Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 49575-49577 [2016-17719]

Download as PDF Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules of the nose wheel well body structure for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015; except as required by paragraph (j)(2) of this AD. Do all related investigative and corrective actions before further flight. Repeat the detailed inspection thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2887, dated December 2, 2015. Lhorne on DSK30JT082PROD with PROPOSALS (j) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 747–53A2887, dated December 2, 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 747–53A2887, dated December 2, 2015, specifies to contact Boeing for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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, Seattle 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. (4) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. VerDate Sep<11>2014 14:42 Jul 27, 2016 Jkt 238001 (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on July 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–17718 Filed 7–27–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6990; Directorate Identifier 2016–NE–14–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This proposed AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. This proposed AD would require removing the centrifugal impeller and replacing with a part eligible for installation. We are proposing this AD to prevent failure SUMMARY: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 49575 of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter. DATES: We must receive comments on this NPRM by September 26, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. For service information identified in this proposed AD, 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. 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– 6990; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed 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 in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7770; fax: 781–238–7199; email: philip.haberlen@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–6990; Directorate Identifier 2016–NE–14–AD’’ at the beginning of your comments. We specifically invite E:\FR\FM\28JYP1.SGM 28JYP1 49576 Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2016– 0090, dated May 10, 2016 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Turbomeca reported an anomaly that was generated during the grinding operation associated to the application of modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. This condition, if not corrected, could lead to crack initiation and propagation in the centrifugal impeller bore area, possibly resulting in centrifugal impeller failure, with consequent damage to, and reduced control of, the helicopter. To address this potential unsafe condition, the life of the affected centrifugal impellers was reduced and Turbomeca published Mandatory Service Bulletin (MSB) 292 72 0848 to inform operators about the life reduction and to provide instructions for the replacement of the affected centrifugal impellers. For the reasons described above, this AD requires replacement of each affected centrifugal impeller before it exceeds the applicable reduced life limit. You may obtain further information by examining the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6990. Lhorne on DSK30JT082PROD with PROPOSALS Related Service Information Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) 292 72 0848, Version B, dated April 13, 2016. The MSB describes procedures for reducing the life limit of the centrifugal impellers affected by an anomaly that occurred during the grinding operation required by modification TU376. 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. VerDate Sep<11>2014 14:42 Jul 27, 2016 Jkt 238001 FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of France, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require removal of the centrifugal impeller from service before exceeding the reduced life limit shown in Appendix 1 of EASA AD 2016–0090, dated May 10, 2016, and replacement with a part eligible for installation. Costs of Compliance We estimate that this proposed AD affects 3 engines installed on helicopters of U.S. registry. We also estimate that it would take about 22 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Required parts cost about $96,518 per engine. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $295,164. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Turbomeca S.A.: Docket No. FAA–2016– 6990; Directorate Identifier 2016–NE– 14–AD. (a) Comments Due Date We must receive comments by September 26, 2016. (b) Affected ADs None. (c) Applicability This AD applies to certain Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines, with modification TU376 installed. (d) Reason This AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. We are issuing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter. E:\FR\FM\28JYP1.SGM 28JYP1 Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Remove from service, any centrifugal impeller listed in Table 1 to paragraph (e) of this AD, before exceeding the applicable cycles since new (CSN) and replace with a 49577 centrifugal impeller not listed in Table 1 to paragraph (e) of this AD. TABLE 1 TO PARAGRAPH (e)—CENTRIFUGAL IMPELLER CSNS Part No. 0292254040 0292254040 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 0292254050 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A 729225293A Serial No. ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ................................................................................ ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... ............................................................................... (2) Reserved. 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. Lhorne on DSK30JT082PROD with PROPOSALS (1) For more information about this AD, contact Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7770; fax: 781–238–7199; email: philip.haberlen@faa.gov. (2) Refer to MCAI, European Aviation Safety Agency AD 2016–0090, dated May 10, 2016, for more 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–2016–6990. (3) Turbomeca S.A. Mandatory Service Bulletin (MSB) 292 72 0848, Version B, dated April 13, 2016, can be obtained from Turbomeca S.A., using the contact information in paragraph (g)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For 14:42 Jul 27, 2016 Issued in Burlington, Massachusetts, on July 21, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–17719 Filed 7–27–16; 8:45 am] BILLING CODE 4910–13–P (g) Related Information VerDate Sep<11>2014 44 ................................................................................................ 1762FT ....................................................................................... 1676CAR .................................................................................... 5333OTT .................................................................................... 5017OTT .................................................................................... 1136CAR .................................................................................... 3655OTT .................................................................................... 1757CAR .................................................................................... 1738CAR .................................................................................... 1149CAR .................................................................................... 2677OTT .................................................................................... 3109OTT .................................................................................... 3496OTT .................................................................................... 2074CAR .................................................................................... 290CAR ...................................................................................... 1227FT ....................................................................................... 504FB ......................................................................................... 2517OTT .................................................................................... 2165OTT .................................................................................... 2194FT ....................................................................................... 1331OTT .................................................................................... 1301FT ....................................................................................... 1567FT ....................................................................................... 783FB ......................................................................................... 98OTT ........................................................................................ information on the availability of this material at the FAA, call 781–238–7125. (f) Alternative Methods of Compliance (AMOCs) Jkt 238001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8180; Directorate Identifier 2016–NM–083–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL–600–2D15 (Regional Jet Series 705) airplanes, Model CL–600–2D24 (Regional Jet SUMMARY: PO 00000 Frm 00022 CSN Fmt 4702 Sfmt 4702 5,129 11,476 6,281 5,495 5,491 8,734 4,600 7,913 10,640 12,273 11,145 10,662 5,562 7,423 6,326 8,139 4,600 9,732 6,163 11,461 12,513 7,262 6,305 8,307 9,492 Series 900) airplanes, and Model CL– 600–2E25 (Regional Jet Series 1000) airplanes. This proposed AD was prompted by a determination that the protective polyurethane tapes applied to the upper surfaces of the aluminum and titanium floor structural members may not be trimmed properly, and on some places may overhang the profiles of the floor structural parts. Subsequent tests revealed that the overhanging pieces of tapes that are not bonded to the structure do not meet the flammability requirements and may allow fire propagation below the floor structure. This proposed AD would require an inspection of the polyurethane protective tapes installed on the floor structure for excess tape or incorrect tape installation, and corrective actions if necessary. We are proposing this AD to detect and correct overhanging pieces of protective polyurethane tapes, which are not bonded to the structure and do not meet the flammability requirements; this condition may allow fire propagation below the floor structure. We must receive comments on this proposed AD by September 12, 2016. DATES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: ADDRESSES: E:\FR\FM\28JYP1.SGM 28JYP1

