Airworthiness Directives; Airbus Airplanes, 73496-73501 [2011-29803]
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73496
Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
AD. Use the procedures found in 14 CFR
39.19 to make your request.
TABLE 1—AFFECTED HMUS—
Continued
P/Ns
S/Ns
0292860750
0292860750
0292860750
0292860750
0292861020
830B
861B
944B
967B
632B
Reason
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as:
Non-conformities on adjustment of some
hydromechanical units (HMUs) have been
reported by a Turbomeca repair centre. The
technical investigations carried out by
Turbomeca are showing that only a limited
number of HMUs are potentially affected by
this non-conformity to HMU adjustment.
Twenty nine HMUs have been identified
with potential non-conformities in the proper
adjustment of the metering valve. The exact
location of these 29 HMUs is unknown. We
are issuing this AD to prevent an
uncommanded inflight shutdown, which
could result in an emergency autorotation
landing.
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Actions and Compliance
(e) Unless already done, do the following
actions.
(f) Before further flight, perform a one-time
functional test of the engine to confirm
proper engine operation. This one-time
functional test is not a normal engine run-up
test. Use the instructions in paragraph
2.B.(1)(a) of Turbomeca Alert Mandatory
Service Bulletin No. A292 73 2841, Version
A, dated July 4, 2011, to perform the
functional test.
(1) If the engine fails the functional test,
replace the HMU with an HMU eligible for
installation.
(2) If the engine passes the functional test,
do the following:
(i) Within four months after the effective
date of this AD, install software modification
TU143 on the Engine Electronic Control Unit
of the engine. Use paragraph 2.B. of
Turbomeca Service Bulletin No. 292 73 2143,
dated July 24, 2007 to do the installation; and
(ii) Within 12 months after the effective
date of this AD, replace the HMU with an
HMU eligible for installation.
Definition
(g) For the purpose of this AD, an HMU
eligible for installation is defined as one with
a serial number not listed in Table 1 of this
AD, or, an HMU that passed when tested
using Turbomeca Service Bulletin No. 292 73
2840.
FAA AD Differences
(h) None.
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Engine Certification
Office, FAA, may approve AMOCs for this
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Related Information
(j) Refer to MCAI Airworthiness Directive
2011–0128–E, dated July 6, 2011, for related
information.
(k) Contact Mark Riley, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: (781) 238–7758; fax: (781)
238–7199, email: mark.riley@faa.gov; for
more information about this AD.
Material Incorporated by Reference
(l) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51 of the
following service information on the date
specified:
(1) Turbomeca Alert Mandatory Service
Bulletin No. A292 73 2841, Version A, dated
July 4, 2011, approved for IBR December 14,
2011.
(2) Turbomeca Service Bulletin No. 292 73
2143, dated July 24, 2007, approved for IBR
December 14, 2011.
(3) For service information identified in
this AD, contact Turbomeca S.A., 40220
Tarnos, France; phone: 33–05–59–74–40–00,
fax: 33–05–59–74–45–15.
(4) You may review copies of the service
information at the FAA, New England
Region, 12 New England Executive Park,
Burlington, MA. For information on the
availability of this material at the FAA, call
(781) 238–7125.
(5) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call (202) 741–
6030 or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts on
November 14, 2011.
Peter A. White,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2011–30574 Filed 11–28–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0717; Directorate
Identifier 2010–NM–108–AD; Amendment
39–16869; AD 2011–24–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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ACTION:
Final rule.
We are superseding an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A330–201, –202, –203, –223, –243,
–301, –302, –303, –321, –322, –323,
–341, –342, and –343 airplanes; and
Model A340–200 and –300 series
airplanes. This AD results from
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as:
SUMMARY:
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 3, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 3, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of September 13, 2007 (72 FR
44731, August 9, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on July 19, 2011 (76 FR 42602),
and proposed to supersede AD 2007–
16–02, Amendment 39–15141 (72 FR
44731, August 9, 2007). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
In order to maintain the structural integrity
of the aeroplane, EASA AD 2006–0315R1
required repetitive special detailed
inspections on the horizontal flange of the
keel beam in the area of first fastener hole aft
of FR40.
This [EASA] AD, which supersedes EASA
AD 2006–0315R1:
—Retains the inspection requirements of
EASA AD 2006–0315R1,
—Extends the AD applicability to aeroplanes
which have embodied Airbus modification
49202, and
—Modifies the inspection thresholds and
intervals.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the single comment
received.
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Request To Update Service Information
Airbus requested that we incorporate
the latest revisions of the primary
service bulletins, Airbus Mandatory
Service Bulletins A330–57–3081 and
A340–57–4089, both including
Appendix 01, both Revision 04, both
dated May 31, 2011, and give credit for
actions performed according to the
revisions of these service bulletins
specified in the NPRM (76 FR 42602,
July 19, 2011).
We agree to specify Revision 04, dated
May 31, 2011, of Airbus Mandatory
Service Bulletins A330–57–3081 and
A340–57–4089, and have changed
paragraphs (h), (j)(1), (j)(3), (n), (n)(1)(i),
(n)(1)(ii)(B), (n)(2)(ii), (p)(1), and (p)(2);
tables 1 and 3; and Notes 3 and 4; of this
AD accordingly. Revision 04 of those
service bulletins states that no
additional work is required for airplanes
modified by any previous issue of those
service bulletins. We have also added
Revision 03, dated July 31, 2009, of
those service bulletins to table 2 of this
AD, ‘‘Credit Service Information for
Certain Actions.’’
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
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Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect about
35 products of U.S. registry.
For the 9 airplanes affected by the
existing AD, the actions that are
required by AD 2007–16–02,
Amendment 39–15141 (72 FR 44731,
August 9, 2007), and retained in this AD
take about 41 work-hours per product,
at an average labor rate of $85 per work
hour. Required parts cost about $191 per
product. Based on these figures, the
estimated cost of the currently required
actions is $3,676 per product.
For the 26 additional airplanes added
in this AD, we estimate the actions in
this AD will take about 41 work-hours
per product, at an average labor rate of
$85 per work hour. Required parts will
cost about $191 per product. Based on
these figures, the estimated cost of the
proposed AD is $3,676 per product.
In addition, because this AD advises
to contact the manufacturer for repair
instructions, we cannot estimate the
parts or labor costs for any necessary
follow-on actions. We have no way of
determining the number of products
that may need these actions.
