Airworthiness Directives; Airbus Model A330 Airplanes, 12555-12557 [E7-4740]
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Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
12555
TABLE 5.—SERVICE BULLETINS ACCOMPLISHED PREVIOUSLY—Continued
Airbus service bulletin
Revision level
Date
A310–78–2023 ........................................................................
A310–78–2024 ........................................................................
A310–78–2025 ........................................................................
Original ...................................................................................
Original ...................................................................................
Original ...................................................................................
October 7, 2003.
October 15, 2003.
July 23, 2004.
Alternative Methods of Compliance
(AMOCs)
(i)(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.
Related Information
(j) French airworthiness directive F–
2004–165, dated October 13, 2004, also
addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use the applicable
Airbus service bulletins specified in
Table 6 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 FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington;
or at the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
TABLE 6.—MATERIAL INCORPORATED BY REFERENCE
Airbus service bulletin
Revision level
A300–78–6021, including Appendices 01 and 02 ..................
A300–78–6022, including Appendices 01 and 02 ..................
A300–78–6024 ........................................................................
A300–78–6025 ........................................................................
A310–78–2022, including Appendices 01 and 02 ..................
A310–78–2023 ........................................................................
A310–78–2024, including Appendices 01 and 02 ..................
A310–78–2025 ........................................................................
Issued in Renton, Washington, on March 5,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4734 Filed 3–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26324; Directorate
Identifier 2006–NM–214–AD; Amendment
39–14993; AD 2007–06–12]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
sroberts on PROD1PC70 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A330–300 airplanes. That AD currently
requires reinforcement of the structure
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
02
02
01
01
02
01
01
01
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of the center fuselage by installing
external stiffeners (butt straps) at frame
(FR) 53.3 on the fuselage skin between
left-hand (LH) and right-hand (RH)
stringer (STR) 13, and related
investigative and corrective actions.
This new AD requires additional
reinforcement of the structure of the
center fuselage by installing external
stiffeners (butt straps) at frame FR53.3
on the fuselage skin between LH and RH
STR13, and related investigative and
other specified actions. This AD also
adds airplanes to the applicability. This
AD results from cracking found at the
circumferential joint of FR53.3. We are
issuing this AD to prevent fatigue
cracking of the fuselage, which could
result in reduced structural integrity of
the fuselage.
This AD becomes effective April
20, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 20, 2007.
On October 19, 2005 (70 FR 57732,
October 4, 2005), the Director of the
Federal Register approved the
incorporation by reference of Airbus
DATES:
PO 00000
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Date
Fmt 4700
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June 8, 2005.
June 8, 2005.
April 22, 2005.
April 22, 2005.
July 18, 2006.
April 22, 2005.
June 13, 2005.
April 22, 2005.
Service Bulletin A330–53–3127,
Revision 01, dated November 21, 2003.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 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 airworthiness
directive (AD) docket on the Internet at
https://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
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12556
Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
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 2005–20–07, amendment
39–14300 (70 FR 57732, October 4,
2005). The existing AD applies to
certain Airbus Model A330–300 series
airplanes. That NPRM was published in
the Federal Register on November 15,
2006 (71 FR 66472). That NPRM
proposed to continue to require
reinforcement of the structure of the
center fuselage by installing external
stiffeners (butt straps) at frame (FR) 53.3
on the fuselage skin between left-hand
(LH) and right-hand (RH) stringer (STR)
13, and related investigative and
corrective actions. That NPRM also
proposed to require additional
reinforcement of the structure of the
center fuselage by installing external
stiffeners (butt straps) at frame FR53.3
on the fuselage skin between LH and RH
STR13, and related investigative and
other specified actions. That NPRM also
proposed to add airplanes to the
applicability.
sroberts on PROD1PC70 with RULES
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Revise Paragraph (h)
Airbus requests that we revise the
phrase ‘‘For all airplanes * * *’’ in
paragraph (h) of the NPRM to duplicate
paragraph 2 of European Aviation Safety
Agency (EASA) airworthiness directive
2006–0266, dated August 30, 2006, as
follows: ‘‘For all A330–200 and –300
series aircraft [as listed in the
applicability of this directive] which
have received embodiment of AIRBUS
modification 41652S11819.’’