Agencies

[Federal Register Volume 81, Number 145 (Thursday, July 28, 2016)]
[Proposed Rules]
[Pages 49575-49577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-17719]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 
1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This proposed AD 
was prompted by an anomaly that occurred during the grinding operation 
required by modification TU376, which increases the clearance between 
the rear curvic coupling of the centrifugal impeller and the fuel 
injection manifold. This proposed AD would require removing the 
centrifugal impeller and replacing with a part eligible for 
installation. We are proposing this AD to prevent failure of the 
centrifugal impeller, uncontained centrifugal impeller release, damage 
to the engine, and damage to the helicopter.

DATES: We must receive comments on this NPRM by September 26, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    For service information identified in this proposed AD, 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.

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-
6990; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed 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 in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-
238-7199; email: philip.haberlen@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6990; 
Directorate Identifier 2016-NE-14-AD'' at the beginning of your 
comments. We specifically invite

[[Page 49576]]

comments on the overall regulatory, economic, environmental, and energy 
aspects of this proposed AD. We will consider all comments received by 
the closing date and may amend this proposed AD based on those 
comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2016-0090, dated May 10, 2016 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Turbomeca reported an anomaly that was generated during the 
grinding operation associated to the application of modification 
TU376, which increases the clearance between the rear curvic 
coupling of the centrifugal impeller and the fuel injection 
manifold.
    This condition, if not corrected, could lead to crack initiation 
and propagation in the centrifugal impeller bore area, possibly 
resulting in centrifugal impeller failure, with consequent damage 
to, and reduced control of, the helicopter. To address this 
potential unsafe condition, the life of the affected centrifugal 
impellers was reduced and Turbomeca published Mandatory Service 
Bulletin (MSB) 292 72 0848 to inform operators about the life 
reduction and to provide instructions for the replacement of the 
affected centrifugal impellers.
    For the reasons described above, this AD requires replacement of 
each affected centrifugal impeller before it exceeds the applicable 
reduced life limit.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2016-6990.

