Airworthiness Directives; Safran Helicopter Engines, S.A., Turboshaft Engines, 31325-31327 [2018-14340]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 83, Number 129 (Thursday, July 5, 2018)]
[Rules and Regulations]
[Pages 31325-31327]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-14340]



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Rules and Regulations
                                                Federal Register
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Federal Register / Vol. 83, No. 129 / Thursday, July 5, 2018 / Rules 
and Regulations

[[Page 31325]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0024; Product Identifier 2000-NE-12-AD; Amendment 
39-19307; AD 2018-12-03]
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) 2013-11-09 for 
all Safran Helicopter Engines, S.A., Arrius 2B1 and 2F turboshaft 
engines. AD 2013-11-09 required the repetitive replacement of the fuel 
injector manifolds and privilege injector, or only the privilege 
injector. This AD retains the repetitive hardware replacement 
requirements of AD 2013-11-09, but only allows replacement pipe 
injector preferred assembly, part number (P/N) 0 319 73 044 0, on the 
Arrius 2F engines. This AD was prompted by reports of engine flameouts 
as a result of reduced fuel flow due to the presence of coking. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective August 9, 2018.

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; internet address: 
www.tools.safran-helicopter-engines.com. 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 https://www.regulations.gov by searching 
for and locating Docket No. FAA-2013-0024.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0024; 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: Barbara Caufield, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7146; fax: 781-238-7199; email: faa.gov">[email protected]faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-11-09, Amendment 39-17469 (78 FR 32551, 
May 31, 2013), ``AD 2013-11-09''. AD 2013-11-09 applied to all 
Turbomeca S.A., Arrius 2B1 and 2F turboshaft engines. The NPRM 
published in the Federal Register on August 25, 2017 (82 FR 40503). The 
NPRM was prompted by a report that the corrective actions of the 
existing AD were insufficient to eliminate the unsafe condition. The 
NPRM proposed initial and repetitive replacement of the main fuel 
injector half-manifolds and preferred injector for Arrius 2B1 
turboshaft engines, and initial and repetitive replacement of the 
preferred injector and replacing pipe injector preferred assemblies, P/
N 0 319 73 835 0, with assembly, P/N 0 319 73 044 0, for Arrius 2F 
turboshaft engines. 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 each comment.

Request To Add Safran Service Bulletin (SB) 319 73 4085

    An individual commenter requested that we incorporate Safran 
service bulletin (SB) No. 319 73 4085, which installs new insulating 
seals on the fuel manifold assemblies to limit coking, in this AD. The 
commenter does not believe that the proposed AD completely corrects the 
unsafe condition, which could result in another revised or supersedure 
AD in the future.
    We disagree. We have not determined that the Safran SB No. 319 73 
4085, Version A, dated March 23, 2016, provides an effective 
terminating action to the current AD requirements. We did not change 
this AD.

Request To Revise Operating Hours in Figure 1

    Safran Helicopter Engines stated there was an error in Figure 1 to 
paragraph (g)(1)(i) of this AD requiring the post-mod TU117 main fuel 
injector half-manifold be replaced every 600 operating hours. They 
stated the replacement interval is 500 hours (plus a 100 hour non-
cumulative tolerance). The application of the non-cumulative tolerance 
specified in the Arrius 2B1 Maintenance Manual X 319 L5 301 2 was 
misinterpreted.
    We agree with commenter's explanation and justification. We revised 
the main fuel injector half-manifold--post-mod TU117 operating hours in 
Figure 1 to paragraph (g) of this AD from 600 operating hours to 500 
operating hours, which is consistent with the approved Airworthiness 
Limitations for this engine. We also added paragraph (g)(1)(i)(A) to 
this AD that allows a non-cumulative tolerance of 100 operating hours 
to the compliance time for the initial replacement of the post-mod 
TU117 main injector half-manifolds.

Request To Revise the Compliance Requirements

    Safran Helicopter Engines requested that we revise paragraph 
(g)(2)(iii) of this AD to replace ``within 16 months after the 
effective date of this AD'' with ``August 31, 2018.'' Safran Helicopter 
Engines asserted that 16 months was correct when EASA issued AD 2017-
0070, but to be consistent with the compliance in Safran Helicopter

[[Page 31326]]

Engines Mandatory SB No. 319 73 4839, this date must be modified to 
match August 31, 2018.
    We disagree. We determined that 16 months after the effective date 
of the AD is a reasonable timeframe to complete the actions and will 
meet our safety objectives. We did not change this AD.

Request To Revise the Required Actions

    Safran Helicopter Engines requested we clarify paragraph 
(g)(2)(iii) of this AD by deleting the words ``before next flight.''
    We agree with the commenter's request because this change clarifies 
paragraph (g)(2)(iii) of this AD. We revised paragraph (g)(2)(iii) of 
this AD as requested.

Request To Revise Contact Information

    Safran Helicopter Engines requested that we revise the contact 
information for service information in paragraph to the following: 
``Please contact your nearest SAFRAN Helicopter Engines technical 
representative or connect to www.tools.safran-helicopter-engines.com.''
    We agree. We revised the contact information in the ADDRESSES 
section of this AD to include Safran's internet address: 
www.tools.safran-helicopter-engines.com.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously. 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information

    We reviewed Safran Helicopter Engines Mandatory SB No. 319 73 4839, 
Version A, dated December 13, 2016. The SB describes procedures for 
replacing pipe injector preferred assemblies.

