[Federal Register Volume 77, Number 222 (Friday, November 16, 2012)]
[Proposed Rules]
[Pages 68711-68714]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27847]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1163; Directorate Identifier 2011-NM-246-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all Airbus Model A330-200 and -300 series
airplanes; and Model A340-200, -300, -500, and -600 series airplanes.
The existing AD currently requires a one-time detailed inspection of
both main landing gear (MLG) bogie beams in the region of the bogie
stop pad for detection of deformation and damage, and corrective
actions if necessary. Since we issued that AD, we have received reports
of corroded bogie stop pads, including some with cracking. This
proposed AD would add Model A330-200 Freighter series airplanes to the
applicability. For certain airplanes, this proposed AD would also add
repetitive inspections for damage and corrosion of the sliding piston
sub-assembly, with new related investigative and corrective actions. We
are proposing this AD to detect and correct deformation or damage under
the bogie stop pad of both MLG bogie beams, which could result in a
damaged bogie beam and consequent detachment of the beam from the
airplane or collapse of the MLG and departure of the airplane from the
runway.
DATES: We must receive comments on this proposed AD by December 31,
2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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 http://www.airbus.com. You may review copies of the referenced 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.
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 this proposed AD, 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.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-1163;
Directorate Identifier 2011-NM-246-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On January 14, 2010, we issued AD 2010-02-10, Amendment 39-16181
(75 FR 4477, January 28, 2010). That AD required actions intended to
address an unsafe condition on Airbus Model A330-200 and -300 series
airplanes; and Model A340-200, -300, -500, and -600 series airplanes.
Since we issued AD 2010-02-10, Amendment 39-16181 (75 FR 4477,
January 28, 2010), the European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2011-0211, dated October 31,
2011 (referred to after this as ``the MCAI''), to supersede EASA AD
2008-0223, dated December 15, 2008 (referred to in the existing AD),
and correct an unsafe condition for the specified products. The MCAI
states:
During a scheduled maintenance inspection on the MLG [main
landing gear], the bogie stop pad was found deformed and cracked.
Upon removal of the bogie stop pad for replacement, the bogie beam
was also found cracked.
Laboratory investigation indicates that an overload event has
occurred and no fatigue propagation of the crack was evident.
A second bogie beam crack has subsequently been found on another
aeroplane, located under a bogie stop pad which only had superficial
paint damage.
This condition, if not detected and corrected, could result in
the aeroplane departing the runway or to the bogie detaching from
the areoplane or gear collapses, which would all constitute unsafe
conditions at speeds above 30 knots.
As a precautionary measure, EASA AD 2008-0223 [which corresponds
to FAA AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28,
2010] required one-time detailed inspections under the bogie stop
pad of both MLG bogie beams and, in case deformation or damage is
detected, to apply the associated repair.
Numerous bogie stop pad were found corroded and a few cracked as
a result of the one-time inspection required by EASA AD 2008-0223 on
A330, A340-200, and A340-300 aeroplanes.
For the reasons describe above, this [EASA] AD, which supersedes
EASA AD 2008-0223:
--Retains the initial inspection requirement of EASA AD 2008-0223
for A330, A340-200, and A340-300 aeroplanes.
--Introduces a repetitive detailed visual inspection for A330, A340-
200, and A340-300 aeroplanes.
--Retains the requirement of EASA AD 2008-0223 for A340-500 and
A340-600 aeroplanes, for which further mandatory requirements might
follow in future mandatory requirements might follow in future
depending on the results of the one-time mandatory inspection in
place.
The required actions include repetitive detailed inspections for
[[Page 68712]]
damage and corrosion of the sliding piston sub-assembly, with new
related investigative and corrective actions. Related investigative
actions include a test for indications of corrosion and damage to the
bogie assembly base material, and a magnetic particle inspection for
cracks, corrosion, and damage of the bogie beam. Corrective actions
include repairing affected parts.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following service bulletins:
Airbus Mandatory Service Bulletin A330-32-3220, Revision
01, dated October 5, 2011 (for Model A330-200 and -300 series
airplanes).
Airbus Mandatory Service Bulletin A330-32-3248, including
Appendix 1, dated October 5, 2011 (for Model A330-200, -200 Freighter,
and -300 series airplanes).
Airbus Mandatory Service Bulletin A340-32-4286, including
Appendix 1, dated October 5, 2011 (for Model A340-200 and -300 series
airplanes).
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between Proposed AD and Service Information
Although the service information specifies to contact the
manufacturer for instructions to repair certain conditions, this
proposed AD would require repairing those conditions using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the EASA (or its delegated agent).
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 67 products of U.S. registry.
The actions that are required by AD 2010-02-10, Amendment 39-16181
(75 FR 4477, January 28, 2010), and retained in this proposed AD take
about 2 work-hours per product, at an average labor rate of $85 per
work hour. Based on these figures, the estimated cost of the currently
required actions is $170 per product.
