Airworthiness Directives; Agusta S.p.A. Helicopters, 15495-15498 [2018-07285]
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Federal Register / Vol. 83, No. 70 / Wednesday, April 11, 2018 / Rules and Regulations
e. In paragraph (c)(1)(iii), by removing
the word ‘‘rinderpest,’’;
■ f. In paragraphs (c)(1)(v) and (c)(5) and
(6), by removing the words ‘‘rinderpest
or’’; and
■ g. In paragraph (c)(7), by removing the
word ‘‘rinderpest,’’.
The revision reads as follows:
■
Done in Washington, DC, this 4th day of
April 2018.
Kevin Shea,
Administrator, Animal and Plant Health
Inspection Service.
[FR Doc. 2018–07232 Filed 4–10–18; 8:45 am]
BILLING CODE 3410–34–P
§ 98.34 Import permits for poultry semen
and animal semen.
DEPARTMENT OF TRANSPORTATION
*
Federal Aviation Administration
*
*
*
*
(c) * * *
(1) * * *
(i) The donor animal shall have been
inspected on the farm of origin or on
another premises (the inspection may be
on another premises only if a
veterinarian of the Department has
traced the donor animal back to its farm
of origin) by a veterinarian of the United
States Department of Agriculture who,
in cooperation with the veterinary
service of the region of origin of the
donor animal, shall have determined,
insofar as possible, that the donor
animal was never infected with footand-mouth disease; that the donor
animal was never on a farm or other
premises where foot-and-mouth disease
then existed; that the donor animal has
not been on a premises that had an
animal that was susceptible to the virus
of foot-and-mouth disease and that was
exposed to the disease during the 12
months immediately prior to the date of
inspection of the donor animal; that the
donor animal, if a swine, has never been
vaccinated against foot-and-mouth
disease; and that the donor animal was
free from evidence of other
communicable disease;
*
*
*
*
*
PART 104—PERMITS FOR
BIOLOGICAL PRODUCTS
47. The authority for part 104
continues to read as follows:
■
Authority: 21 U.S.C. 151–159; 7 CFR 2.22,
2.80, and 371.4.
48. Section 104.2 is amended by
revising paragraph (b) to read as follows:
■
§ 104.2
Permit authorized.
nshattuck on DSK9F9SC42PROD with RULES
*
*
*
*
*
(b) A permit shall not be issued for a
biological product from countries
known to have exotic diseases,
including but not limited to foot-andmouth disease, highly pathogenic avian
influenza, swine vesicular disease,
Newcastle disease, and African swine
fever, if in the opinion of the
Administrator, such products may
endanger the livestock or poultry of this
country.
*
*
*
*
*
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14 CFR Part 39
[Docket No. FAA–2018–0170; Product
Identifier 2017–SW–091–AD; Amendment
39–19239; AD 2018–07–08]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model A109E, A109K2,
A109S, AW109SP, A119, and AW119
MKII helicopters. This AD reduces the
life limit of and requires inspecting a
tail rotor blade retention bolt (bolt). This
AD is prompted by the discovery of a
cracked bolt. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD becomes effective April
26, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of April 26, 2018.
We must receive comments on this
AD by June 11, 2018.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
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15495
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0170; 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 AD, the
European Aviation Safety Agency
(EASA) AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for Docket Operations
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
For service information identified in
this final rule, contact Leonardo S.p.A.
Helicopters, Matteo Ragazzi, Head of
Airworthiness, Viale G.Agusta 520,
21017 C.Costa di Samarate (Va) Italy;
telephone +39–0331–711756; fax +39–
0331–229046; or at https://
www.leonardocompany.com/-/bulletins.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy., Room 6N–321,
Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0170.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Section, Rotorcraft
Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email
matthew.fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
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rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
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Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued Emergency AD No.
2016–0173–E, dated August 24, 2016, to
correct an unsafe condition for
Leonardo S.p.A. (formerly Agusta)
Model A109E, A109K2, A109LUH,
A109S, A119, AW109SP, and
AW119MKII helicopters. EASA advises
of a crack found in a bolt, part number
(P/N) 709–0160–57–101, during a preflight inspection of a Model A109E
helicopter. This part-numbered bolt is
also installed on Model A109K2,
A109LUH, A109S, A119, AW109SP,
and AW119MKII helicopters.
