[Federal Register Volume 78, Number 48 (Tuesday, March 12, 2013)]
[Rules and Regulations]
[Pages 15599-15602]
[FR Doc No: 2013-05503]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD;
Amendment 39-17301; AD 2012-26-06]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft-Manufactured Model S-
64F Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Aircraft Corporation-manufactured Model S-64F helicopters, now
under the Erickson Air-Crane Incorporated (Erickson) Model S-64F type
certificate. This AD supersedes an existing AD which requires
inspections, rework, and replacement, if necessary, of the main gearbox
(MGB) second stage lower planetary plate (plate). Since we issued that
AD, the manufacturer has conducted a configuration review and analysis,
and a review of the service history of certain components. The actions
of this AD are intended to establish life limits for certain
components, remove various parts from service, and require consistency
in the part numbers of certain four bladed tail rotor (T/R) assemblies
to prevent fatigue cracking, failure from static overload, and
subsequent loss of control of the helicopter.

DATES: This AD is effective April 16, 2013.

ADDRESSES: For service information identified in this AD, contact
Erickson Air-Crane Incorporated, ATTN: Chris Erickson/Compliance
Officer, 3100 Willow Springs Rd., P.O. Box 3247, Central Point, OR
97502, telephone<PHONE_NUMBER>, fax<PHONE_NUMBER>, email address
<EMAIL_ADDRESS>You may review a copy of the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone:<PHONE_NUMBER>) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76137, telephone<PHONE_NUMBER>, email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    On June 29, 2012, at 77 FR 38744, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to Sikorsky Aircraft
Corporation-manufactured Model S-64F helicopters, now under the
Erickson Air-Crane Incorporated Model S-64F type certificate. That NPRM
proposed to supersede existing AD 97-10-15 (62 FR 28321, May 23, 1997),
to require reducing or establishing the life limits for certain flight-
critical components, removing other parts with service difficulties
from service, and require that T/R blade assembly, P/N 65160-00001-048,
be installed only as a set of four and not be installed with another
part-numbered blade. The proposed requirements were intended to prevent
a fatigue crack in a flight critical component, which could result in
component failure from static overload and subsequent loss of control
of the helicopter.

Comments

    We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 38744,
June 29, 2012).

FAA's Determination

    We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design and that air safety and the public
interest require adopting the AD requirements as proposed except for
minor editorial changes to meet current publication requirements. These
minor editorial changes are consistent with the intent of the proposals
in the NPRM (77 FR 38744, June 29, 2012) and will not increase the
economic burden on any operator nor increase the scope of the AD.

Related Service Information

    Erickson Service Bulletin No. 64F General-1, Rev. 17, contains the
Airworthiness Limitations Schedule for the Model S-64F helicopter and
lists the parts and assemblies with their specified retirement lives.

Costs of Compliance

    We estimate that this AD will affect 7 helicopters of U.S. Registry
and estimate, at an average labor rate of $85 per hour, the following
costs for removing from service the parts listed in Table 2 of this AD:
     Reviewing helicopter records to determine if an affected
part is installed will require approximately 2 work-hours, for a cost
per helicopter of $170 and a fleet cost of $1,190.
     Replacing the rotary rudder spindle assembly will require
10 work-hours and a parts cost of $2,787, for a cost per helicopter of
$3,637 and a fleet cost of $25,459.
     Replacing the plate will require 40 work-hours and a parts
cost of $43,750, for a cost per helicopter of $47,150 and a fleet cost
of $330,050.
     Replacing the main servo bracket assembly will require 2
work-hours and a parts cost of $5,223, for a cost per helicopter of
$5,393 and a fleet cost of $37,751.
     Replacing the primary servo link assembly of the M/R
tandem servo will require 10 work-hours and a parts cost of $14,533,
for a cost per helicopter of $15,383 and a fleet cost of $107,681.
     Replacing the T/R shoulder bolt will require 10 work-hours
and a parts cost of $571, for a cost per helicopter of $1,421 and a
fleet cost of $9,947.
     Replacing the T/R Blade Assembly will require 8 work-hours
and a parts cost of $125,765 for a cost per helicopter of $126,445 and
a fleet cost of $885,115.
     The total cost to replace the parts that are required to
be removed from service is estimated to be $199,599 per helicopter and
a fleet cost of $1,397,193.

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

    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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; 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 an economic evaluation of the estimated costs to comply
with this 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.

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 removing Amendment 39-10028 (62 FR
28321, May 23, 1997) and adding the following new airworthiness
directive (AD):

2012-26-06 ERICKSON AIR-CRANE INCORPORATED: Amendment 39-17301;
Docket No. FAA-2012-0689; Directorate Identifier 2009-SW-065-AD.

(a) Applicability

    This AD applies to Sikorsky Aircraft Corporation-manufactured
Model S-64F helicopters, now under the Erickson Air-Crane
Incorporated Model S-64F type certificate, certificated in any
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a fatigue crack in a
flight critical component. This condition could result in component
failure from static overload and subsequent loss of control of the
helicopter.

(c) Other Affected ADs

    This AD supersedes AD 97-10-15, Amendment 39-10028 (62 FR 28321,
May 23, 1997).

(d) Effective Date

    This AD becomes effective April 16, 2013.

(e) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

(f) Required Actions

    (1) Before further flight:
    (i) Remove from service any part with a number of hours time-in-
service (TIS) equal to or greater than the part's retirement life as
stated in Table 1 to Paragraph (f) of this AD.

                         Table 1 to Paragraph (f)--Parts With New or Revised Life Limits
----------------------------------------------------------------------------------------------------------------
                    Part name                        Part No. (P/N)                  Retirement life
----------------------------------------------------------------------------------------------------------------
Main Rotor (M/R) Blade Assembly.................        6415-20601-045  13,280 hours TIS.
Main Transmission Support Beam Assembly, LH.....        6420-62363-045  9,300 hours TIS.
Main Transmission Support Beam Assembly, RH.....        6420-62363-046  9,300 hours TIS.
Left Splice Fitting (Transition Fitting),               6420-66341-101  8,300 hours TIS.
 Rotary, Rudder Boom.
Right Splice Fitting (Transition Fitting),              6420-66341-102  8,300 hours TIS.
 Rotary, Rudder Boom.
M/R Drive Shaft.................................        6435-20536-101  2,200 hours TIS.
Pressure Plate Assembly, Rotary Wing Head.......       65101-11016-042  8,800 hours TIS.
Horn and Liner Assembly.........................       65102-11047-041  1,140 hours TIS.
Lower Hub Plate Assembly........................       65103-11009-041  15,500 hours TIS.
Horizontal Hinge Pin, Rotary Wing Head..........       65103-11020-103  5,100 hours TIS.
Damper Bracket Assembly, Rotary Wing Head.......       65103-11032-043  20,000 hours TIS.
Hub Subassembly, Rotary Wing....................       65103-11310-043  21,600 hours TIS.
Shaft Assembly, Pitch Control Tail Gearbox......       65358-07035-043  9,400 hours TIS.
Rod End Assembly, Primary Servo Assembly........       65652-11212-041  20,800 hours TIS.
----------------------------------------------------------------------------------------------------------------

    Note 1 to Table 1 to Paragraph (f) of this AD:  The list of
parts in Table 1 to Paragraph (f) of this AD contains only a portion
of the life-limited parts for this model helicopter and is not an
all-inclusive list.

    (ii) Revise the retirement life of each part as shown in Table 1
to Paragraph (f) of this AD by making pen and ink changes or by
inserting a copy of this AD into the Airworthiness Limitations
section of the maintenance manual.
    (iii) Record on the component history card or equivalent record
the retirement life for each part as shown in Table 1 to Paragraph
(f) of this AD.
    (2) Before further flight, remove from service any part with a
P/N listed in Table 2 to Paragraph (f) of this AD, regardless of the
part's TIS. The P/Ns listed in Table 2 to Paragraph (f) of this AD
are not eligible for installation on any helicopter.

