Airworthiness Directives; Agusta S.p.A. Helicopters, 14297-14299 [2015-05715]
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Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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 AD:
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■
2015–06–03 Stemme AG: Amendment 39–
18121; Docket No. FAA–2015–0633;
Directorate Identifier 2015–CE–005–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 24, 2015.
VerDate Sep<11>2014
15:06 Mar 18, 2015
Jkt 235001
(b) Affected ADs
None.
(c) Applicability
This AD applies to Stemme AG TSA–M
Models S6 and S6–RT gliders, all serial
numbers, certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 27: Flight Controls.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as a bending
defect of the fork head installed in the
aileron, speed brake, and flap control
systems. We are issuing this AD to detect and
correct the bending defect of the fork head
that could result in failure of the flight
control system, possibly resulting in loss of
control.
(f) Actions and Compliance
Unless already done, before further flight,
after March 24, 2015 (the effective date of
this AD), modify the affected flight control
systems, or take other actions, following a
method approved specifically for this AD by
the FAA, Small Airplane Directorate. Contact
Stemme AG to obtain FAA-approved repair
instructions approved specifically for
compliance with this AD and incorporate
those instructions. You can find contact
information for Stemme AG in paragraph
(i)(2) of this AD.
Note 1 to paragraph (f) of this AD: At the
time of issuance of this AD, no design
solution is available to restore the
airworthiness of the respective type designs
to a level corresponding to their approved
type design specifications.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816) 329–
4090; email: jim.rutherford@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Special Flight Permit
Special flight permits are prohibited.
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14297
(i) Related Information
(1) Refer to MCAI European Aviation
Safety Agency (EASA) AD No.: 2015–0034–
E, dated February 27, 2015, for related
information. You may examine the MCAI on
the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–0633.
(2) For information concerning this action,
contact Stemme AG, Flugplatzstra+e F2, Nr.
6–7, D–15344 Strausberg, Germany; phone:
+49 (0) 3341/3612 0; fax: none; email: info@
stemme.de; internet: www.stemme.info.
Issued in Kansas City, Missouri, on March
12, 2015.
Robert Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–06296 Filed 3–18–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0579; Directorate
Identifier 2014–SW–020–AD; Amendment
39–18115; AD 2015–05–05]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–04–
14 for Agusta S.p.A. (Agusta) Model
A109S, AW109SP, A119, and AW119
MKII helicopters. AD 2014–04–14
required removing certain rod end
assemblies from service because of
reports of fractures. This new AD retains
the requirements of AD 2014–04–14 but
expands the scope of applicable rod end
assemblies. This AD was prompted by
reports of additional fractured rod end
assemblies. We are issuing this AD to
prevent failure of a rod end assembly,
which could result in damage to the
main rotor assembly and loss of control
of the helicopter.
DATES: This AD is effective April 23,
2015.
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-bulletins. You may view this
referenced service information at the
FAA, Office of the Regional Counsel,
SUMMARY:
E:\FR\FM\19MRR1.SGM
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14298
Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations
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, 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:
Robert Grant, Aviation Safety Engineer,
Safety Management Group, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2014–04–14,
Amendment 39–17773 (79 FR 11699,
March 3, 2014) for Agusta Model
A109S, AW109SP, A119, and AW119
MKII helicopters with a main rotor lag
damper assembly (lag damper), part
number (P/N) 109–0112–39–103, 109–
0112–39–105, 109–0112–05–105, or
109–0112–05–107, installed with a rod
end assembly, P/N M004–01H007–041
or P/N M004–01H007–045, with a serial
number from 84 through 132 or from
4964 through 5011, and add a new AD.