Subsequent investigation did not
identify the cause of the crack. EASA
advises that this condition, if not
detected and corrected, could lead to
failure of the tail rotor, possibly
resulting in loss of control of the
helicopter. As a precautionary measure
pending the completion of the
investigation and to address the unsafe
condition, the EASA AD requires
reducing the life limit of and
repetitively inspecting the bolts. The
EASA AD is considered an interim
action and further AD action may
follow.
Accordingly, this AD requires
reducing the life limit of bolt P/N 709–
0160–57–101 to 800 hours time-inservice (TIS) or 3,200 landings,
depending on the model helicopter on
which the bolt is installed. This AD also
requires, within 25 hours TIS,
inspecting each bolt for a crack using a
10X or higher power magnifying glass,
both before and after cleaning and
degreasing the bolts. Additional
inspections of the bolts at longer
intervals may also be necessary. We
plan to publish a notice of proposed
rulemaking to give the public an
opportunity to comment on those longterm requirements.
The FAA is in the process of updating
Agusta’s name change to Leonardo
Helicopters on its FAA type certificate.
Because this name change is not yet
effective, this AD specifies Agusta.
FAA’s Determination
These helicopters have been approved
by the aviation authority of Italy and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with Italy, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
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Jkt 244001
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs.
Related Service Information Under
1 CFR Part 51
Leonardo Helicopters has issued
Mandatory Bollettino Tecnico (BT) No.
109EP–149 for Model A109E
helicopters, Mandatory BT No. 109K–72
for Model A109K2 helicopters,
Mandatory BT No. 109S–072 for Model
A109S helicopters, Mandatory BT No.
109SP–105 for Model AW109SP
helicopters, and Mandatory BT No. 119–
080 for Model A119 and AW119 MKII
helicopters, all dated August 19, 2016.
This service information specifies
reducing the life limit of bolt P/N 709–
0160–57–101 and repetitively
inspecting the bolts for cracks.
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.
AD Requirements
This AD requires, before further flight,
removing from service any bolt P/N
709–0160–57–101 that has reached or
exceeded its new life limit. Thereafter,
this AD requires removing from service
any bolt P/N 709–0160–57–101 before it
reaches its new life limit.
This AD also requires, within 25
hours time-in-service, inspecting each
bolt for a crack using a 10X or higher
power magnifying glass, both before and
after cleaning and degreasing the bolts,
and replacing a cracked bolt before
further flight.
Differences Between This AD and the
EASA AD
The EASA AD applies to Model
A109LUH helicopters. This AD does not
because the Model A109LUH does not
have an FAA type certificate. The EASA
AD does not specify life limits for bolt
P/N 709–0160–57–101 that has been
interchanged between model helicopter
installations, while this AD does. The
EASA AD requires repeating the visual
inspection every 200 hours, while this
AD does not, as this time interval would
allow for sufficient time for notice and
comment.
Interim Action
We consider this AD to be an interim
action. The design approval holder is
currently developing a modification that
will address the unsafe condition
identified in this AD. Once this
modification is developed, approved,
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and available, we might consider
additional rulemaking.
Costs of Compliance
We estimate that this AD affects 234
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
Labor costs are estimated at $85 per
work-hour.
Removing a bolt that has reached its
new life limit will take about 2 workhours for a cost of $170 per bolt.
Inspecting the bolts will take about 4
work-hours for an estimated cost of
$340 per helicopter and $79,560 for the
U.S. fleet. Replacing a bolt will take
negligible additional labor time and
parts will cost about $500.
According to Leonardo Helicopter’s
service information, some of the costs of
this AD may be covered under warranty,
thereby reducing the cost impact on
affected individuals. We do not control
warranty coverage by Leonardo
Helicopter. Accordingly, we have
included all costs in our cost estimate.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies waiving notice
and comment prior to adoption of this
rule because some of the required
corrective actions must be completed
before further flight. Therefore, we find
good cause that notice and opportunity
for prior public comment are
impracticable.
