Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines, 46727-46729 [2017-21344]

Download as PDF Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules provisions of paragraphs (i)(4)(i) and (i)(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. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (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. (j) Related Information (1) For more information about this AD, contact Lu Lu, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6478; fax: 425–917–6590; email: lu.lu@faa.gov. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, Seattle, WA 98168; phone: 1–206–830–7699; fax: 1– 206–767–3355; email: leng@ aviationpartners.com; Internet: http:// www.aviationpartnersboeing.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. torque between the low-pressure (LP) pump impeller and the high-pressure (HP) pump shaft on the HP/LP pump and metering valve assembly, hereafter referred to as the hydro-mechanical metering unit (HMU). Since we issued AD 2012–03–11, the manufacturer determined that incorporating Modification TU 178 is a more effective method to reduce the risk of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft than the prior Modification TU 147. This proposed AD would require inspection and possible replacement of the HMU. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 20, 2017. [Docket No. FAA–2009–0889; Product Identifier 2009–NE–35–AD] 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Safran Helicopter Engines, 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 and Propeller Standards Branch, 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–2009– 0889. RIN 2120–AA64 Examining the AD Docket Issued in Renton, Washington, on September 25, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–21225 Filed 10–5–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). asabaliauskas on DSKBBXCHB2PROD with PROPOSALS AGENCY: We propose to supersede airworthiness directive (AD) 2012–03– 11 that applies to all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines. AD 2012–03–11 requires checking the transmissible SUMMARY: VerDate Sep<11>2014 17:27 Oct 05, 2017 Jkt 244001 ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2009– 0889; 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 proposed 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 in the ADDRESSES section. Comments will be PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 46727 available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7754; fax: 781–238–7199; email: robert.green@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2009–0889; Product Identifier 2009– NE–35–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of 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 we receive about this NPRM. Discussion We issued AD 2012–03–11, Amendment 39–16953 (77 FR 8092, February 14, 2012), ‘‘AD 2012–03–11,’’ for all Turbomeca S.A. Arriel 2B and 2B1 turboshaft engines. AD 2012–03–11 requires checking the transmissible torque between the LP pump impeller and the HP pump shaft on the pre- and post-Modification TU 147 HMUs. AD 2012–03–11 resulted from instances of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft. We issued AD 2012–03–11 to prevent an uncommanded in-flight shutdown, which can result in a forced autorotation landing or accident. Actions Since AD 2012–03–11 Was Issued Since we issued AD 2012–03–11, the manufacturer determined that modification of an engine to incorporate Modification TU 178 is a more effective method to reduce the risk of uncoupling between the LP fuel pump impeller and the HP fuel pump shaft than the prior Modification TU 147. Also since we issued AD 2012–03–11, the European Aviation Safety Agency (EASA) has issued AD 2017–0102, dated June 13, 2017, which requires inspection and possible replacement of the HMU. E:\FR\FM\06OCP1.SGM 06OCP1 46728 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules Other Related Service Information Related Service Information Under 1 CFR Part 51 Turbomeca, S.A., has issued Alert Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July 10, 2009, and Alert MSB A292 73 2836, Version A, dated August 17, 2010. Turbomeca Alert MSB A292 73 2830, Version B, is used to do the inspection for preModification TU 147 HMUs. Turbomeca Alert MSB A292 73 2836, Version A, is used to do the inspection for HMUs that have incorporated Modification TU 147. 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. Safran Helicopter Engines has issued MSB 292 73 2178, Version B, dated March 23, 2017, introducing an HMU with a reinforced drive link between the LP impeller and fuel pump drive shaft (Modification TU 178). Safran Helicopter Engines has also issued MSB A292 73 2830, Version C; and A292 73 2836, Version B, both dated April 5, 2017, which exempt HMUs incorporating Modification TU 178 from the inspections previously recommended by Turbomeca. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require inspection and, depending on the results of the inspection, possible replacement of the HMU. This proposed AD would further require replacement of pre-Modification TU 178 HMUs with an HMU incorporating Modification TU 178 within 2,200 engine flight hours or 72 months, whichever occurs later, after the effective date of this AD. Costs of Compliance We estimate that this proposed AD affects 417 engines installed on helicopters of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Remove and replace the HP/LP fuel pump metering unit. