Airworthiness Directives; Airbus Airplanes, 25666-25669 [2013-10361]
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
12,000 flight hours or 4,400 flight cycles,
whichever occurs first.
(1) At the latest of the times specified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD.
(i) Within 12,000 flight hours since the
airplane’s first flight; or
(ii) Within 12,000 flight hours since the
most recent THSA ballscrew shaft integrity
test was done as specified in maintenance
review board report (MRBR) Task 274000–12;
or
(iii) Within 12,000 flight hours since the
most recent THSA ballscrew shaft integrity
test was done, as specified in Airbus
Mandatory Service Bulletin A330–27–3179
or Airbus Mandatory Service Bulletin A340–
27–4175, as applicable. (These service
bulletins specify testing in case of type II or
type III findings).
(2) Within 1,000 flight hours after the
effective date of this AD, but without
exceeding the latest of the times specified in
paragraphs (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of
this AD.
(i) 16,000 flight hours since the airplane’s
first flight.
(ii) 16,000 flight hours since the most
recent THSA ballscrew shaft integrity test
was done, as specified in MRBR task 274000–
12.
(iii) 16,000 flight hours since the most
recent THSA ballscrew shaft integrity test
was done, as specified in Airbus Mandatory
Service Bulletin A330–27–3179, or Airbus
Mandatory Service Bulletin A340–27–4175,
as applicable. (These service bulletins specify
testing in case of type II or type III findings).
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(h) Replacement
If the result from any test required by
paragraph (g) of this AD is not correct, as
specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–27–3191, dated June 7, 2012;
or Airbus Mandatory Service Bulletin A340–
27–4186, dated June 7, 2012; as applicable:
Before further flight, replace the THSA with
a serviceable THSA, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–27–3191,
dated June 7, 2012; or Airbus Mandatory
Service Bulletin A340–27–4186, dated June
7, 2012; as applicable. Replacement of a
THSA, as required by this paragraph, with a
THSA having P/N 47147–500 or P/N 47147–
700, is not terminating action for the
repetitive tests required by paragraph (g) of
this AD.
(i) 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
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Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to: 9ANM-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.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0210, dated October 11, 2012,
and the service bulletins specified in
paragraphs (j)(1)(i) and (j)(1)(ii) of this AD,
for related information.
(i) Airbus Mandatory Service Bulletin
A330–27–3191, dated June 7, 2012.
(ii) Airbus Mandatory Service Bulletin
A340–27–4186, dated June 7, 2012.
(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 https://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 April 23,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–10366 Filed 5–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0360; Directorate
Identifier 2013–NM–033–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to supersede an
existing airworthiness directive (AD)
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that applies to all Airbus Model A318,
A319, A320, and A321 series airplanes.
The existing AD currently requires
revising the airplane flight manual
(AFM) to advise the flightcrew of
emergency procedures for addressing
angle of attack (AoA) sensor blockage.
The existing AD also provides for
optional terminating action for the AFM
revision, which involves replacing AoA
sensor conic plates with AoA sensor flat
plates. Since we issued that AD, we
have determined that the replacement of
AoA sensor conic plates is necessary to
address the identified unsafe condition.
This proposed AD would mandate the
installation of AoA sensor flat plates
and removal of the AFM revision. We
are proposing this AD to prevent
reduced control of the airplane.
DATES: We must receive comments on
this proposed AD by June 17, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://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 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 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
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
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–2013–0360; Directorate Identifier
2013–NM–033–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 https://
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.
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Discussion
On December 27, 2012, we issued AD
2012–26–51, Amendment 39–17312 (78
FR 1723, January 9, 2013). That AD
required actions intended to address an
unsafe condition on all Airbus Model
A318, A319, A320, and A321 series
airplanes.