We agree to clarify paragraph (h) of
this AD. The term ‘‘for all airplanes’’ in
paragraph (h) of the NPRM applies to
the airplanes identified in paragraph (c)
of the NPRM (the applicability of the
NPRM). Even though paragraph (h) of
the NPRM is essentially the same as
paragraph 2 of EASA airworthiness
directive 2006–0266, we have revised
paragraph (h) of this AD as follows: ‘‘For
Airbus Model A330–201, –202, –203,
–223, –243, –301, –321, –322, –323,
–341, –342, and –343 airplanes, on
which Airbus Modification
41652S11819 has been incorporated in
production or in accordance with
paragraph (f) of this AD, except those
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
airplanes on which Airbus Modification
49202 has been incorporated in
production * * *.’’ This change has not
expanded the scope of this AD.
Request To Include Note
Airbus requests that we revise the
NPRM to include Note 2 of EASA
airworthiness directive 2006–0266:
‘‘Notwithstanding the compliance times
referenced above, EASA supports the
Airbus recommendation to embody SB
A330–53–3143 at latest within 8,300 FC
or 29,200 FH, whichever occurs first, in
order to reduce the extent of any
required repairs.’’
We disagree with including the note.
We acknowledge that accomplishing the
required actions sooner could reduce
the extent of repairs needed in the
future. However, it is not appropriate
and, therefore, not the FAA’s practice to
state recommendations in an AD. We
have not revised this AD in this regard.
Request To Revise Discussion Section
Airbus requests that we revise the
Discussion section of the NPRM to state
the unsafe condition was found during
fatigue tests (EF2) of the fuselage.
We agree with Airbus’s statement.
However, that portion of the Discussion
section is not retained in this final rule.
We have not revised this AD in this
regard.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been received, 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
Currently, the action required by AD
2005–20–07 and retained in this AD
affects 12 airplanes of U.S. registry.
However, we have been advised that all
affected U.S. operators have already
accomplished that action. If an affected
airplane is imported and placed on the
U.S. Register in the future, the action
required by AD 2005–20–07 takes about
315 work hours per airplane, at an
average labor rate of $80 per work hour.
Required parts cost about $8,920 per
airplane. Based on these figures, the
estimated cost of the currently required
action is $34,120 per airplane.
The new action affects about 27
airplanes of U.S. registry. The new
action takes about 316 work hours per
airplane, at an average labor rate of $80
per work hour. Required parts cost
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Fmt 4700
Sfmt 4700
about $9,160 per airplane. Based on
these figures, the estimated cost of the
new action specified in this AD for U.S.
operators is $929,880, or $34,440 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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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Federal Register / Vol. 72, No. 51 / Friday, March 16, 2007 / Rules and Regulations
´ ´
Contact the FAA/Direction Generale de
l’Aviation Civile (DGAC)/European Aviation
Safety Agency (EASA) for Certain Repair
Instructions
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14300 (70
FR 57732, October 4, 2005) and by
adding the following new airworthiness
directive (AD):
I
2007–06–12 Airbus: Amendment 39–14993.
Docket No. FAA–2006–26324;
Directorate Identifier 2006–NM–214–AD.
(a) This AD becomes effective April 20,
2007.
Affected ADs
(b) This AD supersedes AD 2005–20–07.
Applicability
(c) This AD applies to Airbus Model A330–
201, –202, –203, –223, –243, –301, –321,
–322, –323, –341, –342, and –343 airplanes,
certificated in any category; except those on
which Airbus Modification 49202 has been
incorporated in production.
Unsafe Condition
(d) This AD results from cracking found at
the circumferential joint of frame (FR) 53.3.
We are issuing this AD to prevent fatigue
cracking of the fuselage, which could result
in reduced structural integrity of the fuselage.
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.
Requirements of AD 2005–20–07
Installation for Model A330–300 Series
Airplanes
sroberts on PROD1PC70 with RULES
Related Information
(k) EASA airworthiness directive 2006–
0266, dated August 30, 2006, also addresses
the subject of this AD.
(g) For Airbus Model A330–301, –321,
–322, –323, –341, –342, and –343 airplanes,
except those on which Airbus Modification
41652S11819 has been incorporated in
production: If any crack is detected during
the related investigative actions (rototest)
required by paragraph (f) of this AD, before
further flight, repair the crack according to a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; the DGAC (or its
delegated agent); or the EASA (or its
delegated agent).