The NPRM published in the Federal
Register on August 18, 2014 (79 FR
48698). AD 2014–04–14 required
removing the rod end assemblies from
service. AD 2014–04–14 was prompted
by AD No. 2012–0208, dated October 5,
2012, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for Agusta Model
A109LUH, A109S, AW109SP, A119,
and AW119 MKII helicopters. EASA
advises of cases of in-flight fractures of
rod end assembly, P/N M004–01H007–
045, installed on main rotor lag dampers
on Model A109LUH and AW109SP
helicopters. An investigation revealed
that two batches of rod end assemblies,
P/N M004–01H007–041 and M004–
01H007–045, could have cracks,
according to EASA. EASA states that
this condition, if not corrected, could
VerDate Sep<11>2014
15:06 Mar 18, 2015
Jkt 235001
lead to main rotor damage, possibly
resulting in loss of control of the
helicopter. The actions of AD 2014–04–
14 were intended to prevent such
damage and loss of control of the
helicopter.
Actions Since AD 2014–04–14 Was
Issued
Between the time we published the
NPRM for AD 2014–04–14 (78 FR
44042, July 23, 2013) and the Final Rule
for AD 2014–04–14 (79 FR 11699,
March 3, 2014), EASA issued AD No.
2013–0290, dated December 9, 2013.
EASA advises in AD No. 2013–0290 that
a new case of a fractured rod end
assembly has been reported and that
additional batches of rod end assembly,
P/N M004–01H007–041 and P/N M004–
01H007–045, as well as batches of P/N
109–0112–11–101 and P/N 109–0112–
22–105 could also have cracks. EASA
expanded the applicability of its AD to
include the additional rod end
assemblies.
We consequently issued the NPRM
(79 FR 48698, August 18, 2014) to
amend 14 CFR part 39 to remove AD
2014–04–14 and add a new AD. The
NPRM proposed to retain the
requirements of AD 2014–04–14 but
expand the scope of applicable rod end
assemblies. The NPRM also proposed to
add a provision requiring compliance
with the AD if the rod end assembly is
removed during maintenance before 25
hours time-in-service (TIS).
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(79 FR 48698, August 18, 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 we have correctly
stated the design holder’s name as
Agusta S.p.A. instead of
AgustaWestland S.p.A. as specified by
the current FAA type certificate. This
change is consistent with the intent of
the proposals in the NPRM (79 FR
48698, August 18, 2014) and will not
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Fmt 4700
Sfmt 4700
increase the economic burden on any
operator nor increase the scope of the
AD.
Differences Between This AD and the
EASA AD
The EASA AD calls for replacing
certain rod end assemblies with
airworthy rod end assemblies within 25
hours TIS, 2 months, or the next time
maintenance of the applicable
helicopters involves removing the rod
end assembly. This AD does not have a
calendar time requirement. The EASA
AD applies to Agusta Model A109LUH
helicopters. This AD does not apply to
Model A109LUH helicopters because
that model does not have a U.S. type
certificate.
Related Service Information
We reviewed AgustaWestland
Bollettino Tecnico (BT) No. 109S–49 for
Model A109S helicopters, BT No.
109SP–052 for Model AW109SP
helicopters, and BT No. 119–50 for
Model A119 and AW119 MKII
helicopters. All of the BTs are revision
A, and dated December 3, 2013. The
BTs specify a one-time inspection of
each rod end assembly to determine its
serial number. The BTs then require
removal from service of certain serialnumbered rod end assemblies because
fractures had been reported on rod ends
in these batches. According to the BTs,
no one was injured in the helicopters,
and no helicopters were damaged
because of these fractures.
Costs of Compliance
We estimate that this AD affects 91
helicopters of U.S. Registry and that
labor costs average $85 a work-hour.
Based on these estimates, we expect the
following costs:
• Replacing a rod end assembly
requires 1.5 work-hours for a labor cost
of $128. Parts cost $3,918 for a total cost
of $4,046 per helicopter, $368,186 for
the U.S. fleet.
According to the manufacturer’s
service information, costs of this AD
may be covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage by manufacturers.
Accordingly, 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.
E:\FR\FM\19MRR1.SGM
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Federal Register / Vol. 80, No. 53 / Thursday, March 19, 2015 / Rules and Regulations
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have 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
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.