Since we issued AD 2012–26–51,
Amendment 39–17312 (78 FR 1723,
January 9, 2013), we have determined
that the replacement of the AoA sensor
conic plates with flat plates is necessary
to address the identified 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 2013–
0022, dated February 1, 2013 (referred
to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Recently, an Airbus A330 aeroplane
equipped with Angle of Attack (AoA) sensors
with conic plates installed, experienced
blockage of all sensors during climb, leading
to autopilot disconnection and activation of
the alpha protection (Alpha Prot) when Mach
number was increased.
Based on the results of the subsequent
analysis, it is suspected that these conic
plates may have contributed to the event.
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Investigations are on-going to determine what
caused the blockage of these AoA sensors.
Blockage of two or three AoA sensors at the
same angle may cause the Alpha Prot of the
normal law to activate. Under normal flight
conditions (in normal law), if the Alpha Prot
activates and Mach number increases, the
flight control laws order a pitch down of the
aeroplane that the flight crew may be unable
to counteract with a side stick deflection,
even in the full backward position.
This condition, if not corrected, could
result in reduced control of the aeroplane.
AoA conic plates of similar design are also
installed on A320 family aeroplanes, and
installation of these AoA sensor conic plates
was required by EASA AD 2012–0236,
making reference to Airbus Service Bulletin
(SB) A320–34–1521 for in-service
modification.
That requirement was deleted by EASA AD
2012–0236R1.
To address this potential unsafe condition
on A320 family aeroplanes, Airbus
developed an ‘‘AOA Blocked’’ emergency
procedure, published as a temporary revision
(TR) of the Airplane Flight Manual (AFM), to
ensure that flight crews, in case of AoA
sensors blockage, apply the applicable
emergency procedure.
Consequently, EASA issued Emergency AD
2012–0264–E [which corresponds to FAA AD
2012–26–51, Amendment 39–17312 (78 FR
1723, January 9, 2013)] to require amendment
of the AFM by incorporating the Airbus TR.
Since that [EASA] AD was issued, Airbus
published approved instructions to re-install
AoA sensor flat plates on A320 family
aeroplanes.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2012–0264–E which is superseded, and
requires installation of AoA sensor flat
plates, after which the AFM operational
procedure can be removed.
Therefore, we have revised paragraph
(h) of this proposed AD to require that
after the modification for an airplane
has been done, Airbus A318/A319/
A320/A321 Temporary Revision TR286,
Issue 1.0, dated December 17, 2012,
must be removed before further flight.
For airplanes on which the modification
has already been done, we have allowed
a compliance time of ‘‘within 5 days
after the effective date of this AD’’ for
accomplishing the removal.
You may obtain further information
by examining the MCAI in the AD
docket.
In AD 2012–26–51, Amendment 39–
17312 (78 FR 1723, January 9, 2013), we
determined that the AFM operational
procedure specified in Airbus A318/
A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17,
2012, mitigates risks associated with
installation of conic plates. This
proposed AD would require installation
of flat plates to address the identified
unsafe condition. After analysis of the
safety benefit of the AFM operational
procedure, we determined that the
previously mandated AFM operational
procedure must be removed after
replacement of the conic plates with flat
plates.
Paragraph (h) of AD 2012–26–51,
Amendment 39–17312 (78 FR 1723,
January 9, 2013), only specifies that
Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0,
dated December 17, 2012, may be
removed after accomplishing the
modification (installation of flat plates).
Based on the service information, we
estimate that this proposed AD would
affect about 100 products of U.S.
registry.
The actions that are required by AD
2012–26–51, Amendment 39–17312 (78
FR 1723, January 9, 2013), and retained
in this proposed AD take about 1 workhour 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 $85 per
product.
We estimate that it would take about
7 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. We have received no
definitive data that would enable us to
provide part cost estimates. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
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Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A320–34–1564, including
Appendix 01, dated January 25, 2013.
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
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
proposed AD on U.S. operators to be
$59,500, or $595 per product.
PART 39—AIRWORTHINESS
DIRECTIVES
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.
