Airworthiness Directives; Agusta S.p.A. Helicopters (Type Certificate Currently Held by AgustaWestland S.p.A.) (Agusta), 69039-69041 [2014-26825]
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Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Modification
Within 6,600 flight hours after the effective
date of this AD, but no later than 36 months
after the effective date of this AD: Modify the
MLG by installing a new bracket on the left
and right lower aft-wing planks, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
601R–32–110, dated December 19, 2013.
(h) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, 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 New York ACO, send it to
ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO,
1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516 228–7300; fax 516–
794–5531. Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) 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, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
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(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–10, dated
February 12, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-0489-0002.
(j) 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) Bombardier Service Bulletin 601R–32–
110, dated December 19, 2013.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
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13:14 Nov 19, 2014
Jkt 235001
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–26985 Filed 11–19–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0472; Directorate
Identifier 2013–SW–040–AD; Amendment
39–18018; AD 2014–23–02]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters (Type Certificate
Currently Held by AgustaWestland
S.p.A.) (Agusta)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Agusta Model A109E, A109K2, A119,
and AW119 MKII helicopters. This AD
requires repetitively performing a
magnetic particle inspection of the
Gleason crown for a crack. This AD was
prompted by a report of a crack that was
found on a Gleason crown, which if not
detected, could cause damage to or loss
of the main rotor drive and subsequent
loss of control of the helicopter.
DATES: This AD is effective December
26, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of December 26, 2014.
ADDRESSES: For service information
identified in this AD, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN:
Maurizio D’Angelo; telephone 39–0331–
664757; fax 39–0331–664680; or at
SUMMARY:
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69039
https://www.agustawestland.com/
technical-bullettins. You may review 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 https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this 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 the
Docket Operations Office (phone: 800–
647–5527) 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: Rao
Edupuganti, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
rao.edupuganti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 16, 2014, at 79 FR 41462, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
Agusta Model A109E, A109K2, A119,
and AW119 MKII helicopters with a
main transmission, part number (P/N)
109–0400–03–103, 109–0400–05–103,
and 109–0400–03–109, with a Gleason
crown, P/N 109–0403–07–103, installed.
The NPRM proposed to require, for
main transmissions with 2,400 or more
hours time-in-service (TIS), performing
repetitive magnetic particle inspections
of the Gleason crown for a crack. If there
is a crack, the NPRM proposed replacing
the Gleason crown assembly before
further flight. The NPRM also proposed
to prohibit installing a Gleason crown,
P/N 109–0403–07–103, or a Gleason
crown assembly, P/N 109–0401–27–101
or P/N 109–0401–27–109, on any
helicopter. The proposed requirements
were intended to detect a crack, which
could cause damage to or loss of the
main rotor drive and subsequent loss of
control of the helicopter.
The NPRM was prompted by AD No.
2013–0118, dated June 3, 2013, issued
by EASA, which is the Technical Agent
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Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations
for the Member States of the European
Union, to correct an unsafe condition
for Agusta Model A109K2, A109E,
A119, and AW119MKII helicopters.
EASA advises that during an overhaul
of an A119 main transmission, P/N 109–
0400–05–103, a crack on the Gleason
crown, P/N 109–0403–07–103, was
found. EASA further states that the
crack originated from the bottom of one
of the 40 threaded holes in the Gleason
crown, and that this part-numbered
Gleason crown is also installed on
Model A109 helicopters. EASA states
that this condition, if not corrected,
could cause damage to or loss of the
main rotor drive and loss of control of
the helicopter. To correct this unsafe
condition, EASA AD No. 2013–0118
requires repetitive magnetic particle
inspections of the Gleason crown and, if
there is a crack, replacing the Gleason
crown with a different part-numbered
Gleason crown. EASA AD No. 2013–
0118 also prohibits installing a Gleason
crown, P/N 109–0403–07–103, or a
Gleason crown assembly, P/N 109–
0401–27–101 or P/N 109–0401–27–109,
on any helicopter, as Gleason crown, P/
N 109–0403–07–103, is a component of
these assemblies.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (79 FR 41462, July 16, 2014).
