[Federal Register Volume 77, Number 218 (Friday, November 9, 2012)]
[Rules and Regulations]
[Pages 67263-67267]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-26892]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0428; Directorate Identifier 2011-NM-078-AD;
Amendment 39-17248; AD 2012-22-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD
was prompted by reports of cracking of air intake cowls on Rolls-Royce
Trent engines, worn and detached attachment
[[Page 67264]]
links, and fractured thermal anti-ice (TAI) piccolo tubes. This AD
requires inspecting piccolo tubes, piccolo tube mount links, the aft
side of the forward bulkhead, and outer boundary angles (OBA) for
cracks, fractures, and broken links, and corrective actions if
necessary. We are issuing this AD to prevent degraded structural
integrity of the engine nose cowl in case of forward bulkhead damage in
conjunction with a broken piccolo tube, and damage to the engine due to
operation in icing conditions with reduced TAI performance.
DATES: This AD becomes effective December 14, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 14,
2012.
ADDRESSES: You may examine the AD docket on the Internet at http://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, WA 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 May 8, 2012 (77 FR
26998). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During shop visit, several primary assembly structures of A330
aeroplanes Trent 700 [engine] air intake cowl have been found with
cracks in the forward bulkhead web, web stiffeners and outer
boundary angles. Several attachment links have been found severely
worn, and some had become detached. In 2 cases, the Thermal Anti Ice
(TAI) Piccolo tube was found fractured. Investigations are still
ongoing to determine the root cause(s).
If not detected and corrected, a broken Piccolo tube in
conjunction with forward bulkhead damage could ultimately lead to in
flight detachment of the outer barrel, which would constitute an
unsafe condition.
For the reasons described above, this [European Aviation Safety
Agency (EASA)] AD requires to perform inspections of RR [Rolls-
Royce] Trent 700 [engine] nose cowls and, depending on findings, to
do the applicable corrective action(s). These inspections include
internal inspection of Piccolo tube, detailed inspection of Piccolo
tube mount links, [boroscope] inspection of aft side of forward
bulkhead and outer boundary angle [for cracks, fractures, and broken
links].
We are issuing this AD to prevent degraded structural integrity of the
engine nose cowl in case of forward bulkhead damage in conjunction with
a broken piccolo tube and damage to the engine due to operation in
icing conditions with reduced TAI performance. The corrective action is
replacing the affected engine air intake cowl with a new or serviceable
cowl. 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 comments received.
Request To Delete Completion of Reporting Form
US Airways requested that we delete the requirement to complete
Appendix 01 of Airbus Mandatory Service Bulletin A330-71-3025, dated
January 10, 2011, which is the form for reporting inspection results to
Airbus. US Airways stated that accomplishing this reporting is
burdensome and does not improve the safety aspects of the inlet cowl
inspections.
We agree because reporting is voluntary. Airbus has concurred that
EASA AD 2011-0062, dated April 4, 2011, does not require reporting of
the inspection findings and that it is Airbus's intent that reporting
should be done on a voluntary basis. We have changed the final rule
throughout to exclude Appendix 01 when referring to Airbus Mandatory
Service Bulletin A330-71-3025, dated January 10, 2011.
Request To Change Piccolo Tube Link Inspection
US Airways requested that the piccolo tube link inspection be
completely independent for each inlet cowl, and that a conservative
approach could be incorporated in the NPRM (77 FR 26998, May 8, 2012)
to allow only one broken piccolo tube link on an inlet cowl if the cowl
remains in service on an airplane. US Airways stated that more than one
broken piccolo tube link would mandate removal of the cowl prior to
further flight. US Airways explained that the inspection results tie
the serviceability of cowl being inspected to the condition of the
inlet cowl installed on the other engine of the airplane. US Airways
asserted that this will require a difficult and unnecessarily
complicated management plan by an operator. US Airways reasoned that
the serviceability of the inlet cowl being inspected should be
determined independently of the inlet cowl installed on the other
engine, and that Table 3 ``Detailed Inspection of the Broken Piccolo
Tubes Links'' of Paragraph 1.E., ``Compliance,'' of Airbus Mandatory
Service Bulletin A330-71-3025, dated January 10, 2011, contains 20
different scenarios related to the number of broken piccolo tube links
in both the left and right inlet cowls and flight cycles achieved on
each inlet cowl. US Airways stated that the left and right engines and
nacelles are completely separate and designed to individually provide
continued propulsion to the airplane in the event of failure of one
engine; and that this is the basis of the FAA extended operations
(ETOPS) rules.
