[Federal Register Volume 77, Number 166 (Monday, August 27, 2012)]
[Proposed Rules]
[Pages 51717-51720]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-20966]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 77, No. 166 / Monday, August 27, 2012 /
Proposed Rules
[[Page 51717]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-183-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 certain Airbus Model A300 B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
and B4-622R airplanes. The existing AD currently requires performing a
one-time detailed visual inspection of the forward fitting at frame
(FR) 40 on both sides of the airplane for cracks, and repair if
necessary. Since we issued that AD, we have received reports that new
cracks were found in the FR 40 forward fitting. This proposed AD would
require repetitive detailed inspections of the forward fitting at FR 40
without nut removal, and a one-time eddy current or liquid penetrant
inspection of the forward fitting at FR 40 with nut removal, and repair
if necessary. We are proposing this AD to detect and correct cracking
of the FR 40 forward fitting, which could result in a deterioration of
the structural integrity of the frame.
DATES: We must receive comments on this proposed AD by October 11,
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--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [email protected]; 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, Washington. 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125;
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-2012-0858;
Directorate Identifier 2011-NM-183-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 March 4, 2010, we issued AD 2010-06-05, Amendment 39-16229 (75
FR 11435, March 11, 2010). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010), we have received reports that additional cracks have
been found after the modification had been completed. In addition, new
inspections have been added to address the unsafe condition. The
European Aviation Safety Agency (EASA), which is the Technical Agent
for the Member States of the European Community, has issued EASA
Airworthiness Directive 2011-0163, dated August 30, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
One A300-600 aeroplane operator reported that, during a routine
inspection, a crack was found in the right hand frame (FR) 40
forward fitting between stringer 32 and stringer 33. The subject
aeroplane had previously been modified in accordance with Airbus SB
A300-57-6053 (Mod. 10453).
Therefore and pending completion of the full analysis using a
refined Finite Element Model, EASA issued AD 2009-0094 [which
corresponds with FAA AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010)] to require a one-time Detailed Visual Inspection
(DVI) of the post-SB A300-57-6053 A300-600 aeroplanes and post-SB
A300-53-0297 A300 aeroplanes in order to ensure the structural
integrity of frame 40.
During a recent maintenance check, on two aeroplanes (one A300B4
and one A300-600), cracks were found in the FR 40 forward fitting.
These new crack findings are considered as unexpected, since
they were found after:
--Application of modification SB A300-57-6053 or SB A300-53-0297
which cancels the inspection programme, and
--Accomplishment of EASA AD 2009-0094.
For the reasons described above, this new [EASA] AD, which
supersedes EASA AD 2009-0094, requires repetitive DVI of the FR 40
forward fitting (without nut removal), accomplishment of a one time
Eddy Current
[[Page 51718]]
(EC) inspection or liquid penetrant inspection of this area (with
nut removal) and, depending on findings, the accomplishment of
associated corrective action [repair if any cracking found]. Passing
the EC or liquid penetrant inspection constitutes terminating action
for the repetitive DVI.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued All Operator Telex A300-53A0391, dated August 9,
2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); and All
Operator Telex A300-57A6111, dated August 9, 2011 (for Model A300 B4-
601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 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.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 134 products of U.S. registry.
The actions that are required by AD 2010-06-05, Amendment 39-16229
(75 FR 11435, March 11, 2010), and retained in this proposed AD take
about 3 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 $255 per product.
We estimate that it would take about 3 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 $34,170, or $255
per product.
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) 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010), and
adding the following new AD:
Airbus: Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-
183-AD.
(a) Comments Due Date
We must receive comments by October 11, 2012.
(b) Affected ADs
This AD supersedes AD 2010-06-05, Amendment 39-16229 (75 FR
11435, March 11, 2010).
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, as identified in paragraphs (c)(1) and (c)(2) of this AD.
For airplanes on which Airbus Service Bulletin A300-53-0297 or A300-
57-6053 (Airbus Modification 10453), as applicable, have been
incorporated as a corrective action (repair following crack
finding), no action is required by this AD.
(1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial
numbers, modified preventively in service (without any preliminary
crack findings) as specified in Airbus Service Bulletin A300-53-0297
(Airbus Modification 10453).