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
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73497
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 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 this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM (76 FR 42602, July
19, 2011), the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–15141 (72 FR
■
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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
44731, August 9, 2007) and adding the
following new AD:
2011–24–05 Airbus: Amendment 39–
16869. Docket No. FAA–2011–0717;
Directorate Identifier 2010–NM–108–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 3, 2012.
Affected ADs
(b) This AD supersedes AD 2007–16–02,
Amendment 39–15141 (72 FR 44731, August
9, 2007).
Applicability
(c) This AD applies to the airplanes
identified in paragraphs (c)(1) and (c)(2) of
this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330–201, –202, –203,
–223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
serial numbers, except those on which
Airbus modification 55306 or 55792 has been
embodied in production.
(2) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes, all serial
numbers, except those on which Airbus
modification 55306 or 55792 has been
embodied in production.
(3) This AD is not applicable to Airbus
Model A340–211, –212, –213, –311, –312,
and –313 airplanes on which the repair
specified in Airbus Repair Drawing
R57115053, R57115051, or R57115047
(installation of titanium doubler on both
sides) has been accomplished. AD 2007–12–
08, Amendment 39–15086 (72 FR 31171,
June 6, 2007), applies to these airplanes.
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During A330 and A340 aeroplanes fatigue
tests, cracks appeared on the right (RH) and
left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the
Centre Wing Box (CWB). This condition, if
not corrected, could lead to keel beam
rupture which would affect the area
structural integrity.
*
*
*
*
*
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2007–
16–02, Amendment 39–15141 (72 FR 44731,
August 9, 2007) With Revised Service
Information
(g) For Model A330–201, –202, –203, –223,
–243, –301, –321, –322, –323, –341, –342,
and –343 airplanes, except those on which
Airbus modification 49202 has been
embodied in production, or Airbus Service
Bulletin A330–57–3090 has been embodied
in service, and Model A340–200 and –300
series airplanes, except those on which
Airbus modification 49202 has been
embodied in production or Airbus Service
Bulletin A340–57–4098 has been embodied
in service, and except Model A340–211,
–212, –213, –311, –312, and –313 airplanes
on which the repair specified in Airbus
Repair Drawing R57115053, R57115051, or
R57115047 has been accomplished: Do the
actions required by paragraphs (h), (l), and
(m) of this AD.
(h) For airplanes identified in paragraph (g)
of this AD, within the mandatory threshold
(flight cycles or flight hours) mentioned in
the paragraph 1.E.(2) of Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 02; or A330–57–3081, including
Appendix 01, Revision 02; both dated
January 24, 2006; depending on the
configuration of the aircraft model; or within
3 months after September 13, 2007 (the
effective date of AD 2007–16–02 (72 FR
44731, August 9, 2007)); whichever occurs
later: Carry out the NDT (non-destructive
test) inspection of the hole(s) of the
horizontal flange of the keel beam located on
FR 40 datum on RH (right-hand) and/or LH
(left-hand) side of the fuselage, in accordance
with the instructions of the applicable
service bulletin listed in table 1 of this AD.
After the effective date of this AD, use only
Airbus Mandatory Service Bulletin A330–57–
3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory
Service Bulletin A340–57–4089, including
Appendix 01, Revision 04, dated May 31,
2011; as applicable. Inspection in accordance
with Airbus A330/A340 200–300 Technical
Disposition F57D03012810, Issue B, dated
August 18, 2003; or Airbus A330/A340
Technical Disposition 582.0651/2002, Issue
A, dated October 17, 2002; satisfies the
inspection requirements for the first rotating
probe inspection which is specified at the
inspection threshold of this AD. Doing the
inspection required by paragraph (n) of this
AD terminates the requirements of this
paragraph of this AD.
Note 1: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above inspection according to
recommended thresholds mentioned in
paragraph 1.E.(2) of Airbus Service Bulletin
A340–57–4089, including Appendix 01,
Revision 02; or Airbus Service Bulletin
A330–57–3081, including Appendix 01,
Revision 02; both dated January 24, 2006.
TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR CERTAIN REQUIREMENTS OF PARAGRAPH (H) OF THIS AD
Document
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Airbus
Airbus
Airbus
Airbus
Revision
Service Bulletin A330–57–3081, including Appendix 01 .................................................................
Mandatory Service Bulletin A330–57–3081, including Appendix 01 ...............................................
Service Bulletin A340–57–4089, including Appendix 01 .................................................................
Mandatory Service Bulletin A340–57–4089, including Appendix 01 ...............................................
(i) In case of any crack finding during the
inspection required by paragraph (h) of this
AD, before further flight, contact Airbus in
order to get repair instructions before next
flight, and repair before further flight.
(j) Should no crack be detected during the
inspection required by paragraph (h) of this
AD:
(1) Before further flight: Follow up the
actions indicated in the flow charts, Figure
7, 8, or 9, of Airbus Service Bulletin A340–
57–4089, including Appendix 01, Revision
02, dated January 24, 2006, or Airbus
Mandatory Service Bulletin A340–57–4089,
including Appendix 01, Revision 04, dated
May 31, 2011; or Figure 5, 6, or 7, of Airbus
Service Bulletin A330–57–3081, including
Appendix 01, Revision 02, dated January 24,
2006, or Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
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Revision 04, dated May 31, 2011; in
accordance with the instructions of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006, or Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus
Service Bulletin A330–57–3081, including
Appendix 01, Revision 02, dated January 24,
2006, or Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011; as
applicable.
(2) Within 30 days after September 13,
2007, or within 30 days after doing the
inspection required by paragraph (h) of this
AD, whichever occurs later: Send the report
of actions carried out in paragraph (j)(1) of
this AD to Airbus.
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Date
02
04
02
04
January 24, 2006.
May 31, 2011.
January 24, 2006.
May 31, 2011.
(3) Renew the inspection at mandatory
intervals given in paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006; or Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 02,
dated January 24, 2006; as applicable; in
accordance with the instructions of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006, or Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus
Service Bulletin A330–57–3081, including
Appendix 01, Revision 02, dated January 24,
2006, or Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011; as
applicable; and send the inspection results to
Airbus. Doing the inspection required by
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paragraph (n) of this AD terminates the
requirements of this paragraph of this AD.
Note 2: In order to prevent large repairs or
heavy maintenance, Airbus recommends to
perform the above repetitive inspection
according to recommended intervals
mentioned in paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
2006; or Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 02,
dated January 24, 2006.