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin
A330–53–3127, Revision 01, dated November
21, 2003; and Airbus Service Bulletin A330–
53–3143, Revision 01, including Appendix
01, dated June 29, 2006; as applicable, 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
Airbus Service Bulletin A330–53–3143,
Revision 01, including Appendix 01, dated
June 29, 2006, in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On October 19, 2005 (70 FR 57732,
October 4, 2005), the Director of the Federal
Register approved the incorporation by
reference of Airbus Service Bulletin A330–
53–3127, Revision 01, dated November 21,
2003.
(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 FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; 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: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
New Requirements of This AD
Installation for Model A330–200 and –300
Series Airplanes
Effective Date
(f) For Airbus Model A330–301, –321,
–322, –323, –341, –342, and –343 airplanes,
except those on which Airbus Modification
41652S11819 has been incorporated in
production: At the later of the times in
paragraphs (f)(1) and (f)(2) of this AD, install
the butt straps at FR53.3 on the fuselage skin
between left-hand (LH) and right-hand (RH)
stringer (STR) 13, and do all related
investigative and corrective actions before
further flight. Except as provided by
paragraph (g) of this AD, do all actions in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
53–3127, Revision 01, dated November 21,
2003.
(1) Before the accumulation of 14,700 total
flight cycles or 51,400 total flight hours,
whichever occurs earlier.
(2) Within 6 months after October 19, 2005
(the effective date of AD 2005–20–07).
VerDate Aug<31>2005
15:23 Mar 15, 2007
Jkt 211001
12557
(h) For Airbus Model A330–201, –202,
–203, –223, –243, –301, –321, –322, –323,
–341, –342, and –343 airplanes, on which
Airbus Modification 41652S11819 has been
incorporated in production or in accordance
with paragraph (f) of this AD, except those
airplanes on which Airbus Modification
49202 has been incorporated in production:
At the later of the times in paragraphs (h)(1)
and (h)(2) of this AD, install the butt straps
at FR53.3 on the fuselage skin between LH
and RH STR13; and do all related
investigative and other specified actions
before further flight, as applicable. Do all
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–53–3143, Revision 01,
including Appendix 01, dated June 29, 2006;
except if any crack is detected during a
related investigative action (rototest), before
further flight, repair the crack using a method
approved by the Manager, International
Branch, ANM–116; or the EASA (or its
delegated agent).
(1) Before the accumulation of 17,600 total
flight cycles or 61,600 total flight hours,
whichever occurs earlier.
(2) Within 6 months after the effective date
of this AD.
Credit for Actions Done in Accordance With
Previous Service Bulletin
(i) Actions done before the effective date of
this AD in accordance with Airbus Service
Bulletin A330–53–3143, including Appendix
01, dated December 24, 2004, are acceptable
for compliance with the corresponding
requirements of paragraph (h) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
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Issued in Renton, Washington, on March 7,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4740 Filed 3–15–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26401; Directorate
Identifier 2006–CE–72–AD; Amendment 39–
14987; AD 2007–06–06]
RIN 2120–AA64
Airworthiness Directives; B–N Group
Ltd. BN–2, BN–2A, BN–2B, BN–2T, and
BN–2T–4R Series (All Individual
Models Included in Type Certificate
Data Sheet (TCDS) A17EU, Revision
16, Dated December 9, 2002), and BN–
2A–Mklll Trislander Series (All
Individual Models Included in Type
Certificate Data Sheet (TCDS) A29EU,
Revision 4, Dated December 9, 2002)
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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]]>Agencies
[Federal Register Volume 72, Number 51 (Friday, March 16, 2007)]
[Rules and Regulations]
[Pages 12555-12557]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4740]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-214-AD;
Amendment 39-14993; AD 2007-06-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A330-300 airplanes. That AD
currently requires reinforcement of the structure of the center
fuselage by installing external stiffeners (butt straps) at frame (FR)
53.3 on the fuselage skin between left-hand (LH) and right-hand (RH)
stringer (STR) 13, and related investigative and corrective actions.
