Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 40158-40160 [2016-14406]
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40158
Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations
U.S. Code citation
CMP Description
New maximum amount
(3) 12 U.S.C. 1782(a)(3) ....................................
Failure to submit a report or the submission of
a false or misleading report done knowingly
or with reckless disregard.
Tier 1 CMP for inadvertent failure to submit
certified statement of insured shares and
charges due to NCUSIF, or inadvertent
submission of false or misleading statement.
Tier 2 CMP for non-inadvertent failure to submit certified statement or submission of
false or misleading statement.
Tier 3 CMP for failure to submit a certified
statement or the submission of a false or
misleading statement done knowingly or
with reckless disregard.
Non-compliance with insurance logo requirements.
Non-compliance with NCUA security requirements.
Tier 1 CMP for violations of law, regulation,
and other orders or agreements.
Tier 2 CMP for violations of law, regulation,
and other orders or agreements and for
recklessly engaging in unsafe or unsound
practices or breaches of fiduciary duty.
Tier 3 CMP for knowingly committing the violations under Tier 1 or 2 (natural person).
1,893,610 or 1 percent of the total assets of
the credit union, whichever is less.
(4) 12 U.S.C. 1782(d)(2)(A) ................................
(5) 12 U.S.C. 1782(d)(2)(B) ................................
(6) 12 U.S.C. 1782(d)(2)(C) ...............................
(7) 12 U.S.C. 1785(a)(3) ....................................
(8) 12 U.S.C. 1785(e) (3) ...................................
(9) 12 U.S.C. 1786(k)(2)(A) ................................
(10) 12 U.S.C. 1786(k)(2)(A) ..............................
(11) 12 U.S.C. 1786(k)(2)(A) ..............................
(12) 12 U.S.C. 1786(w)(5)(ii) ..............................
(13) 15 U.S.C. 1639e(k) .....................................
(14) 42 U.S.C. 4012a(f)(5) .................................
(b) The adjusted amounts displayed in
paragraph (a) of this section apply to
civil monetary penalties that are
assessed after the date the increase takes
effect, including those whose associated
violation or violations predate the
increase.
[FR Doc. 2016–14719 Filed 6–20–16; 8:45 am]
BILLING CODE 7535–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0219; Directorate
Identifier 2010–NE–14–AD; Amendment 39–
18556; AD 2016–12–07]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
rmajette on DSK2TPTVN1PROD with RULES
AGENCY:
We are superseding
airworthiness directive (AD) 2010–11–
10 for all Turbomeca S.A. Astazou XIV
B and XIV H turboshaft engines. AD
SUMMARY:
VerDate Sep<11>2014
14:40 Jun 20, 2016
Jkt 238001
Non-compliance with senior examiner postemployment restrictions.
Non-compliance with appraisal independence
requirements.
Non-compliance with flood insurance requirements.
2010–11–10 requires inspection of
certain third stage turbine wheels and
removal of any damaged wheel. This AD
requires expanding the population and
frequency of repetitive inspections. This
AD was prompted by a report of a third
stage turbine wheel crack detected
during engine overhaul. We are issuing
this AD to prevent uncontained failure
of the third stage turbine wheel, which
could result in damage to the engine
and damage to the helicopter.
DATES: This AD is effective July 26,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 26, 2016.
ADDRESSES: For service information
identified in this final rule, contact
Turbomeca S.A., 40220 Tarnos, France;
phone: (33) 05 59 74 40 00; fax: (33) 05
59 74 45 15. You may view this service
information at the FAA, Engine &
Propeller Directorate, 1200 District
Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2010–
0219.
PO 00000
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3,462.
34,620.
1,730,990 or 1 percent of the total assets of
the credit union, whichever is less.
118.
275.
9,468.
47,340.
For a person other than an insured credit
union: $1,893,610;
For an insured credit union: $1,893,610 or 1
percent of the total assets of the credit
union, whichever is less.
311,470.
First violation: $10,875
Subsequent violations: $21,749.
2,056.
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–2010–
0219; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the mandatory
continuing airworthiness information,
regulatory evaluation, any comments
received, and other information. The
address for the Docket Office (phone:
800–647–5527) is Document
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7772, fax: 781–238–7199;
email: brian.kierstead@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
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Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations
part 39 to supersede AD 2010–11–10,
Amendment 39–16315 (75 FR 30270,
June 1, 2010), (‘‘AD 2010–11–10’’). AD
2010–11–10 applied to the specified
products. The NPRM published in the
Federal Register on March 11, 2016 (81
FR 12843) (‘‘the NPRM’’). The NPRM
proposed to continue to require
inspection of certain third stage turbine
wheels and removal of any damaged
wheel. The NPRM also proposed to
expand the population and frequency of
repetitive inspections.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed.