(k) Upon detection of a crack during a
repetitive inspection required by paragraph
(j)(3) of this AD, before further flight, contact
Airbus to get repair instructions, and repair
before further flight.
(l) For airplanes identified in paragraph (g)
of this AD: No additional work is required for
compliance with paragraph (h) of this AD for
aircraft on which the inspection specified in
Airbus Service Bulletin A330–57–3081,
dated October 30, 2003, or Revision 01, dated
May 18, 2004; or Airbus Service Bulletin
A340–57–4089, dated October 30, 2003, or
Revision 01, dated March 2, 2004, has been
accomplished. Nevertheless, the operators
must check that their inspection program is
in accordance with paragraph 1.E.(2) of
Airbus Service Bulletin A340–57–4089,
including Appendix 01, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin
A330–57–3081, including Appendix 01,
Revision 02, dated January 24, 2006; as
applicable; for the repetitive inspection.
(m) For airplanes identified in paragraph
(g) of this AD on which Airbus Modification
41652 is not embodied: When the aircraft has
been modified in accordance with Airbus
Service Bulletin A330–57–3090, dated March
27, 2006; or Airbus Service Bulletin A340–
57–4098, dated March 27, 2006; as
applicable; the repetitive inspections
required by this AD are cancelled. In case of
any crack finding during the modification:
Where the applicable service bulletin
specifies to contact Airbus, before further
flight, contact Airbus to get repair
instructions, and repair.
New Requirements of This AD
(n) At the applicable time in paragraph
(n)(1) or (n)(2) of this AD: Do an NDT
inspection of the hole(s) of the horizontal
flange of the keel beam located on FR 40
datum on RH and/or LH side of the fuselage,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–57–3081, including Appendix
01, Revision 04, dated May 31, 2011; or
Airbus Mandatory Service Bulletin A340–57–
4089, including Appendix 01, Revision 04,
dated May 31, 2011; as applicable. Inspection
in accordance with Airbus A330/A340 200–
300 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003; or Airbus
A330/A340 Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002; is
acceptable for compliance with the
inspection requirements for the first rotating
probe inspection required by this paragraph.
Doing the inspection required by this
paragraph terminates the requirements of
paragraphs (h) and (j)(3) of this AD.
(1) For airplanes on which an inspection
required by paragraph (h) of this AD has not
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been done as of the effective date of this AD:
At the applicable time specified in paragraph
(n)(1)(i) or (n)(1)(ii) of this AD.
(i) For all airplanes except those identified
in paragraph (g) of this AD: Within the
‘‘Mandatory Threshold’’ (flight cycles or
flight hours) specified in table 1 of paragraph
1.E.(2) of the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330–57–
3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory
Service Bulletin A340–57–4089, including
Appendix 01, Revision 04, dated May 31,
2011; as applicable; or within 3 months after
the effective date of this AD; whichever
occurs later. The compliance times for
configurations 02 through 06 specified in the
‘‘Mandatory Threshold’’ column in table 1 of
paragraph 1.E., ‘‘Compliance,’’ are total flight
cycles and total flight hours.
(ii) For airplanes identified in paragraph (g)
of this AD: At the earlier of the times
specified in paragraphs (n)(1)(ii)(A) and
(n)(1)(ii)(B) of this AD.
(A) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340–57–4089, including Appendix
01, Revision 02, dated January 24, 2006; or
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006; depending on the
configuration of the aircraft model; or within
3 months after September 13, 2007;
whichever occurs later. The compliance
times for Model A330 post-mod. No. 41652
and pre-mod. No. 44360, post-mod. No.
44360, and pre-mod. No. 49202 (specified in
Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006); and Model A340 postmod. No. 41652, post-mod. No. 43500 and
pre-mod. No. 44360, post-mod. No. 44360
and pre-mod. No. 49202, and Weight Variant
027 (specified in Airbus Service Bulletin
A340–57–4089, including Appendix 01,
Revision 02, dated January 24, 2006);
specified in the ‘‘Mandatory Threshold’’
column in table 1 of paragraph 1.E.,
‘‘Compliance,’’ are total flight cycles and
total flight hours.
(B) Within the ‘‘Mandatory Threshold’’
(flight cycles or flight hours) specified in
table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–57–3081,
including Appendix 01, Revision 04, dated
May 31, 2011; or Airbus Mandatory Service
Bulletin A340–57–4089, including Appendix
01, Revision 04, dated May 31, 2011; as
applicable; or within 3 months after the
effective date of this AD; whichever occurs
later. The compliance times for
configurations 02 through 06 specified in the
‘‘Mandatory Threshold’’ column in table 1 of
paragraph 1.E., ‘‘Compliance,’’ are total flight
cycles and total flight hours.
(2) For airplanes on which an inspection
required by paragraph (h) of this AD has been
done as of the effective date of this AD: At
the earlier of the times specified in
paragraphs (n)(2)(i) and (n)(2)(ii) of this AD.
(i) Within the ‘‘Mandatory Intervals’’ given
in table 1 of paragraph 1.E.(2) of Airbus
Service Bulletin A340–57–4089, including
Appendix 01, Revision 02, dated January 24,
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
73499
2006; or Airbus Service Bulletin A330–57–
3081, including Appendix 01, Revision 02,
dated January 24, 2006; as applicable.
(ii) Within the applicable ‘‘Mandatory
Interval’’ specified in table 1 of Paragraph
1.E.(2). of Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus
Mandatory Service Bulletin A340–57–4089,
including Appendix 01, Revision 04, dated
May 31, 2011; as applicable; or within 3
months after the effective date of this AD;
whichever occurs later.
Note 3: To prevent large repairs or heavy
maintenance, Airbus recommends to perform
the above inspection according to
recommended thresholds specified in
paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330–57–3081, including
Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011; as
applicable.
(o) If any cracking is found during any
inspection required by paragraph (n) of this
AD, before further flight, repair in accordance
with a method approved by the International
Branch, ANM–116, Transport Airplane
Directorate, FAA, or European Aviation
Safety Agency (EASA) (or its delegated
agent).
(p) If no cracking is found during any
inspection required by paragraph (n) of this
AD, do the actions required by paragraphs
(p)(1) and (p)(2) of this AD.