Costs of Compliance

    We estimate that this AD affects 50 Arrius 2B1 and 105 Arrius 2F 
turboshaft 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
----------------------------------------------------------------------------------------------------------------
Arrius 2B1 fuel injector manifolds   3 work-hours x $85 per hour              $0            $255         $12,750
 and injector replacement.            = $255.
Arrius 2F pipe injector preferred    3 work-hours x $85 per hour           3,154           3,409         357,945
 assembly replacement.                = $255.
----------------------------------------------------------------------------------------------------------------

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

    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 to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Code of Federal 
Regulations (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) 
2013-11-09, Amendment 39-17469 (78 FR 32551), and adding the following 
new AD:

2018-12-03 Safran Helicopter Engines, S.A. (Type Certificate 
previously held by Turbomeca S.A.): Amendment 39-19307; Docket No. 
FAA-2013-0024; Product Identifier 2000-NE-12-AD.

(a) Effective Date

    This AD is effective August 9, 2018.

(b) Affected ADs

    This AD replaces AD 2013-11-09, Amendment 39-17469 (78 FR 32551, 
May 31, 2013).

[[Page 31327]]

(c) Applicability

    This AD applies to all Safran Helicopter Engines, S.A., Arrius 
2B1 and 2F turboshaft engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7320, Fuel 
Controlling System.

(e) Unsafe Condition

    This AD was prompted by several reports of engine flameouts as a 
result of reduced fuel flow due to the presence of coking. We are 
issuing this AD to prevent an engine flameout of Arrius 2B1 and 2F 
turboshaft engines. The unsafe condition, if not addressed, could 
result in an engine flameout and damage to the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For Arrius 2B1 turboshaft engines, do the following:
    (i) Replace each main fuel injector half-manifold and preferred 
injector with a part eligible for installation before exceeding the 
operating hours (hours accumulated by the part since installation on 
an engine) specified in Figure 1 to paragraph (g) of this AD.
    (A) For the post-mod TU117 main injector half-manifold, a one-
time, non-cumulative tolerance of 100 operating hours may be applied 
to the compliance interval specified in Figure 1. This one-time 
tolerance can be applied to the initial replacement or a subsequent 
replacement, as required.
    (B) Reserved.
    [GRAPHIC] [TIFF OMITTED] TR05JY18.000
    
    (ii) Borescope-inspect (BSI) the flame tube and the high-
pressure turbine (HPT) area for turbine distress, when replacing the 
fuel injector manifolds and preferred injector for the first time.
    (iii) Thereafter, replace the fuel injector manifolds and 
preferred injector with a part eligible for installation before 
exceeding the operating hours (hours accumulated by the part since 
installation on an engine) specified in Figure 1 to paragraph (g) of 
this AD.
    (2) For Arrius 2F turboshaft engines, do the following:
    (i) Replace each pipe injector preferred assembly, part number 
(P/N) 0 319 73 835 0 and P/N 0 319 73 044 0, with a part eligible 
for installation before exceeding 400 operating hours (hours 
accumulated by the part since installation on an engine).
    (ii) BSI the flame tube and the HPT area for turbine distress, 
when replacing the privilege injector for the first time.
    (iii) Unless already accomplished as required by paragraph 
(g)(2)(i) of this AD, within 16 months after the effective date of 
this AD, replace the pipe injector preferred assembly, P/N 0 319 73 
835 0, with a part eligible for installation.
    (iv) Thereafter, replace the pipe injector preferred assembly 
with a part eligible for installation within 400 operating hours 
since the last pipe injector preferred assembly replacement.

(h) Definitions

    (1) For Arrius 2B1 turboshaft engines, a main fuel injector 
half-manifold or preferred injector is eligible for installation if 
it has not exceeded the operating hours specified in Figure 1 to 
paragraph (g) of this AD since first installation on an engine or 
since last cleaning.
    (2) For Arrius 2F turboshaft engines, a pipe injector preferred 
assembly, P/N 0 319 73 044 0, is eligible for installation if it has 
not exceeded 400 operating hours since first installation on an 
engine or since last cleaning.

(i) Installation Prohibition

    (1) For Arrius 2B1 turboshaft engines, after the effective date 
of this AD, do not install a main fuel injector half-manifold or 
preferred injector onto any engine, or any engine onto a helicopter, 
unless the main fuel injector half-manifold and preferred injector 
are eligible for installation.
    (2) For Arrius 2F turboshaft engines, after the effective date 
of this AD, do not install a pipe injector preferred assembly onto 
any engine, or any engine onto a helicopter, unless the pipe 
injector preferred assembly is eligible for installation.
    (3) For Arrius 2F turboshaft engines, after the effective date 
of this AD, do not install a pipe injector preferred assembly, P/N 0 
319 73 835 0, onto any engine.

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

(k) Related Information

    (1) For more information about this AD, contact Barbara 
Caufield, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7146; fax: 781-238-7199; email: 
faa.gov">[email protected]faa.gov.
    (2) Refer to European Aviation Safety Agency AD 2017-0070, dated 
April, 25, 2017, for more information. You may examine the EASA AD 
on the internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2013-0024.

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on June 27, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-14340 Filed 7-3-18; 8:45 am]
 BILLING CODE 4910-13-P