In addition, for the reasons stated
above, we find that good cause exists for
making this amendment effective in less
than 30 days.
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
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that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed, 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
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2018–07–08 Agusta S.p.A.: Amendment 39–
19239; Docket No. FAA–2018–0170;
Product Identifier 2017–SW–091–AD.
(a) Applicability
This AD applies to Model A109E, A109K2,
A109S, AW109SP, A119, and AW119 MKII
helicopters, certificated in any category, with
a tail rotor blade retention bolt (bolt) part
number (P/N) 709–0160–57–101 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a bolt. This condition could result
in failure of the tail rotor and loss of control
of the helicopter.
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14:51 Apr 10, 2018
Jkt 244001
(c) Effective Date
This AD becomes effective April 26, 2018.
(d) 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.
(e) Required Actions
(1) Before further flight:
(i) For Model A109E and A109K2
helicopters, remove from service any bolt P/
N 709–0160–57–101 that has 800 or more
hours time-in-service (TIS). If the hours TIS
is unknown, remove the bolt from service.
Thereafter, remove from service any bolt P/
N 709–0160–57–101 before accumulating 800
hours TIS.
(ii) For Model A109S, AW109SP, A119,
and AW119 MKII helicopters, remove from
service any bolt P/N 709–0160–57–101 that
has 3,200 or more landings. If the number of
landings is unknown, remove the bolt from
service. Thereafter, remove from service any
bolt P/N 709–0160–57–101 before
accumulating 3,200 landings. For purposes of
this AD, a landing is counted anytime a
helicopter lifts off into the air and then lands
again regardless of the duration of the
landing and regardless of whether the engine
is shutdown.
(iii) Remove from service any bolt P/N
709–0160–57–101 that has been interchanged
between different model helicopters listed in
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD
that has 800 or more hours TIS or 3,200 or
more landings. If the hours TIS or number of
landings is unknown, remove the bolt from
service. Thereafter, remove from service any
bolt P/N 709–0160–57–101 that has been
interchanged between different model
helicopters listed in paragraphs (e)(1)(i) and
(e)(1)(ii) of this AD before accumulating 800
hours TIS or 3,200 landings, whichever
occurs first.
(2) Within 25 hours TIS, remove each bolt
P/N 709–0160–57–101. Prior to cleaning,
using a 10X or higher power magnifying
glass, visually inspect the bolt for a crack in
the area depicted in Figure 1 of Leonardo
Helicopters Mandatory Bollettino Tecnico
Nos. 109EP–149, 109K–72, 109S–072,
109SP–105, or 119–080, all dated August 19,
2016 (BT Nos. 109EP–149, 109K–72, 109S–
072, 109SP–105, or 119–080), as applicable
to your model helicopter.
(i) If there is a crack, replace the bolt before
further flight.
(ii) If there are no cracks, clean and
degrease the inspection area of the bolt with
solvent, and using a 10X or higher power
magnifying glass, visually inspect the bolt for
a crack in the area depicted in Figure 1 of BT
Nos. 109EP–149, 109K–72, 109S–072,
109SP–105, or 119–080, as applicable to your
model helicopter. If there is a crack, replace
the bolt before further flight.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: Matt Fuller, Senior Aviation
Safety Engineer, Safety Management Section,
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15497
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA)
Emergency AD No. 2016–0173–E, dated
August 24, 2016. You may view the EASA
AD on the internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2018–0170.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6500, Tail Rotor Drive System.
(i) 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) Leonardo Helicopters Mandatory
Bollettino Tecnico No. 109EP–149, dated
August 19, 2016.
(ii) Leonardo Helicopters Mandatory
Bollettino Tecnico No. 109K–72, dated
August 19, 2016.
(iii) Leonardo Helicopters Mandatory
Bollettino Tecnico No. 109S–072, dated
August 19, 2016.
(iv) Leonardo Helicopters Mandatory
Bollettino Tecnico No. 109SP–105, dated
August 19, 2016.
(v) Leonardo Helicopters Mandatory
Bollettino Tecnico No. 119–080, dated
August 19, 2016.