(1) Before further flight: Install new or
oversized fastener, as applicable; seal the
fastener; and do all other applicable actions;
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–57–3081, including Appendix
01, Revision 04, dated May 31, 2011; or
Airbus Mandatory Service Bulletin A340–57–
4089, including Appendix 01, Revision 04,
dated May 31, 2011; as applicable.
(2) Repeat the inspection required by
paragraph (n) of this AD thereafter at
intervals not to exceed the mandatory
intervals specified in Paragraph 1.E.(2). of
Airbus Mandatory Service Bulletin A330–57–
3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory
Service Bulletin A340–57–4089, including
Appendix 01, Revision 04, dated May 31,
2011; as applicable.
Note 4: To prevent large repairs or heavy
maintenance, Airbus recommends to perform
the above repetitive inspection according to
recommended intervals mentioned in
paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330–57–3081, including
Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011; as
applicable.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(q) Inspections done before the effective
date of this AD in accordance with the
service information specified in table 2 of
this AD are acceptable for compliance with
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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
the corresponding inspection required by
paragraph (n) of this AD.
TABLE 2—CREDIT SERVICE INFORMATION FOR CERTAIN ACTIONS
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
Service Bulletin A330–57–3081, including Appendix 01 .................................................................
Mandatory Service Bulletin A330–57–3081 .....................................................................................
Service Bulletin A340–57–4089, including Appendix 01 .................................................................
Mandatory Service Bulletin A340–57–4089 .....................................................................................
Service Bulletin A330–57–3081 .......................................................................................................
Service Bulletin A330–57–3081 .......................................................................................................
Service Bulletin A340–57–4089 .......................................................................................................
Service Bulletin A340–57–4089 .......................................................................................................
(r) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3098, dated August 30, 2007; or
Airbus Service Bulletin A340–57–4106,
dated August 30, 2007; as applicable; before
the effective date of this AD terminates the
requirements of this AD; except for airplanes
on which a crack was detected at hole 5
before oversizing of the keel beam (in
accordance with step 3.B.(1)(b)3 of the
Accomplishment Instructions of Airbus
Service Bulletin A330–57–3098, dated
August 30, 2007; or Airbus Service Bulletin
A340–57–4106, dated August 30, 2007),
before further flight, repair in accordance
with a method approved by the International
Branch, ANM–116, Transport Airplane
Directorate, FAA, or EASA (or its delegated
agent).
(s) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3098, excluding Appendix 1,
Revision 01, dated July 31, 2009; or Airbus
Service Bulletin A340–57–4106, excluding
Appendix 1, Revision 01, dated July 31,
2009; as applicable; terminates the
requirements of this AD.
(t) Modifying the fasteners installation in
the junction keel beam fitting at FR 40, in
accordance with Airbus Service Bulletin
A330–57–3090, dated March 27, 2006; or
Airbus Service Bulletin A340–57–4098,
dated March 27, 2006; as applicable;
terminates the requirements of this AD.
(u) In case of any crack finding during any
modification specified paragraphs (r), (s), and
(t) of this AD: Where the applicable service
bulletin specifies to contact Airbus, before
further flight, repair in accordance with a
method approved by the International
Branch, FAA, or EASA (or its delegated
agent).
FAA AD Differences
Note 5: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(v) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
02
03
02
03
........................
01
........................
01
Date
January 24, 2006.
July 31, 2009.
January 24, 2006.
July 31, 2009.
October 30, 2003.
May 18, 2004.
October 30, 2003.
March 2, 2004.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(w) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2010–
0024, dated February 12, 2010, and the
applicable service information specified in
table 3 of this AD, for related information.
TABLE 3—RELATED SERVICE INFORMATION
pmangrum on DSK3VPTVN1PROD with RULES
Document
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Revision
Service Bulletin A330–57–3081, including Appendix 01 .................................................................
Mandatory Service Bulletin A330–57–3081, including Appendix 01 ...............................................
Service Bulletin A340–57–4089, including Appendix 01 .................................................................
Mandatory Service Bulletin A340–57–4089, including Appendix 01 ...............................................
Service Bulletin A330–57–3090 .......................................................................................................
Service Bulletin A330–57–3098, excluding Appendix 1 ..................................................................
Service Bulletin A340–57–4106, excluding Appendix 1 ..................................................................
Service Bulletin A340–57–4098 .......................................................................................................
A330/A340 200–300 Technical Disposition F57D03012810 ...........................................................
A330/A340 Technical Disposition 582.0651/2002 ...........................................................................
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Fmt 4700
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E:\FR\FM\29NOR1.SGM
02
04
02
04
........................
01
01
........................
Issue B
Issue A
29NOR1
Date
January 24, 2006.
May 31, 2011.
January 24, 2006.
May 31, 2011.
March 27, 2006.
July 31, 2009.
July 31, 2009.
March 27, 2006.
August 18, 2003.
October 17, 2002.
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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations
Material Incorporated by Reference
(x) You must use the following service
information specified in paragraphs (x)(1),
(x)(2), (x)(7), (x)(8), (x)(9), and (x)(10) of this
AD, as applicable, to do the actions required
by this AD, unless the AD specifies
otherwise. If you accomplish the optional
actions specified by this AD, you must use
the service information specified in
paragraphs (x)(3), (x)(4), (x)(5), (x)(6), (x)(9),
and (x)(10) of this AD, as applicable, to
perform those actions, unless the AD
specifies otherwise. The Director of the
Federal Register approved the incorporation
by reference (IBR) under 5 U.S.C. 552(a) and
1 CFR part 51 of the following service
information on the date specified:
(1) Airbus Mandatory Service Bulletin
A330–57–3081, including Appendix 01,
Revision 04, dated May 31, 2011, approved
for IBR January 3, 2012.
(2) Airbus Mandatory Service Bulletin
A340–57–4089, including Appendix 01,
Revision 04, dated May 31, 2011, approved
for IBR January 3, 2012.
(3) Airbus Service Bulletin A330–57–3098,
excluding Appendix 1, Revision 01, dated
July 31, 2009, approved for IBR January 3,
2012.
(4) Airbus Service Bulletin A340–57–4106,
excluding Appendix 1, Revision 01, dated
July 31, 2009, approved for IBR January 3,
2012.
(5) Airbus A330/A340 200–300 Technical
Disposition F57D03012810, Issue B, dated
August 18, 2003, approved for IBR January 3,
2012.