                           Table 2 to Paragraph (f)--Parts To Be Removed From Service
----------------------------------------------------------------------------------------------------------------
                    Part name                                                   P/N
----------------------------------------------------------------------------------------------------------------
Spindle Assembly, Rotary Rudder.................  6410-30302-041.
Main Gearbox Second Stage Lower Planetary Plate.  6435-20516-101 or 6435-20516-102.
Bracket Assembly, Main Servo....................  6435-20527-041 or 6435-20527-042.
Primary Servo Link, Tandem Servo, M/R...........  6465-62161-042.
Shoulder Bolt, Tail Rotor (T/R).................  65111-07001-102.
T/R Blade Assembly..............................  65161-00001-041.
----------------------------------------------------------------------------------------------------------------

     (3) Before further flight, if a T/R blade assembly, P/N 65160-
00001-048, is installed, remove any of the other three T/R blade
assemblies that have a different P/N and replace it with a T/R blade
assembly, P/N 65160-00001-048. The T/R blade assembly, P/N 65160-
00001-048, must be installed in sets of four only.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft
Certification Office, Fort Worth, Texas 76137, telephone (817) 222-
5170, email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(h) Additional Information

    Erickson Service Bulletin No. 64F General-1, Revision 17, dated
August 17, 2010, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact Erickson Air-Crane
Incorporated, ATTN: Chris Erickson/Compliance Officer, 3100 Willow
Springs Rd, P.O. Box 3247, Central Point, OR 97502, telephone (541)
664-5544, fax<PHONE_NUMBER>, email address
<EMAIL_ADDRESS>You may review a copy of this
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6300: Main Rotor
Drive System and 6400: Tail Rotor System.

    Issued in Fort Worth, Texas, on March 1, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-05503 Filed 3-11-13; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 78, Number 64 (Wednesday, April 3, 2013)]
[Notices]
[Page 20100]
[FR Doc No: 2013-07679]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 12690-003]

Public Utility District No. 1 of Snohomish County, WA; Notice of
Technical Meeting

    a. Date and Time of Meeting: April 18, 2013; 10 a.m. Pacific Time
(1:00 p.m. Eastern Time).
    b. Place: Telephone conference call.
    c. FERC Contact: Stephen Bowler<EMAIL_ADDRESS>or (202)
502-6861.
    d. Purpose of Meeting: Discuss the change in the description of the
turbine braking system for the proposed Admiralty Inlet Pilot Tidal
Project included by Public Utility District No. 1 of Snohomish County,
Washington in their comments filed with the Commission on February 14,
2013 in regard to the Environmental Assessment issued by the Commission
on January 15, 2013.
    e. Proposed Agenda: 1. Introduction; 2. Meeting objectives; and 3.
Turbine braking system.
    f. A summary of the meeting will be prepared for the project's
record.
    g. All local, state, and federal agencies, Indian tribes, and other
interested parties are invited to participate by phone. Please email
Stephen Bowler at<EMAIL_ADDRESS>or call<PHONE_NUMBER> by
Monday, April 15, 2013, to RSVP and to receive specific instructions on
how to participate.

    Dated: March 27, 2013.
Kimberly D. Bose,
 Secretary.
[FR Doc. 2013-07679 Filed 4-2-13; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 83, Number 128 (Tuesday, July 3, 2018)]
[Notices]
[Pages 31136-31137]
[FR Doc No: 2018-14225]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. CP16-121-000]

National Grid LNG, LLC; Notice of Availability of the
Environmental Assessment for the Proposed Fields Point Liquefaction
Project

    The staff of the Federal Energy Regulatory Commission (FERC or
Commission) has prepared an environmental assessment (EA) for the
Fields Point Liquefaction Project, proposed by National Grid LNG, LLC
(National Grid) in the above-referenced docket. National Grid requests
authorization to construct natural gas liquefaction facilities at its
existing Fields Point liquefied natural gas (LNG) storage facility in
Providence, Rhode Island.
    The EA assesses the potential environmental effects of the
construction and operation of the Fields Point Liquefaction Project in
accordance with the requirements of the National Environmental Policy
Act (NEPA). The FERC staff concludes that approval of the proposed
project, with appropriate mitigating measures, would not constitute a
major federal action significantly affecting the quality of the human
environment.
    The U.S. Department of Transportation, Rhode Island Department of
Environmental Management, and the Rhode Island Coastal Resources
Management Council participated as cooperating agencies in the
preparation of the EA. Cooperating agencies have jurisdiction by law or
special expertise with respect to resources potentially affected by the
proposal and participate in the NEPA analysis.
    For its Fields Point Liquefaction Project, National Grid would
construct a

natural gas liquefier, including the following facilities:
     Electric-powered booster compressor;
     pretreatment system;
     gas regeneration heater; and
     liquefaction train including heat exchangers cooled by a
closed-loop nitrogen refrigeration cycle.
    The FERC staff mailed copies of the EA to federal, state, and local
government representatives and agencies; elected officials;
environmental and public interest groups; Native American tribes;
potentially affected landowners and other interested individuals and
groups; and newspapers and libraries in the project area. In addition,
the EA is available for public viewing on the FERC's website
(www.ferc.gov) using the eLibrary link. A limited number of copies of
the EA are available for distribution and public inspection at: Federal
Energy Regulatory Commission, Public Reference Room, 888 First Street
NE, Room 2A, Washington, DC 20426<PHONE_NUMBER>.
    Any person wishing to comment on the EA may do so. Your comments
should focus on the potential environmental effects, reasonable
alternatives, and measures to avoid or lessen environmental impacts.
The more specific your comments, the more useful they will be. To
ensure that the Commission has the opportunity to consider your
comments prior to making its decision on this project, it is important
that we receive your comments in Washington, DC on or before 5:00 p.m.
Eastern Time on July 25, 2018.
    For your convenience, there are three methods you can use to file
your comments to the Commission. In all instances please reference the
applicable project docket number (CP16-121-000) with your submission.
The Commission encourages electronic filing of comments and has staff
available to assist you at<PHONE_NUMBER> or
[email protected].
    (1) You can file your comments electronically using the eComment
feature on the Commission's website (www.ferc.gov) under the link to
Documents and Filings. Using eComment is an easy method for submitting
brief, text-only comments on a project;
    (2) You can also file your comments electronically using the
eFiling feature on the Commission's website (www.ferc.gov) under the
link to Documents and Filings. With eFiling, you can provide comments
in a variety of formats by attaching them as a file with your
submission. New eFiling users must first create an account by clicking
on eRegister. You must select the type of filing you are making. A
comment on a particular project is considered a Comment on a Filing; or
    (3) You can file a paper copy of your comments by mailing them to
the following address: Kimberly D. Bose, Secretary, Federal Energy
Regulatory Commission, 888 First Street NE, Room 1A, Washington, DC
20426.
    Any person seeking to become a party to the proceeding must file a
motion to intervene pursuant to Rule 214 of the Commission's Rules of
Practice and Procedures (18 CFR 385.214). Only intervenors have the
right to seek rehearing or judicial review of the Commission's
decision. The Commission grants affected landowners and others with
environmental concerns intervenor status upon showing good cause by
stating that they have a clear and direct interest in this proceeding
which no other party can adequately represent. Simply filing
environmental comments will not give you intervenor status, but you do
not need intervenor status to have your comments considered.
    Additional information about the project is available from the
Commission's Office of External Affairs, at (866) 208-FERC, or on the
FERC website (www.ferc.gov) using the eLibrary link. Click on the
eLibrary link, click on General Search, and enter the docket number in
the Docket Number field excluding the last three digits (i.e., CP16-
121). Be sure you have selected an appropriate date range. For
assistance, please contact FERC Online Support at
[email protected] or toll free at<PHONE_NUMBER>, or for TTY,
contact<PHONE_NUMBER>. The eLibrary link also provides access to the
texts of formal documents issued by the Commission, such as orders,
notices, and rulemakings.
    In addition, the Commission offers a free service called
eSubscription which allows you to keep track of all formal issuances
and submittals in specific dockets. This can reduce the amount of time
you spend researching proceedings by automatically providing you with
notification of these filings, document summaries, and direct links to
the documents. Go to www.ferc.gov/docs-filing/esubscription.asp.