(3) For Leonardo Helicopters service
information identified in this AD, contact
Leonardo S.p.A. Helicopters, Matteo Ragazzi,
Head of Airworthiness, Viale G.Agusta 520,
21017 C.Costa di Samarate (Va) Italy;
telephone +39–0331–711756; fax +39–0331–
229046; or at https://
www.leonardocompany.com/-/bulletins.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Federal Register / Vol. 83, No. 70 / Wednesday, April 11, 2018 / Rules and Regulations
Issued in Fort Worth, Texas, on April 3,
2018.
Scott A. Horn,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2018–07285 Filed 4–10–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
U.S. Customs and Border Protection
19 CFR Part 101
[Docket No. USCBP–2017–0017; CBP Dec.
18–03]
Extension of Port Limits of Savannah,
GA
U.S. Customs and Border
Protection, Department of Homeland
Security.
ACTION: Final rule.
AGENCY:
This document adopts as a
final rule, with changes, proposed
amendments to U.S. Customs and
Border Protection (CBP) regulations
pertaining to the expansion of the
geographical limits of the port of entry
of Savannah, Georgia. The port limits
will be expanded to make the
boundaries more easily identifiable to
the public and to allow for uniform and
continuous service to the extended area
of Savannah, Georgia. This change is
part of CBP’s continuing program to use
its personnel, facilities, and resources
more efficiently and to provide better
service to carriers, importers, and the
general public.
DATES: Effective Date: May 11, 2018.
FOR FURTHER INFORMATION CONTACT:
Roger Kaplan, Office of Field
Operations, U.S. Customs and Border
Protection, (202) 325–4543, or by email
at Roger.Kaplan@dhs.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
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Background
In a Notice of Proposed Rulemaking
(NPRM) published in the Federal
Register (82 FR 30807) on July 3, 2017,
U.S. Customs and Border Protection
(CBP) proposed to amend § 101.3(b)(1)
of title 19 of the Code of Federal
Regulations (CFR) to extend the
geographical limits of the port of entry
of Savannah, Georgia. The proposed
boundaries of the port of entry included
the majority of Chatham County,
Georgia, as well as a small portion of
Jasper County, South Carolina.
As explained in the NPRM, Savannah,
Georgia was designated as a customs
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14:51 Apr 10, 2018
Jkt 244001
port of entry by the President’s message
of March 3, 1913, concerning the
reorganization of the U.S. Customs
Service pursuant to the Act of August
24, 1912 (37 Stat. 434; 19 U.S.C. 1).
Executive Order 8367, dated March 5,
1940, established specific geographical
boundaries for the port of entry of
Savannah, Georgia.
In the July 2017 NPRM, CBP proposed
to amend the geographical limits of the
port of entry of Savannah, Georgia
because the current boundaries
established by the Executive Order do
not include a large portion of SavannahHilton Head International Airport,
including the site of a proposed
replacement Federal Inspection Service
facility for arriving international
travelers, or distribution centers and
cold storage agricultural facilities that
support the seaport. Also, most of the
projected facilities, such as a new ship
terminal with two berths for container
ships and bonded warehouses, which
will be built on the region’s remaining
undeveloped properties will be outside
of the boundaries of the current port of
entry. CBP determined that the
extension of the boundaries would not
result in a change in the service that is
provided to the public by the port and
would not require a change in the
staffing or workload at the port. For the
proposed rule, CBP posted on the
docket on https://www.regulations.gov a
map of the Savannah area with the
current port limits marked by blue lines
and the proposed port limits marked by
red lines.
The NPRM solicited public comment
on the proposed rulemaking. The public
comment period closed on September 1,
2017.
Discussion of Comments
One commenter responded to the
solicitation of comments to the
proposed rule. A description of the
comment received, together with CBP’s
analysis, is set forth below.
Comment:
The commenter fully supported the
expansion of the port limits, but was
concerned that the proposed limits did
not take into consideration the
warehouses and distribution centers
being built to accommodate the current
volume of trade. The commenter
suggested that the western portion of the
boundary line be extended to the county
line (west of Interstate Highway 95) to
support the future growth of the area,
provide jobs and further solidify
Savannah’s position in international
trade.