FAA’s Determination
rmajette on DSK2VPTVN1PROD with RULES
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 and that air
safety and the public interest require
adopting the AD requirements as
proposed, except for minor editorial
changes. These changes are consistent
with the intent of the proposals in the
NPRM (79 FR 41462, July 16, 2014) and
will not increase the economic burden
on any operator nor increase the scope
of the AD.
Differences Between This AD and the
EASA AD
This AD requires compliance within
200 hours TIS for main transmissions
with 2,400 or more hours. The EASA
AD requires different compliance times,
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Jkt 235001
depending on the number of flight hours
the transmission has accumulated.
Related Service Information
We reviewed Agusta Bollettino
Tecnico (BT) No. 109EP–128 for Model
A109E helicopters, Agusta BT No.
109K–57 for Model A109K2 helicopters,
and Agusta BT No. 119–058 for Model
A119 and AW119MKII helicopters, each
Revision A and dated May 28, 2013.
Each BT describes procedures for
performing a magnetic particle
inspection on the Gleason crown, P/N
109–0403–07–103, for a crack. If there is
a crack, each BT specifies replacing the
Gleason crown assembly with a Gleason
crown assembly, P/N 109–0401–27–107.
We also reviewed Agusta BT No.
109EP–126 for Model A109E
helicopters, Agusta BT No. 109K–56 for
Model A109K2 helicopters, and Agusta
BT No. 119–053 for Model A119 and
AW119MKII helicopters, each dated
December 20, 2012. These BTs contain
procedures for upgrading the
transmission system by replacing the
Gleason crown assembly with a Gleason
crown assembly, P/N 109–0401–27–107.
Costs of Compliance
We estimate that this AD affects 218
helicopters of U.S. registry. We estimate
the following costs to comply with this
AD. At an average labor rate of $85 per
hour, magnetic particle inspecting the
Gleason crown requires about 24 workhours, for an estimated cost per
helicopter of $2,040, and a total cost of
$444,720 for the U.S. fleet, per
inspection cycle.
If required, replacing the Gleason
crown assembly requires about 24 workhours, and required parts will cost
$29,000, for a cost per helicopter of
$31,040.
According to the manufacturer, 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 for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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
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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
helicopters 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
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):
■
2014–23–02 Agusta S.p.A. Helicopters
(Type Certificate Currently Held By
AgustaWestland S.p.A.) (Agusta):
Amendment 39–18018; Docket No.
FAA–2014–0472; Directorate Identifier
2013–SW–040–AD.
E:\FR\FM\20NOR1.SGM
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Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations
(a) Applicability
(g) Additional Information
This AD applies to Agusta Model A109E,
A109K2, A119, and AW119 MKII helicopters
with a main transmission, part number (P/N)
109–0400–03–103, 109–0400–05–103, or
109–0400–03–109, with a Gleason crown, P/
N 109–0403–07–103, installed, certificated in
any category.
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2013–0118, dated June 3, 2013. You may
view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2014–0472.
This AD defines the unsafe condition as a
crack in a Gleason crown. This condition
could cause damage to or loss of the main
rotor drive and subsequent loss of control of
the helicopter.
(c) Effective Date
This AD becomes effective December 26,
2014.
(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) For main transmissions with 2,400 or
more hours time-in-service (TIS), within 200
hours TIS and thereafter at intervals not
exceeding 1,600 hours TIS, magnetic particle
inspect the Gleason crown, P/N 109–0403–
07–103, for a crack by following the
procedures in:
(i) Annex 1 of Agusta Bollettino Tecnico
(BT) No. 109EP–128, Revision A, dated May
28, 2013, for Model A109E helicopters;
(ii) Annex 1 of Agusta BT No. 109K–57,
Revision A, dated May 28, 2013, for Model
A109K2 helicopters; or
(iii) Annex 1 of Agusta BT No. 119–058,
Revision A, dated May 28, 2013, for Model
A119 and AW119MKII helicopters.