We disagree with changing the piccolo tube link inspection
requirements, and allowing one piccolo tube link broken on each inlet
cowl. The criteria and corrective actions specified in Airbus Mandatory
Service Bulletin A330-71-3025, dated January 10, 2011, represent the
conditions for the safe operation of the airplane. Only one piccolo
tube link broken on the airplane is allowed. The commenter did not
provide sufficient data to substantiate that its request would provide
an acceptable level of safety. Once we issue this AD, any person may
request approval of an alternate methods of compliance (AMOC) under the
provisions of paragraph (k) of this AD. We have not changed the AD in
this regard.
Request To Change OBA and Forward Bulkhead Inspection Criteria
US Airways recommended a change in the OBA and forward bulkhead
inspection criteria, as follows.
Cracks up to 9 inches in length on the OBA would be
acceptable.
Cracks up to 2 inches in length on the forward bulkhead
would be acceptable.
Re-inspection of the OBA and forward bulkhead would be
required at subsequent intervals not to exceed 2,500 flight cycles.
Replace the inlet cowl for any OBA crack of 22 inches or
greater or any forward bulkhead crack of 13 inches or greater, would be
required prior to further flight.
Replace the inlet cowl for an OBA crack greater than 15
inches, but less than 22 inches, or any forward bulkhead crack greater
than 9 inches, but less than 13 inches, within 100 flight cycles.
[[Page 67265]]
We disagree because Airbus Mandatory Service Bulletin A330-71-3025,
dated January 10, 2011, which references Rolls-Royce Service Bulletin
RB.211-71-AG416, dated September 3, 2010, provides the inspection
criteria and allowable conditions for the safe operation of the
airplane. The commenter did not present sufficient data to substantiate
that the crack lengths in its first and second recommendations would
provide an acceptable level of safety. Actions suggested by the
commenter in its third, fourth, and fifth recommendations are already
reflected in paragraphs (i)(1)(ii), (i)(2)(i), and (i)(2)(ii) of this
AD. However, operators may request approval of an AMOC under the
provisions of paragraph (k) of this AD if sufficient data are submitted
to substantiate that the change would provide a acceptable level of
safety. We have not changed the AD in this regard.
Request To Change Engine Inlet Cowl Inspection
US Airways recommended a simpler re-inspection management plan of
inspecting any engine inlet cowl that has achieved more than 5,000
flight cycles since new at repeat intervals not to exceed 2,500 flight
cycles. US Airways stated that the engine inlet cowl inspection should
follow Airbus Mandatory Service Bulletin A330-71-3025, dated January
10, 2011; and Rolls-Royce Service Bulletin RB.211-71-AG416, dated
September 3, 2010; regarding the inspection schedule of the piccolo
tube, the piccolo tube links, the OBA, and the forward bulkhead.
We disagree because Airbus Mandatory Service Bulletin A330-71-3025,
dated January 10, 2011, which references Rolls-Royce Service Bulletin
RB.211-71-AG416, dated September 3, 2010, specifies the repetitive
inspection intervals for the safe operation of the airplane, which
depend on the crack size. If the crack is within allowable limits, the
inspection interval may be greater or less than 2,500 flight cycles as
recommended by the commenter. Insufficient justification was submitted
to substantiate a 2,500-flight-cycle inspection interval. However,
under the provisions of paragraph (k) of this AD we will consider
requests for an AMOC if sufficient data is submitted to justify an
extended inspection interval for certain limits. We have not changed
the AD in this regard.