We estimate that it would take about 16 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $91,120, or $1,360
per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010), and
adding the following new AD:
Airbus: Docket No. FAA-2012-1163; Directorate Identifier 2011-NM-
246-AD.
(a) Comments Due Date
We must receive comments by December 31, 2012.
(b) Affected ADs
This AD supersedes AD 2010-02-10, Amendment 39-16181 (75 FR
4477, January 28, 2010).
(c) Applicability
This AD applies to all Airbus Model A330-201, -202, -203, -223,
-223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342,
and -343 series airplanes; and Model A340-211, -212, -213, -311, -
312, -313 series airplanes; and A340-541 and -642 airplanes;
certificated in any category; all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
gear.
(e) Reason
This AD was prompted by reports of corroded bogie stop pads,
some with cracking. We are issuing this AD to detect and correct
deformation or damage under the bogie stop pad of both main landing
gear (MLG) bogie beams, which could result in a damaged bogie beam
and consequent detachment of the beam from the airplane or collapse
of the MLG and departure of the airplane from the runway.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the
[[Page 68713]]
compliance times specified, unless the actions have already been
done.
(g) Retained One-Time Inspection and Corrective Actions, With Revised
Service Information
This paragraph restates the requirements of paragraph (f)(1) of
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010),
with revised service information. For Model A330-200 and -300 series
airplanes, and Model A340-200, -300, -500, and -600 series
airplanes, except as required by paragraph (i) of this AD: At the
applicable compliance time specified in paragraph (g)(1), (g)(2),
(g)(3), (g)(4), (g)(5), or (g)(6) of this AD, perform one-time
detailed inspections of both MLG bogie beams in the region of the
bogie stop pad for detection of deformation and damage, and apply
the applicable corrective actions, in accordance with the
Accomplishment Instructions of the applicable service bulletin
specified in paragraph (g)(7) of this AD. Do all applicable
corrective actions before further flight.
(1) Airplanes with 22 months or less and 2,500 flight cycles or
less from the first flight with the original bogie beam as of March
4, 2010 (the effective date of AD 2010-02-10, Amendment 39-16181 (75
FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or
22 months on the original bogie beam, whichever occurs first, but
not later than 40 months from first flight.
(2) Airplanes with 22 months or less and 2,500 flight cycles or
less from the installation date of a new bogie beam in service as of
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight
cycles or 22 months from the installation date of the new bogie
beam, whichever occurs first, but not later than 40 months from the
installation date of a new bogie beam in service.
(3) Airplanes with 22 months or less and 2,500 flight cycles or
less from the installation date of an overhauled bogie beam in
service as of March 4, 2010 (the effective date of AD 2010-02-10,
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Not earlier than
2,500 flight cycles or 22 months from the installation date of the
overhauled bogie beam in service, whichever occurs first, but not
later than 40 months from the installation date of the overhauled
bogie beam in service.
(4) Airplanes with more than 22 months or more than 2,500 flight
cycles from the first flight with the original bogie beam, as of
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March
4, 2010 (the effective date of AD 2010-02-10).
(5) Airplanes with more than 22 months or more than 2,500 flight
cycles from the installation date of a new bogie beam in service, as
of March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March
4, 2010 (the effective date of AD 2010-02-10).
(6) Airplanes with more than 22 months or more than 2,500 flight
cycles from the installation date of an overhauled bogie beam in
service, as of March 4, 2010 (the effective date of AD 2010-02-10,
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Within 18 months
after March 4, 2010 (the effective date of AD 2010-02-10).
(7) Use the applicable service information to accomplish the
actions required by paragraph (g) of this AD.
(i) For Model A330-200 and -300 series airplanes: Airbus
Mandatory Service Bulletin A330-32-3220, dated October 10, 2008; or
Airbus Mandatory Service Bulletin A330-32-3220, Revision 01, dated
October 5, 2011.
(ii) For Model A340-200 and -300 series airplanes: Airbus
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
(iii) For Model A340-500 and -600 series airplanes: Airbus
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.
(h) Retained Reporting Requirement
This paragraph restates the requirements of paragraph (f)(2) of
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010).
Report the results of the inspection required by paragraph (g) of
this AD, including no findings, to Airbus, Customer Services
Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex
France; Attn: SEDCC1 Technical Data and Documentation Services; fax
(+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection is done on or after March 4, 2010 (the
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477,
January 28, 2010)): Submit the report within 30 days after doing the
inspection.
(2) If the inspection was done prior to March 4, 2010 (the
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477,
January 28, 2010)): Submit the report within 30 days after March 4,
2010 (the effective date of AD 2010-02-10).