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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:
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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 airworthiness directive (AD)
2012–26–51, Amendment 39–17312 (78
FR 1723, January 9, 2013), and adding
the following new AD:
■
Airbus: Docket No. FAA–2013–0360;
Directorate Identifier 2013–NM–033–AD.
(a) Comments Due Date
We must receive comments by June 17,
2013.
(b) Affected ADs
This AD supersedes AD 2012–26–51,
Amendment 39–17312 (78 FR 1723, January
9, 2013).
(c) Applicability
This AD applies to the Airbus airplanes
listed in paragraphs (c)(1) through (c)(4) of
this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–111, –211, –212,
–214, –231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 34, Navigation.
(e) Reason
This AD was prompted by a determination
that replacement of angle of attack (AoA)
sensor conic plates is necessary to address
the identified unsafe condition. We are
issuing this AD to prevent reduced control of
the airplane.
(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 Airplane Flight Manual
Revision With New Exception
This paragraph restates the requirements of
paragraph (g) of AD 2012–26–51,
Amendment 39–17312 (78 FR 1723, January
9, 2013), with a new exception. Except as
specified in paragraph (k) of this AD, for
airplanes on which an AoA sensor conic
plate is installed in production by Airbus
modification 153213 or 153214, or in-service
as specified in Airbus Mandatory Service
Bulletin A320–34–1521, dated May 7, 2012;
or Revision 01, dated September 12, 2012:
Within 5 days after January 24, 2013 (the
effective date of AD 2012–26–51), revise the
Emergency Procedures of the Airbus A318/
A319/A320/A321 Airplane Flight Manual
(AFM) by inserting Airbus A318/A319/A320/
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A321 Temporary Revision (TR) TR286, Issue
1.0, dated December 17, 2012, to advise the
flightcrew of emergency procedures for
addressing AoA sensor blockage. When the
information in Airbus A318/A319/A320/
A321 Temporary Revision TR286, Issue 1.0,
dated December 17, 2012, is included in the
general revisions of the AFM, the general
revisions may be inserted in the AFM, and
the TR may be removed. Accomplishment of
the new flat plate installation required by
paragraph (j) of this AD terminates the
actions required by this paragraph; and after
the installation of new flat plates has been
done, Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated
December 17, 2012, must be removed from
the AFM before further flight.
(h) Retained Optional Terminating Action
With Revised TR Removal Requirement
This paragraph restates the requirements of
paragraph (h) of AD 2012–26–51,
Amendment 39–17312 (78 FR 1723, January
9, 2013), with a revised TR removal
requirement. Modification of an airplane by
replacing AoA sensor conic plates with AoA
sensor flat plates, in accordance with a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, constitutes
terminating action for the AFM revision
required by paragraph (g) of this AD; and
after the modification has been done, Airbus
A318/A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17, 2012,
must be removed from the AFM before
further flight, except for airplanes on which
the modification has been done before the
effective date of this AD. For airplanes on
which the modification has been done before
the effective date of this AD, Airbus A318/
A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17, 2012,
must be removed from the AFM within 5
days after the effective date of this AD.
Accomplishment of the actions required by
paragraphs (j) and (l) of this AD terminate the
actions specified in this paragraph.
(i) Retained Parts Installation Prohibition
This paragraph restates the requirements of
paragraph (i) of AD 2012–26–51, Amendment
39–17312 (78 FR 1723, January 9, 2013). As
of January 24, 2013 (the effective date of AD
2012–26–51), no person may install an AoA
sensor conic plate in service using Airbus
Mandatory Service Bulletin A320–34–1521,
dated May 7, 2012; or Revision 01, dated
September 12, 2012; on any airplane.
(j) New Flat Plate Installation
Within 5 months after the effective date of
this AD, remove all AoA sensor conic plates
having part number (P/N) F3411060200000
or P/N F3411060900000 and install AoA
sensor flat plates having part numbers
specified in paragraph (j)(1) or (j)(2) of this
AD, except as specified in paragraph (k) of
this AD. Install the AoA sensor plates in
accordance with the applicable method
specified in paragraph (j)(1) or (j)(2) of this
AD. Accomplishment of the AoA sensor flat
plate installation terminates the AFM
revision required by paragraph (g) of this AD;
and after accomplishing the installation, the
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actions specified in paragraph (l) of this AD
must be done.
