Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 26675-26677 [2016-10279]

Download as PDF Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 717–55A0012, dated June 12, 2015, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015. (1) Do detailed inspections for any loose and missing fasteners of the vertical stabilizer leading edge as specified in ‘‘Part 4’’ of Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015. (2) Do eddy current testing high frequency (ETHF) and radiographic testing (RT) inspections for any crack of the vertical stabilizer spar cap as specified in ‘‘Part 2’’ of Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015; or do ETHF inspections for any crack of the vertical stabilizer spar cap as specified in ‘‘Part 3’’ of Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015. (i) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015 specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 717–55A0012, dated June 12, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. asabaliauskas on DSK3SPTVN1PROD with RULES (j) Credit for Previous Actions This paragraph provides credit for the initial inspection specified in paragraph (g) of this AD, if that inspection was performed before the effective date of this AD using Boeing MOM–MOM–14–0437–01B(R1), dated July 3, 2014, which is not incorporated by reference in this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. 26675 We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires a one-time inspection of the front surface (l) Related Information of the 3rd stage turbine for a groove. This AD was prompted by a report of a For more information about this AD, contact Eric Schrieber, Aerospace Engineer, crack on the 3rd stage turbine wheel. Airframe Branch, ANM–120L, FAA, Los We are issuing this AD to prevent cracks Angeles ACO, 3960 Paramount Boulevard, in the 3rd stage turbine wheel, failure of Lakewood, CA 90712–4137; phone: 562–627– the engine, in-flight shutdown, and loss 5348; fax: 562–627–5210; email: of control of the helicopter. Eric.Schrieber@faa.gov. DATES: This AD becomes effective June (m) Material Incorporated by Reference 8, 2016. (1) The Director of the Federal Register The Director of the Federal Register approved the incorporation by reference approved the incorporation by reference (IBR) of the service information listed in this of a certain publication listed in this AD paragraph under 5 U.S.C. 552(a) and 1 CFR as of June 8, 2016. part 51. ADDRESSES: For service information (2) You must use this service information identified in this final rule, contact as applicable to do the actions required by this AD, unless the AD specifies otherwise. Turbomeca S.A., 40220 Tarnos, France; (i) Boeing Alert Service Bulletin 717– phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 55A0012, dated June 12, 2015. 59 74 45 15. You may view this service (ii) Reserved. information at the FAA, Engine & (3) For Boeing service information Propeller Directorate, 1200 District identified in this AD, contact Boeing Avenue, Burlington, MA. For Commercial Airplanes, Attention: Data & information on the availability of this Services Management, 3855 Lakewood material at the FAA, call 781–238–7125. Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone: 206–544–5000, It is also available on the Internet at extension 2; fax: 206–766–5683; Internet: https://www.regulations.gov by searching https://www.myboeingfleet.com. for and locating Docket No. FAA–2015– (4) You may view this service information 7490. at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on April 20, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–10160 Filed 5–3–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7490; Directorate Identifier 2015–NE–40–AD; Amendment 39– 18500; AD 2016–09–02] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 SUMMARY: 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–2015– 7490; 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 (MCAI), the 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: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238–7199; email: wego.wang@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The E:\FR\FM\04MYR1.SGM 04MYR1 26676 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations NPRM was published in the Federal Register on February 2, 2016 (81 FR 5395). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: During the overhaul of an ASTAZOU XIV engine, a crack was detected on the front face of the third stage turbine wheel between two balancing lugs. The cause of the crack is probably linked to a geometric singularity, likely caused by the transformation operation aimed at introducing expansion slots between the blades during embodiment of Turbomeca mod AB 173. Although there is only one known case of this type of crack, and although it was detected, the possibility exists that additional parts have the same geometric singularity. This condition, if not detected and corrected, may lead to failure of a turbine blade and its associated piece of rim, possibly resulting in an uncommanded inflight shut-down and/or release of high energy debris. You may obtain further information by examining the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 7490. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (81 FR 5395, February 2, 2016). 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 Service Bulletin (SB) No. 283 72 0811, Version A, dated August 25, 2015. The SB describes procedures for inspection of the 3rd stage turbine wheel. 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. asabaliauskas on DSK3SPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects 9 engines installed on helicopters of U.S. registry. We also estimate that it will 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 $3,825. 