Related Service Information Under 1
CFR Part 51
Turbomeca S.A. has issued
Mandatory Service Bulletin (MSB) No.
283 72 0804, Version D, dated July 24,
2015. The MSB describes procedures for
inspecting the third stage turbine
wheels.
Turbomeca S.A. has issued Service
Bulletin (SB) No. 283 72 0805, Version
B, dated December 15, 2010. That SB
describes optional terminating action for
the inspections.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects seven
engines installed on helicopters of U.S.
registry. We also estimate that it would
take about 5 hours per engine to comply
with this AD. The average labor rate is
$85 per hour. Based on these figures, we
estimate the cost of this AD on U.S.
operators to be $2,975.
rmajette on DSK2TPTVN1PROD with RULES
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
VerDate Sep<11>2014
14:40 Jun 20, 2016
Jkt 238001
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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 part 39 of the Federal
Aviation Regulations (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
removing airworthiness directive (AD)
2010–11–10, Amendment 39–16315 (75
FR 30270, June 1, 2010), (‘‘AD 2010–11–
10’’), and adding the following new AD:
■
2016–12–07 Turbomeca S.A.: Amendment
39–18556; Docket No. FAA–2010–0219;
Directorate Identifier 2010–NE–14–AD.
(a) Effective Date
This AD is effective July 26, 2016.
(b) Affected ADs
This AD supersedes AD 2010–11–10.
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40159
(c) Applicability
This AD applies to Turbomeca S.A.,
Astazou XIV B and XIV H turboshaft engines
with the following part number (P/N) and
serial number (S/N) third stage turbine
wheels that incorporate modification AB 173
(Turbomeca S.A. Service Bulletin (SB) No.
283 72 0091) or modification AB 208
(Turbomeca S.A. SB No. 283 72 0117). This
AD does not apply to third stage turbine
wheels that incorporate Turbomeca S.A. SB
No. 283 72 805.
(1) Third stage turbine wheels, P/N 0 265
25 700 0, all S/Ns;
(2) Third stage turbine wheels, P/N 0 265
25 702 0, all S/Ns;
(3) Third stage turbine wheels, P/N 0 265
25 706 0, all S/Ns;
(4) Third stage turbine wheels, P/N 0 265
25 705 0, with an S/N listed in Appendix 2.1
of Turbomeca S.A. Mandatory Service
Bulletin (MSB) No. 283 72 0804, Version D,
dated July 24, 2015.
(d) Unsafe Condition
This AD was prompted by a report of a
third stage turbine wheel crack detected
during engine overhaul. We are issuing this
AD to prevent uncontained failure of the
third stage turbine wheel, which could result
in damage to the engine and damage to the
helicopter.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) Perform a dye penetrant inspection of
the third stage turbine wheel. Use paragraph
2.4.2.2 of Turbomeca S.A. MSB No. 283 72
0804, Version D, dated July 24, 2015, to do
the inspection, as follows:
(i) Inspect third stage turbine wheels with
300 engine cycles (EC) or more accumulated
since last inspection, or since new, or since
last overhaul, or since repair, within 100 EC
after the effective date of this AD.
(ii) Inspect third stage turbine wheels with
less than 300 EC accumulated since last
inspection, or since new, or since last
overhaul, or since repair, within 400 EC since
last inspection, or since new, or since last
overhaul, or since repair.
(2) Repeat the inspection required by this
AD within 400 EC since last inspection.
(3) Remove from service any third stage
turbine wheels that fail the inspection
required by this AD.
(f) Optional Terminating Action
Application of Turbomeca S.A. SB No. 283
72 0805, Version B, dated December 15, 2010
is terminating action for the inspections
required by paragraphs (e)(1) and (2) of this
AD.
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make
your request. You may email your request to:
ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD,
contact Brian Kierstead, Aerospace Engineer,
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40160
Federal Register / Vol. 81, No. 119 / Tuesday, June 21, 2016 / Rules and Regulations
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7772; fax: 781–238–7199; email:
brian.kierstead@faa.gov.
(2) Refer to MCAI EASA AD 2015–0211,
dated October 15, 2015, for related
information. You may examine the MCAI in
the AD docket on the Internet at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2010–0219.
(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) Turbomeca S.A. Mandatory Service
Bulletin No. 283 72 0804, Version D, dated
July 24, 2015.
(ii) Turbomeca S.A. Service Bulletin No.
283 72 0805, Version B, dated December 15,
2010.
