Document ID: FAA-2009-0889-0011
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Safran Helicopter Engines, S.A., Turboshaft Engines
Posted Date: 2017-10-06T04:00Z

[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]

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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).

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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