(2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-
622R airplanes, all serial numbers, modified preventively in service
(without any preliminary crack findings) as specified in Airbus
Service Bulletin A300-57-6053 (Airbus Modification 10453).
(d) Subject
Air Transport Association (ATA) of America Code 53, 57:
Fuselage, Wings.
(e) Reason
This AD was prompted by reports that cracks were found in the
frame (FR) 40 forward fitting. We are issuing this AD to detect and
correct cracking of the FR 40 forward fitting, which could result in
a deterioration of the structural integrity of the frame.
(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) Retained Detailed Inspection
This paragraph restates the actions required by paragraphs
(f)(1), (f)(2), and (f)(3) of AD 2010-06-05, Amendment 39-16229 (75
FR 11435, March 11, 2010).
(1) At the applicable time specified in table 1 to paragraph
(g)(1) of this AD: Do a one-time detailed visual inspection of the
forward fitting at FR 40 on both sides of the airplane, in
accordance with Airbus Mandatory Service Bulletin A300-57A6108 (for
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes) or A300-53A0387 (for Model A300 B4-2C, B4-103, and B4-203
airplanes), both including
[[Page 51719]]
Appendices 01 and 02, both dated September 12, 2008.
Table 1 to Paragraph (g)(1) of This AD--Compliance Times
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Airplane models/configuration Compliance time
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A300 B4-2C and B4-103 airplanes on which Prior to the accumulation of 18,000 total flight cycles, or
Airbus Service Bulletin A300-53-0297 was within 3 months after April 15, 2010 (the effective date of AD
done prior to the accumulation of 9,000 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
total flight cycles. whichever occurs later.
A300 B4-2C and B4-103 airplanes on which Within 5,500 flight cycles after accomplishment of Airbus Service
Airbus Service Bulletin A300-53-0297 was Bulletin A300-53-0297, or within 6 months after April 15, 2010
done on or after the accumulation of 9,000 (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
total flight cycles. 11435, March 11, 2010)), whichever occurs later; except, for
airplanes that, as of April 15, 2010 (the effective date of AD
2010-06-05), have accumulated 11,000 flight cycles or more since
accomplishment of Airbus Service Bulletin A300-53-0297, within 3
months after April 15, 2010 (the effective date of AD 2010-06-
05).
A300 B4-203 airplanes on which Airbus Service Prior to the accumulation of 15,000 total flight cycles, or
Bulletin A300-53-0297 was done prior to the within 3 months after April 15, 2010 (the effective date of AD
accumulation of 8,300 total flight cycles. 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
whichever occurs later.
A300 B4-203 airplanes on which Airbus Service Within 4,100 flight cycles after accomplishment of Airbus Service
Bulletin A300-53-0297 was done on or after Bulletin A300-53-0297, or within 6 months after April 15, 2010
the accumulation of 8,300 total flight (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
cycles. 11435, March 11, 2010)), whichever occurs later; except, for
airplanes that, as of April 15, 2010 (the effective date of AD
2010-06-05), have accumulated 8,200 flight cycles or more since
accomplishment of Airbus Service Bulletin A300-53-0297, within 3
months after April 15, 2010 (the effective date of AD 2010-06-
05).
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, Prior to the accumulation of 11,500 total flight cycles, or
and B4-622R airplanes on which Airbus within 3 months after April 15, 2010 (the effective date of AD
Service Bulletin A300-57-6053 was done prior 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010)),
to the accumulation of 6,100 total flight whichever occurs later.
cycles.
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, Within 3,300 flight cycles after accomplishment of Airbus Service
and B4-622R airplanes on which Airbus Bulletin A300-57-6053, or within 6 months after April 15, 2010
Service Bulletin A300-57-6053 was done on or (the effective date of AD 2010-06-05, Amendment 39-16229 (75 FR
after the accumulation of 6,100 total flight 11435, March 11, 2010)), whichever occurs later; except, for
cycles. airplanes that, as of April 15, 2010 (the effective date of AD
2010-06-05), have accumulated 6,600 flight cycles or more since
accomplishment of Airbus Service Bulletin A300-57-6053, within 3
months after April 15, 2010 (the effective date of AD 2010-06-
05).
