Wu, Y S, Lee, H K, and Li, S F ( 2001). High performance chiral separation of fourteen triazole fungicides by sulfated beta cyclodextrin mediated capillary electrophoresis. Journal Of Chromatography. A 912: 171 179. Rejection Code: CHEM METHODS.

YOUNG DJ, SULLIVAN LM, and ENGLE CE ( 1985). STEROL INHIBITING FUNGICIDES FOR CONTROL OF SOUTHWESTERN RUST PUCCINIA CACABATA ON COTTON GOSSYPIUM HIRSUTUM. ANNUAL MEETING OF THE AMERICAN Page 239 of 241 PHYTOPATHOLOGICAL SOCIETY, RENO, NEVADA, USA, AUG. 11 15, 1985. PHYTOPATHOLOGY; 75 1384. Rejection Code: ABSTRACT.

Zhou, Chang Xin, Liu, Jun Yan, Ye, Wen Cai, Liu, Chang Hong, and Tan, Ren Xiang ( 2003). Neoverataline A and B, two antifungal alkaloids with a novel carbon skeleton from Veratrum taliense. Tetrahedron 59: 5743 5747. Rejection Code: CHEM METHODS. Page 240 of 241 APPENDIX I: FUGACITY APPROACH FOR EARTHWORM PESTICIDE RESIDUE MODELING Fugacity capacities ( Z) for a given chemical are calculated for the phases of interest as part of the exposure point estimation methodology ( Mackay and Paterson 1981; Mackay et al. 1995). The following calculations require several specific parameters and an assumption of the system temperature, e. g. 25 C.

Earthworms dwelling within the soil are assumed to be exposed to both soil pore water and via the ingestion of soil ( Belfroid et al. 1994). The concentration of earthworms is calculated as a combination of uptake from soil pore water and ingested soil across the gastro intestinal tract:

C earthworm = [( Csoil)( Zearthworm/ Zsoil)]+[( Csoil water)( Zearthworm/ Zwater)]

where: Csoil is the concentration of chemical in bulk soil ( note: a chemical concentration averaged over a 15 cm soil depth was used to reflect a concentration across the earthworm occupied area of soil) Zearthworm is the fugacity capacity of chemical in earthworms = ( lipid)( Kow)( Dearthworm)/ H Zsoil is the fugacity capacity of chemical in soil = ( Kd)( Dsoil)/ H Zwater is the fugacity capacity of chemical in water = 1/ H Csoil water is the concentration of chemical in soil water = Csoil/ Kbw Kbw is the bulk soil to water partitioning coefficient = ( Dsoil)( Kd)+ 2 +(, 2)( Kaw) as per Trapp and McFarlane ( 1995) Kaw is the air to water partitioning coefficient = H/ RT H = Henry's Constant specific to the chemical ( Pa m3/ mole) R = universal gas constant, 8.31 Joules m3/ mol oK T = temperature oK, assumed to be 298 oK Kd = soil partitioning coefficient = ( chemical Koc )( fraction of soil organic carbon) Dsoil = bulk density of soil g/ cm3 2 = volumetric fraction of the soil , = volumetric total porosity of the soil lipid = fraction of lipid in organism 0.01 ( Cobb et al. 1995) Kow = chemical octanol to water partitioning coefficient Dearthworm = the density of the organism g/ cm3, assumed to be 1 g/ cm3 The following parameters were used to calculate earthworm triadimefon concentrations:

Soil Concentration: Triadimefon soil concentrations at one centimeter were calculated using the following equation:

application rate ( kg/ ha) x 1x106 mg/ kg x 1 ha/ 1x108 x 1.3 g/ cm3 Csoil ( maximum application of 2.7 lb ai/ A  golf course turf) = 31 mg/ kg Page 241 of 241 Parameters used to calculate earthworm triadimefon concentration:

Vapor Pressure: 1x10 4 Pa Solubility: 70 mg/ L Henry's Law Constant: 1.7x10 2 pa m3/ mol Kow: 2.77 Koc: 387 fraction of soil organic carbon: 0.02 soil bulk density: 1.3 g/ cm3 volumetric soil fraction: 0.30 volumetric soil porosity: 0.50 Organism ( worm) density: 1 g/ cm3 fraction of lipid in an organism: 0.01 Parameter triadimefon/ triadimefnol max C sed at surface ( ppm) 3.10E+ 01 C sed avg in 15 cm ( ppm) 2.07E+ 00 Vapor Pressure ( Pa) 1.00E 04 Solubility ( mg/ L) 7.00E+ 01 Solubility ( mol/ L) 2.06E+ 01 Henry's C 1.170E 02 Kow 2.77 Koc 387 foc 0.02 Zwater 8.55E+ 01 Zinv 2.37E+ 00 Cwater 4.01E+ 00 pworm 1 lipid 0.01 Invert Conc mg/ kg 1.11E 01


[Federal Register Volume 83, Number 205 (Tuesday, October 23, 2018)]
[Proposed Rules]
[Pages 53404-53407]
[FR Doc No: 2018-22827]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0902; Product Identifier 2018-NM-047-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 787 series airplanes. This proposed AD was
prompted by a report of an uncommanded descent and turn that occurred
after an inflight switch to the spare flight management function (FMF).
This proposed AD would require an inspection of the flight management
system (FMS) to determine if certain operational program software (OPS)
is installed and installation of new FMS OPS and a software check if
necessary. For certain airplanes, this proposed AD would also require
concurrent actions. We are proposing this AD to address the unsafe
condition on these products.

DATES: We must receive comments on this proposed AD by December 7,
2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may
view this referenced service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>. It
is also available on the internet at http://www.regulations.gov by
searching for and locating Docket No. FAA-2018-0902.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0902; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nelson Sanchez, Aerospace Engineer,
Systems and Equipment Section, FAA, Seattle ACO Branch, 2200 South
216th St., Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-

2018-0902; Product Identifier 2018-NM-047-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. We will
consider all comments received by the closing date and may amend this
NPRM because of 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

    We have received a report of an uncommanded descent and turn that
occurred when the spare FMF became the master FMF in flight. When the
master FMF and spare FMF are operating normally, the FMF
synchronization function sends data from the master to the spare so
they will have the same flight data. It was found that an anomaly had
prevented this communication for several flights, causing stale flight
data to be retained in the spare FMF. In addition, no mechanism is
currently in place to detect, remove, and replace stale flight data.
This condition, if not addressed, could result in controlled flight
into terrain or a mid-air collision.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Requirements Bulletin B787-81205-SB340038-
00 RB, Issue 001, dated November 16, 2017. The service information
describes procedures for installing FMS OPS Block Point 3B (BP3B) and
performing a software check.
    We also reviewed Boeing Service Bulletin B787-81205-SB340013-00,
Issue 002, dated May 6, 2016. The service information describes
procedures for installing FMS OPS Block Point 3 (BP3) and performing a
software check. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions
identified in the service information described previously, except as
discussed under ``Differences Between this Proposed AD and the Service
Information,'' and except for any differences identified as exceptions
in the regulatory text of this proposed AD.
    For information on the procedures and compliance times, see this
service information at http://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0902.

Explanation of Requirements Bulletin

    The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement is a process for
annotating which steps in the service information are ``required for
compliance'' (RC) with an AD. Boeing has implemented this RC concept
into Boeing service bulletins.
    In an effort to further improve the quality of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).

Differences Between This Proposed AD and the Service Information

    The effectivity of Boeing Alert Requirements Bulletin B787-81205-
SB340038-00 RB, Issue 001, dated November 16, 2017, is limited to
certain Model 787-8 and 787-9 airplanes. However, the applicability of
this proposed AD includes all Boeing Model 787 series airplanes.
Because the affected software versions are rotable parts, we have
determined that these parts could later be installed on airplanes that
were initially delivered with acceptable software versions, thereby
subjecting those airplanes to the unsafe condition. This difference has
been coordinated with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 144 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per         Cost on U.S.
              Action                      Labor cost           Parts cost        product          operators
----------------------------------------------------------------------------------------------------------------
Records check or inspection......  1 work-hour x $85 per                 $0             $85  $12,240.
                                    hour = $85.
Software installation............  4 work-hours x $85 per                 0             340  Up to $48,960.
                                    hour = $340.
Concurrent actions...............  4 work-hours x $85 per                 0             340  Up to $48,960.
                                    hour = $340.
----------------------------------------------------------------------------------------------------------------

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.
    This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated

appliances to the Director of the System Oversight Division.