(i) New Inspections of Beams That Have Not Been Inspected as of the
Effective Date of This AD
For bogie beams on which the inspection required by paragraph
(g) of this AD has not been accomplished as of the effective date of
this AD: At the later of the times specified in paragraphs (i)(1)
and (i)(2) of this AD, perform one-time detailed inspections of both
main landing gear bogie beams in the region of the bogie stop pad
for detection of deformation and damage, and apply the applicable
corrective actions, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraph (i)(3) of this AD. Do all applicable corrective actions
before further flight.
(1) At the applicable time in paragraph (i)(1)(i) or (i)(1)(ii)
of this AD.
(i) For bogie beams that have not been overhauled: Not earlier
than 2,500 flight cycles or 22 months, whichever occurs first, on a
bogie beam since its first flight on an airplane since new, but not
later than 40 months since its first flight on an airplane since
new.
(ii) For bogie beams that have been overhauled: Not earlier than
2,500 flight cycles or 22 months, whichever occurs first, on a bogie
beam since its first flight on an airplane after its most recent
overhaul, but not later than 40 months since its first flight on an
airplane after its most recent overhaul.
(2) Within 90 days after the effective date of this AD.
(3) Use the applicable service information specified in
paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to
accomplish the actions required by paragraph (i) of this AD.
(i) For Model A330-200 and -300 series airplanes: Airbus
Mandatory Service Bulletin A330-32-3220, Revision 01, dated October
5, 2011.
(ii) For Model A340-200 and -300 series airplanes: Airbus
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
(iii) For Model A340-500 and -600 series airplanes: Airbus
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.
(j) New Repetitive Inspections
Except for bogie beams that have been inspected as specified in
Airbus Mandatory Service Bulletin A340-32-5087: At the later of the
times specified in paragraphs (j)(1) and (j)(2) of this AD, do the
detailed inspection of both MLG bogie beams in the bogie stop pad
area for damage and corrosion, and all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-32-3248, dated October 5, 2011 (for Model A330-200, -200
Freighter, and -300 series airplanes); or Airbus Mandatory Service
Bulletin A340-32-4286, dated October 5, 2011 (for Model A340-200 and
-300 series airplanes); except as required by paragraph (k) of this
AD. Do all applicable related investigative and corrective actions
before further flight. Repeat the inspection thereafter at intervals
not to exceed 2,500 flight cycles or 24 months, whichever is first.
(1) Within 2,500 flight cycles or 24 months, whichever occurs
first, accumulated by a MLG bogie beam since its first flight after
the most recent accomplishment of Airbus Mandatory Service Bulletin
A330-32-3220 or A340-32-4264, as applicable.
(2) Within 3 months after the effective date of this AD.
(k) Service Information Exception
If any cracking of the bogie beam is detected during any
inspection or repair required by paragraph (j) of this AD, or any
repair required by paragraph (j) of this AD is beyond the maximum
repair allowance specified in the service information required by
paragraph (j) of this AD: Before further flight, repair using a
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated agent).
(l) New Reporting Requirement
Report the results of the initial inspection required by
paragraph (j) of this AD, including both positive and negative
findings, to Airbus, Customer Services Directorate, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical
Data and Documentation Services; fax (+33) 5 61 93 28 06; email
sb.reporting@airbus.com at the applicable
[[Page 68714]]
time specified in paragraph (l)(1) or (1)(2) of this AD.
(1) If the inspection is done on or after the effective date of
this AD: Submit the report within 30 days after doing the
inspection.
(2) If the inspection was done prior to the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(m) 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,
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. AMOCs approved previously in accordance with AD 2010-02-10,
Amendment 39-16181 (75 FR 4477, January 28, 2010), are approved as
AMOCs for the corresponding provisions of 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.
(n) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed if any crack is found during any
inspection required by this AD.
(o) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0211, dated
October 1, 2011, and the service information specified in paragraphs
(o)(1)(i) through (o)(1)(vi) of this AD, for related information.
(i) Airbus Mandatory Service Bulletin A330-32-3220, dated
October 10, 2008.
(ii) Airbus Mandatory Service Bulletin A330-32-3220, Revision
01, dated October 5, 2011.
(iii) Airbus Mandatory Service Bulletin A330-32-3248, dated
October 5, 2011.
(iv) Airbus Mandatory Service Bulletin A340-32-4264, dated
October 10, 2008.
(v) Airbus Mandatory Service Bulletin A340-32-4286, dated
October 5, 2011.
(vi) Airbus Mandatory Service Bulletin A340-32-5087, dated
October 10, 2008.
(2) 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 http://www.airbus.com. You may review copies of the
referenced 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.
Issued in Renton, Washington, on November 8, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-27847 Filed 11-15-12; 8:45 am]
BILLING CODE 4910-13-P