Request To Change Wording in Paragraphs (h)(2) and (h)(3) of the NPRM
(77 FR 26998, May 8, 2012)
Airbus requested that we change the word ``engine'' to ``aircraft''
in paragraph (h)(2) of the NPRM (77 FR 26998, May 8, 2012).
US Airways requested that we clarify the instructions in paragraph
(h)(3) of the NPRM (77 FR 26998, May 8, 2012) by revising ``* * * and
the opposite intake cowl of the same engine has * * *,'' to state ``* *
* and the intake cowl of the opposite engine has * * *.''
We agree to clarify paragraphs (h)(2) and (h)(3) of this AD. We
changed the word ``engine'' to ``airplane'' in paragraphs (h)(2) and
(h)(3) of the AD, since each engine has one inlet cowl.
Request To Change Unsafe Condition Statement
Airbus requested that we remove the information that a broken
piccolo tube could lead to in-flight damage of the engine and reduced
TAI performance from the unsafe condition statement in the NPRM (77 FR
26998, May 8, 2012).
We agree with the commenter's requested wording change of the
unsafe condition statement in this AD. In addition, we have revised the
unsafe condition statement in this AD to match the unsafe condition
statement defined in Airbus Mandatory Service Bulletin A330-71-3025,
dated January 10, 2011. We have changed the Summary and Discussion
sections, and paragraph (e) of the AD.
Request To Change Repetitive Inspection Interval
Airbus requested that we lower the repetitive inspection interval
for the OBA and forward bulkhead inspections from 450 flight cycles to
250 flight cycles, and from 400 flight cycles to 200 flight cycles
respectively. The commenter stated that these lower inspection
intervals will be introduced in the forthcoming revisions of the Airbus
and Rolls-Royce service information.
We disagree to change the repetitive inspection intervals in this
AD. We have determined that the compliance times required by this AD
adequately address the identified unsafe condition. However, if
additional data are presented that would justify a shorter compliance
time, we might consider further rulemaking on this issue. New revisions
of the service information referenced in this AD have not been
released. We have not changed the AD in this regard.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously, except for minor
editorial changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 26998, May 8, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 26998, May 8, 2012).
Costs of Compliance
Based on the service information, we estimate that this AD affects
about 14 products of U.S. registry. We also estimate that it takes
about 10 work-hours per engine to comply with the basic requirements of
this AD. The average labor rate is $85 per work-hour. Based on these
figures, we estimate the cost of the AD on U.S. operators to be $11,900
per engine, or $850 per engine.
In addition, we estimate that any necessary follow-on actions would
take about 16 work-hours per engine for a cost of $1,360 per engine. We
have received no definitive data that would enable us to provide
material cost estimates for the on-condition actions specified in this
AD. We have no way of determining the number of products that might
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.
[[Page 67266]]
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 the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. 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 http://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 (77 FR 26998, May 8, 2012),
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 adding the following new AD:
2012-22-12 Airbus: Amendment 39-17248. Docket No. FAA-2012-0428;
Directorate Identifier 2011-NM-078-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective December 14,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-243, -243F, -341, -342, and
-343 airplanes, certificated in any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of cracking of air intake cowls
on Rolls-Royce Trent engines, worn and detached attachment links,
and fractured thermal anti-ice (TAI) piccolo tubes. We are issuing
this AD to prevent degraded structural integrity of the engine nose
cowl in case of forward bulkhead damage in conjunction with a broken
piccolo tube, and damage to the engine due to operation in icing
conditions with reduced TAI performance.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Piccolo Tube Inspection
At the applicable time specified in paragraph (g)(1) or (g)(2)
of this AD, do a boroscope inspection of each air intake cowl
assembly of each engine to detect cracked or fractured piccolo
tubes, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011. If any cracked or fractured piccolo tube
is found: Before further flight, replace the affected engine air
intake cowl with a new or serviceable engine air intake cowl, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A330-71-3025, excluding Appendices 01 and 02, dated
January 10, 2011.