(2) If there is a crack, before further flight,
replace the Gleason crown assembly with a
Gleason Crown assembly, P/N 109–0401–27–
107. Replacing the Gleason crown assembly
with P/N 109–0401–27–107 is terminating
action for the inspection requirements of this
AD.
(3) After the effective date of this AD, do
not install a Gleason crown, P/N 109–0403–
07–103, or a Gleason crown assembly, P/N
109–0401–27–101 or P/N 109–0401–27–109,
on any helicopter.
rmajette on DSK2VPTVN1PROD with RULES
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Rao Edupuganti,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
rao.edupuganti@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.
13:14 Nov 19, 2014
DEPARTMENT OF COMMERCE
Bureau of Economic Analysis
15 CFR Part 801
[Docket No. 1206013202–4700–01]
RIN 0691–AA83
(h) Subject
(b) Unsafe Condition
VerDate Sep<11>2014
69041
Jkt 235001
Joint Aircraft Service Component (JASC)
Code: 6320: Main Rotor Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) AgustaWestland Bollettino Tecnico No.
109EP–128, Revision A, dated May 28, 2013.
(ii) AgustaWestland Bollettino Tecnico No.
109K–57, Revision A, dated May 28, 2013.
(iii) AgustaWestland Bollettino Tecnico
No. 119–058, Revision A, dated May 28,
2013.
(3) For AgustaWestland service
information identified in this AD, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN: Maurizio
D’Angelo; telephone 39–0331–664757; fax
39–0331–664680; or at https://
www.agustawestland.com/technicalbullettins.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. 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.
Issued in Fort Worth, Texas, on October 30,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–26825 Filed 11–19–14; 8:45 am]
BILLING CODE 4910–13–P
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Direct Investment Surveys: BE–10,
Benchmark Survey of U.S. Direct
Investment Abroad
Bureau of Economic Analysis,
Commerce.
ACTION: Final rule.
AGENCY:
This final rule amends
regulations of the Department of
Commerce’s Bureau of Economic
Analysis (BEA) to reinstate reporting
requirements for the 2014 BE–10,
Benchmark Survey of U.S. Direct
Investment Abroad. Benchmark surveys
are conducted every five years; the prior
survey covered 2009. The benchmark
survey covers the universe of U.S. direct
investment abroad, and is BEA’s most
comprehensive survey of such
investment in terms of subject matter.
For the 2014 benchmark survey, BEA
will make changes in the data items
collected. No changes will be made to
the reporting requirements for the
survey. This mandatory survey will be
conducted under the authority of the
International Investment and Trade in
Services Survey Act (the Act). Unlike
many other BEA surveys conducted
pursuant to the Act, a response will be
required from persons subject to the
reporting requirements of the BE–10,
Benchmark Survey of U.S. Direct
Investment Abroad, whether or not they
are contacted by BEA, in order to ensure
that respondents subject to the
requirements for U.S. direct investment
abroad are identified.
DATES: This final rule is effective
December 22, 2014.
FOR FURTHER INFORMATION CONTACT:
Patricia Abaroa, Chief, Direct
Investment Division (BE–50), Bureau of
Economic Analysis, U.S. Department of
Commerce, Washington, DC 20230;
phone (202) 606–9591.
SUPPLEMENTARY INFORMATION: On August
14, 2014, BEA published a notice of
proposed rulemaking that set forth
revised reporting criteria for the BE–10,
Benchmark Survey of U.S. Direct
Investment Abroad (79 FR 47599–
47603). On September 9, 2014, BEA
published a correction to the notice of
proposed rulemaking to correct the
Regulation Identifier Number (RIN) that
was listed in the first notice (79 FR
53355). BEA received two comments on
the proposed rule.