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 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 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 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 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. Authority for This Rulemaking § 39.13 Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, ■ VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 2016–09–02 Turbomeca S.A.: Amendment 39–18500; Docket No. FAA–2015–7490; Directorate Identifier 2015–NE–40–AD. (a) Effective Date This AD becomes effective June 8, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all Astazou XIV B and XIV H turboshaft engines with 3rd stage turbine wheel, part number (P/N) 0 265 25 700 0 or P/N 0 265 25 706 0, installed, if the engine incorporates Turbomeca modification AB–173 or AB–208. (d) Reason This AD was prompted by a report of a crack on the 3rd stage turbine wheel. We are issuing this AD to prevent cracks in the 3rd stage turbine wheel, failure of the engine, inflight shutdown, and loss of control of the helicopter. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) At the next piece part exposure of the 3rd stage turbine wheel or within 1,000 engine hours after the effective date of this AD whichever comes first, perform a onetime inspection for a groove on the front surface of the 3rd stage turbine wheel. Use Accomplishment Instructions, paragraph 4.4.2, of Turbomeca S.A. Service Bulletin (SB) No. 283 72 0811, Version A, dated August 25, 2015 to perform the inspection. (2) If the 3rd stage turbine wheel passes inspection required by paragraph (e)(1) of this AD, no further action is required. (3) If the 3rd stage turbine wheel fails inspection required by paragraph (e)(1) of this AD, remove the part and replace with a part eligible for installation. (f) Installation Prohibition After the effective date of this AD, do not install any 3rd stage turbine wheel, P/N 0 265 25 700 0 or P/N 0 265 25 706 0, unless it was inspected per the Accomplishment Instructions, paragraph 4.4.2, of Turbomeca S.A. SB No. 283 72 0811, Version A, dated August 25, 2015. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, 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 Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7134; fax: 781–238–7199; email: wego.wang@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2015–0223, dated November 16, 2015, for more information. You may examine the MCAI in the AD E:\FR\FM\04MYR1.SGM 04MYR1 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2015-7490-0001. (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. Service Bulletin No. 283 72 0811, Version A, dated August 25, 2015. (ii) Reserved. (3) For Turbomeca S.A. service information identified in this AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 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 April 21, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–10279 Filed 5–3–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–5811; Directorate Identifier 2014–NM–158–AD; Amendment 39–18489; AD 2016–08–13] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2004–19– 11 for certain Airbus Model A320 series airplanes. AD 2004–19–11 required modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, asabaliauskas on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 and corrective action if necessary. AD 2004–19–11 also provided optional terminating action for the repetitive inspections. This new AD retains the requirements of AD 2004–19–11, and requires the previously optional terminating action. This AD was prompted by a determination that the previously optional terminating action is necessary to address the unsafe condition. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG. DATES: This AD becomes effective June 8, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 8, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 5, 2004 (69 FR 58828, October 1, 2004). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 30, 2000 (65 FR 34069, May 26, 2000). The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 14, 1994 (59 FR 1903, January 13, 1994). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 11, 1993 (58 FR 27923, May 12, 1993). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@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 and locating Docket No. FAA–2015– 5811. 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–2015– 5811; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 26677 except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004–19–11, Amendment 39–13805 (69 FR 58828, October 1, 2004) (‘‘AD 2004–19–11’’). AD 2004–19–11 applied to certain Airbus Model 320 series airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74058) (‘‘the NPRM’’). The NPRM was prompted by a determination that the previously optional terminating action is necessary to address the unsafe condition. The NPRM proposed to retain the requirements of AD 2004–19– 11, and requires the previously optional terminating action. We are issuing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0169, dated July 17, 2014, corrected July 22, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Airbus Model 320 series airplanes. The MCAI states: During centre fuselage certification full scale fatigue test, cracks were found on the inner rear spar at holes position 52 on the right hand wing due to fatigue aspects. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To prevent such cracks, Airbus developed modifications, which were introduced in production and in service through several Airbus Service Bulletins (SB). DGAC France issued * * * [an earlier AD], which was subsequently superseded by [DGAC] AD 2001–249 [which corresponds with FAA AD 2004–19–11, Amendment 39– 13805 (69 FR 58828, October 1, 2004)], to require modification of the rear spar on some E:\FR\FM\04MYR1.SGM 04MYR1