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.

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 adding the following new airworthiness
directive (AD):

The Boeing Company: Docket No. FAA-2018-0902; Product Identifier
2018-NM-047-AD.

(a) Comments Due Date

    We must receive comments by December 7, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 787 series
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 34, Navigation.

(e) Unsafe Condition

    This AD was prompted by a report of an uncommanded descent and
turn that occurred after an inflight switch to the spare flight
management function (FMF), due to the retention of stale flight data
in the spare FMF. We are issuing this AD to address the retention of
stale flight data in the spare FMF, which, if not addressed, could
result in controlled flight into terrain or a mid-air collision.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Required Actions

    (1) For Boeing Model 787 series airplanes that have an original
certificate of airworthiness or export certificate of airworthiness
issued on or before the effective date of this AD: Within 12 months
after the effective date of this AD, inspect the flight management
system (FMS) to determine if operational program software (OPS) part
number (P/N) HNP5F-AL11-5010 or HNP58-AL11-5006 is installed. A
review of airplane maintenance records is acceptable in lieu of this
inspection if the part number of the FMS OPS can be conclusively
determined from that review.
    (2) If, during any inspection or records review required by
paragraph (g)(1) of this AD, FMS OPS P/N HNP5F-AL11-5010 or HNP58-
AL11-5006 is found: Within 12 months after the effective date of
this AD, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin B787-81205-SB340038-00 RB, Issue 001, dated November 16,
2017; except where Boeing Alert Requirements Bulletin B787-81205-
SB340038-00 RB, Issue 001, dated November 16, 2017, specifies
installing 34 FMS OPS Block Point 3B, P/N HNP5E-AL11-5011, this AD
requires installing P/N HNP5E-AL11-5011 or later-approved software
versions. Later-approved software versions are only those Boeing
software versions that are approved as a replacement for the
applicable software, and are approved as part of the type design by
the FAA or the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) after issuance of Boeing Alert Requirements
Bulletin B787-81205-SB340038-00 RB, Issue 001, dated November 16,
2017.

    Note 1 to paragraph (g) of this AD:  Guidance for accomplishing
the actions required by paragraph (g) of this AD can be found in
Boeing Alert Service Bulletin B787-81205-SB340038-00, Issue 001,
dated November 16, 2017, which is referred to in Boeing Alert
Requirements Bulletin B787-81205-SB340038-00 RB, Issue 001, dated
November 16, 2017.

(h) Concurrent Requirements

    For airplanes identified in Boeing Service Bulletin B787-81205-
SB340013-00, Issue 002, dated May 6, 2016: Prior to or concurrently
with the action required by paragraph (g) of this AD, install FMS,
Thrust Management System (TMS), and Communication Management
Function (CMF) software identified in Boeing Service Bulletin B787-
81205-SB340013-00, Issue 002, dated May 6, 2016, and do a software
check, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin B787-81205-SB340013-00, Issue 002, dated May 6,
2016; except where Boeing Service Bulletin B787-81205-SB340013-00,
Issue 002, dated May 6, 2016, specifies installing software, this AD
requires installing that software or later-approved software
versions. Later-approved software versions are only those Boeing
software versions that are approved as a replacement for the
applicable software, and are approved as part of the type design by
the FAA or the Boeing Commercial Airplanes ODA after issuance of
Boeing Service Bulletin B787-81205-SB340013-00, Issue 002, dated May
6, 2016. If the software check fails, before further flight,
accomplish corrective actions and repeat the software check and
applicable corrective actions until the software check is passed.

(i) Parts Installation Prohibition

    As of the effective date of this AD, installation on any
airplane of FMS OPS version HNP5F-AL11-5010 or HNP58-AL11-5006 is
prohibited, except as required by paragraph (h) of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin B787-81205-
SB340013-00, Issue 001, dated December 23, 2015.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (l)(1) of this AD. Information may be
emailed to: [email protected].
    (2) 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.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes ODA that has
been authorized by the Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair method, modification
deviation, or alteration deviation must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.