(1) Install P/N D3411013520200 in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–34–1564, including Appendix
01, dated January 25, 2013.
(2) Install P/N D3411007620000 or P/N
D3411013520000, in accordance with 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).
(k) New Exception to Paragraphs (g) and (j)
of This AD
An airplane on which Airbus modification
154863 (installation of AOA sensor flat plate)
and modification 154864 (coating protection)
have been embodied in production is not
affected by the requirements of paragraph (g)
or (j) of this AD, provided that, since first
flight, no AoA sensor conic plate having
P/N F3411060200000 or P/N
F3411060900000 has been installed on that
airplane.
(l) New Removal of AFM Revision
After modification of an airplane as
required by paragraph (j) of this AD, Airbus
A318/A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17, 2012,
that was inserted into the Airbus A318/A319/
A320/A321 AFM as required by paragraph (g)
of this AD is no longer required and must be
removed from the AFM of that airplane
before further flight.
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(m) New Parts Installation Prohibition
(1) As of the effective date of this AD, for
any airplane that has AoA sensor flat plates
installed: As of the effective date of this AD,
do not install any AoA sensor conic plate
having P/N F3411060200000 or P/N
F3411060900000, and do not use any AoA
protection cover having P/N
98D34203003000.
(2) For any airplane that has AoA sensor
conic plates installed: As of the effective date
of this AD, after modification of the airplane
as required by paragraph (j) of this AD, do
not install any AoA sensor conic plate having
P/N F3411060200000 or P/N
F3411060900000, and do not use any AoA
protection cover having P/N
98D34203003000.
(n) Special Flight Permits
Special flight permits may be issued in
accordance with §§ 21.197 and 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a
location where the airplane can be modified
(if the operator elects to do so), provided
Airbus A318/A319/A320/A321 Temporary
Revision TR286, Issue 1.0, dated December
17, 2012, has been inserted into the
Emergency Procedures of the Airbus A318/
A319/A320/A321 AFM.
(o) 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
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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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1405; fax (425) 227–
1149. Information may be emailed to: 9ANM-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.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0022, dated
February 1, 2013; Airbus Mandatory Service
Bulletin A320–34–1564, including Appendix
01, dated January 25, 2013; and Airbus A318/
A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17, 2012.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
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 April 23,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–10361 Filed 5–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF STATE
22 CFR Part 62
[Public Notice 8308]
RIN 1400–AC60
Exchange Visitor Program—Teachers
AGENCY:
PO 00000
Department of State.
Frm 00050
Fmt 4702
Sfmt 4702
25669
Proposed rule with request for
comment.
ACTION:
SUMMARY: The Department is amending
existing regulations governing the
teacher category of the Exchange Visitor
Program. The proposed amendments
clarify the duration of program
participation; amend eligibility
requirements with respect to verifying
English proficiency; and reduce the
required teaching or related experience
from three years to the equivalent of two
years full-time teaching experience;
introduce a required cultural
component; and propose the
implementation of a two-year bar for
repeat participation to foster the
purpose of the Mutual Educational and
Cultural Exchange Act of 1961,
(‘‘Fulbright-Hays Act’’). These proposed
changes will enhance the integrity and
programmatic effectiveness of the
teacher category.
DATES: The Department will accept
comments on the proposed regulation
from the public up to July 1, 2013.
ADDRESSES: You may submit comments
identified by any of the following
methods:
• Persons with access to the Internet
may also view this notice and provide
comments by going to the
regulations.gov Web site at: https://
www.regulations.gov/index.cfm and
searching for the RIN (1400–AC60)
• Mail (paper, disk, or CD–ROM
submissions): U.S. Department of State,
Office of Private Sector Exchange, SA–
5, Floor 5, 2200 C Street NW.,
Washington, DC 20522–0505.
