
Bulletins A330-57-3085 or A340-57-4093, each Revision 02, each dated
September 29, 2005, as applicable. After accomplishing that
inspection, repeat the applicable inspections required by paragraph
(f) or (h) of this AD at the applicable repetitive inspection
interval specified in Figure 4 of the Accomplishment Instructions of
the applicable service bulletin, until the terminating action
specified in paragraph (n) of this AD is done.
Hard or Overweight Landing
(m) For Model A330 series airplanes with 8,000 or more total
flight cycles or 25,000 or more total flight hours, and Model A340
series airplanes with 8,000 or more total flight cycles or 30,200 or
more total flight hours that have not been modified in accordance
with paragraph (n) of this AD: Before further flight after any hard
or overweight landing of the airplane, accomplish the applicable
follow-on inspections and any applicable corrective actions
according to a method approved by either the Manager, International
Branch, ANM-116; or the EASA (or its delegated agent). Accomplishing
the inspections in Chapter 05-51-11, titled ``Inspection After Hard/
Overweight Landing--Inspection/Check,'' dated April 1, 2005, or July
1, 2006, of the Airbus A330 Aircraft Maintenance Manual (AMM); or
Chapter 05-51-11, titled ``Inspection After Hard/Overweight
Landing--Inspection/Check,'' dated July 1, 2006, of the Airbus A340
AMM; as applicable; and Airbus A330/A340 Technical Disposition (TD)
TD/J1/S3/00608/2005, Issue C, dated April 26, 2005, titled
``Inspections following hard landing, both wings,'' are approved
methods. Operators can obtain the TD from Airbus.
Terminating Modification
(n) For airplanes on which support rib 6 on both wings has not
been repaired in accordance with paragraph (k) of this AD: Within 60
months after the effective date of this AD, modify the fuel pipe
connector and the fastener holes of support rib 6 on both wings by
doing all the actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A330-57-3088 or A340-57-4096, each
including Appendix 01, each dated September 21, 2005, as applicable.
Accomplishing the modification in this paragraph ends the repetitive
inspections required by this AD. Repair of support rib 6 on both
wings before the effective date of this AD using Airbus A330/A340
Repair Instruction R572-57023, Issue D, dated May 11, 2005; or R572-
57026, Issue C, dated December 2005; as applicable, ends the
repetitive inspections required by this AD.
Alternative Methods of Compliance (AMOCs)
(o)(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 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.
Related Information
(p) French airworthiness directives F-2006-008 and F-2006-009,
both dated January 4, 2006, also address the subject of this AD.
Material Incorporated by Reference
(q) You must use the applicable Airbus service bulletins
specified in Table 1 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 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
.
[[Page 64884]]
Table 1.--Material Incorporated by Reference
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Airbus Service Bulletin Revision level Date
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A330-57-3085.......................... 02................................. September 29, 2005.
A330-57-3087.......................... Original........................... February 15, 2005.
A330-57-3087.......................... 01................................. September 22, 2005.
A330-57-3088, including Appendix 01... Original........................... September 21, 2005.
A340-57-4093.......................... 02................................. September 29, 2005.
A340-57-4095.......................... Original........................... February 15, 2005.
A340-57-4095.......................... 01................................. September 22, 2005.
A340-57-4096, including Appendix 01... Original........................... September 21, 2005.
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Issued in Renton, Washington, on October 25, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-18471 Filed 11-3-06; 8:45 am]
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