(l) Related Information

    (1) For more information about this AD, contact Nelson Sanchez,
Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO
Branch, 2200 South 216th St.,

Des Moines, WA 98198; phone and fax:<PHONE_NUMBER>; email:
[email protected].
    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Des Moines, Washington, on October 10, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-22827 Filed 10-22-18; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 81, Number 70 (Tuesday, April 12, 2016)]
[Notices]
[Pages 21574-21576]
[FR Doc No: 2016-08334]

-----------------------------------------------------------------------

DEPARTMENT OF HEALTH AND HUMAN SERVICES

Food and Drug Administration

[Docket No. FDA-2014-E-2337]

Determination of Regulatory Review Period for Purposes of Patent
Extension; APTIOM

AGENCY: Food and Drug Administration, HHS.

ACTION: Notice.

-----------------------------------------------------------------------

SUMMARY: The Food and Drug Administration (FDA) has determined the
regulatory review period for APTIOM and is publishing this notice of
that determination as required by law. FDA has made the determination
because of the submission of an application to the Director of the U.S.
Patent and Trademark Office (USPTO), Department of Commerce, for the
extension of a patent which claims that human drug product.

DATES: Anyone with knowledge that any of the dates as published (in the
SUPPLEMENTARY INFORMATION section) are incorrect may submit either
electronic or written comments and ask for a redetermination by June
13, 2016. Furthermore, any interested person may petition FDA for a
determination regarding whether the applicant for extension acted with
due diligence during the regulatory review period by October 11, 2016.
See ``Petitions'' in the SUPPLEMENTARY INFORMATION section for more
information.

ADDRESSES: You may submit comments as follows:

Electronic Submissions

    Submit electronic comments in the following way:
     Federal eRulemaking Portal: http://www.regulations.gov.
Follow the instructions for submitting comments. Comments submitted
electronically, including attachments, to http://www.regulations.gov
will be posted to the docket unchanged. Because your comment will be
made public, you are solely responsible for ensuring that your comment
does not include any confidential information that you or a third party
may not wish to be posted, such as medical information, your or anyone
else's Social Security number, or confidential business information,
such as a manufacturing process. Please note that if you include your
name, contact information, or other information that identifies you in
the body of your comments, that information will be posted on http://www.regulations.gov.
     If you want to submit a comment with confidential
information that you do not wish to be made available to the public,
submit the comment as a written/paper submission and in the manner
detailed (see ``Written/Paper Submissions'' and ``Instructions'').

Written/Paper Submissions

    Submit written/paper submissions as follows:
     Mail/Hand delivery/Courier (for written/paper
submissions): Division of Dockets Management (HFA-305), Food and Drug
Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852.
     For written/paper comments submitted to the Division of
Dockets Management, FDA will post your comment, as well as any
attachments, except for information submitted, marked and identified,
as confidential, if submitted as detailed in ``Instructions.''
    Instructions: All submissions received must include the Docket No.
FDA-2014-E-2337 for ``Determination of Regulatory Review Period for
Purposes of Patent Extension; APTIOM.'' Received comments will be
placed in the docket and, except for those submitted as ``Confidential
Submissions,'' publicly viewable at http://www.regulations.gov or at
the Division of Dockets Management between 9 a.m. and 4 p.m., Monday
through Friday.
     Confidential Submissions--To submit a comment with
confidential information that you do not wish to be made publicly
available, submit your comments only as a written/paper submission. You
should submit two copies total. One copy will include the information
you claim to be confidential with a heading or cover note that states
``THIS DOCUMENT CONTAINS CONFIDENTIAL INFORMATION''. The Agency will
review this copy, including the claimed confidential information, in
its consideration of comments. The second copy, which will have the
claimed confidential information redacted/blacked out, will be
available for public viewing and posted on http://www.regulations.gov.
Submit both copies to the Division of Dockets Management. If you do not
wish your name and contact information to be made publicly available,
you can provide this information on the cover sheet and not in the body
of your comments and you must identify this information as
``confidential.'' Any information marked as ``confidential'' will not
be disclosed except in accordance with 21 CFR 10.20 and other
applicable disclosure law. For more information about FDA's posting of
comments to public dockets, see 80 FR 56469, September 18, 2015, or
access the information at: http://www.fda.gov/regulatoryinformation/dockets/default.htm.
    Docket: For access to the docket to read background documents or
the electronic and written/paper comments received, go to http://www.regulations.gov and insert the docket number, found in brackets in
the heading of this document, into the ``Search'' box and follow the
prompts and/or go to the Division of Dockets Management, 5630 Fishers
Lane, Rm. 1061, Rockville, MD 20852.