    Dated: June 25, 2018.
Kimberly D. Bose,
Secretary.
[FR Doc. 2018-14225 Filed 7-2-18; 8:45 am]
 BILLING CODE 6717-01-P


[Federal Register Volume 83, Number 75 (Wednesday, April 18, 2018)]
[Notices]
[Pages 17168-17170]
[FR Doc No: 2018-08073]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Project No. 2669-085]

Notice of Application Tendered for Filing With the Commission and
Establishing Procedural Schedule for Licensing and Deadline for
Submission of Final Amendments; Bear Swamp Power Company, LLC

    Take notice that the following hydroelectric application has been
filed with the Commission and is available for public inspection.
    a. Type of Application: New Major License.

    b. Project No.: 2669-085.
    c. Date Filed: March 30, 2018.
    d. Applicant: Bear Swamp Power Company, LLC (Bear Swamp).
    e. Name of Project: Bear Swamp Project.
    f. Location: The existing project is located on the Deerfield River
in Berkshire and Franklin Counties, Massachusetts. The project does not
affect federal lands.
    g. Filed Pursuant to: Federal Power Act, 16 U.S.C. 791(a)-825(r).
    h. Applicant Contact: Steven P. Murphy, Director of Licensing,
Brookfield Renewable Energy Group, 33 West 1st Street South, Fulton, NY
13069; Telephone<PHONE_NUMBER>.
    i. FERC Contact: John Baummer,<PHONE_NUMBER> or
[email protected].
    j. This application is not ready for environmental analysis at this
time.
    k. Project Description: The existing Bear Swamp Project consists of
a pumped storage development, the Bear Swamp Pumped Storage
Development, and a conventional hydropower development, the Fife Brook
Development, with a combined authorized capacity of 676 megawatts (MW).
The project generates an average of 483,863 megawatt-hours (MWh)
annually, and uses an average of 618,293 MWh annually to operate the
pumped storage development.

Bear Swamp Pumped Storage Development

    The existing Bear Swamp Pumped Storage Development consists of the
following existing facilities: (1) A 118-acre upper reservoir with a
gross storage capacity of 8,300 acre-feet at the normal full water
surface elevation of approximately 1,600 feet National Geodetic
Vertical Datum of 1929 (NGVD), which is contained by existing
topography and 4 dikes: (a) An approximately 1,300-foot-long, 155-foot-
high curved, earth and rock-fill dike (North Dike); (b) an
approximately 350-foot-long, 23-foot-high earth and rock-fill dike
extending from the eastside of the North Dike (North Dike Extension);
(c) an approximately 2,880-foot-long, 140-foot-high earth and rock-fill
dike (South Dike); and (d) an approximately 750-foot-long, 50-foot-high
earth and rock-fill dike (East Dike); (2) a 420-foot long emergency
spillway to the east of the North Dike Extension; (3) an 88-foot-long,
1.5- to 4-foot-wide, 4-foot-high submerged weir with three 5-foot-wide,
3-foot-high concrete stoplog gates; (4) a 40-foot-diameter concrete
inlet/outlet structure located at the bottom of the upper reservoir to
the west of the North Dike; (5) an approximately 1,430.5-foot-long
tunnel system that includes: (a) A 75-foot-long concrete-lined section
that tapers from 40 feet to 25 feet in diameter; (b) an approximately
965-foot-long, 25-foot-diameter concrete-lined section; (c) a 15-foot-
long concrete-lined section that bifurcates from a single 25-foot-
diameter section to two 20-foot-diameter penstock sections; (d) two 25-
foot-long concrete-lined penstock sections that taper from 20 feet to
17.5 feet in diameter; (e) two 322-foot-long, 17.5-foot-diameter
concrete-lined penstock sections; (f) two 20-foot-long concrete-lined
penstock sections that taper from 17.5 feet to 11 feet in diameter; and
(g) two 8.5-foot-long, 11-foot-diameter, steel-lined penstock sections;
(6) a 227-foot-long, 79-foot-wide, 182-foot-high underground powerhouse
containing two reversible Francis pump turbine-generator units with a
total authorized capacity of 666 MW; (7) two 504-foot-long, 22-foot-
wide, 29.5-foot-high concrete-lined draft tube tunnels; (8) a lower
reservoir inlet/outlet structure with four 15-foot-wide, 20-foot-high
bays, each equipped with 16-foot-wide, 20.6-foot-high steel slide
gates; (9) four 15-foot-wide, 26.7-foot-tall steel trashracks with 6-
inch bar spacing; (10) two 13.8-kilovolt (kV) motor-generator lead
electrical lines, one approximately 890 feet long (east lead) and one
approximately 900 feet long (west lead); (11) a 600-foot-long, 15-foot-
wide, 23-foot-high access tunnel for the generator lead lines; (12) two
13.8/230-kV step-up transformers; (13) two 230-kV above-ground
transmission lines, one approximately 4,075 feet long (south line) and
one approximately 3,960 feet long (north line), which terminate at a
non-project switchyard owned by National Grid; (14) a 700-foot-long,
25-foot-wide, 29-foot-high tunnel for the access road; and (15)
appurtenant facilities.

Fife Brook Development

    The existing Fife Brook Development consists of: (1) An 890-foot-
long, 130-foot-high earthen rock-fill dam; (2) a 152-acre impoundment
with a gross storage capacity of 6,900 acre-feet at a normal maximum
water surface elevation of 870 feet NGVD, which also serves as the
lower reservoir for the Bear Swamp Pumped Storage Development; (3) two
36-foot-wide, 40-foot-high steel Tainter spillway gates that are
integral with the dam; (4) a concrete intake structure that is integral
with the dam and includes an 11.2-foot-wide, 24-foot-tall trashrack
with 3-inch bar spacing and a 15-foot-wide, 18-foot-high headgate; (5)
a 10-foot-diameter, 200-foot-long steel penstock; (6) an approximately
79.25-foot-long, 44-foot-wide, 94-foot-tall concrete powerhouse
containing a 10-MW Francis turbine-generator unit; (7) a 21-foot-long
steel-lined draft tube; (8) an approximately 325-foot-long, 30-inch-
diameter minimum flow release pipe that is gated at its intake and
bifurcates into an approximately 55-foot-long, 20-inch-diameter pipe
and an approximately 55-foot-long, 24-inch-diameter pipe; (9) a
partially buried (860-foot-long section) and partially above-ground
(7,060-foot-long section) 13.8-kV transmission line that connects the
turbine-generator unit to the regional grid at a non-project substation
owned by Great River Hydro, LLC; and (10) appurtenant facilities.
    The Bear Swamp Pumped Storage Development uses a storage capacity
of 4,600 acre-feet to generate approximately 3,028 MWh of energy over a
generation run time of approximately 5.3 hours. The Bear Swamp Pumped
Storage Development normally generates and pumps back some or all of
its useable storage capacity over a 24-hour period.
    The impoundment for the Fife Brook Development is the lower
reservoir of the Bear Swamp Pumped Storage Development. The Fife Brook
impoundment has an allowable drawdown of 40 feet to provide a useable
storage capacity of 4,600 acre-feet to the upper reservoir of the Bear
Swamp Pumped Storage Development for daily peaking operations. Releases
from Fife Brook dam generally match the inflow from the Station No. 5
Development of Great River Hydro, LLC's Deerfield River Project (FERC
No. 2323), which discharges directly into the Fife Brook impoundment.
    The project's current license requires Bear Swamp to release a
continuous minimum flow of 125 cubic feet per second (cfs) from Fife
Brook dam, and to use water from the Bear Swamp Pumped Storage
Development to meet the required 125 cfs minimum flow as necessary. The
existing license also requires Bear Swamp to provide 106 scheduled
annual releases of 700 cfs for whitewater recreation downstream of the
Fife Brook dam from April 1 through October 31.
    l. Locations of the Application: A copy of the application is
available for review at the Commission in the Public Reference Room or
may be viewed on the Commission's website at http://www.ferc.gov using
the ``eLibrary'' link. Enter the docket number excluding the last three
digits in the docket number field to access the document. For
assistance, please contact FERC Online Support at
[email protected],<PHONE_NUMBER> (toll free), or (202) 502-
8659 (TTY). A copy is also available for inspection and

reproduction at the Rowe Town Library, located at 318 Zoar Road, Rowe,
MA 01367; or the North Adams Public Library, located at 74 Church
Street, North Adams, MA 01247.
    m. You may also register online at http://www.ferc.gov/docs-filing/esubscription.asp to be notified via email of new filings and issuances
related to this or other pending projects. For assistance, contact FERC
Online Support.
    n. Procedural Schedule: Pursuant to section 5.19(d) of the
Commission's regulations, the Director, Office of Energy Projects will
issue an order within 30 days of the filing date of the final license
application to resolve study requests that were filed in comments on
the draft license application. At this time, the application is
expected to be processed according to the following preliminary Hydro
Licensing Schedule. Revisions to the schedule may be made following the
Director's determination on the study requests, or as otherwise
appropriate.