This new AD requires additional reinforcement of the structure of the
center fuselage by installing external stiffeners (butt straps) at
frame FR53.3 on the fuselage skin between LH and RH STR13, and related
investigative and other specified actions. This AD also adds airplanes
to the applicability. This AD results from cracking found at the
circumferential joint of FR53.3. We are issuing this AD to prevent
fatigue cracking of the fuselage, which could result in reduced
structural integrity of the fuselage.
DATES: This AD becomes effective April 20, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of April 20,
2007.
On October 19, 2005 (70 FR 57732, October 4, 2005), the Director of
the Federal Register approved the incorporation by reference of Airbus
Service Bulletin A330-53-3127, Revision 01, dated November 21, 2003.
ADDRESSES: You may examine the AD docket on the Internet at https://
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: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
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 airworthiness directive (AD) docket on the
Internet at https://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
[[Page 12556]]
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 2005-20-07, amendment
39-14300 (70 FR 57732, October 4, 2005). The existing AD applies to
certain Airbus Model A330-300 series airplanes. That NPRM was published
in the Federal Register on November 15, 2006 (71 FR 66472). That NPRM
proposed to continue to require reinforcement of the structure of the
center fuselage by installing external stiffeners (butt straps) at
frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-
hand (RH) stringer (STR) 13, and related investigative and corrective
actions. That NPRM also proposed to require additional reinforcement of
the structure of the center fuselage by installing external stiffeners
(butt straps) at frame FR53.3 on the fuselage skin between LH and RH
STR13, and related investigative and other specified actions. That NPRM
also proposed to add airplanes to the applicability.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Revise Paragraph (h)
Airbus requests that we revise the phrase ``For all airplanes * *
*'' in paragraph (h) of the NPRM to duplicate paragraph 2 of European
Aviation Safety Agency (EASA) airworthiness directive 2006-0266, dated
August 30, 2006, as follows: ``For all A330-200 and -300 series
aircraft [as listed in the applicability of this directive] which have
received embodiment of AIRBUS modification 41652S11819.''
We agree to clarify paragraph (h) of this AD. The term ``for all
airplanes'' in paragraph (h) of the NPRM applies to the airplanes
identified in paragraph (c) of the NPRM (the applicability of the
NPRM). Even though paragraph (h) of the NPRM is essentially the same as
paragraph 2 of EASA airworthiness directive 2006-0266, we have revised
paragraph (h) of this AD as follows: ``For Airbus Model A330-201, -202,
-203, -223, -243, -301, -321, -322, -323, -341, -342, and -343
airplanes, on which Airbus Modification 41652S11819 has been
incorporated in production or in accordance with paragraph (f) of this
AD, except those airplanes on which Airbus Modification 49202 has been
incorporated in production * * *.'' This change has not expanded the
scope of this AD.
Request To Include Note
Airbus requests that we revise the NPRM to include Note 2 of EASA
airworthiness directive 2006-0266: ``Notwithstanding the compliance
times referenced above, EASA supports the Airbus recommendation to
embody SB A330-53-3143 at latest within 8,300 FC or 29,200 FH,
whichever occurs first, in order to reduce the extent of any required
repairs.''
We disagree with including the note. We acknowledge that
accomplishing the required actions sooner could reduce the extent of
repairs needed in the future. However, it is not appropriate and,
therefore, not the FAA's practice to state recommendations in an AD. We
have not revised this AD in this regard.
Request To Revise Discussion Section
Airbus requests that we revise the Discussion section of the NPRM
to state the unsafe condition was found during fatigue tests (EF2) of
the fuselage.
We agree with Airbus's statement. However, that portion of the
Discussion section is not retained in this final rule. We have not
revised this AD in this regard.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, 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
Currently, the action required by AD 2005-20-07 and retained in
this AD affects 12 airplanes of U.S. registry. However, we have been
advised that all affected U.S. operators have already accomplished that
action. If an affected airplane is imported and placed on the U.S.
Register in the future, the action required by AD 2005-20-07 takes
about 315 work hours per airplane, at an average labor rate of $80 per
work hour. Required parts cost about $8,920 per airplane. Based on
these figures, the estimated cost of the currently required action is
$34,120 per airplane.