FOR FURTHER INFORMATION CONTACT: Beverly Friedman, Office of Regulatory
Policy, Food and Drug Administration, 10903 New Hampshire Ave., Bldg.
51, Rm. 6250, Silver Spring, MD 20993,<PHONE_NUMBER>.

SUPPLEMENTARY INFORMATION:

I. Background

    The Drug Price Competition and Patent Term Restoration Act of 1984
(Pub. L. 98-417) and the Generic Animal Drug and Patent Term
Restoration Act (Pub. L. 100-670) generally provide that a patent may
be extended for a period of up to 5 years so long as the patented item
(human drug product, animal drug product, medical device, food
additive, or color additive) was subject to regulatory review by FDA
before the item was marketed. Under these acts, a product's regulatory
review period forms the basis for determining the amount of extension
an applicant may receive.
    A regulatory review period consists of two periods of time: A
testing phase and an approval phase. For human drug products, the
testing phase begins when the exemption to permit the clinical
investigations of the drug becomes effective and runs until the
approval phase begins. The approval phase starts with the initial
submission of an application to market the human drug product and
continues until FDA grants permission to market the drug product.
Although only a portion of a regulatory review period may count toward
the actual amount of extension that the Director of USPTO may award
(for example, half the testing phase must be subtracted as well as any
time that may have occurred before the patent was issued), FDA's
determination of the length of a regulatory review period for a human
drug product will include all of the testing phase and approval phase
as specified in 35 U.S.C. 156(g)(1)(B).
    FDA has approved for marketing the human drug product APTIOM
(eslicarbazepine acetate). APTIOM is indicated as an adjunctive
treatment of partial-onset seizures. Subsequent to this approval, the
USPTO received a patent term restoration application for APTIOM (U.S.
Patent No. 5,753,646) from BIAL-PORTELA & CA, S.A., and the USPTO
requested FDA's assistance in determining this patent's eligibility for
patent term restoration. In a letter dated March 19, 2015, FDA advised
the USPTO that this human drug product had undergone a regulatory
review period and that the approval of APTIOM represented the first
permitted commercial marketing or use of the product. Thereafter, the
USPTO requested that FDA determine the product's regulatory review
period.

II. Determination of Regulatory Review Period

    FDA has determined that the applicable regulatory review period for
APTIOM is 2,517 days. Of this time, 832 days occurred during the
testing phase of the regulatory review period, while 1,685 days
occurred during the approval phase. These periods of time were derived
from the following dates:
    1. The date an exemption under section 505(i) of the Federal Food,
Drug, and Cosmetic Act (the FD&C Act) (21 U.S.C. 355(i)) became
effective: December 20, 2006. FDA has verified the BIAL-PORTELA & CA,
S.A. claim that December 20, 2006, is the date the investigational new
drug application became effective.
    2. The date the application was initially submitted with respect to
the human drug product under section 505(b) of the FD&C Act: March 30,
2009.

The applicant claims March 29, 2009 as the date the NDA for APTIOM was
initially submitted. However, FDA records indicate that NDA 22-416 was
submitted on March 30, 2009.
    3. The date the application was approved: November 8, 2013. FDA has
verified the applicant's claim that NDA 22-416 was approved on November
8, 2013.
    This determination of the regulatory review period establishes the
maximum potential length of a patent extension. However, the USPTO
applies several statutory limitations in its calculations of the actual
period for patent extension. In its application for patent extension,
this applicant seeks 1,826 days of patent term extension.

III. Petitions

    Anyone with knowledge that any of the dates as published are
incorrect may submit either electronic or written comments and ask for
a redetermination (see DATES). Furthermore, any interested person may
petition FDA for a determination regarding whether the applicant for
extension acted with due diligence during the regulatory review period.
To meet its burden, the petition must be timely (see DATES) and contain
sufficient facts to merit an FDA investigation. (See H. Rept. 857, part
1, 98th Cong., 2d sess., pp. 41-42, 1984.) Petitions should be in the
format specified in 21 CFR 10.30.
    Submit petitions electronically to http://www.regulations.gov at
Docket No. FDA-2013-S-0610. Submit written petitions (two copies are
required) to the Division of Dockets Management (HFA-305), Food and
Drug Administration, 5630 Fishers Lane, Rm. 1061, Rockville, MD 20852.