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS Action 2 work-hours × $85 per hour = $170 ............. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. VerDate Sep<11>2014 17:27 Oct 05, 2017 Jkt 244001 Parts cost Regulatory Findings We have 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 that the 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. Cost per product $17,400 Cost on U.S. operators $17,570 $7,326,690 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) 2012–03–11, Amendment 39–16953 (77 FR 8092, February 14, 2012), and adding the following new AD: ■ Safran Helicopter Engines (Type Certificate previously held by Turbomeca, S.A.): Docket No. FAA–2009–0889; Product Identifier 2009–NE–35–AD. (a) Comments Due Date We must receive comments by November 20, 2017. (b) Affected ADs This AD replaces AD 2012–03–11, Amendment 39–16953 (77 FR 8092, February 14, 2012). (c) Applicability This AD applies to Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines, except those incorporating Modification TU 178. The Proposed Amendment (d) Subject Joint Aircraft System Component (JASC) Code 7300, Engine Fuel and Control. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (e) Unsafe Condition This AD was prompted by analysis that indicated the modification of an engine to incorporate Modification TU 178 provides a PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 E:\FR\FM\06OCP1.SGM 06OCP1 Federal Register / Vol. 82, No. 193 / Friday, October 6, 2017 / Proposed Rules more effective method than Modification TU 147 to reduce the risk of uncoupling between the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft of the HP/LP pump and hydro-mechanical metering unit (HMU). We are issuing this AD to prevent failure of the HMU. The unsafe condition, if not corrected, could result in failure of the engine, in-flight shutdown, and loss of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Check the transmissible torque between the LP fuel pump impeller and the HP fuel pump shaft as follows: (i) For pre-Modification TU 147 HMUs, check the torque before accumulating 500 engine flight hours (FHs) since March 11, 2010 or before the next flight, whichever occurs later. Use Paragraph 2 of Turbomeca Alert Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July 10, 2009 to do the check. (ii) For HMUs that incorporated Modification TU 147 on or before March 31, 2010, and those HMUs not listed in Figures 2 or 3 of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, check the torque before the next flight. Use Paragraph 2 of Turbomeca Alert MSB A292 73 2836, Version A, to do the check. (2) If the HMU does not pass the torque check, replace the HMU with a postModification TU 178 HMU before the next flight. (g) Mandatory Terminating Action Within 2,200 engine FHs or 72 months after the effective date of this AD, whichever occurs first, replace any pre-Modification TU 178 HMU with a post-Modification TU 178 configuration HMU. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (h) Installation Prohibition After the effective date of this AD, do not install a pre-Modification TU 178 HMU on engines incorporating a post-Modification TU 178 HMU. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, may 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. You may email your request to: ANE-AD-AMOC@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. (j) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: robert.green@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2017–0102, dated June 13, VerDate Sep<11>2014 17:27 Oct 05, 2017 Jkt 244001 2017, 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–2009–0889. (3) For service information identified in this AD, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this referenced service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on September 29, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–21344 Filed 10–5–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0902; Product Identifier 2016–NM–188–AD] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2004–03– 07, which applies to certain Airbus Model A320–111, –211, –212, and –231 series airplanes. AD 2004–03–07 requires repetitive inspections for fatigue cracking around the fasteners attaching the pressure panel to the flexible bracket at frame (FR) 36, adjacent to the longitudinal beams on the left and right sides of the airplane; and repair as necessary. Since we issued AD 2004–03–07, additional cracking has been found under the longitudinal beams in locations outside of the inspection areas required by AD 2004– 03–07. This proposed AD would retain certain requirements of AD 2004–03–07, expand the applicability, and require an inspection of the fastener holes on the pressure panel between FR 35 and FR 36 under the longitudinal beam and modification or repair as applicable. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 20, 2017. SUMMARY: Frm 00014 Fmt 4702 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. ADDRESSES: Examining the AD Docket Airworthiness Directives; Airbus Airplanes PO 00000 46729 Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0902; 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 proposed 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: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0902; Product Identifier 2016– NM–188–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, E:\FR\FM\06OCP1.SGM 06OCP1