Related Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) 292 72 
0848, Version B, dated April 13, 2016. The MSB describes procedures for 
reducing the life limit of the centrifugal impellers affected by an 
anomaly that occurred during the grinding operation required by 
modification TU376. 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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of France, 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with the European Community, EASA has notified us 
of the unsafe condition described in the MCAI and service information 
referenced above. We are proposing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design. This proposed AD would require removal of the centrifugal 
impeller from service before exceeding the reduced life limit shown in 
Appendix 1 of EASA AD 2016-0090, dated May 10, 2016, and replacement 
with a part eligible for installation.

Costs of Compliance

    We estimate that this proposed AD affects 3 engines installed on 
helicopters of U.S. registry. We also estimate that it would take about 
22 hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Required parts cost about $96,518 per engine. 
Based on these figures, we estimate the cost of this proposed AD on 
U.S. operators to be $295,164.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Turbomeca S.A.: Docket No. FAA-2016-6990; Directorate Identifier 
2016-NE-14-AD.

(a) Comments Due Date

    We must receive comments by September 26, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to certain Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 
1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines, 
with modification TU376 installed.

(d) Reason

    This AD was prompted by an anomaly that occurred during the 
grinding operation required by modification TU376, which increases 
the clearance between the rear curvic coupling of the centrifugal 
impeller and the fuel injection manifold. We are issuing this AD to 
prevent failure of the centrifugal impeller, uncontained centrifugal 
impeller release, damage to the engine, and damage to the 
helicopter.

[[Page 49577]]

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service, any centrifugal impeller listed in 
Table 1 to paragraph (e) of this AD, before exceeding the applicable 
cycles since new (CSN) and replace with a centrifugal impeller not 
listed in Table 1 to paragraph (e) of this AD.

           Table 1 to Paragraph (e)--Centrifugal Impeller CSNs
------------------------------------------------------------------------
             Part No.                    Serial No.             CSN
------------------------------------------------------------------------
0292254040........................  44..................           5,129
0292254040........................  1762FT..............          11,476
0292254050........................  1676CAR.............           6,281
0292254050........................  5333OTT.............           5,495
0292254050........................  5017OTT.............           5,491
0292254050........................  1136CAR.............           8,734
0292254050........................  3655OTT.............           4,600
0292254050........................  1757CAR.............           7,913
0292254050........................  1738CAR.............          10,640
0292254050........................  1149CAR.............          12,273
0292254050........................  2677OTT.............          11,145
0292254050........................  3109OTT.............          10,662
0292254050........................  3496OTT.............           5,562
0292254050........................  2074CAR.............           7,423
729225293A........................  290CAR..............           6,326
729225293A........................  1227FT..............           8,139
729225293A........................  504FB...............           4,600
729225293A........................  2517OTT.............           9,732
729225293A........................  2165OTT.............           6,163
729225293A........................  2194FT..............          11,461
729225293A........................  1331OTT.............          12,513
729225293A........................  1301FT..............           7,262
729225293A........................  1567FT..............           6,305
729225293A........................  783FB...............           8,307
729225293A........................  98OTT...............           9,492
------------------------------------------------------------------------

    (2) Reserved.

(f) 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.

(g) Related Information

    (1) For more information about this AD, contact Philip Haberlen, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7770; fax: 781-238-7199; email: 
philip.haberlen@faa.gov.
    (2) Refer to MCAI, European Aviation Safety Agency AD 2016-0090, 
dated May 10, 2016, for more 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-2016-6990.
    (3) Turbomeca S.A. Mandatory Service Bulletin (MSB) 292 72 0848, 
Version B, dated April 13, 2016, can be obtained from Turbomeca 
S.A., using the contact information in paragraph (g)(4) of this 
proposed AD.
    (4) For service information identified in this proposed AD, 
contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 
40 00; fax: 33 (0)5 59 74 45 15.
    (5) 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.

    Issued in Burlington, Massachusetts, on July 21, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-17719 Filed 7-27-16; 8:45 am]
 BILLING CODE 4910-13-P