(1) For any engine air intake cowl that has accumulated fewer
than 5,000 flight cycles since its first installation on an airplane
as of the effective date of this AD: Inspect within 24 months after
the engine air intake cowl has accumulated 5,000 total flight
cycles.
(2) For any engine air intake cowl that has accumulated 5,000 or
more flight cycles since its first installation on an airplane as of
the effective date of this AD: Inspect within 24 months after the
effective date of this AD.
(h) Piccolo Link Inspection
If the inspection findings of paragraph (g) of this AD indicate
no cracked or fractured piccolo tube: Before further flight, do a
boroscope inspection of the piccolo tube links to detect broken
links, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011. If no broken links are found: Before
further flight, do the actions required by paragraph (i) of this AD.
(1) If four or more broken piccolo tube links are found: Before
further flight, replace the affected engine air intake cowl with a
new or serviceable engine air intake cowl, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-71-3025, excluding Appendices 01 and 02, dated January 10,
2011.
(2) If three or fewer broken piccolo tube links are found, and
the opposite engine air intake cowl of the same airplane has
accumulated 5,000 flight cycles or less since the engine air intake
cowl was first installed on an airplane: Before further flight, do
the actions in Figure A-FBBAA-Sheet 03, Flow Chart, of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011, as required by paragraph (i) of this AD.
(3) If three or fewer broken piccolo tube links are found, and
the opposite engine air intake cowl of the same airplane has
accumulated more than 5,000 flight cycles since the engine air
intake cowl was first installed on an airplane: Before further
flight, do a boroscope inspection of the piccolo tube links of the
opposite engine air intake cowl side to detect broken links, in
accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A330-71-3025, excluding Appendices 01 and 02, dated
January 10, 2011.
(i) If the inspection findings of the piccolo tube links of the
opposite engine air intake cowl side indicate no broken piccolo tube
links: Before further flight, do the actions required by paragraph
(i) of this AD.
(ii) If the inspection findings of the piccolo tube links of the
opposite engine air intake cowl side indicate one or more broken
piccolo tube links: Before further flight, do the actions specified
in Note 01 of Figure A-FBBAA-Sheet 02, Flow Chart, of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011, at the time specified in Note 01 of
Figure A-FBBAA-Sheet 02, Flow Chart, of Airbus Mandatory Service
Bulletin A330-71-3025, excluding Appendices 01 and 02, dated January
10, 2011, except for the instructions to ``See Sheet 03.'' Where
Note 01 of Figure A-FBBAA-Sheet 02, Flow Chart, of Airbus Mandatory
Service Bulletin A330-71-3025, excluding Appendices 01 and 02, dated
January 10, 2011, specifies to ``See Sheet 03'' to do a detailed
inspection of the OBA and bulkhead, as specified in Rolls-Royce
Service Bulletin RB.211-71-AG416, excluding Appendix 1, dated
September 3, 2010: This AD requires the detailed inspection
specified in Figure A-FBBAA-Sheet 03, Flow Chart, of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011, to be done in accordance with paragraph
(i) of this AD.
(i) Repetitive Outer Boundary Angle and Forward Bulkhead Inspection
If the results of the inspection required by paragraph (h) of
this AD indicate no broken piccolo tube links, or if the
requirements in paragraph (h)(2) or (h)(3)(ii) of this AD specify to
do the actions in Figure A-FBBAA-Sheet 03, Flow Chart, of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011: Before further flight, do a boroscope
inspection of the OBA and forward bulkhead to detect cracks or
fractures, in accordance with the Accomplishment Instructions of
Airbus
[[Page 67267]]
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011; and the Accomplishment Instructions of
Rolls-Royce Service Bulletin RB.211-71-AG416, excluding Appendix 1,
dated September 3, 2010.