------------------------------------------------------------------------
                  Milestone                           Target date
------------------------------------------------------------------------
Notice of Acceptance/Notice of Ready for       October 2018.
 Environmental Analysis.
Filing of recommendations, preliminary terms   December 2018.
 and conditions, and fishway prescriptions.
Commission issues Draft Environmental          June 2019.
 Assessment (EA).
Comments on Draft EA.........................  August 2019.
Modified terms and conditions................  October 2019.
Commission issues Final EA...................  January 2020.
------------------------------------------------------------------------

    o. Final amendments to the application must be filed with the
Commission no later than 30 days from the issuance date of the notice
of ready for environmental analysis.

    Dated: April 12, 2018.
Nathaniel J. Davis, Sr.,
Deputy Secretary.
[FR Doc. 2018-08073 Filed 4-17-18; 8:45 am]
 BILLING CODE 6717-01-P


[Federal Register Volume 80, Number 40 (Monday, March 2, 2015)]
[Rules and Regulations]
[Pages 11136-11138]
[FR Doc No: 2015-04142]

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

ENVIRONMENTAL PROTECTION AGENCY

40 CFR Part 52

[EPA-R04-OAR-2012-0694; FRL-9923-56-Region 4]

Approval and Promulgation of Implementation Plans; South
Carolina; Infrastructure Requirements for the 2008 8-Hour Ozone
National Ambient Air Quality Standards

AGENCY: Environmental Protection Agency (EPA).

ACTION: Final rule.

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

SUMMARY: The Environmental Protection Agency (EPA) is taking final
action to approve the July 17, 2012, State Implementation Plan (SIP)
submission, provided by the South Carolina Department of Health and
Environmental Control (SC DHEC) for inclusion into the South Carolina
SIP. This final rulemaking pertains to the Clean Air Act (CAA or the
Act) infrastructure requirements for the 2008 8-hour ozone national
ambient air quality standards (NAAQS). The CAA requires that each state
adopt and submit a SIP for the implementation, maintenance and
enforcement of each NAAQS promulgated by EPA, which is commonly
referred to as an ``infrastructure'' SIP. SC DHEC certified that the
South Carolina SIP contains provisions that ensure the 2008 8-hour
ozone NAAQS is implemented, enforced, and maintained in South Carolina
(hereafter referred to as an ``infrastructure SIP submission''). With
the exception of provisions pertaining to prevention of significant
deterioration (PSD) permitting, interstate transport, and visibility
protection requirements, EPA is taking final action to approve South
Carolina's infrastructure SIP submission, provided to EPA on July 17,
2012, because it addresses the infrastructure elements for the 2008 8-
hour ozone NAAQS.

DATES: This rule will be effective April 1, 2015.

ADDRESSES: EPA has established a docket for this action under Docket
Identification No. EPA-R04-OAR-2012-0694. All documents in the docket
are listed on the www.regulations.gov Web site. Although listed in the
index, some information is not publicly available, i.e., Confidential
Business Information or other information whose disclosure is
restricted by statute. Certain other material, such as copyrighted
material, is not placed on the Internet and will be publicly available
only in hard copy form. Publicly available docket materials are
available either electronically through www.regulations.gov or in hard
copy at the Air Regulatory Management Section, (formerly the Regulatory
Development Section), Air Planning and Implementation Branch, (formerly
the Air Planning Branch), Air, Pesticides and Toxics Management
Division, U.S. Environmental Protection Agency, Region 4, 61 Forsyth
Street SW., Atlanta, Georgia 30303-8960. EPA requests that if at all
possible, you contact the person listed in the FOR FURTHER INFORMATION
CONTACT section to schedule your inspection. The Regional Office's
official hours of business are Monday through Friday, 8:30 a.m. to 4:30
p.m. excluding Federal holidays.

FOR FURTHER INFORMATION CONTACT: Nacosta C. Ward, Air Regulatory
Management Section, Air Planning and Implementation Branch, Air,
Pesticides and Toxics Management Division, U.S. Environmental
Protection Agency, Region 4, 61 Forsyth Street SW., Atlanta, Georgia
30303-8960. The telephone number is<PHONE_NUMBER>. Ms. Ward can be
reached via electronic mail at<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

I. Background

    Upon promulgation of a new or revised NAAQS, sections 110(a)(1) and
(2) of the CAA require states to address basic SIP requirements,
including emissions inventories, monitoring, and modeling to assure
attainment and maintenance for that new NAAQS. Section 110(a) of the
CAA generally requires states to make a SIP submission to meet
applicable requirements in order to provide for the implementation,
maintenance, and enforcement of a new or revised NAAQS within three
years following the promulgation of such NAAQS, or within such shorter
period as EPA may prescribe. These SIP submissions are commonly
referred to as ``infrastructure'' SIP submissions. Section 110(a)
imposes the obligation upon states to make an infrastructure SIP
submission to EPA for a new or revised NAAQS, but the contents of that
submission may vary depending upon the facts and circumstances. In
particular, the data and analytical tools available at the time the
state develops and submits the infrastructure SIP for a new or revised
NAAQS affect the content of the submission. The contents of such
infrastructure SIP submissions may also vary depending upon what
provisions the state's existing SIP already contains. In the case of
the 2008 8-hour ozone NAAQS, states typically have met the basic
program elements required in section 110(a)(2) through

earlier SIP submissions in connection with previous ozone NAAQS.
    More specifically, section 110(a)(1) provides the procedural and
timing requirements for SIPs. Section 110(a)(2) lists specific elements
that states must meet for infrastructure SIP requirements related to a
newly established or revised NAAQS. As mentioned above, these
requirements include basic structural SIP elements such as modeling,
monitoring, and emissions inventories that are designed to assure
attainment and maintenance of the NAAQS. The requirements of section
110(a)(2) are summarized below and in EPA's September 13, 2013,
memorandum entitled ``Guidance on Infrastructure State Implementation
Plan (SIP) Elements under Clean Air Act Sections 110(a)(1) and
110(a)(2).'' \1\

    \1\ Two elements identified in section 110(a)(2) are not
governed by the three year submission deadline of section 110(a)(1)
because SIPs incorporating necessary local nonattainment area
controls are not due within three years after promulgation of a new
or revised NAAQS, but rather due at the time the nonattainment area
plan requirements are due pursuant to other provisions of the CAA
for submission of SIP revisions specifically applicable for
attainment planning purposes. These requirements are: (1)
Submissions required by section 110(a)(2)(C) to the extent that
subsection refers to a permit program as required in part D Title I
of the CAA; and (2) submissions required by section 110(a)(2)(I)
which pertain to the nonattainment planning requirements of part D,
Title I of the CAA. Today's proposed rulemaking does not address
infrastructure elements related to section 110(a)(2)(I) or the
nonattainment planning requirements of 110(a)(2)(C).
---------------------------------------------------------------------------

 110(a)(2)(A): Emission Limits and Other Control Measures
 110(a)(2)(B): Ambient Air Quality Monitoring/Data System
 110(a)(2)(C): Programs for Enforcement of Control Measures and
for Construction or Modification of Stationary Sources \2\
---------------------------------------------------------------------------

