Document ID: FAA-2009-0889-0015
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Safran Helicopter Engines, S.A., Turboshaft Engines
Posted Date: 2018-08-08T04:00Z

[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Rules and Regulations]
[Pages 38951-38953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16652]

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 Rules and Regulations
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  Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / 
Rules and Regulations  

[[Page 38951]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0889; Product Identifier 2009-NE-35-AD; Amendment 
39-19305; AD 2018-12-01]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2012-03-11 for 
all Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft 
engines. AD 2012-03-11 required 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 AD requires inspection and 
possible replacement of the HMU. This AD was prompted by three cases of 
uncoupling of the HMU LP fuel pump impeller and the HP fuel pump shaft 
since AD 2012-03-11 was issued. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective September 12, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 11, 
2010 (75 FR 5689, February 4, 2010).
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 20, 
2012 (77 FR 8092, February 14, 2012).

ADDRESSES: For service information identified in this final rule, 
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 01803. For information on the 
availability of this material at the FAA, call 781-238-7759. 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 Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the mandatory continuing airworthiness information, 
regulatory evaluation, any comments received, and other information. 
The address for Docket Operations (phone: 800-647-5527) is Document 
Operations, 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: John Frost, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7756; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-03-11, Amendment 39-16953 (77 FR 8092, 
February 14, 2012), (``AD 2012-03-11''). AD 2012-03-11 applied to all 
Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines. 
The NPRM published in the Federal Register on October 6, 2017 (82 FR 
46727). The NPRM was prompted by instances of uncoupling between the LP 
fuel pump impeller and the HP fuel pump shaft. The NPRM proposed to 
require inspection and, depending on the results of the inspection, 
possible replacement of the HMU. The NPRM also proposed to 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 first, after the effective date of this AD. We are 
issuing this AD to address the unsafe condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to the comment.

Request To Clarify Reason for AD

    An individual commenter questioned how the new modification in this 
AD is better and different from the actions required by the previous AD 
2012-03-11.
    AD 2012-03-11 required a check of the transmissible torque between 
the LP fuel pump impeller and the HP fuel pump shaft and replacement of 
the HMU if it does not pass the torque check. Since we issued AD 2012-
03-11, Safran Service Bulletin (SB) 292 73 2178, Version A, dated April 
1, 2015 introduced Modification TU 178. This AD accepts Modification TU 
178 as a more robust drive link between the LP fuel pump impeller and 
the HP fuel pump shaft that ensures the LP impeller pump is driven even 
if the link with the drive shaft loosens. This AD requires installation 
of a Modification TU 178 HMU for any HMU that fails the torque sensor 
check and as a mandatory terminating action for the inspections 
required by this AD, as well as purging the fleet of the pre- and post-
TU 147 configuration parts. We did not change this AD.

Clarification to Service Information for Torque Check

    We updated paragraphs (g)(1)(i) and (ii) of this AD to clarify that 
only paragraph 2.A, rather than paragraph 2, in Turbomeca Alert 
Mandatory SB (MSB) A292 73 2830, Version B, dated July 10, 2009, and 
Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, is 
used to perform the torque check.

[[Page 38952]]

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Turbomeca, S.A., Alert 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, describes 
procedures for inspecting pre-Modification TU 147 HMUs. Turbomeca Alert 
MSB A292 73 2836, Version A, dated August 17, 2010, describes 
procedures for inspecting 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

    We reviewed Safran Helicopter Engines MSB 292 73 2178, Version B, 
dated March 23, 2017. Safran Helicopter Engines MSB 292 73 2178, 
Version B, describes HMU improvements that includes a reinforced drive 
link between the LP impeller and HP fuel pump 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 Safran Helicopter Engines.

Costs of Compliance

    We estimate that this AD affects 417 engines installed on 
helicopters of U.S. registry.
    We estimate the following costs to comply with this 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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, 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 removing Airworthiness Directive (AD) 
2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), and 
adding the following new AD:

2018-12-01 Safran Helicopter Engines (Type Certificate previously 
held by Turbomeca, S.A.): Amendment 39-19305; Docket No. FAA-2009-
0889; Product Identifier 2009-NE-35-AD.

(a) Effective Date

    This AD is effective September 12, 2018.

(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 more 
effective method than Modification TU

[[Page 38953]]

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.

(g) Required Actions

    (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 after the effective date of this AD, 
whichever occurs later. Use Paragraph 2.A. 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 Figure 2 or 3 of 
Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, 
check the torque before the next flight after the effective date of 
this AD. Use Paragraph 2.A. of Turbomeca Alert MSB A292 73 2836, 
Version A, dated August 17, 2010, 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 after the 
effective date of this AD.

(h) 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.

(i) 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.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, 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 
certification office, send it to the attention of the person 
identified in paragraph (k)(1) of this AD. You may email your 
request to: [email protected].
    (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.

(k) Related Information

    (1) For more information about this AD, contact John Frost, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to European Aviation Safety Agency (EASA) AD 2017-
0102, dated June 13, 2017, for more information. You may examine the 
EASA AD on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2009-0889.

(l) 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.
    (3) The following service information was approved for IBR on 
March 11, 2010 (75 FR 5689, February 4, 2010).
    (i) Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 73 
2830, Version B, dated July 10, 2009.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
March 20, 2012 (77 FR 8092, February 14, 2012).
    (i) Turbomeca Alert MSB No. A292 73 2836, Version A, dated 
August 17, 2010.
    (ii) Reserved.
    (5) For Safran Helicopter Engines, S.A, 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.
    (6) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (7) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on July 31, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-16652 Filed 8-7-18; 8:45 am]
 BILLING CODE 4910-13-P