(1) If the findings of the inspection are within the allowable
damage limits, as specified in the Accomplishment Instructions of
Rolls-Royce Service Bulletin RB.211-71-AG416, excluding Appendix 1,
dated September 3, 2010: Do the actions in paragraphs (i)(1)(i) and
(i)(1)(ii) of this AD.
(i) Repeat the inspection of the OBA and forward bulkhead
thereafter at the repeat interval specified in Part 3.B. of the
Accomplishment Instructions of Rolls-Royce Service Bulletin RB.211-
71-AG416, excluding Appendix 1, dated September 3, 2010.
(ii) Repeat the inspections specified in paragraphs (g) and (h)
of this AD thereafter at intervals not to exceed 2,500 flight
cycles.
(2) If the findings of the inspection are not within the
allowable damage limits, as specified in the Accomplishment
Instructions of Rolls-Royce Service Bulletin RB.211-71-AG416,
excluding Appendix 1, dated September 3, 2010: Do the actions in
paragraphs (i)(2)(i) or (i)(2)(ii) of this AD, as applicable.
(i) If any OBA crack is 22 inches or greater, or any forward
bulkhead crack is 13 inches or greater: Before further flight,
replace the affected engine air intake cowl with a new or
serviceable engine air intake cowl, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-71-3025, excluding Appendices 01 and 02, dated January 10,
2011.
(ii) If any OBA crack is 15 inches or greater, but less than 22
inches, or any forward bulkhead crack is 9 inches or greater, but
less than 13 inches: Within 100 flight cycles, replace the affected
engine air intake cowl with a new or serviceable engine air intake
cowl, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330-71-3025, excluding Appendices 01 and
02, dated January 10, 2011.
(j) Repetitive Inspections for Replaced Engine Air Intake Cowls
If any engine air intake cowl is replaced in accordance with the
requirements of this AD with an engine air intake cowl that has less
than 5,000 flight cycles since the engine air intake cowl was first
installed on an airplane: Repeat the inspection required by
paragraph (g) of this AD thereafter at the compliance time specified
in paragraph (g)(1) of this AD.
(1) If any engine air intake cowl is replaced in accordance with
the requirements of this AD with an engine air intake cowl with
5,000 flight cycles or more since the engine air intake cowl was
first installed on an airplane: Repeat the inspections required by
paragraphs (g) and (h) of this AD thereafter at intervals not to
exceed 2,500 flight cycles.
(2) If any engine air intake cowl is replaced in accordance with
the requirements of this AD with an engine air intake cowl with
5,000 flight cycles or more since the engine air intake cowl was
first installed on an airplane: Repeat the inspections required by
paragraph (i) of this AD thereafter at the intervals specified in
the Accomplishment Instructions of Rolls-Royce Service Bulletin
RB.211-71-AG416, excluding Appendix 1, dated September 3, 2010.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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,
WA 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Information may be emailed to: [email protected].
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.
(l) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0062, dated April 4, 2011, and the service
information specified in paragraphs (l)(1) and (l)(2) of this AD,
for related information.
(1) Airbus Mandatory Service Bulletin A330-71-3025, excluding
Appendices 01 and 02, dated January 10, 2011.
(2) Rolls-Royce Service Bulletin RB.211-71-AG416, excluding
Appendix 1, dated September 3, 2010.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin A330-71-3025, excluding
Appendices 01 and 02, dated January 10, 2011.
(ii) Rolls-Royce Service Bulletin RB.211-71-AG416, excluding
Appendix 1, dated September 3, 2010.
(3) For Airbus 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 [email protected];
Internet http://www.airbus.com.
(4) For Rolls-Royce service information identified in this AD,
contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby,
DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0)
1332 249936; Internet http://www.Rolls-Royce.com.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
(6) You may view this service information that is incorporated
by reference 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 26, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-26892 Filed 11-8-12; 8:45 am]
BILLING CODE 4910-13-P