[Federal Register Volume 79, Number 36 (Monday, February 24, 2014)]
[Rules and Regulations]
[Pages 9990-9991]
From the Federal Register Online via the Government Publishing 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: [email protected].
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: [email protected]; 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