Agencies

[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)]
[Rules and Regulations]
[Pages 26675-26677]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10279]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7490; Directorate Identifier 2015-NE-40-AD; 
Amendment 39-18500; AD 2016-09-02]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires 
a one-time inspection of the front surface of the 3rd stage turbine for 
a groove. This AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. We are issuing this AD to prevent cracks in the 3rd 
stage turbine wheel, failure of the engine, in-flight shutdown, and 
loss of control of the helicopter.

DATES: This AD becomes effective June 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 8, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 
00; fax: 33 (0)5 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-2015-7490.

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-2015-
7490; 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 
(MCAI), the 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: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-
238-7199; email: wego.wang@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The

[[Page 26676]]

NPRM was published in the Federal Register on February 2, 2016 (81 FR 
5395). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During the overhaul of an ASTAZOU XIV engine, a crack was 
detected on the front face of the third stage turbine wheel between 
two balancing lugs. The cause of the crack is probably linked to a 
geometric singularity, likely caused by the transformation operation 
aimed at introducing expansion slots between the blades during 
embodiment of Turbomeca mod AB 173. Although there is only one known 
case of this type of crack, and although it was detected, the 
possibility exists that additional parts have the same geometric 
singularity.
    This condition, if not detected and corrected, may lead to 
failure of a turbine blade and its associated piece of rim, possibly 
resulting in an uncommanded in-flight shut-down and/or release of 
high energy debris.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2015-7490.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (81 FR 5395, February 2, 
2016).

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 Service Bulletin (SB) No. 283 72 0811, 
Version A, dated August 25, 2015. The SB describes procedures for 
inspection of the 3rd stage turbine wheel. 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 9 engines installed on helicopters 
of U.S. registry. We also estimate that it will 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 $3,825.

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

    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 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 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 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-09-02 Turbomeca S.A.: Amendment 39-18500; Docket No. FAA-2015-
7490; Directorate Identifier 2015-NE-40-AD.

(a) Effective Date

    This AD becomes effective June 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Astazou XIV B and XIV H turboshaft 
engines with 3rd stage turbine wheel, part number (P/N) 0 265 25 700 
0 or P/N 0 265 25 706 0, installed, if the engine incorporates 
Turbomeca modification AB-173 or AB-208.

(d) Reason

    This AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. We are issuing this AD to prevent cracks in the 3rd 
stage turbine wheel, failure of the engine, in-flight shutdown, and 
loss of control of the helicopter.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next piece part exposure of the 3rd stage turbine 
wheel or within 1,000 engine hours after the effective date of this 
AD whichever comes first, perform a one-time inspection for a groove 
on the front surface of the 3rd stage turbine wheel. Use 
Accomplishment Instructions, paragraph 4.4.2, of Turbomeca S.A. 
Service Bulletin (SB) No. 283 72 0811, Version A, dated August 25, 
2015 to perform the inspection.
    (2) If the 3rd stage turbine wheel passes inspection required by 
paragraph (e)(1) of this AD, no further action is required.
    (3) If the 3rd stage turbine wheel fails inspection required by 
paragraph (e)(1) of this AD, remove the part and replace with a part 
eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, do not install any 3rd 
stage turbine wheel, P/N 0 265 25 700 0 or P/N 0 265 25 706 0, 
unless it was inspected per the Accomplishment Instructions, 
paragraph 4.4.2, of Turbomeca S.A. SB No. 283 72 0811, Version A, 
dated August 25, 2015.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, 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 Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7134; fax: 781-238-7199; email: wego.wang@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0223, 
dated November 16, 2015, for more information. You may examine the 
MCAI in the AD

[[Page 26677]]

docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-7490-0001.

(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. Service Bulletin No. 283 72 0811, Version A, 
dated August 25, 2015.
    (ii) Reserved.
    (3) For Turbomeca S.A. service information identified in this 
AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 
74 40 00; fax: 33 (0)5 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 April 21, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10279 Filed 5-3-16; 8:45 am]
 BILLING CODE 4910-13-P
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