    Dated: April 6, 2016.
Leslie Kux,
Associate Commissioner for Policy.
[FR Doc. 2016-08334 Filed 4-11-16; 8:45 am]
 BILLING CODE P


[Federal Register Volume 79, Number 64 (Thursday, April 3, 2014)]
[Rules and Regulations]
[Pages 18626-18629]
[FR Doc No: 2014-07235]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0363; Directorate Identifier 2013-NM-031-AD;
Amendment 39-17769; AD 2014-04-10]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A330-200, -300 and -200 Freighter series airplanes; and
Model A340-200, -300, -500, and -600 series airplanes. This AD was
prompted by a report that an airplane equipped with Angle of Attack
(AOA) sensors installed with conic plates recently experienced blockage
of all sensors during climb, leading to autopilot disconnection and
activation of the alpha protection (Alpha Prot) when Mach number was
increased. This AD requires, for certain airplanes, revising the
airplane flight manual (AFM) to advise the flightcrew of emergency
procedures for addressing AOA sensor blockage. This AD also requires
replacing the AOA sensor conic plates with AOA sensor flat plates,
which is a terminating action for the AFM revision. We are issuing this
AD to prevent reduced control of the airplane.

DATES: This AD becomes effective May 8, 2014.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 8, 2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0363; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
    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<EMAIL_ADDRESS>Internet http://www.airbus.com. You may view this 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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone:<PHONE_NUMBER>; fax:
425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to all Airbus
Model A330-200, -300 and -200 Freighter series airplanes; and Model
A340-200, -300, -500, and -600 series airplanes. The SNPRM published in
the Federal Register on October 2, 2013 (78 FR 60798). We preceded the
SNPRM with a notice of proposed rulemaking (NPRM), which published in
the Federal Register on May 3, 2013 (78 FR 25902). The SNPRM was
prompted by a report that an airplane equipped with AOA sensors
installed with conic plates recently experienced blockage of all
sensors during climb, leading to autopilot disconnection and activation
of the alpha protection (Alpha Prot) when Mach number was increased.
The NPRM and the SNPRM both proposed to revise the airplane flight
manual (AFM) to advise the flightcrew of emergency procedures for
addressing AOA sensor blockage, for certain airplanes. The NPRM and the
SNPRM also proposed to require replacing the AOA sensor conic plates
with AOA sensor flat plates, which is a terminating action for the AFM
revision. We are issuing this AD to prevent reduced control of the
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0023, 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:

    An A330 aeroplane experienced a blockage of all Angle of Attack
(AOA) probes during climb leading to Autopilot (AP) disconnection
and activation of the alpha protection (Alpha Prot) when Mach number
increased.
    Analysis showed that this aeroplane was equipped with AOA probes
having conic plates, and it is suspected that these plates might
have contributed to the event. Investigations are on-going to
determine the root cause of this AOA probes blockage. The AOA conic
plates can also be installed on A340 aeroplanes.
    These AOA conic plates could have been installed in production
through Airbus modification (mod.) 201609, associated to Thales
Avionics AOA probes Part Number (P/N) C16291AA and P/N C16291AB, or
mod. 201610, associated to Goodrich AOA probes P/N 0861ED, or in
service through Airbus Service Bulletin (SB) A330-34-3255 or SB
A340-34-4250 or SB A340-34-5081.
    The blockage of two or three AOA probes of 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 not be
able to counteract with a sidestick deflection, even in the full
backward position.
    This condition, if not corrected, could result in reduced
control of the aeroplane.
    To address this condition, Airbus developed a ``Blocked AOA
probes'' emergency procedure included in Airbus Airplane Flight
Manual (AFM) A330 Temporary Revision (TR) TR293 issue 1 and Airbus
AFM A340 TR294 issue 1.
    Consequently, EASA issued Emergency AD 2012-0258-E to require
amendment of the AFM to ensure that flight crews, in case of AOA
probe blockage, apply the applicable emergency procedure.
    Since that [EASA] AD was issued, Airbus published approved
instructions to re-install AOA probe flat plates on A330/A340 family
aeroplanes.
    For the reasons described above, this [EASA] AD retains the
requirements of EASA [Emergency] AD 2012-0258-E which is superseded,
and requires installation of AOA probe flat plates, after which the
AFM operational procedure must be removed.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0363-0002.