CBP Response:
CBP agrees with the commenter’s
suggestion to extend the western portion
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of the boundary line as the purpose of
expanding the port of entry of Savannah
is to provide better services to the
carriers, importers and the general
public. In addition, CBP has become
aware that import facilities are just
outside of Chatham County. Thus, CBP
is extending the western boundary
slightly into Effingham County to
include those facilities. The further
extension of the port would not require
a change in staffing or workload at the
port.
Conclusion
After review of the comment, CBP has
determined to further expand the
boundaries of the Savannah port of
entry in this final rule. Instead of the
western boundaries being along the
Federal Interstate Highway 95, they
begin where Highway 204 (Fort Argyle
Road) intersects with Federal Interstate
Highway 95, then proceed north to the
intersection with Old River Road, then
north along Old River Road until it
intersects with Federal Interstate
Highway 16, then east along Federal
Interstate Highway 16 until it meets the
Chatham County line, and then north
along the Chatham County line until it
meets the intersection with Federal
Interstate Highway 95 and the GeorgiaSouth Carolina state line. The new port
limits are described below, and the map
posted on the docket on https://
www.regulations.gov shows the new
port limits as expanded by this final
rule marked by the blue and black lines.
Port Description of Savannah, Georgia
The final port limits of the port of
entry of Savannah, Georgia, are as
follows: From 32°14.588′ N–081°
08.455′ W (where Federal Interstate
Highway 95 crosses the Georgia-South
Carolina state line) and extending in a
straight line to 32°04.903′ N–
080°54.998′ W (where Walls Cut meets
Wright River and Turtle Island); then
proceeding in a straight line to
31°52.651′ N–081°03.331′ W (where
Adams Creek meets Green Island
Sound); then proceeding northwest in a
straight line to 32°00.280′ N–081°17.00′
W (where Highway 204 intersects
Federal Interstate Highway 95); then
proceeding northwest along Fort Argyle
Road (Highway 204) to the intersection
with Old River Road; then proceeding
north on Old River Road to the
intersection with Federal Interstate
Highway 16; then proceeding southeast
along Federal Interstate Highway 16 to
the Chatham County line; then
proceeding northeast and then east
along the length of the Chatham County
line until it intersects with Federal
Interstate Highway 95 at Knoxboro
E:\FR\FM\11APR1.SGM
11APR1
]]>Agencies
[Federal Register Volume 83, Number 70 (Wednesday, April 11, 2018)]
[Rules and Regulations]
[Pages 15495-15498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07285]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0170; Product Identifier 2017-SW-091-AD; Amendment
39-19239; AD 2018-07-08]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta
S.p.A. (Agusta) Model A109E, A109K2, A109S, AW109SP, A119, and AW119
MKII helicopters. This AD reduces the life limit of and requires
inspecting a tail rotor blade retention bolt (bolt). This AD is
prompted by the discovery of a cracked bolt. The actions of this AD are
intended to address an unsafe condition on these products.
DATES: This AD becomes effective April 26, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of April 26, 2018.
We must receive comments on this AD by June 11, 2018.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0170; 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 AD, the European Aviation Safety Agency (EASA) AD, any
incorporated-by-reference service information, the economic evaluation,
any comments received, and other information. The street address for
Docket Operations (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
For service information identified in this final rule, contact
Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness,
Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone
+39-0331-711756; fax +39-0331-229046; or at https://www.leonardocompany.com/-/bulletins. You may review the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0170.
FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this
[[Page 15496]]
rulemaking during the comment period. We will consider all the comments
we receive and may conduct additional rulemaking based on those
comments.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued Emergency AD No. 2016-0173-E, dated August
24, 2016, to correct an unsafe condition for Leonardo S.p.A. (formerly
Agusta) Model A109E, A109K2, A109LUH, A109S, A119, AW109SP, and
AW119MKII helicopters. EASA advises of a crack found in a bolt, part
number (P/N) 709-0160-57-101, during a pre-flight inspection of a Model
A109E helicopter. This part-numbered bolt is also installed on Model
A109K2, A109LUH, A109S, A119, AW109SP, and AW119MKII helicopters.