(3) For Turbomeca S.A. service information
identified in this AD, contact Turbomeca
S.A., 40220 Tarnos, France; phone: (33) 05 59
74 40 00; fax: (33) 05 59 74 45 15.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
(5) You may view this service information
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 Burlington, Massachusetts, on
June 7, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2016–14406 Filed 6–20–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–7263; Directorate
Identifier 2016–NM–072–AD; Amendment
39–18564; AD 2016–12–15]
RIN 2120–AA64
rmajette on DSK2TPTVN1PROD with RULES
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2016–07–
SUMMARY:
VerDate Sep<11>2014
14:40 Jun 20, 2016
Jkt 238001
30 for all Airbus Model A330–200, –200
Freighter, and –300 series airplanes, and
all Airbus Model A340–200, –300, –500,
and –600 series airplanes. For certain
airplanes, AD 2016–07–30 required
replacing certain Angle of Attack (AOA)
sensors (probes) with certain new AOA
sensors. For certain other airplanes, AD
2016–07–30 also required inspections
and functional heat testing of certain
AOA sensors for discrepancies, and
replacement if necessary. This new AD
requires the same actions as AD 2016–
07–30. This new AD was prompted by
a report of a typographical error in the
regulatory text of AD 2016–07–30. We
are issuing this AD to prevent erroneous
AOA information and Alpha Protection
(Alpha Prot) activation due to blocked
AOA probes, which could result in a
continuous nose-down command and
consequent loss of control of the
airplane.
This AD is effective July 6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 18, 2016 (81 FR 21722, April
13, 2016).
We must receive comments on this
AD by August 5, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this final rule, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
DATES:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
and locating Docket No. FAA–2016–
7263.
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–2016–
7263; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m. Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1138;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On March 26, 2016, we issued AD
2016–07–30, Amendment 39–18475 (81
FR 21722, April 13, 2016) (‘‘AD 2016–
07–30’’), for all Airbus Model A330–
200, –200 Freighter, and –300 series
airplanes; and all Airbus Model A340–
200, –300, –500, and –600 series
airplanes. AD 2016–07–30 was
prompted by a report of blockage of
AOA probes during climb, leading to
activation of the Alpha Prot while the
Mach number increased. This activation
could cause a continuous nose-down
pitch rate that cannot be stopped with
backward sidestick input, even in the
full backward position. For certain
airplanes, AD 2016–07–30 required
replacing certain AOA sensors (probes)
with certain new AOA sensors. For
certain other airplanes, AD 2016–07–30
also required inspections and functional
heat testing of certain AOA sensors for
discrepancies, and replacement if
necessary. We issued AD 2016–07–30 to
prevent erroneous AOA information and
Alpha Prot activation due to blocked
AOA probes, which could result in a
continuous nose-down command and
loss of control of the airplane.
Since we issued AD 2016–07–30, we
received a report of a typographical
error in the regulatory text of AD 2016–
07–30. Paragraph (l) of AD 2016–07–30
inadvertently referred to paragraph (g)
and should have referred to paragraph
(j), ‘‘Repetitive Inspections/Tests of
Certain Thales AOA Sensors.’’ The
intent of paragraph (l) of AD 2016–07–
30 was to give credit for doing the
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]]>Agencies
[Federal Register Volume 81, Number 119 (Tuesday, June 21, 2016)]
[Rules and Regulations]
[Pages 40158-40160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14406]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0219; Directorate Identifier 2010-NE-14-AD;
Amendment 39-18556; AD 2016-12-07]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2010-11-10 for
all Turbomeca S.A. Astazou XIV B and XIV H turboshaft engines. AD 2010-
11-10 requires inspection of certain third stage turbine wheels and
removal of any damaged wheel. This AD requires expanding the population
and frequency of repetitive inspections. This AD was prompted by a
report of a third stage turbine wheel crack detected during engine
overhaul. We are issuing this AD to prevent uncontained failure of the
third stage turbine wheel, which could result in damage to the engine
and damage to the helicopter.
DATES: This AD is effective July 26, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 26,
2016.
ADDRESSES: For service information identified in this final rule,
contact Turbomeca S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40
00; fax: (33) 05 59 74 45 15. You may view this service information at
the FAA, Engine & Propeller Directorate, 1200 District Avenue,
Burlington, MA. For information on the availability of this material at
the FAA, call 781-238-7125. It is also available on the Internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2010-0219.
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-2010-
0219; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the mandatory continuing airworthiness information,
regulatory evaluation, any comments received, and other information.
The address for the Docket Office (phone: 800-647-5527) is Document
Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Brian Kierstead, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7772, fax: 781-
238-7199; email: brian.kierstead@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
[[Page 40159]]
part 39 to supersede AD 2010-11-10, Amendment 39-16315 (75 FR 30270,
June 1, 2010), (``AD 2010-11-10''). AD 2010-11-10 applied to the
specified products. The NPRM published in the Federal Register on March
11, 2016 (81 FR 12843) (``the NPRM''). The NPRM proposed to continue to
require inspection of certain third stage turbine wheels and removal of
any damaged wheel. The NPRM also proposed to expand the population and
frequency of repetitive inspections.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed.