(6) Airbus A330/A340 Technical
Disposition 582.0651/2002, Issue A, dated
October 17, 2002, approved for IBR January
3, 2012.
(7) Airbus Service Bulletin A330–57–3081,
including Appendix 01, Revision 02, dated
January 24, 2006, approved for IBR
September 13, 2007 (72 FR 44731, August 9,
2007).
(8) Airbus Service Bulletin A340–57–4089,
including Appendix 01, Revision 02, dated
January 24, 2006, approved for IBR
September 13, 2007 (72 FR 44731, August 9,
2007).
(9) Airbus Service Bulletin A330–57–3090,
March 27, 2006, approved for IBR September
13, 2007 (72 FR 44731, August 9, 2007).
(10) Airbus Service Bulletin A340–57–
4098, March 27, 2006, approved for IBR
September 13, 2007 (72 FR 44731, August 9,
2007).
(11) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com.
(12) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
(425) 227–1221.
(13) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
VerDate Mar<15>2010
14:37 Nov 28, 2011
Jkt 226001
73501
material at an NARA facility, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
71.1. The Class E airspace designations
listed in this document will be
published subsequently in the Order.
Issued in Renton, Washington, on
November 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
The Rule
[FR Doc. 2011–29803 Filed 11–28–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2011–0845; Airspace
Docket No. 11–ACE–19]
Amendment of Class E Airspace;
Carroll, IA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends Class E
airspace for Carroll, IA.
Decommissioning of the Carroll nondirectional beacon (NDB) at Arthur N.
Neu Airport, Carroll, IA, has made this
action necessary to enhance the safety
and management of Instrument Flight
Rule (IFR) operations at the airport.
DATES: Effective date: 0901 UTC,
February 9, 2012. The Director of the
Federal Register approves this
incorporation by reference action under
1 CFR Part 51, subject to the annual
revision of FAA Order 7400.9 and
publication of conforming amendments.
FOR FURTHER INFORMATION CONTACT:
Scott Enander, Central Service Center,
Operations Support Group, Federal
Aviation Administration, Southwest
Region, 2601 Meacham Blvd., Fort
Worth, TX 76137; telephone (817) 321–
7716.
SUPPLEMENTARY INFORMATION:
SUMMARY:
History
On August 26, 2011, the FAA
published in the Federal Register a
notice of proposed rulemaking to amend
Class E airspace for Carroll, IA,
reconfiguring controlled airspace at
Arthur N. Neu Airport (76 FR 53353)
Docket No. FAA–2011–0845. Interested
parties were invited to participate in
this rulemaking effort by submitting
written comments on the proposal to the
FAA. No comments were received. Class
E airspace designations are published in
paragraph 6005 of FAA Order 7400.9V
dated August 9, 2011, and effective
September 15, 2011, which is
incorporated by reference in 14 CFR
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
This action amends Title 14 Code of
Federal Regulations (14 CFR) part 71 by
amending Class E airspace extending
upward from 700 feet above the surface
for the Carroll, IA area.
Decommissioning of the Carroll NDB
and cancellation of the NDB approach at
Arthur N. Neu Airport has made
reconfiguration of the airspace
necessary for the safety and
management of IFR operations at the
airport.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation: (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)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this rule, when
promulgated, will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the U.S. Code. Subtitle 1,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the agency’s
authority. This rulemaking is
promulgated under the authority
described in subtitle VII, part A, subpart
I, section 40103. Under that section, the
FAA is charged with prescribing
regulations to assign the use of airspace
necessary to ensure the safety of aircraft
and the efficient use of airspace. This
regulation is within the scope of that
authority as it amends controlled
airspace at Arthur N. Neu Airport,
Carroll, IA.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (air).
Adoption of the Amendment
In consideration of the foregoing, the
Federal Aviation Administration
amends 14 CFR part 71 as follows:
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]]>Agencies
[Federal Register Volume 76, Number 229 (Tuesday, November 29, 2011)]
[Rules and Regulations]
[Pages 73496-73501]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-29803]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0717; Directorate Identifier 2010-NM-108-AD;
Amendment 39-16869; AD 2011-24-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
that applies to certain Airbus Model A330-201, -202, -203, -223, -243,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and
Model A340-200 and -300 series airplanes. This AD results from
mandatory continuing airworthiness information (MCAI) originated by an
aviation authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective January 3, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 3,
2012.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
September 13, 2007 (72 FR 44731, August 9, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on July 19, 2011 (76 FR
42602), and proposed to supersede AD 2007-16-02, Amendment 39-15141 (72
FR 44731, August 9, 2007). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
[[Page 73497]]
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
In order to maintain the structural integrity of the aeroplane,
EASA AD 2006-0315R1 required repetitive special detailed inspections
on the horizontal flange of the keel beam in the area of first
fastener hole aft of FR40.
This [EASA] AD, which supersedes EASA AD 2006-0315R1:
--Retains the inspection requirements of EASA AD 2006-0315R1,
--Extends the AD applicability to aeroplanes which have embodied
Airbus modification 49202, and
--Modifies the inspection thresholds and intervals.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the single comment received.
Request To Update Service Information
Airbus requested that we incorporate the latest revisions of the
primary service bulletins, Airbus Mandatory Service Bulletins A330-57-
3081 and A340-57-4089, both including Appendix 01, both Revision 04,
both dated May 31, 2011, and give credit for actions performed
according to the revisions of these service bulletins specified in the
NPRM (76 FR 42602, July 19, 2011).
We agree to specify Revision 04, dated May 31, 2011, of Airbus
Mandatory Service Bulletins A330-57-3081 and A340-57-4089, and have
changed paragraphs (h), (j)(1), (j)(3), (n), (n)(1)(i), (n)(1)(ii)(B),
(n)(2)(ii), (p)(1), and (p)(2); tables 1 and 3; and Notes 3 and 4; of
this AD accordingly. Revision 04 of those service bulletins states that
no additional work is required for airplanes modified by any previous
issue of those service bulletins. We have also added Revision 03, dated
July 31, 2009, of those service bulletins to table 2 of this AD,
``Credit Service Information for Certain Actions.''
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a Note within the AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect about 35 products of U.S. registry.
For the 9 airplanes affected by the existing AD, the actions that
are required by AD 2007-16-02, Amendment 39-15141 (72 FR 44731, August
9, 2007), and retained in this AD take about 41 work-hours per product,
at an average labor rate of $85 per work hour. Required parts cost
about $191 per product. Based on these figures, the estimated cost of
the currently required actions is $3,676 per product.