The new action affects about 27 airplanes of U.S. registry. The new
action takes about 316 work hours per airplane, at an average labor
rate of $80 per work hour. Required parts cost about $9,160 per
airplane. Based on these figures, the estimated cost of the new action
specified in this AD for U.S. operators is $929,880, or $34,440 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:
[[Page 12557]]
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 39-14300 (70 FR 57732, October 4, 2005) and by
adding the following new airworthiness directive (AD):
2007-06-12 Airbus: Amendment 39-14993. Docket No. FAA-2006-26324;
Directorate Identifier 2006-NM-214-AD.
Effective Date
(a) This AD becomes effective April 20, 2007.
Affected ADs
(b) This AD supersedes AD 2005-20-07.
Applicability
(c) This AD applies to Airbus Model A330-201, -202, -203, -223,
-243, -301, -321, -322, -323, -341, -342, and -343 airplanes,
certificated in any category; except those on which Airbus
Modification 49202 has been incorporated in production.
Unsafe Condition
(d) This AD results from cracking found at the circumferential
joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue
cracking of the fuselage, which could result in reduced structural
integrity of the fuselage.
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.
Requirements of AD 2005-20-07
Installation for Model A330-300 Series Airplanes
(f) For Airbus Model A330-301, -321, -322, -323, -341, -342, and
-343 airplanes, except those on which Airbus Modification
41652S11819 has been incorporated in production: At the later of the
times in paragraphs (f)(1) and (f)(2) of this AD, install the butt
straps at FR53.3 on the fuselage skin between left-hand (LH) and
right-hand (RH) stringer (STR) 13, and do all related investigative
and corrective actions before further flight. Except as provided by
paragraph (g) of this AD, do all actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-53-3127,
Revision 01, dated November 21, 2003.
(1) Before the accumulation of 14,700 total flight cycles or
51,400 total flight hours, whichever occurs earlier.
(2) Within 6 months after October 19, 2005 (the effective date
of AD 2005-20-07).
Contact the FAA/Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC)/European Aviation Safety Agency (EASA) for Certain Repair
Instructions
(g) For Airbus Model A330-301, -321, -322, -323, -341, -342, and
-343 airplanes, except those on which Airbus Modification
41652S11819 has been incorporated in production: If any crack is
detected during the related investigative actions (rototest)
required by paragraph (f) of this AD, before further flight, repair
the crack according to a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
the DGAC (or its delegated agent); or the EASA (or its delegated
agent).
New Requirements of This AD
Installation for Model A330-200 and -300 Series Airplanes
(h) For Airbus Model A330-201, -202, -203, -223, -243, -301, -
321, -322, -323, -341, -342, and -343 airplanes, on which Airbus
Modification 41652S11819 has been incorporated in production or in
accordance with paragraph (f) of this AD, except those airplanes on
which Airbus Modification 49202 has been incorporated in production:
At the later of the times in paragraphs (h)(1) and (h)(2) of this
AD, install the butt straps at FR53.3 on the fuselage skin between
LH and RH STR13; and do all related investigative and other
specified actions before further flight, as applicable. Do all
actions in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-53-3143, Revision 01, including Appendix 01,
dated June 29, 2006; except if any crack is detected during a
related investigative action (rototest), before further flight,
repair the crack using a method approved by the Manager,
International Branch, ANM-116; or the EASA (or its delegated agent).
(1) Before the accumulation of 17,600 total flight cycles or
61,600 total flight hours, whichever occurs earlier.
(2) Within 6 months after the effective date of this AD.
Credit for Actions Done in Accordance With Previous Service Bulletin
(i) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletin A330-53-3143, including
Appendix 01, dated December 24, 2004, are acceptable for compliance
with the corresponding requirements of paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(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
(k) EASA airworthiness directive 2006-0266, dated August 30,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Service Bulletin A330-53-3127, Revision
01, dated November 21, 2003; and Airbus Service Bulletin A330-53-
3143, Revision 01, including Appendix 01, dated June 29, 2006; as
applicable, 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 Airbus Service Bulletin A330-53-3143,
Revision 01, including Appendix 01, dated June 29, 2006, in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On October 19, 2005 (70 FR 57732, October 4, 2005), the
Director of the Federal Register approved the incorporation by
reference of Airbus Service Bulletin A330-53-3127, Revision 01,
dated November 21, 2003.
(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 FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; 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: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-4740 Filed 3-15-07; 8:45 am]
BILLING CODE 4910-13-P