Subsequent investigation did not identify the cause of the crack. EASA
advises that this condition, if not detected and corrected, could lead
to failure of the tail rotor, possibly resulting in loss of control of
the helicopter. As a precautionary measure pending the completion of
the investigation and to address the unsafe condition, the EASA AD
requires reducing the life limit of and repetitively inspecting the
bolts. The EASA AD is considered an interim action and further AD
action may follow.
Accordingly, this AD requires reducing the life limit of bolt P/N
709-0160-57-101 to 800 hours time-in-service (TIS) or 3,200 landings,
depending on the model helicopter on which the bolt is installed. This
AD also requires, within 25 hours TIS, inspecting each bolt for a crack
using a 10X or higher power magnifying glass, both before and after
cleaning and degreasing the bolts. Additional inspections of the bolts
at longer intervals may also be necessary. We plan to publish a notice
of proposed rulemaking to give the public an opportunity to comment on
those long-term requirements.
The FAA is in the process of updating Agusta's name change to
Leonardo Helicopters on its FAA type certificate. Because this name
change is not yet effective, this AD specifies Agusta.
FAA's Determination
These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, EASA, its technical representative,
has notified us of the unsafe condition described in the EASA AD. We
are issuing this AD because we evaluated all information provided by
EASA and determined the unsafe condition exists and is likely to exist
or develop on other helicopters of these same type designs.
Related Service Information Under 1 CFR Part 51
Leonardo Helicopters has issued Mandatory Bollettino Tecnico (BT)
No. 109EP-149 for Model A109E helicopters, Mandatory BT No. 109K-72 for
Model A109K2 helicopters, Mandatory BT No. 109S-072 for Model A109S
helicopters, Mandatory BT No. 109SP-105 for Model AW109SP helicopters,
and Mandatory BT No. 119-080 for Model A119 and AW119 MKII helicopters,
all dated August 19, 2016. This service information specifies reducing
the life limit of bolt P/N 709-0160-57-101 and repetitively inspecting
the bolts for cracks.
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.
AD Requirements
This AD requires, before further flight, removing from service any
bolt P/N 709-0160-57-101 that has reached or exceeded its new life
limit. Thereafter, this AD requires removing from service any bolt P/N
709-0160-57-101 before it reaches its new life limit.
This AD also requires, within 25 hours time-in-service, inspecting
each bolt for a crack using a 10X or higher power magnifying glass,
both before and after cleaning and degreasing the bolts, and replacing
a cracked bolt before further flight.
Differences Between This AD and the EASA AD
The EASA AD applies to Model A109LUH helicopters. This AD does not
because the Model A109LUH does not have an FAA type certificate. The
EASA AD does not specify life limits for bolt P/N 709-0160-57-101 that
has been interchanged between model helicopter installations, while
this AD does. The EASA AD requires repeating the visual inspection
every 200 hours, while this AD does not, as this time interval would
allow for sufficient time for notice and comment.
Interim Action
We consider this AD to be an interim action. The design approval
holder is currently developing a modification that will address the
unsafe condition identified in this AD. Once this modification is
developed, approved, and available, we might consider additional
rulemaking.
Costs of Compliance
We estimate that this AD affects 234 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work-hour.
Removing a bolt that has reached its new life limit will take about
2 work-hours for a cost of $170 per bolt. Inspecting the bolts will
take about 4 work-hours for an estimated cost of $340 per helicopter
and $79,560 for the U.S. fleet. Replacing a bolt will take negligible
additional labor time and parts will cost about $500.
According to Leonardo Helicopter's service information, some of the
costs of this AD may be covered under warranty, thereby reducing the
cost impact on affected individuals. We do not control warranty
coverage by Leonardo Helicopter. Accordingly, we have included all
costs in our cost estimate.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because some of the required corrective actions must be completed
before further flight. Therefore, we find good cause that notice and
opportunity for prior public comment are impracticable.
In addition, for the reasons stated above, we find that good cause
exists for making this amendment effective in less than 30 days.