For the 26 additional airplanes added in this AD, we estimate the
actions in this AD will take about 41 work-hours per product, at an
average labor rate of $85 per work hour. Required parts will cost about
$191 per product. Based on these figures, the estimated cost of the
proposed AD is $3,676 per product.
In addition, because this AD advises to contact the manufacturer
for repair instructions, we cannot estimate the parts or labor costs
for any necessary follow-on actions. We have no way of determining the
number of products that may need these actions.
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 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 this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (76 FR 42602, July 19, 2011),
the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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:
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 FAA amends Sec. 39.13 by removing Amendment 39-15141 (72 FR
[[Page 73498]]
44731, August 9, 2007) and adding the following new AD:
2011-24-05 Airbus: Amendment 39-16869. Docket No. FAA-2011-0717;
Directorate Identifier 2010-NM-108-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
3, 2012.
Affected ADs
(b) This AD supersedes AD 2007-16-02, Amendment 39-15141 (72 FR
44731, August 9, 2007).
Applicability
(c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD; certificated in any category; except
as provided by paragraph (c)(3) of this AD.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial
numbers, except those on which Airbus modification 55306 or 55792
has been embodied in production.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, all serial numbers, except those on which Airbus
modification 55306 or 55792 has been embodied in production.
(3) This AD is not applicable to Airbus Model A340-211, -212, -
213, -311, -312, and -313 airplanes on which the repair specified in
Airbus Repair Drawing R57115053, R57115051, or R57115047
(installation of titanium doubler on both sides) has been
accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June
6, 2007), applies to these airplanes.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During A330 and A340 aeroplanes fatigue tests, cracks appeared
on the right (RH) and left (LH) sides between the crossing area of
the keel beam fitting and the front spar of the Centre Wing Box
(CWB). This condition, if not corrected, could lead to keel beam
rupture which would affect the area structural integrity.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2007-16-02, Amendment 39-15141 (72 FR
44731, August 9, 2007) With Revised Service Information
(g) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which
Airbus modification 49202 has been embodied in production, or Airbus
Service Bulletin A330-57-3090 has been embodied in service, and
Model A340-200 and -300 series airplanes, except those on which
Airbus modification 49202 has been embodied in production or Airbus
Service Bulletin A340-57-4098 has been embodied in service, and
except Model A340-211, -212, -213, -311, -312, and -313 airplanes on
which the repair specified in Airbus Repair Drawing R57115053,
R57115051, or R57115047 has been accomplished: Do the actions
required by paragraphs (h), (l), and (m) of this AD.
(h) For airplanes identified in paragraph (g) of this AD, within
the mandatory threshold (flight cycles or flight hours) mentioned in
the paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089,
including Appendix 01, Revision 02; or A330-57-3081, including
Appendix 01, Revision 02; both dated January 24, 2006; depending on
the configuration of the aircraft model; or within 3 months after
September 13, 2007 (the effective date of AD 2007-16-02 (72 FR
44731, August 9, 2007)); whichever occurs later: Carry out the NDT
(non-destructive test) inspection of the hole(s) of the horizontal
flange of the keel beam located on FR 40 datum on RH (right-hand)
and/or LH (left-hand) side of the fuselage, in accordance with the
instructions of the applicable service bulletin listed in table 1 of
this AD. After the effective date of this AD, use only Airbus
Mandatory Service Bulletin A330-57-3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; as applicable. Inspection in accordance with Airbus A330/
A340 200-300 Technical Disposition F57D03012810, Issue B, dated
August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002; satisfies the inspection
requirements for the first rotating probe inspection which is
specified at the inspection threshold of this AD. Doing the
inspection required by paragraph (n) of this AD terminates the
requirements of this paragraph of this AD.
Note 1: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above inspection according to
recommended thresholds mentioned in paragraph 1.E.(2) of Airbus
Service Bulletin A340-57-4089, including Appendix 01, Revision 02;
or Airbus Service Bulletin A330-57-3081, including Appendix 01,
Revision 02; both dated January 24, 2006.
Table 1--Acceptable Service Information for Certain Requirements of
Paragraph (h) of This AD
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Service Bulletin A330- 02 January 24, 2006.
57-3081, including Appendix
01.
Airbus Mandatory Service 04 May 31, 2011.
Bulletin A330-57-3081,
including Appendix 01.
Airbus Service Bulletin A340- 02 January 24, 2006.
57-4089, including Appendix
01.
Airbus Mandatory Service 04 May 31, 2011.
Bulletin A340-57-4089,
including Appendix 01.
------------------------------------------------------------------------
(i) In case of any crack finding during the inspection required
by paragraph (h) of this AD, before further flight, contact Airbus
in order to get repair instructions before next flight, and repair
before further flight.
(j) Should no crack be detected during the inspection required
by paragraph (h) of this AD:
(1) Before further flight: Follow up the actions indicated in
the flow charts, Figure 7, 8, or 9, of Airbus Service Bulletin A340-
57-4089, including Appendix 01, Revision 02, dated January 24, 2006,
or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; or Figure 5, 6, or 7,
of Airbus Service Bulletin A330-57-3081, including Appendix 01,
Revision 02, dated January 24, 2006, or Airbus Mandatory Service
Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May
31, 2011; in accordance with the instructions of Airbus Service
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated
January 24, 2006, or Airbus Mandatory Service Bulletin A340-57-4089,
including Appendix 01, Revision 04, dated May 31, 2011; or Airbus
Service Bulletin A330-57-3081, including Appendix 01, Revision 02,
dated January 24, 2006, or Airbus Mandatory Service Bulletin A330-
57-3081, including Appendix 01, Revision 04, dated May 31, 2011; as
applicable.
(2) Within 30 days after September 13, 2007, or within 30 days
after doing the inspection required by paragraph (h) of this AD,
whichever occurs later: Send the report of actions carried out in
paragraph (j)(1) of this AD to Airbus.
(3) Renew the inspection at mandatory intervals given in
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006; as applicable; in accordance with the instructions
of Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 02, dated January 24, 2006, or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; or Airbus Service Bulletin A330-57-3081, including
Appendix 01, Revision 02, dated January 24, 2006, or Airbus
Mandatory Service Bulletin A330-57-3081, including Appendix 01,
Revision 04, dated May 31, 2011; as applicable; and send the
inspection results to Airbus. Doing the inspection required by
[[Page 73499]]
paragraph (n) of this AD terminates the requirements of this
paragraph of this AD.