    \2\ This rulemaking only addresses requirements for this element
as they relate to attainment areas.
---------------------------------------------------------------------------

 110(a)(2)(D)(i)(I) and (II): Interstate Pollution Transport
 110(a)(2)(D)(ii): Interstate Pollution Abatement and
International Air Pollution
 110(a)(2)(E): Adequate Resources and Authority, Conflict of
Interest, and Oversight of Local Governments and Regional Agencies
 110(a)(2)(F): Stationary Source Monitoring and Reporting
 110(a)(2)(G): Emergency Powers
 110(a)(2)(H): SIP revisions
 110(a)(2)(I): Plan Revisions for Nonattainment Areas \3\
---------------------------------------------------------------------------

    \3\ As mentioned above, this element is not relevant to today's
rulemaking.
---------------------------------------------------------------------------

 110(a)(2)(J): Consultation with Government Officials, Public
Notification, and Prevention of Significant Deterioration (PSD) and
Visibility Protection
 110(a)(2)(K): Air Quality Modeling and Submission of Modeling
Data
 110(a)(2)(L): Permitting fees
 110(a)(2)(M): Consultation and Participation by Affected Local
Entities

    On August 22, 2014, EPA proposed to approve South Carolina's July
17, 2012, 2008 8-hour ozone NAAQS infrastructure SIP submission with
the exception of the PSD permitting requirements for major sources of
sections 110(a)(2)(C) and (J), the interstate transport requirements of
section 110(a)(2)(D)(i)(I) and (II) (prongs 1 through 4), and the
visibility requirements of section 110(a)(2)(J), which EPA will address
in a separate action. See 79 FR 49736. EPA did not receive any
comments, adverse or otherwise, on the Agency's August 22, 2014,
proposed action. In this rulemaking, EPA is taking final action to
approve South Carolina's infrastructure submission as demonstrating
that the State meets the applicable requirements of sections 110(a)(1)
and (2) of the CAA for the 2008 8-hour ozone NAAQS, as proposed in the
Agency's August 22, 2014 rulemaking. EPA will act on other portions of
South Carolina's submission in a separate action.

II. Final Action

    With the exception of the PSD permitting requirements for major
sources of sections 110(a)(2)(C) and (J), the interstate transport
requirements of section 110(a)(2)(D)(i)(I) and (II) (prongs 1 through
4), and the visibility requirements of section 110(a)(2)(J), EPA is
taking final action to approve South Carolina's July 17, 2012, SIP
submission. This submission addresses infrastructure requirements for
the 2008 8-hour ozone NAAQS for the South Carolina SIP. With the
exceptions noted above SC DHEC has addressed the elements of the CAA
110(a)(1) and (2) SIP requirements pursuant to section 110 of the CAA
to ensure that the 2008 8-hour ozone NAAQS is implemented, enforced,
and maintained in South Carolina.

III. Statutory and Executive Order Reviews

    Under the CAA, the Administrator is required to approve a SIP
submission that complies with the provisions of the Act and applicable
Federal regulations. 42 U.S.C. 7410(k); 40 CFR 52.02(a). Thus, in
reviewing SIP submissions, EPA's role is to approve state choices,
provided that they meet the criteria of the CAA. Accordingly, this
action merely approves state law as meeting federal requirements and
does not impose additional requirements beyond those imposed by State
law. For that reason, this action:
     Is not a ``significant regulatory action'' subject to
review by the Office of Management and Budget under Executive Order
12866 (58 FR 51735, October 4, 1993);
     does not impose an information collection burden under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.);
     is certified as not having a significant economic impact
on a substantial number of small entities under the Regulatory
Flexibility Act (5 U.S.C. 601 et seq.);
     does not contain any unfunded mandate or significantly or
uniquely affect small governments, as described in the Unfunded
Mandates Reform Act of 1995 (Pub. L. 104-4);
     does not have Federalism implications as specified in
Executive Order 13132 (64 FR 43255, August 10, 1999);
     is not an economically significant regulatory action based
on health or safety risks subject to Executive Order 13045 (62 FR
19885, April 23, 1997);
     is not a significant regulatory action subject to
Executive Order 13211 (66 FR 28355, May 22, 2001);
     is not subject to requirements of Section 12(d) of the
National Technology Transfer and Advancement Act of 1995 (15 U.S.C. 272
note) because application of those requirements would be inconsistent
with the CAA; and
     does not provide EPA with the discretionary authority to
address, as appropriate, disproportionate human health or environmental
effects, using practicable and legally permissible methods, under
Executive Order 12898 (59 FR 7629, February 16, 1994).
    In addition, this action for the state of South Carolina does not
have Tribal implications as specified by Executive Order 13175 (65 FR
67249, November 9, 2000). The Catawba Indian Nation Reservation is
located within the State of South Carolina. Pursuant to the Catawba
Indian Claims Settlement Act, S.C. Code Ann. 27-16-120, ``all state and
local environmental laws and regulations apply to the [Catawba Indian
Nation] and Reservation and are fully enforceable by all relevant state
and local agencies and authorities.'' However, EPA has determined that
because this rule does not have substantial direct effects on an Indian
Tribe because, as noted above, this action is not approving any
specific rule, but rather proposing that South Carolina's already
approved SIP meets certain CAA requirements. EPA notes today's action
will not impose

substantial direct costs on Tribal governments or preempt Tribal law.
    The Congressional Review Act, 5 U.S.C. 801 et seq., as added by the
Small Business Regulatory Enforcement Fairness Act of 1996, generally
provides that before a rule may take effect, the agency promulgating
the rule must submit a rule report, which includes a copy of the rule,
to each House of the Congress and to the Comptroller General of the
United States. EPA will submit a report containing this action and
other required information to the U.S. Senate, the U.S. House of
Representatives, and the Comptroller General of the United States prior
to publication of the rule in the Federal Register. A major rule cannot
take effect until 60 days after it is published in the Federal
Register. This action is not a ``major rule'' as defined by 5 U.S.C.
804(2).
    Under section 307(b)(1) of the CAA, petitions for judicial review
of this action must be filed in the United States Court of Appeals for
the appropriate circuit by May 1, 2015. Filing a petition for
reconsideration by the Administrator of this final rule does not affect
the finality of this action for the purposes of judicial review nor
does it extend the time within which a petition for judicial review may
be filed, and shall not postpone the effectiveness of such rule or
action. This action may not be challenged later in proceedings to
enforce its requirements. See section 307(b)(2).

List of Subjects in 40 CFR Part 52

    Environmental protection, Air pollution control, Incorporation by
reference, Intergovernmental relations, Nitrogen dioxide, Ozone,
Reporting and recordkeeping requirements, Volatile organic compounds.

    Dated: February 11, 2015.
V. Anne Heard,
Acting Regional Administrator, Region 4.

    40 CFR part 52 is amended as follows:

PART 52--APPROVAL AND PROMULGATION OF IMPLEMENTATION PLANS

0
1. The authority citation for part 52 continues to read as follows:

    Authority: 42 U.S.C. 7401 et seq.

Subpart PP--South Carolina

0
2. Section 52.2120(e), is amended by adding a new entry ``110(a)(1) and
(2) Infrastructure Requirements for the 2008 8-Hour Ozone National
Ambient Air Quality Standards'' at the end of the table to read as
follows:

Sec.  52.2120  Identification of plan.