----------------------------------------------------------------------------------------------------------------
(2) Except as required by paragraph (g)(3) of this AD: If any
crack is found during the inspection required by paragraph (g)(1) of
this AD, before further flight, do a temporary or definitive repair,
as applicable, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings
15R53810394, Issue A, dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes).
(3) If any crack found during the inspection required by
paragraph (g)(1) of this AD cannot be repaired in accordance with
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7,
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002 including Airbus Drawings
15R53810394, Issue A, dated December 21, 1998, and 21R57110247,
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes): Contact Airbus for
repair instructions and, before further flight, repair the crack
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the European Aviation
Safety Agency (EASA) (or its delegated agent).
(h) Retained Reporting Requirement
This paragraph restates the requirements of paragraph (f)(4) of
AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010).
Submit an inspection report in accordance with Appendix 01 of Airbus
Mandatory Service Bulletin A300-53A0387, including Appendices 01 and
02, dated September 12, 2008 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57A6108,
including Appendices 01 and 02, dated September 12, 2008 (for Model
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes); to the address identified on the reporting sheet, at the
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after April 15, 2010 (the
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010)): Submit the report within 30 days after the
inspection.
(2) If the inspection was done before April 15, 2010 (the
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435,
March 11, 2010)): Submit the report within 30 days after April 15,
2010 (the effective date of AD 2010-06-05).
(i) New Requirement: Repetitive Detailed Visual Inspections
Within 300 flight cycles after the effective date of this AD:
Perform a detailed inspection for cracks of the forward fitting at
FR 40 without nut removal on both sides of the airplane, in
accordance with Airbus All Operator Telex A300-53A0391, dated August
9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or
Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R
airplanes). Thereafter, repeat the inspection at intervals not to
exceed 300 flight cycles.
(j) New Requirement: Eddy Current Inspection or Liquid Penetrant
Inspection
Within 36 months after the effective date of this AD: Perform an
eddy current inspection or a liquid penetrant inspection for cracks
of the forward fitting at FR 40 with nut removal on both sides of
the airplane, in accordance with Airbus All Operator Telex A300-
53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus All Operator Telex A300-57A6111, dated
August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, and B4-622R airplanes).
(k) New Requirement: Corrective Action
If, during any inspection required by paragraph (i) or (j) of
this AD, any crack is detected: Before further flight, repair the
crack in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA (or its delegated agent).
[[Page 51720]]
(l) New Requirement: Reporting Requirement
Submit a one-time report of the findings (both positive and
negative) of the inspections required by paragraphs (i) and (j) of
this AD to Airbus, Sebastien Faure, SEES1, SAS--EAW (Airworthiness
Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email
[email protected], at the applicable time specified in
paragraph (l)(1) or (l)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(m) New Requirement: Terminating Action
Accomplishment of the one-time eddy current inspection or a
liquid penetrant inspection required by paragraph (j) of this AD,
including doing all applicable repairs, constitutes terminating
action for the inspections required by paragraph (i) of this AD.
(n) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 227-2125;
fax: (425) 227-1149; email: [email protected]. 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. AMOCs
approved previously in accordance with AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11, 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.
(o) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2011-0163, dated
August 30, 2011, and the service information in paragraphs (o)(1)(i)
through (o)(1)(vi) of this AD, for related information.
(i) Airbus All Operator Telex A300-53A0391, dated August 9,
2011.
(ii) Airbus All Operator Telex A300-57A6111, dated August 9,
2011.
(iii) Airbus Mandatory Service Bulletin A300-57A6108, including
Appendices 01 and 02, dated September 12, 2008.
(iv) Airbus Mandatory Service Bulletin A300-53A0387, including
Appendices 01 and 02, dated September 12, 2008.
(v) Airbus Service Bulletin A300-53-0268, Revision 06, dated
January 7, 2002.
(vi) Airbus Service Bulletin A300-57-6052, Revision 03, dated
May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated
December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email [email protected];
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 August 17, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-20966 Filed 8-24-12; 8:45 am]
BILLING CODE 4910-13-P