Note 2: In order to prevent large repairs or heavy maintenance,
Airbus recommends to perform the above repetitive inspection
according to recommended intervals mentioned in paragraph 1.E.(2) of
Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 02, dated January 24, 2006; or Airbus Service Bulletin
A330-57-3081, including Appendix 01, Revision 02, dated January 24,
2006.
(k) Upon detection of a crack during a repetitive inspection
required by paragraph (j)(3) of this AD, before further flight,
contact Airbus to get repair instructions, and repair before further
flight.
(l) For airplanes identified in paragraph (g) of this AD: No
additional work is required for compliance with paragraph (h) of
this AD for aircraft on which the inspection specified in Airbus
Service Bulletin A330-57-3081, dated October 30, 2003, or Revision
01, dated May 18, 2004; or Airbus Service Bulletin A340-57-4089,
dated October 30, 2003, or Revision 01, dated March 2, 2004, has
been accomplished. Nevertheless, the operators must check that their
inspection program is in accordance with paragraph 1.E.(2) of Airbus
Service Bulletin A340-57-4089, including Appendix 01, Revision 02,
dated January 24, 2006; or Airbus Service Bulletin A330-57-3081,
including Appendix 01, Revision 02, dated January 24, 2006; as
applicable; for the repetitive inspection.
(m) For airplanes identified in paragraph (g) of this AD on
which Airbus Modification 41652 is not embodied: When the aircraft
has been modified in accordance with Airbus Service Bulletin A330-
57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-
4098, dated March 27, 2006; as applicable; the repetitive
inspections required by this AD are cancelled. In case of any crack
finding during the modification: Where the applicable service
bulletin specifies to contact Airbus, before further flight, contact
Airbus to get repair instructions, and repair.
New Requirements of This AD
(n) At the applicable time in paragraph (n)(1) or (n)(2) of this
AD: Do an NDT inspection of the hole(s) of the horizontal flange of
the keel beam located on FR 40 datum on RH and/or LH side of the
fuselage, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-57-3081, including Appendix
01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; as applicable. Inspection in accordance with Airbus A330/
A340 200-300 Technical Disposition F57D03012810, Issue B, dated
August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002; is acceptable for compliance
with the inspection requirements for the first rotating probe
inspection required by this paragraph. Doing the inspection required
by this paragraph terminates the requirements of paragraphs (h) and
(j)(3) of this AD.
(1) For airplanes on which an inspection required by paragraph
(h) of this AD has not been done as of the effective date of this
AD: At the applicable time specified in paragraph (n)(1)(i) or
(n)(1)(ii) of this AD.
(i) For all airplanes except those identified in paragraph (g)
of this AD: Within the ``Mandatory Threshold'' (flight cycles or
flight hours) specified in table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or
within 3 months after the effective date of this AD; whichever
occurs later. The compliance times for configurations 02 through 06
specified in the ``Mandatory Threshold'' column in table 1 of
paragraph 1.E., ``Compliance,'' are total flight cycles and total
flight hours.
(ii) For airplanes identified in paragraph (g) of this AD: At
the earlier of the times specified in paragraphs (n)(1)(ii)(A) and
(n)(1)(ii)(B) of this AD.
(A) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated
January 24, 2006; or Airbus Service Bulletin A330-57-3081, including
Appendix 01, Revision 02, dated January 24, 2006; depending on the
configuration of the aircraft model; or within 3 months after
September 13, 2007; whichever occurs later. The compliance times for
Model A330 post-mod. No. 41652 and pre-mod. No. 44360, post-mod. No.
44360, and pre-mod. No. 49202 (specified in Airbus Service Bulletin
A330-57-3081, including Appendix 01, Revision 02, dated January 24,
2006); and Model A340 post-mod. No. 41652, post-mod. No. 43500 and
pre-mod. No. 44360, post-mod. No. 44360 and pre-mod. No. 49202, and
Weight Variant 027 (specified in Airbus Service Bulletin A340-57-
4089, including Appendix 01, Revision 02, dated January 24, 2006);
specified in the ``Mandatory Threshold'' column in table 1 of
paragraph 1.E., ``Compliance,'' are total flight cycles and total
flight hours.
(B) Within the ``Mandatory Threshold'' (flight cycles or flight
hours) specified in table 1 of paragraph 1.E.(2) of the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or
within 3 months after the effective date of this AD; whichever
occurs later. The compliance times for configurations 02 through 06
specified in the ``Mandatory Threshold'' column in table 1 of
paragraph 1.E., ``Compliance,'' are total flight cycles and total
flight hours.
(2) For airplanes on which an inspection required by paragraph
(h) of this AD has been done as of the effective date of this AD: At
the earlier of the times specified in paragraphs (n)(2)(i) and
(n)(2)(ii) of this AD.
(i) Within the ``Mandatory Intervals'' given in table 1 of
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated
January 24, 2006; as applicable.
(ii) Within the applicable ``Mandatory Interval'' specified in
table 1 of Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or
within 3 months after the effective date of this AD; whichever
occurs later.
Note 3: To prevent large repairs or heavy maintenance, Airbus
recommends to perform the above inspection according to recommended
thresholds specified in paragraph 1.E.(2) of Airbus Mandatory
Service Bulletin A330-57-3081, including Appendix 01, Revision 04,
dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-
4089, including Appendix 01, Revision 04, dated May 31, 2011; as
applicable.
(o) If any cracking is found during any inspection required by
paragraph (n) of this AD, before further flight, repair in
accordance with a method approved by the International Branch, ANM-
116, Transport Airplane Directorate, FAA, or European Aviation
Safety Agency (EASA) (or its delegated agent).
(p) If no cracking is found during any inspection required by
paragraph (n) of this AD, do the actions required by paragraphs
(p)(1) and (p)(2) of this AD.
(1) Before further flight: Install new or oversized fastener, as
applicable; seal the fastener; and do all other applicable actions;
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-57-3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; as applicable.
(2) Repeat the inspection required by paragraph (n) of this AD
thereafter at intervals not to exceed the mandatory intervals
specified in Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin
A330-57-3081, including Appendix 01, Revision 04, dated May 31,
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011; as applicable.