(a) Applicability
This AD applies to the following
helicopters, certificated in any category:
(1) Agusta S.p.A. (Agusta) Model A109S
and AW109SP helicopters, with a main rotor
lag damper assembly (lag damper), part
number (P/N) 109–0112–39–103 or 109–
0112–39–105, installed on rod end assembly,
P/N M004–01H007–041 with a serial number
(S/N) 1 through 202; or rod end assembly, P/
N M004–01H007–045 with a S/N 1RW
through 202RW or 4964 through 5011.
(2) Agusta Model A119 and AW119 MKII
helicopters, with a lag damper, P/N 109–
0112–05–105 or 109–0112–05–107, installed
on rod end assembly, P/N 109–0112–11–101
with a S/N 1 through 78; or rod end
assembly, P/N 109–0112–11–105 with a S/N
1RW through 78RW; or rod end assembly, P/
N M004–01H007–045 with a S/N 1RW
through 202RW or 4964 through 5011.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a rod end assembly, which could
result in fracture of the rod end assembly,
damage to the main rotor, and subsequent
loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2014–04–14,
amendment 39–17773 (79 FR 11699, March
3, 2014).
(d) Effective Date
This AD becomes effective April 23, 2015.
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
PART 39—AIRWORTHINESS
DIRECTIVES
(g) Alternative Methods of Compliance
(AMOCs)
Adoption of the Amendment
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2014–04–14, Amendment 39–17773 (79
FR 11699, March 3, 2014), and adding
the following new AD:
Rmajette on DSK2VPTVN1PROD with RULES
■
2015–05–05 Agusta S.p.A.: Amendment 39–
18115; Docket No. FAA–2014–0579;
Directorate Identifier 2014–SW–020–AD.
VerDate Sep<11>2014
21:52 Mar 18, 2015
Jkt 235001
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6200, Main Rotor System.
Issued in Fort Worth, Texas, on March 4,
2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–05715 Filed 3–18–15; 8:45 am]
BILLING CODE 4910–13–P
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Robert Grant,
Aviation Safety Engineer, Safety Management
Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222–
5110; email robert.grant@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.
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Fmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(h) Additional Information
(1) AgustaWestland S.p.A. Bollettino
Tecnico (BT) No. 109S–49, BT No. 109SP–
052, and BT No. 119–50, all Revision A, and
all dated December 3, 2013, which are not
incorporated by reference, contain additional
information about the subject of this AD. 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/technicalbulletins. You may review a copy of the
service information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
(2) The subject of this AD is addressed in
the European Aviation Safety Agency (EASA)
AD No. 2013–0290, dated December 9, 2013.
You may view the EASA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2014–0579.
(e) Compliance
(1) Within 25 hours time-in-service or the
next time maintenance of the helicopter
involves removing the rod end assembly,
whichever occurs first, remove the rod end
assembly from service.
(2) Do not install a rod end assembly, P/
N M004–01H007–041 with a S/N 1 through
202; P/N M004–01H007–045 with a S/N 1RW
through 202RW or 4964 through 5011; P/N
109–0112–11–101 with a S/N 1 through 78;
or P/N 109–0112–11–105 with a S/N 1RW
through 78RW, on any helicopter.
List of Subjects in 14 CFR Part 39
14299
Sfmt 4700
[Docket No. FAA–2014–1001; Directorate
Identifier 2014–CE–034–AD; Amendment
39–18103; AD 2015–04–01]
RIN 2120–AA64
Airworthiness Directives; Short
Brothers & Harland Ltd. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all Short Brothers &
Harland Ltd. Model SC–7 Series 3
airplanes. The amendment number in
the Agency Identification Numbers in
the preamble section of the AD is
incorrect. Although no other part of the
preamble or regulatory information has
been corrected, we are publishing the
entire rule in the Federal Register.
