
[Federal Register Volume 78, Number 143 (Thursday, July 25, 2013)]
[Proposed Rules]
[Pages 44897-44899]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17864]


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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]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft engines. This 
proposed AD was prompted by in-flight shutdowns caused by interrupted 
fuel supply at the hydro-mechanical metering unit (HMU). This proposed 
AD would require initial and repetitive inspections of the 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. We are proposing this AD to prevent in-flight shutdown and 
damage to the engine.

DATES: We must receive comments on this proposed AD by September 23, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    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. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed 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 the same as the 
Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0381; 
Directorate Identifier 2013-NE-16-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may view the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2013-

[[Page 44898]]

0082, dated April 2, 2013, referred to hereinafter as ``the MCAI'', 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 obtain further information by examining the MCAI in the AD 
docket. We are proposing this AD to prevent in-flight shutdown and 
damage to the engine.

Relevant Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin No. SB 319 73 
2825, Version G, dated January 24, 2013. The service information 
describes procedures for correcting the unsafe condition described in 
the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of France, 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with the European Community, EASA has notified us 
of the unsafe condition described in the MCAI and service information 
referenced above. We are proposing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design. This proposed AD would require initial and repetitive 
inspections and cleaning of the 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.

Costs of Compliance

    We estimate that this proposed AD would affect 162 engines 
installed on helicopters of U.S. registry. We also estimate that it 
would take about one hour per engine to comply with this proposed AD. 
The average labor rate is $85 per hour. Required parts cost about $753 
per engine. Based on these figures, we estimate the cost of the 
proposed 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 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 this 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed 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.

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 adding the following new airworthiness 
directive (AD):

Turbomeca S.A.: Docket No. FAA-2013-0381; Directorate Identifier 
2013-NE-16-AD.

(a) Comments Due Date

    We must receive comments by September 23, 2013.

(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

    Unless already done, do the following actions.

(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 per 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 
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 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.

[[Page 44899]]

(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 Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; email: frederick.zink@faa.gov; phone: 781-238-7779; fax: 781-
238-7199.
    (2) Refer to European Aviation Safety Agency, AD 2013-0082, 
dated April 2, 2013, for more information. You may examine the AD on 
the Internet at http://www.regulations.gov.
    (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.


    Issued in Burlington, Massachusetts, on July 18, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-17864 Filed 7-24-13; 8:45 am]
BILLING CODE 4910-13-P