• Email: JExchanges@state.gov. You
must include the RIN (1400–AC60) in
the subject line of your message.
FOR FURTHER INFORMATION CONTACT:
Robin J. Lerner, Deputy Assistant
Secretary for Private Sector Exchange,
U.S. Department of State, SA–5, Floor 5,
2200 C Street NW., Washington, DC
20522–0505; telephone: (202) 632–2805;
fax (202) 632–2701.
SUMMARY: Statement of Need. In recent
years, the teacher exchange program has
been used by some sponsors in a
manner that falls outside the original
intent of the program. Occasionally, it
has been used to fill a labor need in U.S.
public and private schools rather than to
further a cultural exchange. The
Department has identified issues
regarding job placements, wages and
hours, and is of the opinion that the
program lacks a cultural component
necessary for the program to be
consistent with the Mutual Educational
and Cultural Exchange Act of 1961, as
amended. In addition, the substance of
this rule has been informed by analysis
E:\FR\FM\02MYP1.SGM
02MYP1
]]>Agencies
[Federal Register Volume 78, Number 85 (Thursday, May 2, 2013)]
[Proposed Rules]
[Pages 25666-25669]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10361]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0360; Directorate Identifier 2013-NM-033-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to all Airbus Model A318, A319, A320, and A321 series
airplanes. The existing AD currently requires revising the airplane
flight manual (AFM) to advise the flightcrew of emergency procedures
for addressing angle of attack (AoA) sensor blockage. The existing AD
also provides for optional terminating action for the AFM revision,
which involves replacing AoA sensor conic plates with AoA sensor flat
plates. Since we issued that AD, we have determined that the
replacement of AoA sensor conic plates is necessary to address the
identified unsafe condition. This proposed AD would mandate the
installation of AoA sensor flat plates and removal of the AFM revision.
We are proposing this AD to prevent reduced control of the airplane.
DATES: We must receive comments on this proposed AD by June 17, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://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 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 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
[[Page 25667]]
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405;
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-2013-0360;
Directorate Identifier 2013-NM-033-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 https://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 December 27, 2012, we issued AD 2012-26-51, Amendment 39-17312
(78 FR 1723, January 9, 2013). That AD required actions intended to
address an unsafe condition on all Airbus Model A318, A319, A320, and
A321 series airplanes.
Since we issued AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013), we have determined that the replacement of the AoA
sensor conic plates with flat plates is necessary to address the
identified 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 2013-0022,
dated February 1, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Recently, an Airbus A330 aeroplane equipped with Angle of Attack
(AoA) sensors with conic plates installed, experienced blockage of
all sensors during climb, leading to autopilot disconnection and
activation of the alpha protection (Alpha Prot) when Mach number was
increased.
Based on the results of the subsequent analysis, it is suspected
that these conic plates may have contributed to the event.
Investigations are on-going to determine what caused the blockage of
these AoA sensors.
Blockage of two or three AoA sensors at the same angle may cause
the Alpha Prot of the normal law to activate. Under normal flight
conditions (in normal law), if the Alpha Prot activates and Mach
number increases, the flight control laws order a pitch down of the
aeroplane that the flight crew may be unable to counteract with a
side stick deflection, even in the full backward position.
This condition, if not corrected, could result in reduced
control of the aeroplane.
AoA conic plates of similar design are also installed on A320
family aeroplanes, and installation of these AoA sensor conic plates
was required by EASA AD 2012-0236, making reference to Airbus
Service Bulletin (SB) A320-34-1521 for in-service modification.
That requirement was deleted by EASA AD 2012-0236R1.
To address this potential unsafe condition on A320 family
aeroplanes, Airbus developed an ``AOA Blocked'' emergency procedure,
published as a temporary revision (TR) of the Airplane Flight Manual
(AFM), to ensure that flight crews, in case of AoA sensors blockage,
apply the applicable emergency procedure.