SUMMARY:
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]]>Agencies
[Federal Register Volume 79, Number 224 (Thursday, November 20, 2014)]
[Rules and Regulations]
[Pages 69039-69041]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26825]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0472; Directorate Identifier 2013-SW-040-AD;
Amendment 39-18018; AD 2014-23-02]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Helicopters (Type
Certificate Currently Held by AgustaWestland S.p.A.) (Agusta)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD
requires repetitively performing a magnetic particle inspection of the
Gleason crown for a crack. This AD was prompted by a report of a crack
that was found on a Gleason crown, which if not detected, could cause
damage to or loss of the main rotor drive and subsequent loss of
control of the helicopter.
DATES: This AD is effective December 26, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of December 26,
2014.
ADDRESSES: For service information identified in this AD, contact
AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-
664757; fax 39-0331-664680; or at https://www.agustawestland.com/technical-bullettins. You may review 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 https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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 the Docket Operations Office (phone: 800-647-
5527) 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: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email rao.edupuganti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On July 16, 2014, at 79 FR 41462, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to Agusta Model A109E,
A109K2, A119, and AW119 MKII helicopters with a main transmission, part
number (P/N) 109-0400-03-103, 109-0400-05-103, and 109-0400-03-109,
with a Gleason crown, P/N 109-0403-07-103, installed. The NPRM proposed
to require, for main transmissions with 2,400 or more hours time-in-
service (TIS), performing repetitive magnetic particle inspections of
the Gleason crown for a crack. If there is a crack, the NPRM proposed
replacing the Gleason crown assembly before further flight. The NPRM
also proposed to prohibit installing a Gleason crown, P/N 109-0403-07-
103, or a Gleason crown assembly, P/N 109-0401-27-101 or P/N 109-0401-
27-109, on any helicopter. The proposed requirements were intended to
detect a crack, which could cause damage to or loss of the main rotor
drive and subsequent loss of control of the helicopter.
The NPRM was prompted by AD No. 2013-0118, dated June 3, 2013,
issued by EASA, which is the Technical Agent
[[Page 69040]]
for the Member States of the European Union, to correct an unsafe
condition for Agusta Model A109K2, A109E, A119, and AW119MKII
helicopters. EASA advises that during an overhaul of an A119 main
transmission, P/N 109-0400-05-103, a crack on the Gleason crown, P/N
109-0403-07-103, was found. EASA further states that the crack
originated from the bottom of one of the 40 threaded holes in the
Gleason crown, and that this part-numbered Gleason crown is also
installed on Model A109 helicopters. EASA states that this condition,
if not corrected, could cause damage to or loss of the main rotor drive
and loss of control of the helicopter. To correct this unsafe
condition, EASA AD No. 2013-0118 requires repetitive magnetic particle
inspections of the Gleason crown and, if there is a crack, replacing
the Gleason crown with a different part-numbered Gleason crown. EASA AD
No. 2013-0118 also prohibits installing a Gleason crown, P/N 109-0403-
07-103, or a Gleason crown assembly, P/N 109-0401-27-101 or P/N 109-
0401-27-109, on any helicopter, as Gleason crown, P/N 109-0403-07-103,
is a component of these assemblies.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (79 FR 41462,
July 16, 2014).
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 and that air
safety and the public interest require adopting the AD requirements as
proposed, except for minor editorial changes. These changes are
consistent with the intent of the proposals in the NPRM (79 FR 41462,
July 16, 2014) and will not increase the economic burden on any
operator nor increase the scope of the AD.
Differences Between This AD and the EASA AD
This AD requires compliance within 200 hours TIS for main
transmissions with 2,400 or more hours. The EASA AD requires different
compliance times, depending on the number of flight hours the
transmission has accumulated.
Related Service Information
We reviewed Agusta Bollettino Tecnico (BT) No. 109EP-128 for Model
A109E helicopters, Agusta BT No. 109K-57 for Model A109K2 helicopters,
and Agusta BT No. 119-058 for Model A119 and AW119MKII helicopters,
each Revision A and dated May 28, 2013. Each BT describes procedures
for performing a magnetic particle inspection on the Gleason crown, P/N
109-0403-07-103, for a crack. If there is a crack, each BT specifies
replacing the Gleason crown assembly with a Gleason crown assembly, P/N
109-0401-27-107.
