Document ID: FAA-2013-0381-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2014-02-24T05:00Z

[Federal Register Volume 79, Number 36 (Monday, February 24, 2014)]
[Rules and Regulations]
[Pages 9990-9991]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-03672]

[[Page 9990]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0381; Directorate Identifier 2013-NE-16-AD; 
Amendment 39-17764; AD 2014-04-06]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft engines. This 
AD requires initial and repetitive inspections of the hydro-mechanical 
metering unit (HMU) high pressure pump drive gear shaft splines, 
cleaning and inspections of the sleeve assembly splines, and 
replacement of the HMU if it fails inspection. This AD was prompted by 
in-flight shutdowns caused by interrupted fuel supply at the HMU. We 
are issuing this AD to prevent in-flight shutdown and damage to the 
engine.

DATES: This AD becomes effective March 31, 2014.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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-2013-
0381; 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 AD, the mandatory continuing airworthiness information 
(MCAI), the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(phone: 800-647-5527) is provided in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Anthony W. Cerra, Jr., Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
phone: 781-238-7128; fax: 781-238-7199; email: anthony.cerra@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
Part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on July 25, 2013 (78 FR 
44897). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A number of in-flight shutdown occurrences have been reported 
for Arrius 2 engines. The results of the technical investigations 
concluded that these events were caused by deterioration of the 
splines on the high pressure (HP)/low pressure (LP) pump assembly 
drive shaft of the hydro-mechanical metering unit (HMU), which 
eventually interrupted the fuel supply to the engine. This 
condition, if not detected and corrected, could lead to further 
cases of engine in-flight shutdown, possibly resulting in forced 
landing.
    To address these occurrences, Turbomeca published Service 
Bulletin (SB) No. SB 319 73 2825, which provides inspection 
instructions. After that SB was issued, further similar occurrences 
prompted Turbomeca to perform a new assessment of the issue. As a 
result, it was determined that repetitive inspections of the HMU, 
including an additional inspection of the sleeve assembly, was 
necessary to address the issue. Those instructions are provided in 
Turbomeca Mandatory SB (MSB) No. SB 319 73 2825 version G.
    For the reasons described above, this AD requires repetitive 
inspections of drive gear shaft splines of the HP pump, and 
depending on findings, accomplishment of applicable corrective 
actions.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/# !documentDetail;D=FAA-2013-0381-0004.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 44897, July 25, 
2013).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

Costs of Compliance

    We estimate that this AD will affect about 162 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
one hour per product to comply with this AD. The average labor rate is 
$85 per hour. Required parts will cost about $753 per engine. Based on 
these figures, we estimate the cost of this AD on U.S. operators to be 
$135,756.

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 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 this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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:

[[Page 9991]]

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):

2014-04-06 Turbomeca S.A.: Amendment 39-17764; Docket No. FAA-2013-
0381; Directorate Identifier 2013-NE-16-AD.

(a) Effective Date

    This AD becomes effective March 31, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 
2K1 turboshaft engines.

(d) Reason

    This AD was prompted by in-flight shutdowns caused by 
interrupted fuel supply at the hydro-mechanical metering unit (HMU). 
We are issuing this AD to prevent in-flight shutdown and damage to 
the engine.

(e) Actions and Compliance

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

(f) Initial Visual Inspection for HMUs Not Previously Inspected

    (1) On the effective date of this AD, for those HMUs that have 
not previously been inspected using Turbomeca Mandatory Service 
Bulletin (MSB) No. SB 319 73 2825, Version G, dated January 24, 
2013, or earlier versions; perform an initial visual inspection of 
the HMU high-pressure pump drive gear shaft splines for wear, 
corrosion, scaling, or cracks, and clean and inspect the sleeve 
assembly splines for wear, corrosion, scaling, or cracks, at the 
following:
    (i) For HMUs that have accumulated more than 150 operating hours 
(OHs) since new or since last overhaul, within 50 HMU OHs after 
effective date of this AD.
    (ii) For HMUs that have accumulated 150 or fewer OHs since new 
or since last overhaul, before exceeding 200 HMU OHs.

 (g) Initial Visual Inspection for HMUs That Have Been Previously 
Inspected

    (1) On the effective date of this AD, for those HMUs that have 
been previously inspected per Turbomeca MSB No. SB 319 73 2825, 
Version G, dated January 24, 2013, or earlier versions; perform a 
visual inspection of HMU aft splines of the high pressure pump for 
wear, corrosion, scaling, or cracks, and clean and inspect the 
sleeve assembly splines for wear, corrosion, scaling, or cracks, at 
the following:
    (i) For HMUs that have accumulated 300 OHs or more since last 
inspection, within 200 HMU OHs after effective date of this AD.
    (ii) For HMUs that have accumulated fewer than 300 OHs since 
last inspection, before exceeding 500 HMU OHs.

(h) Repetitive Visual Inspections of HMUs

    (1) Thereafter, repetitively visually inspect the HMU aft 
splines of the high pressure pump, and clean and inspect the sleeve 
assembly splines for wear, corrosion, scaling, or cracks, at 
intervals not to exceed 500 HMU OHs.
    (2) If, during any initial or repetitive inspection required by 
this AD, an HMU does not pass inspection, then before further 
flight, replace the sleeve assembly on the affected high pressure 
pump drive gear shaft or replace the affected HMU.

(i) Installation Prohibition

    After the effective date of this AD, do not install any engine 
on any helicopter unless the HMU was inspected as required by this 
AD.

(j) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(k) Related Information

    (1) For more information about this AD, contact Anthony W. 
Cerra, Jr., Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; email: anthony.cerra@faa.gov; phone: 781-238-
7128; fax: 781-238-7199.
    (2) Refer to MCAI European Aviation Safety Agency, AD 2013-0082, 
dated April 2, 2013, for more information. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0381-0004.
    (3) Turbomeca MSB No. SB 319 73 2825, Version G, dated January 
24, 2013, which is not incorporated by reference in this AD, can be 
obtained from Turbomeca, S.A. using the contact information in 
paragraph (k)(4) of this AD.
    (4) For service information identified in this AD, contact 
Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; 
telex: 570 042; fax: 33 (0)5 59 74 45 15.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on February 10, 2014.
Robert J. Ganley,
Acting Assistant Directorate Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2014-03672 Filed 2-21-14; 8:45 am]
BILLING CODE 4910-13-P