* * * * *
    (e) * * *

                              EPA-Approved South Carolina Non-Regulatory Provisions
----------------------------------------------------------------------------------------------------------------
                                             State
               Provision                effective date      EPA Approval date               Explanation
----------------------------------------------------------------------------------------------------------------

                                                  * * * * * * *
110(a)(1) and (2) Infrastructure             7/17/2012  3/2/2015 [Insert citation  With the exception of PSD
 Requirements for the 2008 8-Hour                        of publication].           permitting requirements for
 Ozone National Ambient Air Quality                                                 major sources of sections
 Standards.                                                                         110(a)(2)(C) and (J);
                                                                                interstate transport
                                                                                requirements of section
                                                                                110(a)(2)(D)(i)(I) and (II),
                                                                                and the visibility
                                                                                requirements of section
                                                                                110(a)(2)(J).
----------------------------------------------------------------------------------------------------------------

[FR Doc. 2015-04142 Filed 2-27-15; 8:45 am]
BILLING CODE 6560-50-P


[Federal Register Volume 88, Number 134 (Friday, July 14, 2023)]
[Proposed Rules]
[Pages 45118-45121]
[FR Doc No: 2023-14751]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-1412; Project Identifier MCAI-2022-01588-E]
RIN 2120-AA64

Airworthiness Directives; Austro Engine GmbH Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Austro Engine GmbH Model E4 and E4P engines. This proposed
AD was prompted by reports of piston failures and the determination
that certain batches of pistons were manufactured with a dimensional
deviation in the piston pin bore and piston diameter. This proposed AD
would require repetitive engine oil analysis for aluminum content
outside the acceptable limits and, if necessary, replacement of the
pistons, piston rings, con-rods assembly, and crankcase or, as an
alternative, replacement of the engine core. The FAA is proposing this
AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this NPRM by August 28, 2023.

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 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.
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1412; 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 mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
    Material Incorporated by Reference:
     For service information identified in this NPRM, contact
Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A-2700 Weiner Neustadt,
Austria; phone: +43 2622 23000; website: austroengine.at.
     You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone:<PHONE_NUMBER>; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2023-1412; Project Identifier
MCAI-2022-01588-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI

should be sent to Barbara Caufield, Aviation Safety Engineer, FAA, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590. Any commentary that the
FAA receives which is not specifically designated as CBI will be placed
in the public docket for this rulemaking.

Background

    The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, has issued
EASA AD 2022-0240R1, dated December 15, 2022 (referred to after this as
the MCAI), to address an unsafe condition on Austro Engine GmbH Model
E4 and E4P engines. The MCAI states that a manufacturer investigation
into reports of piston failures determined that certain batches of
pistons were manufactured with a dimensional deviation in the piston
pin bore and in the piston diameter, which could cause piston failure,
with consequent loss of oil, loss of engine power, and reduced control
of the airplane. To address the unsafe condition, EASA issued EASA AD
2022-0240, dated December 6, 2022, to specify repetitive oil analyses
and replacement of the pistons, piston rings, con-rods assembly, and
crankcase, or as an alternative, replacement of the engine core. EASA
AD 2022-0240 also prohibited release to service of an airplane until
receipt of the results for each oil analysis.
    Since EASA AD 2022-0240 was issued, the manufacturer determined
that aluminum levels outside of the acceptable limits would be found
during the first oil analysis, and are unlikely to be found during
subsequent oil analyses. As a result, EASA revised EASA AD 2022-0240
and issued the MCAI to allow release to service of airplanes for a
limited number of flight hours immediately after the second and
subsequent oil samples are taken for analyses.
    You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2023-1412.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Austro Engine GmbH Mandatory Service Bulletin MSB-
E4-039/1, Revision 1, dated April 24, 2023, which specifies procedures
for oil analysis and replacement of the pistons, piston rings, con-rods
assembly, crankcase, and engine core.
    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 ADDRESSES.

FAA's Determination

    These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI and service information described above. The FAA is issuing
this NPRM after determining that the unsafe condition described
previously is likely to exist or develop on other products of the same
type design.

Proposed AD Requirements in This NPRM

    This proposed AD would require initial and repetitive engine oil
analysis for aluminum content outside the acceptable limits and, if
necessary, replacement of the pistons, piston rings, con-rods assembly,
and crankcase, or as an alternative, replacement of the engine core.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would
affect 357 engines installed on airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Oil Analysis.......................  .25 work-hours x $85 per                 $0          $21.25       $7,586.25
                                      hour = $21.25.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The agency has no way of determining the number of
aircraft that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace engine core...........................  50 work-hours x $85 per hour =           $15,524         $19,774
                                                 $4,250.
Replace pistons, piston rings, and con-rods     60 work-hours x $85 per hour =             2,216           7,316
 assembly.                                       $5,100.
Replace pistons, piston rings, con-rods         70 work-hours x $85 per hour =             4,141          10,091
 assembly, and crankcase.                        $5,950.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected operators.

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.
    The FAA is 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

    The FAA 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) Would not affect intrastate aviation in Alaska, and
    (3) Would 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:

Austro Engine GmbH: Docket No. FAA-2023-1412; Project Identifier
MCAI-2022-01588-E.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive
(AD) by August 28, 2023.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Austro Engine GmbH Model E4 and E4P engines
with a serial number listed in Tables 1, 2, 3, and 4 of Austro
Engine GMBH Mandatory Service Bulletin MSB-E4-039/1, Revision 1,
dated April 24, 2023 (MSB-E4-039/1).

(d) Subject

    Joint Aircraft System Component (JASC) Codes 8530, Reciprocating
Engine Cylinder Section; 8550, Reciprocating Engine Oil System.

(e) Unsafe Condition

    This AD was prompted by reports of piston failures and the
determination that certain batches of pistons were manufactured with
a dimensional deviation in the piston pin bore and piston diameter.
The FAA is issuing this AD to prevent piston failure. The unsafe
condition, if not addressed, could result in loss of oil, loss of
engine power, and reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For all affected engines, within the applicable compliance
times specified in Table 1 to paragraph (g)(1) of this AD, perform
an oil analysis in accordance with paragraph 2., Technical Details,
Engine Oil Analysis of MSB-E4-039/1, and do not return the engine to
service until the results of the oil analysis have been determined.

   Table 1 to Paragraph (g)(1)--Oil Analysis for All Affected Engines
------------------------------------------------------------------------
        Engine group             Compliance time          Interval
------------------------------------------------------------------------
Group 1 and Group 3.........  Within 15 flight      Before exceeding 50
                               hours (FHs) from      FHs since last oil
                               the effective date    analysis.
                               of this AD.
Group 2 and Group 4.........  Within 25 FHs from    Before exceeding 100
                               the effective date    FHs since last oil
                               of this AD.           analysis.
------------------------------------------------------------------------

    (2) Thereafter, repeat the oil analysis required by paragraph
(g)(1) of this AD before exceeding the applicable interval specified
in Table 1 to paragraph (g)(1) of this AD.
    (3) Following each repetitive oil analysis, the engine may be
returned to service for no more than the applicable interval
specified in Table 1 to paragraph (g)(1) of this AD, until receipt
of the oil analysis result.
    (4) If the result of any oil analysis required by paragraph
(g)(1) of this AD indicates the aluminum content of the oil is
greater than the limit specified in paragraph 2., Technical Details,
Engine Oil Analysis, Table 5--Oil check analysis--Aluminum PPM
allowable of MSB-E4-039/1, before further flight, replace the
pistons, piston rings, con-rods assembly, and crankcase, or replace
the engine core in accordance with paragraph 2., Technical Details,
Engine core replacement; or Pistons, piston rings, crankcase and
con-rod assy replacement; as applicable, of MSB-E4-039/1.
    (5) For Group 3 and Group 4 engines, within the applicable
compliance times specified in Table 2 to paragraph (g)(5) of this
AD, replace the pistons, piston rings, and con-rods assembly, or
replace the engine core in accordance with paragraph 2., Technical
Details, Engine core replacement; or Pistons, piston rings and con-
rod assy replacement, as applicable, of MSB-E4-039/1.

   Table 2 to Paragraph (g)(5)--Replacement for Groups 3 and 4 Engines
------------------------------------------------------------------------
           Engine group                        Compliance time
------------------------------------------------------------------------
Group 3...........................  Before exceeding 900 FHs since new,
                                     or within 15 FHs after the
                                     effective date of this AD,
                                     whichever occurs later.
Group 4...........................  Before exceeding 1,000 FHs since
                                     new, or within 25 FHs after the
                                     effective date of this AD,
                                     whichever occurs later.
------------------------------------------------------------------------

    Note 1 to paragraph (g)(5): FHs since new indicated in Table 2
to paragraph (g)(5) of this AD are FHs accumulated by the engine
since first installation on an airplane or since last overhaul as of
the effective date of this AD.