Related Service Information Under 1 CFR Part 51
Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 283
72 0804, Version D, dated July 24, 2015. The MSB describes procedures
for inspecting the third stage turbine wheels.
Turbomeca S.A. has issued Service Bulletin (SB) No. 283 72 0805,
Version B, dated December 15, 2010. That SB describes optional
terminating action for the inspections.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects seven engines installed on
helicopters of U.S. registry. We also estimate that it would take about
5 hours per engine to comply with this AD. The average labor rate is
$85 per hour. Based on these figures, we estimate the cost of this AD
on U.S. operators to be $2,975.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
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 part 39 of the Federal Aviation
Regulations (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)
2010-11-10, Amendment 39-16315 (75 FR 30270, June 1, 2010), (``AD 2010-
11-10''), and adding the following new AD:
2016-12-07 Turbomeca S.A.: Amendment 39-18556; Docket No. FAA-2010-
0219; Directorate Identifier 2010-NE-14-AD.
(a) Effective Date
This AD is effective July 26, 2016.
(b) Affected ADs
This AD supersedes AD 2010-11-10.
(c) Applicability
This AD applies to Turbomeca S.A., Astazou XIV B and XIV H
turboshaft engines with the following part number (P/N) and serial
number (S/N) third stage turbine wheels that incorporate
modification AB 173 (Turbomeca S.A. Service Bulletin (SB) No. 283 72
0091) or modification AB 208 (Turbomeca S.A. SB No. 283 72 0117).
This AD does not apply to third stage turbine wheels that
incorporate Turbomeca S.A. SB No. 283 72 805.
(1) Third stage turbine wheels, P/N 0 265 25 700 0, all S/Ns;
(2) Third stage turbine wheels, P/N 0 265 25 702 0, all S/Ns;
(3) Third stage turbine wheels, P/N 0 265 25 706 0, all S/Ns;
(4) Third stage turbine wheels, P/N 0 265 25 705 0, with an S/N
listed in Appendix 2.1 of Turbomeca S.A. Mandatory Service Bulletin
(MSB) No. 283 72 0804, Version D, dated July 24, 2015.
(d) Unsafe Condition
This AD was prompted by a report of a third stage turbine wheel
crack detected during engine overhaul. We are issuing this AD to
prevent uncontained failure of the third stage turbine wheel, which
could result in damage to the engine and damage to the helicopter.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Perform a dye penetrant inspection of the third stage
turbine wheel. Use paragraph 2.4.2.2 of Turbomeca S.A. MSB No. 283
72 0804, Version D, dated July 24, 2015, to do the inspection, as
follows:
(i) Inspect third stage turbine wheels with 300 engine cycles
(EC) or more accumulated since last inspection, or since new, or
since last overhaul, or since repair, within 100 EC after the
effective date of this AD.
(ii) Inspect third stage turbine wheels with less than 300 EC
accumulated since last inspection, or since new, or since last
overhaul, or since repair, within 400 EC since last inspection, or
since new, or since last overhaul, or since repair.
(2) Repeat the inspection required by this AD within 400 EC
since last inspection.
(3) Remove from service any third stage turbine wheels that fail
the inspection required by this AD.
(f) Optional Terminating Action
Application of Turbomeca S.A. SB No. 283 72 0805, Version B,
dated December 15, 2010 is terminating action for the inspections
required by paragraphs (e)(1) and (2) of this AD.
(g) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.
(h) Related Information
(1) For more information about this AD, contact Brian Kierstead,
Aerospace Engineer,
[[Page 40160]]
Engine Certification Office, FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA 01803; phone: 781-238-7772;
fax: 781-238-7199; email: brian.kierstead@faa.gov.
(2) Refer to MCAI EASA AD 2015-0211, dated October 15, 2015, for
related information. You may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2010-0219.
(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) Turbomeca S.A. Mandatory Service Bulletin No. 283 72 0804,
Version D, dated July 24, 2015.
(ii) Turbomeca S.A. Service Bulletin No. 283 72 0805, Version B,
dated December 15, 2010.
(3) For Turbomeca S.A. service information identified in this
AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: (33) 05 59
74 40 00; fax: (33) 05 59 74 45 15.
(4) You may view this service information at FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA. For
information on the availability of this material at the FAA, call
781-238-7125.
(5) You may view this service information 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 Burlington, Massachusetts, on June 7, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2016-14406 Filed 6-20-16; 8:45 am]
BILLING CODE 4910-13-P