DATES: This final rule is effective March
30, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
SUMMARY:
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]]>Agencies
[Federal Register Volume 80, Number 53 (Thursday, March 19, 2015)]
[Rules and Regulations]
[Pages 14297-14299]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-05715]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0579; Directorate Identifier 2014-SW-020-AD;
Amendment 39-18115; AD 2015-05-05]
RIN 2120-AA64
Airworthiness Directives; Agusta S.p.A. Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-04-14 for
Agusta S.p.A. (Agusta) Model A109S, AW109SP, A119, and AW119 MKII
helicopters. AD 2014-04-14 required removing certain rod end assemblies
from service because of reports of fractures. This new AD retains the
requirements of AD 2014-04-14 but expands the scope of applicable rod
end assemblies. This AD was prompted by reports of additional fractured
rod end assemblies. We are issuing this AD to prevent failure of a rod
end assembly, which could result in damage to the main rotor assembly
and loss of control of the helicopter.
DATES: This AD is effective April 23, 2015.
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-bulletins. You may view this referenced service information
at the FAA, Office of the Regional Counsel,
[[Page 14298]]
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, 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: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2014-04-14, Amendment 39-17773 (79 FR 11699, March
3, 2014) for Agusta Model A109S, AW109SP, A119, and AW119 MKII
helicopters with a main rotor lag damper assembly (lag damper), part
number (P/N) 109-0112-39-103, 109-0112-39-105, 109-0112-05-105, or 109-
0112-05-107, installed with a rod end assembly, P/N M004-01H007-041 or
P/N M004-01H007-045, with a serial number from 84 through 132 or from
4964 through 5011, and add a new AD. The NPRM published in the Federal
Register on August 18, 2014 (79 FR 48698). AD 2014-04-14 required
removing the rod end assemblies from service. AD 2014-04-14 was
prompted by AD No. 2012-0208, dated October 5, 2012, issued by EASA,
which is the Technical Agent for the Member States of the European
Union, to correct an unsafe condition for Agusta Model A109LUH, A109S,
AW109SP, A119, and AW119 MKII helicopters. EASA advises of cases of in-
flight fractures of rod end assembly, P/N M004-01H007-045, installed on
main rotor lag dampers on Model A109LUH and AW109SP helicopters. An
investigation revealed that two batches of rod end assemblies, P/N
M004-01H007-041 and M004-01H007-045, could have cracks, according to
EASA. EASA states that this condition, if not corrected, could lead to
main rotor damage, possibly resulting in loss of control of the
helicopter. The actions of AD 2014-04-14 were intended to prevent such
damage and loss of control of the helicopter.
Actions Since AD 2014-04-14 Was Issued
Between the time we published the NPRM for AD 2014-04-14 (78 FR
44042, July 23, 2013) and the Final Rule for AD 2014-04-14 (79 FR
11699, March 3, 2014), EASA issued AD No. 2013-0290, dated December 9,
2013. EASA advises in AD No. 2013-0290 that a new case of a fractured
rod end assembly has been reported and that additional batches of rod
end assembly, P/N M004-01H007-041 and P/N M004-01H007-045, as well as
batches of P/N 109-0112-11-101 and P/N 109-0112-22-105 could also have
cracks. EASA expanded the applicability of its AD to include the
additional rod end assemblies.
We consequently issued the NPRM (79 FR 48698, August 18, 2014) to
amend 14 CFR part 39 to remove AD 2014-04-14 and add a new AD. The NPRM
proposed to retain the requirements of AD 2014-04-14 but expand the
scope of applicable rod end assemblies. The NPRM also proposed to add a
provision requiring compliance with the AD if the rod end assembly is
removed during maintenance before 25 hours time-in-service (TIS).
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (79 FR 48698, August
18, 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 we have correctly stated the design holder's name as
Agusta S.p.A. instead of AgustaWestland S.p.A. as specified by the
current FAA type certificate. This change is consistent with the intent
of the proposals in the NPRM (79 FR 48698, August 18, 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
The EASA AD calls for replacing certain rod end assemblies with
airworthy rod end assemblies within 25 hours TIS, 2 months, or the next
time maintenance of the applicable helicopters involves removing the
rod end assembly. This AD does not have a calendar time requirement.
The EASA AD applies to Agusta Model A109LUH helicopters. This AD does
not apply to Model A109LUH helicopters because that model does not have
a U.S. type certificate.