(h) Terminating Action

    (1) Replacement of the pistons, piston rings, con-rods assembly,
and crankcase, or replacement of the engine core, as specified in
paragraph (g)(4) of this AD, constitutes terminating action for the
repetitive oil analysis required by paragraph (g)(2) of this AD.
    (2) Replacement of the pistons, piston rings, and con-rods
assembly, or replacement of the engine core, as specified in
paragraph (g)(5) of this AD, constitutes terminating

action for the repetitive oil analysis required by paragraph (g)(2)
of this AD.

(i) Definitions

    (1) For the purpose of this AD, Group 1 engines are engines
having a serial number (S/N) listed in Table 1 of MSB-E4-039/1.
    (2) For the purpose of this AD, Group 2 engines are engines
having an S/N listed in Table 2 of MSB-E4-039/1.
    (3) For the purpose of this AD, Group 3 engines are engines
having an S/N listed in Table 3 of MSB-E4-039/1.
    (4) For the purpose of this AD, Group 4 engines are engines
having an S/N listed in Table 4 of MSB-E4-039/1.

(j) Credit for Previous Actions

    You may take credit for the actions required by paragraph
(g)(1), (4), or (5) of this AD, if you performed those actions
before the effective date of this AD using Austro Engine Mandatory
Service Bulletin MSB-E4-039/0, dated October 24, 2022.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation 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)(2) of this AD
and email 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.

(l) Additional Information

    (1) Refer to European Union Aviation Safety Agency (EASA) AD
2022-0240R1, dated December 15, 2022, for related information. This
EASA AD may be found in the AD docket at regulations.gov under
Docket No. FAA-2023-1412.
    (2) For more information about this AD, contact Barbara
Caufield, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; phone:<PHONE_NUMBER>; email:
[email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference 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) Austro Engine GMBH Mandatory Service Bulletin MSB-E4-039/1,
Revision 1, dated April 24, 2023.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact
Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A-2700 Weiner
Neustadt, Austria; phone: +43 2622 23000; website: austroengine.at.
    (4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call<PHONE_NUMBER>.
    (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, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on July 7, 2023.
Michael Linegang,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-14751 Filed 7-13-23; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39525-39529]
[FR Doc No: 2017-16579]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0130; Product Identifier 2016-NM-058-AD; Amendment
39-18986; AD 2017-16-09]
RIN 2120-AA64

Airworthiness Directives; Dassault Aviation Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all
Dassault Aviation Model MYSTERE-FALCON 50 airplanes and FALCON 2000
airplanes. This AD was prompted by a report indicating that during
ground maintenance, a Model FALCON 2000 airplane experienced a loss of
hydraulic pressure affecting both hydraulic systems due to damage to
both brake hoses on the main landing gear (MLG). This AD requires an
inspection for certain brake hoses, installation of protective wraps or
installation of certain brake hoses, and replacement of certain brake
hoses. We are issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective September 25, 2017.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 25,
2017.

ADDRESSES: For service information identified in this final rule,
contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box
2000, South Hackensack, NJ 07606; telephone:<PHONE_NUMBER>; Internet:
http://www.dassaultfalcon.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 1601 Lind Avenue
SW., Renton, 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-2017-0130.

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-2017-
0130; 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 Office (telephone
800-647-5527) is 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 20590.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone:<PHONE_NUMBER>; fax: 425-
227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Dassault Aviation Model
MYSTERE-FALCON 50 airplanes and FALCON 2000 airplanes. The NPRM
published in the Federal Register on March 23, 2017 (82 FR 14832)
(``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2013-0255, dated October 23, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for all Dassault Aviation Model MYSTERE-
FALCON 50 airplanes and FALCON 2000 airplanes. The MCAI states:

    During ground maintenance, a Falcon 2000 aeroplane experienced a
loss of hydraulic pressure, affecting both hydraulic systems.
    The investigation results revealed that this event was due to
damage to both brake hoses on the same main landing gear (MLG),
which chafed against the torque link assembly during MLG extension/
retraction cycle. The Part Numbers (P/N) of the affected brake hoses
are P/N AE705317-1 and P/N 00-200-1268, which are made of a braided
stainless steel sleeve.
    This condition, if not detected and corrected, could lead to
loss of braking during landing or a rejected take-off, possibly
resulting in a runway excursion. In addition, there is a risk of
fire if the leaking brake hydraulic fluid reaches hot parts.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the brake hoses to identify the P/N and determine
the presence of protection against chafing and, depending on
findings, installation of protective wraps or replacement of the
brake hoses with serviceable parts that have a Dacron sleeve
protection.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0130.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.

Request To Clarify the Applicability

    Dassault Aviation requested that the ``Applicability'' paragraph of
the proposed AD be clarified. Dassault Aviation stated the
``Applicability'' paragraph should be clarified to state that the
proposed AD affects Dassault Aviation Model MYSTERE-FALCON 50 airplanes
(including all commercial variants) and FALCON 2000 airplanes. Dassault
Aviation stated that all commercial variants include F50EX airplanes.
    We agree to clarify the applicability of this AD. Paragraph (c) of
this AD specifies all Dassault Aviation Model MYSTERE-FALCON 50
airplanes and FALCON 2000 airplanes. The applicability of this AD
identifies model designations as published in the most recent type
certificate data sheet for the affected models. We have revised this AD
by adding a new Note 1 to paragraph (c) of this AD to state that Model
MYSTERE-FALCON 50 airplanes include all commercial variants, including
F50EX airplanes.

Request To Revise the Compliance Time Threshold

    NetJets requested that we revise the compliance time threshold in
paragraph (h) of the proposed AD. NetJets commented that paragraph (h)
of the proposed AD requires that the protective wrap installation be
performed concurrently with paragraph (g) of the proposed AD. NetJets
stated that if the compliance time threshold in paragraph (h) of the
proposed AD was changed to ``within 9 months after the effective date
of this AD,'' it would allow a records review per paragraph (g) and
compliance with paragraph (h) without unnecessarily grounding airplanes
and also maintain the intended compliance threshold of the NPRM.
NetJets stated that paragraph (g) of the proposed AD may be performed
by a records inspection, which could be accomplished independently of
access to the airplane and could possibly ground an airplane due to
records discrepancies well before the compliance time threshold
specified in paragraph (g) of the proposed AD.
    We agree with the commenter's request. We have revised paragraph
(h) of this AD to include a compliance time of 9 months, which
corresponds with the compliance time in the MCAI.

Request To Use Messier-Dowty Service Information

    NetJets requested that the NPRM be revised to include Messier-Dowty
service information as an optional method of compliance. NetJets stated
that paragraph (i) of the proposed AD specifies compliance using
Dassault Service Bulletin F50-518, dated April 14, 2011, and Dassault
Service Bulletin F2000-368, dated May 29, 2009, which incorporate
Messier-Dowty Service Bulletin C23791-32-062, dated February 22, 2011,
and Messier-Dowty Service Bulletin D23345-32-020, dated May 14, 2009,
respectively. Net Jets stated that new and overhauled landing gear
include compliance information with the Messier-Dowty service
information, but not with the Dassault service information; therefore,
compliance with the Messier-Dowty service information should be
included as optional methods of compliance with paragraph (i) of the
proposed AD in addition to the Dassault service information.
    We agree with the commenter's request. We agree that in the
Accomplishment Instructions of Dassault Service Bulletin F50-518, dated
April 14, 2011; and Dassault Service Bulletin F2000-368, dated May 29,
2009, specifies to replace the MLG brake hose using Messier-Dowty
Service Bulletin C23791-32-062, dated February 22, 2011, and Messier-
Dowty Service Bulletin D23345-32-020, dated May 14, 2009, as
applicable. For clarification, we have added Note 2 to paragraphs
(h)(2) and (i) of this AD to state that Dassault Service Bulletin F50-
518, dated April 14, 2011, refers to Messier-Dowty Service Bulletin
C23791-32-062, dated February 22, 2011; and Dassault Service Bulletin
F2000-368, dated May 29, 2009, refers to Messier-Dowty Service Bulletin
D23345-32-020, dated May 14, 2009; as additional sources of guidance
for doing the replacement of certain brake hoses.