We also reviewed Agusta BT No. 109EP-126 for Model A109E
helicopters, Agusta BT No. 109K-56 for Model A109K2 helicopters, and
Agusta BT No. 119-053 for Model A119 and AW119MKII helicopters, each
dated December 20, 2012. These BTs contain procedures for upgrading the
transmission system by replacing the Gleason crown assembly with a
Gleason crown assembly, P/N 109-0401-27-107.
Costs of Compliance
We estimate that this AD affects 218 helicopters of U.S. registry.
We estimate the following costs to comply with this AD. At an average
labor rate of $85 per hour, magnetic particle inspecting the Gleason
crown requires about 24 work-hours, for an estimated cost per
helicopter of $2,040, and a total cost of $444,720 for the U.S. fleet,
per inspection cycle.
If required, replacing the Gleason crown assembly requires about 24
work-hours, and required parts will cost $29,000, for a cost per
helicopter of $31,040.
According to the manufacturer, 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 for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 helicopters 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 adding the following new airworthiness
directive (AD):
2014-23-02 Agusta S.p.A. Helicopters (Type Certificate Currently
Held By AgustaWestland S.p.A.) (Agusta): Amendment 39-18018; Docket
No. FAA-2014-0472; Directorate Identifier 2013-SW-040-AD.
[[Page 69041]]
(a) Applicability
This AD applies to Agusta Model A109E, A109K2, A119, and AW119
MKII helicopters with a main transmission, part number (P/N) 109-
0400-03-103, 109-0400-05-103, or 109-0400-03-109, with a Gleason
crown, P/N 109-0403-07-103, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a Gleason
crown. This condition could cause damage to or loss of the main
rotor drive and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 26, 2014.
(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) For main transmissions with 2,400 or more hours time-in-
service (TIS), within 200 hours TIS and thereafter at intervals not
exceeding 1,600 hours TIS, magnetic particle inspect the Gleason
crown, P/N 109-0403-07-103, for a crack by following the procedures
in:
(i) Annex 1 of Agusta Bollettino Tecnico (BT) No. 109EP-128,
Revision A, dated May 28, 2013, for Model A109E helicopters;
(ii) Annex 1 of Agusta BT No. 109K-57, Revision A, dated May 28,
2013, for Model A109K2 helicopters; or
(iii) Annex 1 of Agusta BT No. 119-058, Revision A, dated May
28, 2013, for Model A119 and AW119MKII helicopters.
(2) If there is a crack, before further flight, replace the
Gleason crown assembly with a Gleason Crown assembly, P/N 109-0401-
27-107. Replacing the Gleason crown assembly with P/N 109-0401-27-
107 is terminating action for the inspection requirements of this
AD.
(3) After the effective date of this AD, do not install a
Gleason crown, P/N 109-0403-07-103, or a Gleason crown assembly, P/N
109-0401-27-101 or P/N 109-0401-27-109, on any helicopter.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email rao.edupuganti@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) AD No. 2013-0118, dated June 3, 2013. You may view the
EASA AD on the Internet at https://www.regulations.gov in Docket No.
FAA-2014-0472.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor
Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) AgustaWestland Bollettino Tecnico No. 109EP-128, Revision A,
dated May 28, 2013.
(ii) AgustaWestland Bollettino Tecnico No. 109K-57, Revision A,
dated May 28, 2013.
(iii) AgustaWestland Bollettino Tecnico No. 119-058, Revision A,
dated May 28, 2013.
(3) For AgustaWestland service information identified in this
AD, contact AgustaWestland, Product Support Engineering, Via del
Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio
D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at https://www.agustawestland.com/technical-bullettins.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. 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.
Issued in Fort Worth, Texas, on October 30, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-26825 Filed 11-19-14; 8:45 am]
BILLING CODE 4910-13-P