Agencies

[Federal Register Volume 82, Number 193 (Friday, October 6, 2017)]
[Proposed Rules]
[Pages 46727-46729]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-21344]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0889; Product Identifier 2009-NE-35-AD]
RIN 2120-AA64


Airworthiness Directives; Safran Helicopter Engines, S.A., 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directive (AD) 2012-03-
11 that applies to all Safran Helicopter Engines, S.A., Arriel 2B and 
2B1 turboshaft engines. AD 2012-03-11 requires checking the 
transmissible torque between the low-pressure (LP) pump impeller and 
the high-pressure (HP) pump shaft on the HP/LP pump and metering valve 
assembly, hereafter referred to as the hydro-mechanical metering unit 
(HMU). Since we issued AD 2012-03-11, the manufacturer determined that 
incorporating Modification TU 178 is a more effective method to reduce 
the risk of uncoupling between the LP fuel pump impeller and the HP 
fuel pump shaft than the prior Modification TU 147. This proposed AD 
would require inspection and possible replacement of the HMU. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by November 20, 
2017.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Safran 
Helicopter Engines, 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 and Propeller Standards Branch, 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-2009-0889.

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-2009-
0889; 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 proposed 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 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7754; fax: 781-238-7199; email: robert.green@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2009-0889; 
Product Identifier 2009-NE-35-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of 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 we 
receive about this NPRM.

Discussion

    We issued AD 2012-03-11, Amendment 39-16953 (77 FR 8092, February 
14, 2012), ``AD 2012-03-11,'' for all Turbomeca S.A. Arriel 2B and 2B1 
turboshaft engines. AD 2012-03-11 requires checking the transmissible 
torque between the LP pump impeller and the HP pump shaft on the pre- 
and post-Modification TU 147 HMUs. AD 2012-03-11 resulted from 
instances of uncoupling between the LP fuel pump impeller and the HP 
fuel pump shaft. We issued AD 2012-03-11 to prevent an uncommanded in-
flight shutdown, which can result in a forced autorotation landing or 
accident.

Actions Since AD 2012-03-11 Was Issued

    Since we issued AD 2012-03-11, the manufacturer determined that 
modification of an engine to incorporate Modification TU 178 is a more 
effective method to reduce the risk of uncoupling between the LP fuel 
pump impeller and the HP fuel pump shaft than the prior Modification TU 
147. Also since we issued AD 2012-03-11, the European Aviation Safety 
Agency (EASA) has issued AD 2017-0102, dated June 13, 2017, which 
requires inspection and possible replacement of the HMU.

[[Page 46728]]

Related Service Information Under 1 CFR Part 51

    Turbomeca, S.A., has issued Alert Mandatory Service Bulletin (MSB) 
A292 73 2830, Version B, dated July 10, 2009, and Alert MSB A292 73 
2836, Version A, dated August 17, 2010. Turbomeca Alert MSB A292 73 
2830, Version B, is used to do the inspection for pre-Modification TU 
147 HMUs. Turbomeca Alert MSB A292 73 2836, Version A, is used to do 
the inspection for HMUs that have incorporated Modification TU 147. 
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.