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
[[Page 15497]]
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed, 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 adding the following new airworthiness
directive (AD):
2018-07-08 Agusta S.p.A.: Amendment 39-19239; Docket No. FAA-2018-
0170; Product Identifier 2017-SW-091-AD.
(a) Applicability
This AD applies to Model A109E, A109K2, A109S, AW109SP, A119,
and AW119 MKII helicopters, certificated in any category, with a
tail rotor blade retention bolt (bolt) part number (P/N) 709-0160-
57-101 installed.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a bolt. This
condition could result in failure of the tail rotor and loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective April 26, 2018.
(d) 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.
(e) Required Actions
(1) Before further flight:
(i) For Model A109E and A109K2 helicopters, remove from service
any bolt P/N 709-0160-57-101 that has 800 or more hours time-in-
service (TIS). If the hours TIS is unknown, remove the bolt from
service. Thereafter, remove from service any bolt P/N 709-0160-57-
101 before accumulating 800 hours TIS.
(ii) For Model A109S, AW109SP, A119, and AW119 MKII helicopters,
remove from service any bolt P/N 709-0160-57-101 that has 3,200 or
more landings. If the number of landings is unknown, remove the bolt
from service. Thereafter, remove from service any bolt P/N 709-0160-
57-101 before accumulating 3,200 landings. For purposes of this AD,
a landing is counted anytime a helicopter lifts off into the air and
then lands again regardless of the duration of the landing and
regardless of whether the engine is shutdown.
(iii) Remove from service any bolt P/N 709-0160-57-101 that has
been interchanged between different model helicopters listed in
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD that has 800 or more
hours TIS or 3,200 or more landings. If the hours TIS or number of
landings is unknown, remove the bolt from service. Thereafter,
remove from service any bolt P/N 709-0160-57-101 that has been
interchanged between different model helicopters listed in
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD before accumulating
800 hours TIS or 3,200 landings, whichever occurs first.
(2) Within 25 hours TIS, remove each bolt P/N 709-0160-57-101.
Prior to cleaning, using a 10X or higher power magnifying glass,
visually inspect the bolt for a crack in the area depicted in Figure
1 of Leonardo Helicopters Mandatory Bollettino Tecnico Nos. 109EP-
149, 109K-72, 109S-072, 109SP-105, or 119-080, all dated August 19,
2016 (BT Nos. 109EP-149, 109K-72, 109S-072, 109SP-105, or 119-080),
as applicable to your model helicopter.
(i) If there is a crack, replace the bolt before further flight.
(ii) If there are no cracks, clean and degrease the inspection
area of the bolt with solvent, and using a 10X or higher power
magnifying glass, visually inspect the bolt for a crack in the area
depicted in Figure 1 of BT Nos. 109EP-149, 109K-72, 109S-072, 109SP-
105, or 119-080, as applicable to your model helicopter. If there is
a crack, replace the bolt before further flight.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected].
(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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) Emergency AD No. 2016-0173-E, dated August 24, 2016.
You may view the EASA AD on the internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2018-0170.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor
Drive System.
(i) 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) Leonardo Helicopters Mandatory Bollettino Tecnico No. 109EP-
149, dated August 19, 2016.
(ii) Leonardo Helicopters Mandatory Bollettino Tecnico No. 109K-
72, dated August 19, 2016.
(iii) Leonardo Helicopters Mandatory Bollettino Tecnico No.
109S-072, dated August 19, 2016.
(iv) Leonardo Helicopters Mandatory Bollettino Tecnico No.
109SP-105, dated August 19, 2016.
(v) Leonardo Helicopters Mandatory Bollettino Tecnico No. 119-
080, dated August 19, 2016.
(3) For Leonardo Helicopters service information identified in
this AD, contact Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head
of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va)
Italy; telephone +39-0331-711756; fax +39-0331-229046; or at https://www.leonardocompany.com/-/bulletins.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(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 (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 15498]]
Issued in Fort Worth, Texas, on April 3, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018-07285 Filed 4-10-18; 8:45 am]
BILLING CODE 4910-13-P