Consequently, EASA issued Emergency AD 2012-0264-E [which
corresponds to FAA AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013)] to require amendment of the AFM by incorporating
the Airbus TR.
Since that [EASA] AD was issued, Airbus published approved
instructions to re-install AoA sensor flat plates on A320 family
aeroplanes.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2012-0264-E which is superseded, and
requires installation of AoA sensor flat plates, after which the AFM
operational procedure can be removed.
You may obtain further information by examining the MCAI in the AD
docket.
In AD 2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013),
we determined that the AFM operational procedure specified in Airbus
A318/A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated December
17, 2012, mitigates risks associated with installation of conic plates.
This proposed AD would require installation of flat plates to address
the identified unsafe condition. After analysis of the safety benefit
of the AFM operational procedure, we determined that the previously
mandated AFM operational procedure must be removed after replacement of
the conic plates with flat plates.
Paragraph (h) of AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013), only specifies that Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012, may be
removed after accomplishing the modification (installation of flat
plates). Therefore, we have revised paragraph (h) of this proposed AD
to require that after the modification for an airplane has been done,
Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated
December 17, 2012, must be removed before further flight. For airplanes
on which the modification has already been done, we have allowed a
compliance time of ``within 5 days after the effective date of this
AD'' for accomplishing the removal.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-34-1564,
including Appendix 01, dated January 25, 2013. 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 100 products of U.S. registry.
The actions that are required by AD 2012-26-51, Amendment 39-17312
(78 FR 1723, January 9, 2013), and retained in this proposed AD take
about 1 work-hour 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 $85 per product.
We estimate that it would take about 7 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. We have received no definitive data
that would enable us to provide part cost estimates. Where the service
information lists required parts costs that are covered under warranty,
we have assumed that there will be no charge for these parts. As we do
not control warranty coverage for affected parties, some parties may
incur costs higher than estimated here. Based on these figures, we
estimate the cost of the
[[Page 25668]]
proposed AD on U.S. operators to be $59,500, or $595 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
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 airworthiness directive (AD)
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), and
adding the following new AD:
Airbus: Docket No. FAA-2013-0360; Directorate Identifier 2013-NM-
033-AD.
(a) Comments Due Date
We must receive comments by June 17, 2013.
(b) Affected ADs
This AD supersedes AD 2012-26-51, Amendment 39-17312 (78 FR
1723, January 9, 2013).
(c) Applicability
This AD applies to the Airbus airplanes listed in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 34, Navigation.
(e) Reason
This AD was prompted by a determination that replacement of
angle of attack (AoA) sensor conic plates is necessary to address
the identified unsafe condition. We are issuing this AD to prevent
reduced control of the airplane.
(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 Airplane Flight Manual Revision With New Exception
This paragraph restates the requirements of paragraph (g) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a
new exception. Except as specified in paragraph (k) of this AD, for
airplanes on which an AoA sensor conic plate is installed in
production by Airbus modification 153213 or 153214, or in-service as
specified in Airbus Mandatory Service Bulletin A320-34-1521, dated
May 7, 2012; or Revision 01, dated September 12, 2012: Within 5 days
after January 24, 2013 (the effective date of AD 2012-26-51), revise
the Emergency Procedures of the Airbus A318/A319/A320/A321 Airplane
Flight Manual (AFM) by inserting Airbus A318/A319/A320/A321
Temporary Revision (TR) TR286, Issue 1.0, dated December 17, 2012,
to advise the flightcrew of emergency procedures for addressing AoA
sensor blockage. When the information in Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012, is
included in the general revisions of the AFM, the general revisions
may be inserted in the AFM, and the TR may be removed.
Accomplishment of the new flat plate installation required by
paragraph (j) of this AD terminates the actions required by this
paragraph; and after the installation of new flat plates has been
done, Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, must be removed from the AFM before
further flight.