Other Related Service Information

    Safran Helicopter Engines has issued MSB 292 73 2178, Version B, 
dated March 23, 2017, introducing an HMU with a reinforced drive link 
between the LP impeller and fuel pump drive shaft (Modification TU 
178). Safran Helicopter Engines has also issued MSB A292 73 2830, 
Version C; and A292 73 2836, Version B, both dated April 5, 2017, which 
exempt HMUs incorporating Modification TU 178 from the inspections 
previously recommended by Turbomeca.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require inspection and, depending on the 
results of the inspection, possible replacement of the HMU. This 
proposed AD would further require replacement of pre-Modification TU 
178 HMUs with an HMU incorporating Modification TU 178 within 2,200 
engine flight hours or 72 months, whichever occurs later, after the 
effective date of this AD.

Costs of Compliance

    We estimate that this proposed AD affects 417 engines installed on 
helicopters of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Remove and replace the HP/LP fuel pump  2 work-hours x $85 per           $17,400         $17,570      $7,326,690
 metering unit.                          hour = $170.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We have 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 that the 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 removing airworthiness directive (AD) 
2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), and 
adding the following new AD:

Safran Helicopter Engines (Type Certificate previously held by 
Turbomeca, S.A.): Docket No. FAA-2009-0889; Product Identifier 2009-
NE-35-AD.

(a) Comments Due Date

    We must receive comments by November 20, 2017.

(b) Affected ADs

    This AD replaces AD 2012-03-11, Amendment 39-16953 (77 FR 8092, 
February 14, 2012).

(c) Applicability

    This AD applies to Safran Helicopter Engines, S.A., Arriel 2B 
and 2B1 turboshaft engines, except those incorporating Modification 
TU 178.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7300, Engine Fuel 
and Control.

(e) Unsafe Condition

    This AD was prompted by analysis that indicated the modification 
of an engine to incorporate Modification TU 178 provides a

[[Page 46729]]

more effective method than Modification TU 147 to reduce the risk of 
uncoupling between the low-pressure (LP) fuel pump impeller and the 
high-pressure (HP) fuel pump shaft of the HP/LP pump and hydro-
mechanical metering unit (HMU). We are issuing this AD to prevent 
failure of the HMU. The unsafe condition, if not corrected, could 
result in failure of the engine, in-flight shutdown, and loss of the 
helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Check the transmissible torque between the LP fuel pump 
impeller and the HP fuel pump shaft as follows:
    (i) For pre-Modification TU 147 HMUs, check the torque before 
accumulating 500 engine flight hours (FHs) since March 11, 2010 or 
before the next flight, whichever occurs later. Use Paragraph 2 of 
Turbomeca Alert Mandatory Service Bulletin (MSB) A292 73 2830, 
Version B, dated July 10, 2009 to do the check.
    (ii) For HMUs that incorporated Modification TU 147 on or before 
March 31, 2010, and those HMUs not listed in Figures 2 or 3 of 
Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, 
check the torque before the next flight. Use Paragraph 2 of 
Turbomeca Alert MSB A292 73 2836, Version A, to do the check.
    (2) If the HMU does not pass the torque check, replace the HMU 
with a post-Modification TU 178 HMU before the next flight.

(g) Mandatory Terminating Action

    Within 2,200 engine FHs or 72 months after the effective date of 
this AD, whichever occurs first, replace any pre-Modification TU 178 
HMU with a post-Modification TU 178 configuration HMU.

(h) Installation Prohibition

    After the effective date of this AD, do not install a pre-
Modification TU 178 HMU on engines incorporating a post-Modification 
TU 178 HMU.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, may 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. 
You may email your request to: ANE-AD-AMOC@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.

(j) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 
robert.green@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2017-0102, 
dated June 13, 2017, 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-2009-0889.
    (3) For service information identified in this AD, contact 
Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 
05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this 
referenced service information at the FAA, Engine and Propeller 
Standards Branch, 1200 District Avenue, Burlington, MA 01803. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on September 29, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-21344 Filed 10-5-17; 8:45 am]
 BILLING CODE 4910-13-P