Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 40158-40160 [2016-14406]

Download as PDF 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 http://www.regulations.gov by searching for and locating Docket No. FAA–2010– 0219. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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 http:// 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 E:\FR\FM\21JNR1.SGM 21JNR1 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. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 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, E:\FR\FM\21JNR1.SGM 21JNR1 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 http:// 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: http:// 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 http://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 http://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 http:// 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 http:// 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 E:\FR\FM\21JNR1.SGM 21JNR1

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]


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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 
http://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 http://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 http://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: 
http://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