Conclusion

    We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We have reviewed the following Dassault service information.
     Dassault Service Bulletin F50-510, Revision 2, dated
December 20, 2012; and Dassault Service Bulletin F2000-382, Revision 2,
dated May 12, 2011. This service information describes procedures for
an inspection of the brake hoses to identify whether brake hoses having
certain part numbers are

installed, and installation of protective wraps on the brake hoses or
installation of certain brake hoses that are fitted with Dacron
sleeves. These documents are distinct since they apply to different
airplane models.
     Dassault Service Bulletin F50-518, dated April 14, 2011;
and Dassault Service Bulletin F2000-368, dated May 29, 2009. This
service information describes replacement of certain brake hoses. These
documents are distinct since they apply to different airplane models.
    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.

Costs of Compliance

    We estimate that this AD affects 302 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
----------------------------------------------------------------------------------------------------------------
Inspection.........................  1 work-hour x $85 per hour               $0             $85         $25,670
                                      = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary installations
and replacements that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need these installations and replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of brake hose.................  1 work-hour x $85 per hour = $85...            $340            $425
Installation of protective wraps...........  1 work-hour x $85 per hour = $85...             340             425
Replacement................................  1 work-hour x $85 per hour = $85...             340             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.
    This 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 to
the Director of the System Oversight Division.

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.

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 airworthiness
directive (AD):

2017-16-09 Dassault Aviation: Amendment 39-18986; FAA-2017-0130;
Product Identifier 2016-NM-058-AD.

(a) Effective Date

    This AD is effective September 25, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Dassault Aviation Model MYSTERE-FALCON 50
airplanes and FALCON 2000 airplanes, certificated in any category,
all serial numbers.
    Note 1 to paragraph (c) of this AD: Model MYSTERE-FALCON 50
airplanes include all commercial variants, including F50EX
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing
gear.

(e) Reason

    This AD was prompted by a report indicating that during ground
maintenance, a Model FALCON 2000 airplane experienced a loss of
hydraulic pressure affecting both hydraulic systems due to damage to
both

brake hoses on the main landing gear (MLG). We are issuing this AD
to detect and correct unprotected brake hoses, which could lead to
loss of braking during landing or a rejected take-off, and result in
a runway excursion and a risk of fire if the leaking brake hydraulic
fluid reaches hot parts.

(f) Compliance

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

(g) Inspection

    Within 9 months after the effective date of this AD, inspect the
brake hoses to identify whether any brake hose having part number
(P/N) AE705317-1 or P/N 00-200-1268 is installed. A review of
airplane maintenance records is acceptable in lieu of this
inspection if the part number of the brake hose can be conclusively
determined from that review.

(h) Installation

    If, during the inspection required by paragraph (g) of this AD,
it is determined that any brake hose having P/N AE705317-1 or P/N
00-200-1268 is installed, within 9 months after the effective date
of this AD, do the actions specified in paragraph (h)(1) or (h)(2)
of this AD.
    (1) Install protective wraps on the brake hoses, in accordance
with the Accomplishment Instructions of Dassault Service Bulletin
F50-510, Revision 2, dated December 20, 2012; or Dassault Service
Bulletin F2000-382, Revision 2, dated May 12, 2011; as applicable.
    (2) Install brake hoses having P/N 00-200-1534 that are fitted
with Dacron sleeves, in accordance with the Accomplishment
Instructions of Dassault Service Bulletin F50-518, dated April 14,
2011; or Dassault Service Bulletin F2000-368, dated May 29, 2009; as
applicable.
    Note 2 to paragraphs (h)(2) and (i) of this AD: Dassault Service
Bulletin F50-518, dated April 14, 2011, refers to Messier-Dowty
Service Bulletin C23791-32-062, dated February 22, 2011; and
Dassault Service Bulletin F2000-368, dated May 29, 2009, refers to
Messier-Dowty Service Bulletin D23345-32-020, dated May 14, 2009; as
additional sources of guidance for doing the replacement.

(i) Replacement

    Within 6,000 flight cycles, or within 149 months, whichever
occurs first after the effective date of this AD: Replace brake
hoses having P/N AE705317-1 and P/N 00-200-1268 with brake hoses
having P/N 00-200-1534 that are fitted with Dacron sleeves, in
accordance with the Accomplishment Instructions of Dassault Service
Bulletin F50-518, dated April 14, 2011; or Dassault Service Bulletin
F2000-368, dated May 29, 2009; as applicable. Once brake hoses
having P/N 00-200-1534 are fitted in an MLG leg, no further action
is required for that MLG leg, as specified in paragraph (j) of this
AD.

(j) Provisions for Unaffected MLG Leg Assemblies

    If, during the inspection required by paragraph (g) of this AD,
it is determined that the airplane is equipped with an MLG leg
assembly with a part number specified in table 1 to paragraph (j) of
this AD, the requirement of paragraph (h) of this AD is not
applicable, provided that the MLG leg assembly has not been modified
in service after its installation on an airplane.

                       Table 1 to Paragraph (j) of This AD--MLG Leg Assembly Not Affected
----------------------------------------------------------------------------------------------------------------
                   Model                          MLG leg position                       Part No.
----------------------------------------------------------------------------------------------------------------
MYSTERE-FALCON 50 airplanes...............  Left Hand (LH).............  C23791-1009 amdt F.
MYSTERE-FALCON 50 airplanes...............  Right Hand (RH)............  C23792-1009 amdt F.
FALCON 2000...............................  LH.........................  D23345000-7 amdt B.
FALCON 2000...............................  RH.........................  D23346000-7 amdt B.
----------------------------------------------------------------------------------------------------------------

    Note 3 to paragraph (j) of this AD: The parts specified in table
1 to paragraph (j) of this AD are known to be delivered with brake
hoses having P/N 00-200-1534 that are fitted with Dacron sleeves.

(k) Parts Installation Limitation

    As of the effective date of this AD, no person may install a
brake hose having P/N AE705317-1 or P/N 00-200-1268 on any airplane,
unless the brake hose has been inspected to verify that protective
wraps are installed on the hose, in accordance with the
Accomplishment Instructions of Dassault Service Bulletin F50-510,
Revision 2, dated December 20, 2012; or Dassault Service Bulletin
F2000-382, Revision 2, dated May 12, 2011; as applicable.

(l) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, on
any airplane, a brake hose having P/N AE705317-1 or P/N 00-200-1268,
or an MLG leg or shock absorber equipped with a brake hose having P/
N AE705317-1 or P/N 00-200-1268, after the actions in paragraphs
(h)(2) or (i) of this AD are done.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by
paragraphs (h)(1) and (k) of this AD, if those actions were
performed before the effective date of this AD using Dassault
Service Bulletin F50-510, Revision 1, dated December 15, 2010; or
Dassault Service Bulletin F2000-382, Revision 1, dated December 15,
2010.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards 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 International Section, send it to the attention of
the person identified in paragraph (o)(2) of this AD. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Dassault Aviation's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2013-0255, dated October 23, 2013, for related
information. This MCAI may be found in the AD docket on the Internet
at http://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0130.
    (2) For more information about this AD, contact Tom Rodriguez,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone:
425-227-1137; fax:<PHONE_NUMBER>.
    (3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(3) and (p)(4) of this AD.

(p) 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 this AD specifies otherwise.
    (i) Dassault Service Bulletin F50-510, Revision 2, dated
December 20, 2012.
    (ii) Dassault Service Bulletin F50-518, dated April 14, 2011.
    (iii) Dassault Service Bulletin F2000-368, dated May 29, 2009.
    (iv) Dassault Service Bulletin F2000-382, Revision 2, dated May
12, 2011.

    (3) For service information identified in this AD, contact
Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000,
South Hackensack, NJ 07606; telephone:<PHONE_NUMBER>; Internet:
http://www.dassaultfalcon.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>.
    (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 July 28, 2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-16579 Filed 8-18-17; 8:45 am]
 BILLING CODE 4910-13-P