Comments

    We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. The following
presents the comment received on the proposal (78 FR 60798, October 2,
2013) and the FAA's response to each comment.

Request To Reduce Compliance Times

    Airbus asked that we reduce the compliance time of 5 months, as
specified in paragraphs (h) and (i) of the SNPRM (78 FR 60798, October
2, 2013), to 10 weeks. Airbus stated that, taking into account that
this AD was delayed due to issuance of an SNPRM, and that the
terminating action required by EASA AD 2013-0023, dated February 1,
2013 (http://www.regulations.gov/#!documentDetail;D=FAA-2013-0363-
0002), was already completed, it

recommends a 10-week compliance time for the actions in those
paragraphs.
    We acknowledge the commenter's recommendation to reduce the
compliance time specified in the SNPRM (78 FR 60798, October 2, 2013)
to 10 weeks. While there might be merit to reducing the compliance time
in this AD, the suggested reduction would make the actions currently
required by this AD more restrictive, so additional rulemaking would be
necessary. We find that further delaying this action would be
inappropriate in light of the identified unsafe condition. Therefore,
we have not changed this final rule in this regard.

Conclusion

    We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
     Are consistent with the intent that was proposed in the
SNPRM (78 FR 60798, October 2, 2013) for correcting the unsafe
condition; and
     Do not add any additional burden upon the public than was
already proposed in the SNPRM (78 FR 60798, October 2, 2013).

Costs of Compliance

    We estimate that this AD affects 64 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AFM revision..........................  1 work-hour x $85 per                 $0             $85          $5,440
                                         hour = $85.
Replacement of certain AOA sensor       7 work-hours x $85 per                 0             595          38,080
 conic plates.                           hour = $595.
Modification of installations of        5 work-hours x $85 per                 0             425          27,200
 certain AOA sensor flat plates.         hour = $425.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
    We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0363; or in person at the
Docket Management Facility between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD docket contains this 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2014-04-10 Airbus: Amendment 39-17769. Docket No. FAA-2013-0363;
Directorate Identifier 2013-NM-031-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 8, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301,
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all
manufacturer serial numbers.
    (2) Model A340-211, -212, -213, -311, -312, -313, -541, and -642
airplanes, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 34: Navigation.

(e) Reason

    This AD was prompted by a report that an airplane equipped with
Angle of Attack (AOA) sensors installed with conic plates recently
experienced blockage of all sensors during climb, leading to
autopilot disconnection and activation of the alpha protection
(Alpha Prot) when Mach number was increased. 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) Airplane Flight Manual Revision

    For airplanes identified in paragraphs (g)(1) and (g)(2) of this
AD, except as provided by paragraph (j) of this AD: Within 10 days
after the effective date of this AD, revise the Emergency Procedures
of the Airbus A330 and A340 Airplane Flight Manuals (AFMs), by
incorporating Airbus A330 Temporary Revision TR293, Issue 1.0, dated
December 4, 2012; or Airbus A340 Temporary Revision TR294, Issue
1.0, dated December 4, 2012; as applicable; to advise the flightcrew
of emergency procedures for addressing AOA sensor blockage. This can
be done by inserting Airbus A330 Temporary Revision TR293, Issue
1.0, dated December 4, 2012; or Airbus A340 Temporary Revision
TR294, Issue 1.0, dated December 4, 2012; into the applicable AFM.
When the information in Airbus A330 Temporary Revision TR293, Issue
1.0, dated December 4, 2012; or Airbus A340 Temporary Revision
TR294, Issue 1.0, dated December 4, 2012; is included in the general
revisions of the applicable AFM, the general revisions may be
incorporated into the AFM, and the temporary revisions may be
removed.
    (1) Model A330-201, -202, -203, -223, 223F, -243, -243F, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all
manufacturer serial numbers, on which Airbus modification 201609 or
201610 has been embodied in production; or on which Airbus Service
Bulletin A330-34-3255 has been embodied in service.
    (2) Model A340-211, -212, -213, -311, -312, -313, -541, and -642
airplanes, all manufacturer serial numbers, on which Airbus
modification 201609 or 201610 has been embodied in production; or on
which Airbus Service Bulletin A340-34-4250 or A340-34-5081 has been
embodied in service.