(h) Retained Optional Terminating Action With Revised TR Removal
Requirement
This paragraph restates the requirements of paragraph (h) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a
revised TR removal requirement. Modification of an airplane by
replacing AoA sensor conic plates with AoA sensor flat plates, in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, constitutes
terminating action for the AFM revision required by paragraph (g) of
this AD; and after the modification has been done, Airbus A318/A319/
A320/A321 Temporary Revision TR286, Issue 1.0, dated December 17,
2012, must be removed from the AFM before further flight, except for
airplanes on which the modification has been done before the
effective date of this AD. For airplanes on which the modification
has been done before the effective date of this AD, Airbus A318/
A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated December
17, 2012, must be removed from the AFM within 5 days after the
effective date of this AD. Accomplishment of the actions required by
paragraphs (j) and (l) of this AD terminate the actions specified in
this paragraph.
(i) Retained Parts Installation Prohibition
This paragraph restates the requirements of paragraph (i) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013). As of
January 24, 2013 (the effective date of AD 2012-26-51), no person
may install an AoA sensor conic plate in service using Airbus
Mandatory Service Bulletin A320-34-1521, dated May 7, 2012; or
Revision 01, dated September 12, 2012; on any airplane.
(j) New Flat Plate Installation
Within 5 months after the effective date of this AD, remove all
AoA sensor conic plates having part number (P/N) F3411060200000 or
P/N F3411060900000 and install AoA sensor flat plates having part
numbers specified in paragraph (j)(1) or (j)(2) of this AD, except
as specified in paragraph (k) of this AD. Install the AoA sensor
plates in accordance with the applicable method specified in
paragraph (j)(1) or (j)(2) of this AD. Accomplishment of the AoA
sensor flat plate installation terminates the AFM revision required
by paragraph (g) of this AD; and after accomplishing the
installation, the
[[Page 25669]]
actions specified in paragraph (l) of this AD must be done.
(1) Install P/N D3411013520200 in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-34-1564, including Appendix 01, dated January 25, 2013.
(2) Install P/N D3411007620000 or P/N D3411013520000, in
accordance with 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).
(k) New Exception to Paragraphs (g) and (j) of This AD
An airplane on which Airbus modification 154863 (installation of
AOA sensor flat plate) and modification 154864 (coating protection)
have been embodied in production is not affected by the requirements
of paragraph (g) or (j) of this AD, provided that, since first
flight, no AoA sensor conic plate having P/N F3411060200000 or P/N
F3411060900000 has been installed on that airplane.
(l) New Removal of AFM Revision
After modification of an airplane as required by paragraph (j)
of this AD, Airbus A318/A319/A320/A321 Temporary Revision TR286,
Issue 1.0, dated December 17, 2012, that was inserted into the
Airbus A318/A319/A320/A321 AFM as required by paragraph (g) of this
AD is no longer required and must be removed from the AFM of that
airplane before further flight.
(m) New Parts Installation Prohibition
(1) As of the effective date of this AD, for any airplane that
has AoA sensor flat plates installed: As of the effective date of
this AD, do not install any AoA sensor conic plate having P/N
F3411060200000 or P/N F3411060900000, and do not use any AoA
protection cover having P/N 98D34203003000.
(2) For any airplane that has AoA sensor conic plates installed:
As of the effective date of this AD, after modification of the
airplane as required by paragraph (j) of this AD, do not install any
AoA sensor conic plate having P/N F3411060200000 or P/N
F3411060900000, and do not use any AoA protection cover having P/N
98D34203003000.
(n) Special Flight Permits
Special flight permits may be issued in accordance with
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the airplane can be modified (if the operator elects to do so),
provided Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, has been inserted into the Emergency
Procedures of the Airbus A318/A319/A320/A321 AFM.
(o) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-1405; 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0022, dated February 1,
2013; Airbus Mandatory Service Bulletin A320-34-1564, including
Appendix 01, dated January 25, 2013; and Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://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 April 23, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10361 Filed 5-1-13; 8:45 am]
BILLING CODE 4910-13-P