Related Service Information
We reviewed AgustaWestland Bollettino Tecnico (BT) No. 109S-49 for
Model A109S helicopters, BT No. 109SP-052 for Model AW109SP
helicopters, and BT No. 119-50 for Model A119 and AW119 MKII
helicopters. All of the BTs are revision A, and dated December 3, 2013.
The BTs specify a one-time inspection of each rod end assembly to
determine its serial number. The BTs then require removal from service
of certain serial-numbered rod end assemblies because fractures had
been reported on rod ends in these batches. According to the BTs, no
one was injured in the helicopters, and no helicopters were damaged
because of these fractures.
Costs of Compliance
We estimate that this AD affects 91 helicopters of U.S. Registry
and that labor costs average $85 a work-hour. Based on these estimates,
we expect the following costs:
Replacing a rod end assembly requires 1.5 work-hours for a
labor cost of $128. Parts cost $3,918 for a total cost of $4,046 per
helicopter, $368,186 for the U.S. fleet.
According to the manufacturer's service information, costs of this
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage by
manufacturers. Accordingly, 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.
[[Page 14299]]
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have 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 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 removing Airworthiness Directive (AD)
2014-04-14, Amendment 39-17773 (79 FR 11699, March 3, 2014), and adding
the following new AD:
2015-05-05 Agusta S.p.A.: Amendment 39-18115; Docket No. FAA-2014-
0579; Directorate Identifier 2014-SW-020-AD.
(a) Applicability
This AD applies to the following helicopters, certificated in
any category:
(1) Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters,
with a main rotor lag damper assembly (lag damper), part number (P/
N) 109-0112-39-103 or 109-0112-39-105, installed on rod end
assembly, P/N M004-01H007-041 with a serial number (S/N) 1 through
202; or rod end assembly, P/N M004-01H007-045 with a S/N 1RW through
202RW or 4964 through 5011.
(2) Agusta Model A119 and AW119 MKII helicopters, with a lag
damper, P/N 109-0112-05-105 or 109-0112-05-107, installed on rod end
assembly, P/N 109-0112-11-101 with a S/N 1 through 78; or rod end
assembly, P/N 109-0112-11-105 with a S/N 1RW through 78RW; or rod
end assembly, P/N M004-01H007-045 with a S/N 1RW through 202RW or
4964 through 5011.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a rod end
assembly, which could result in fracture of the rod end assembly,
damage to the main rotor, and subsequent loss of control of the
helicopter.
(c) Affected ADs
This AD supersedes AD 2014-04-14, amendment 39-17773 (79 FR
11699, March 3, 2014).
(d) Effective Date
This AD becomes effective April 23, 2015.
(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) Within 25 hours time-in-service or the next time maintenance
of the helicopter involves removing the rod end assembly, whichever
occurs first, remove the rod end assembly from service.
(2) Do not install a rod end assembly, P/N M004-01H007-041 with
a S/N 1 through 202; P/N M004-01H007-045 with a S/N 1RW through
202RW or 4964 through 5011; P/N 109-0112-11-101 with a S/N 1 through
78; or P/N 109-0112-11-105 with a S/N 1RW through 78RW, on any
helicopter.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; telephone (817) 222-5110; email
robert.grant@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.
(h) Additional Information
(1) AgustaWestland S.p.A. Bollettino Tecnico (BT) No. 109S-49,
BT No. 109SP-052, and BT No. 119-50, all Revision A, and all dated
December 3, 2013, which are not incorporated by reference, contain
additional information about the subject of this AD. 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-bulletins. You may review a copy of the service information at the
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in the European Aviation
Safety Agency (EASA) AD No. 2013-0290, dated December 9, 2013. You
may view the EASA AD on the Internet at https://www.regulations.gov
in Docket No. FAA-2014-0579.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.
Issued in Fort Worth, Texas, on March 4, 2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2015-05715 Filed 3-18-15; 8:45 am]
BILLING CODE 4910-13-P