Note 4: To prevent large repairs or heavy maintenance, Airbus
recommends to perform the above repetitive inspection according to
recommended intervals mentioned in paragraph 1.E.(2) of Airbus
Mandatory Service Bulletin A330-57-3081, including Appendix 01,
Revision 04, dated May 31, 2011; or Airbus Mandatory Service
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May
31, 2011; as applicable.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(q) Inspections done before the effective date of this AD in
accordance with the service information specified in table 2 of this
AD are acceptable for compliance with
[[Page 73500]]
the corresponding inspection required by paragraph (n) of this AD.
Table 2--Credit Service Information for Certain Actions
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Service Bulletin A330- 02 January 24, 2006.
57-3081, including Appendix
01.
Airbus Mandatory Service 03 July 31, 2009.
Bulletin A330-57-3081.
Airbus Service Bulletin A340- 02 January 24, 2006.
57-4089, including Appendix
01.
Airbus Mandatory Service 03 July 31, 2009.
Bulletin A340-57-4089.
Airbus Service Bulletin A330- .............. October 30, 2003.
57-3081.
Airbus Service Bulletin A330- 01 May 18, 2004.
57-3081.
Airbus Service Bulletin A340- .............. October 30, 2003.
57-4089.
Airbus Service Bulletin A340- 01 March 2, 2004.
57-4089.
------------------------------------------------------------------------
(r) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3098, dated August 30, 2007; or Airbus Service Bulletin
A340-57-4106, dated August 30, 2007; as applicable; before the
effective date of this AD terminates the requirements of this AD;
except for airplanes on which a crack was detected at hole 5 before
oversizing of the keel beam (in accordance with step 3.B.(1)(b)3 of
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-
4106, dated August 30, 2007), before further flight, repair in
accordance with a method approved by the International Branch, ANM-
116, Transport Airplane Directorate, FAA, or EASA (or its delegated
agent).
(s) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3098, excluding Appendix 1, Revision 01, dated July 31,
2009; or Airbus Service Bulletin A340-57-4106, excluding Appendix 1,
Revision 01, dated July 31, 2009; as applicable; terminates the
requirements of this AD.
(t) Modifying the fasteners installation in the junction keel
beam fitting at FR 40, in accordance with Airbus Service Bulletin
A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-
57-4098, dated March 27, 2006; as applicable; terminates the
requirements of this AD.
(u) In case of any crack finding during any modification
specified paragraphs (r), (s), and (t) of this AD: Where the
applicable service bulletin specifies to contact Airbus, before
further flight, repair in accordance with a method approved by the
International Branch, FAA, or EASA (or its delegated agent).
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(v) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the International Branch, send it
to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch,
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW.,
Renton, Washington 98057-3356; telephone (425) 227-1138; fax (425)
227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
Related Information
(w) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2010-0024, dated February 12, 2010, and the applicable
service information specified in table 3 of this AD, for related
information.
Table 3--Related Service Information
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus Service Bulletin A330- 02 January 24, 2006.
57-3081, including Appendix
01.
Airbus Mandatory Service 04 May 31, 2011.
Bulletin A330-57-3081,
including Appendix 01.
Airbus Service Bulletin A340- 02 January 24, 2006.
57-4089, including Appendix
01.
Airbus Mandatory Service 04 May 31, 2011.
Bulletin A340-57-4089,
including Appendix 01.
Airbus Service Bulletin A330- .............. March 27, 2006.
57-3090.
Airbus Service Bulletin A330- 01 July 31, 2009.
57-3098, excluding Appendix
1.
Airbus Service Bulletin A340- 01 July 31, 2009.
57-4106, excluding Appendix
1.
Airbus Service Bulletin A340- .............. March 27, 2006.
57-4098.
Airbus A330/A340 200-300 Issue B August 18, 2003.
Technical Disposition
F57D03012810.
Airbus A330/A340 Technical Issue A October 17, 2002.
Disposition 582.0651/2002.
------------------------------------------------------------------------
[[Page 73501]]
Material Incorporated by Reference
(x) You must use the following service information specified in
paragraphs (x)(1), (x)(2), (x)(7), (x)(8), (x)(9), and (x)(10) of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise. If you accomplish the optional
actions specified by this AD, you must use the service information
specified in paragraphs (x)(3), (x)(4), (x)(5), (x)(6), (x)(9), and
(x)(10) of this AD, as applicable, to perform those actions, unless
the AD specifies otherwise. The Director of the Federal Register
approved the incorporation by reference (IBR) under 5 U.S.C. 552(a)
and 1 CFR part 51 of the following service information on the date
specified:
(1) Airbus Mandatory Service Bulletin A330-57-3081, including
Appendix 01, Revision 04, dated May 31, 2011, approved for IBR
January 3, 2012.
(2) Airbus Mandatory Service Bulletin A340-57-4089, including
Appendix 01, Revision 04, dated May 31, 2011, approved for IBR
January 3, 2012.
(3) Airbus Service Bulletin A330-57-3098, excluding Appendix 1,
Revision 01, dated July 31, 2009, approved for IBR January 3, 2012.
(4) Airbus Service Bulletin A340-57-4106, excluding Appendix 1,
Revision 01, dated July 31, 2009, approved for IBR January 3, 2012.
(5) Airbus A330/A340 200-300 Technical Disposition F57D03012810,
Issue B, dated August 18, 2003, approved for IBR January 3, 2012.
(6) Airbus A330/A340 Technical Disposition 582.0651/2002, Issue
A, dated October 17, 2002, approved for IBR January 3, 2012.
(7) Airbus Service Bulletin A330-57-3081, including Appendix 01,
Revision 02, dated January 24, 2006, approved for IBR September 13,
2007 (72 FR 44731, August 9, 2007).
(8) Airbus Service Bulletin A340-57-4089, including Appendix 01,
Revision 02, dated January 24, 2006, approved for IBR September 13,
2007 (72 FR 44731, August 9, 2007).
(9) Airbus Service Bulletin A330-57-3090, March 27, 2006,
approved for IBR September 13, 2007 (72 FR 44731, August 9, 2007).
(10) Airbus Service Bulletin A340-57-4098, March 27, 2006,
approved for IBR September 13, 2007 (72 FR 44731, August 9, 2007).
(11) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(12) You may review copies of the service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call (425) 227-1221.
(13) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call (202) 741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-29803 Filed 11-28-11; 8:45 am]
BILLING CODE 4910-13-P