(h) Replacement

    Except as provided by paragraph (j) of this AD: Within 5 months
after the effective date of this AD, replace all AOA sensor conic
plates having part number (P/N) F3411060200000 or P/N F3411060900000
with an applicable AOA sensor flat plate identified in paragraph
(h)(1) or (h)(2) of this AD. Performing this replacement constitutes
terminating action for the AFM revision required by paragraph (g) of
this AD; and Airbus A330 Temporary Revision TR293, Issue 1.0, dated
December 4, 2012, and Airbus A340 Temporary Revision TR294, Issue
1.0, dated December 4, 2012, to the Airbus A330 and A340 AFMs, as
applicable, must be removed from the AFM before further flight after
doing the replacement.
    (1) Replace with a flat plate having P/N F3411007920200 or P/N
F3411007920300, as applicable, in accordance with the applicable
service information specified in paragraph (h)(1)(i), (h)(1)(ii), or
(h)(1)(iii) of this AD.
    (i) Airbus Mandatory Service Bulletin A330-34-3293, Revision 01,
including Appendix 01, dated June 12, 2013.
    (ii) Airbus Mandatory Service Bulletin A340-34-4273, Revision
01, including Appendix 01, dated June 12, 2013.
    (iii) Airbus Mandatory Service Bulletin A340-34-5093, Revision
01, including Appendix 01, dated June 12, 2013.
    (2) Replace with a flat plate having P/N F3411007920000 or P/N
F3411007920100, 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.

(i) Modification of Installation

    For airplanes on which any AOA sensor conic plate has been
replaced with an AOA sensor flat plate, in accordance with the
applicable service information specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD: Within 5 months after the effective
date of this AD, modify the installation of the AOA sensor flat
plates so that the plates are flush with the fuselage, in accordance
with the applicable service information identified in paragraph
(h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD.
    (1) Airbus Mandatory Service Bulletin A330-34-3293, including
Appendix 01, dated January 31, 2013.
    (2) Airbus Mandatory Service Bulletin A340-34-4273, including
Appendix 01, dated January 30, 2013.
    (3) Airbus Mandatory Service Bulletin A340-34-5093, including
Appendix 01, dated January 30, 2013.

(j) Exception to the Requirements of Paragraphs (g) and (h) of this AD

    For airplanes on which Airbus modification 203285 (improved AOA
flat plate protection treatment) has been embodied in production:
The actions specified in paragraphs (g) and (h) of this AD are not
required, provided that, since first flight, no AOA probe conic
plate having P/N F3411060200000 or P/N F3411060900000 has been
installed.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on
any airplane, an AOA sensor conic plate having P/N F3411060200000 or
P/N F3411060900000 or an AOA protection cover having P/N
98D34203003000.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.
Information may be emailed to<EMAIL_ADDRESS>
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, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). For a repair method to be approved,
the repair approval must specifically refer to this AD. You are
required to ensure the product is airworthy before it is returned to
service.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information EASA
Airworthiness Directive 2013-0023, dated February 1, 2013, for
related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0363-0002.
    (2) Service information identified in this AD that is not
incorporated by reference may be viewed at the addresses specified
in paragraphs (n)(3) and (n)(4) of this AD.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus A330 Temporary Revision TR293, Issue 1.0, dated
December 4, 2012, to the Airbus A330 Airplane Flight Manual (AFM).
    (ii) Airbus A340 Temporary Revision TR294, Issue 1.0, dated
December 4, 2012, to the Airbus A340 Airplane Flight Manual (AFM).
    (iii) Airbus Mandatory Service Bulletin A330-34-3293, Revision
01, including Appendix 01, dated June 12, 2013.
    (iv) Airbus Mandatory Service Bulletin A340-34-4273, Revision
01, including Appendix 01, dated June 12, 2013.
    (v) Airbus Mandatory Service Bulletin A340-34-5093, Revision 01,
including Appendix 01, dated June 12, 2013.
    (3) 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<EMAIL_ADDRESS>
Internet http://www.airbus.com.
    (4) You may view this 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.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-07235 Filed 4-2-14; 8:45 am]
BILLING CODE 4910-13-P