Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

[Federal Register Volume 79, Number 158 (Friday, August 15, 2014)]
[Rules and Regulations]
[Pages 48028-48030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-19228]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0219; Directorate Identifier 2014-NE-04-AD; 
Amendment 39-17939; AD 2014-16-15]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Makila 2A and Makila 2A1 turboshaft engines. This AD 
requires initial and repetitive visual inspections, and replacement of 
the splines of the high-pressure (HP) fuel pump/metering valve and the 
module M01 drive gear, if necessary. This AD was prompted by the 
failure of two HP fuel pumps that resulted in engine in-flight 
shutdowns. We are issuing this AD to prevent failure of the HP fuel 
pump, which could lead to an in-flight shutdown, damage to the engine, 
and forced landing or accident.

DATES: This AD becomes effective September 19, 2014.

ADDRESSES: 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 by searching for and locating Docket No. FAA-2014-
0219; or in person at the Docket Management Facility 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 address for the Docket Office (phone: 800-647-5527) is 
Document Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

[[Page 48029]]


FOR FURTHER INFORMATION CONTACT: Katheryn Malatek, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7747; 
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 May 12, 2014 (79 FR 
26905). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Two uncommanded in-flight shutdowns on Makila 2A/2A1 engines 
have been reported. The results of the technical investigations 
concluded that these events were caused by deterioration of the 
splines on the high-pressure (HP) fuel pump drive link, which 
eventually interrupted the fuel supply to the engine.
    This condition, if not detected and corrected, could lead to 
further cases of uncommanded engine in-flight shutdown, and may 
ultimately lead to an emergency landing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (79 FR 26905, May 12, 
2014).

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 affects 8 engines installed on helicopters 
of U.S. registry. We also estimate that it will take about 2 hours per 
engine to comply with this AD. The average labor rate is $85 per hour. 
Required parts cost about $750 per engine. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $1,360.

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.

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 adding the following new airworthiness 
directive (AD):

2014-16-15 Turbomeca S.A.: Amendment 39-17939; Docket No. FAA-2014-
0219; Directorate Identifier 2014-NE-04-AD.

(a) Effective Date

    This AD becomes effective September 19, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Turbomeca S.A. Makila 2A and Makila 2A1 
turboshaft engines with a high-pressure (HP) fuel pump, part number 
(P/N) 0 298 91 806 0 or P/N 0 298 91 805 0, installed, that have not 
incorporated Turbomeca modification TU 59.

(d) Reason

    This AD was prompted by the failure of two HP fuel pumps that 
resulted in engine in-flight shutdowns. We are issuing this AD to 
prevent failure of the HP fuel pump, which could lead to an in-
flight shutdown, damage to the engine, and forced landing or 
accident.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 25 flight hours (FHs) or 6 months after the effective 
date of this AD, whichever occurs earlier, clean and visually 
inspect the splines of the HP fuel pump/metering valve and the 
module M01 drive gear for wear, corrosion, scaling, pitting, and 
chafing.
    (2) Thereafter, reinspect every 100 FHs since-last-inspection.
    (3) If the HP fuel pump/metering valve or the module M01 drive 
gear fails the inspection required by this AD, replace it with a 
part eligible for installation before further flight.
    (4) After the effective date of this AD, do not install any HP 
fuel pump, HP fuel pump drive shaft, module M01 drive gear, or 
module M01 77-tooth gear onto any engine, or install any engine onto 
any helicopter, unless the HP fuel pump/metering valve and the 
module M01 drive gear passed the inspection required by paragraph 
(e) of this AD.

(f) 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.

(g) Related Information

    (1) For more information about this AD, contact Katheryn 
Malatek, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency (EASA) AD 
2014-0059, dated March 10, 2014, and EASA AD 2014-0059R1, dated 
April 15, 2014, for more information. You may examine the MCAIs in 
the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0219-0003.
    (3) Turbomeca S.A. Mandatory Service Bulletin No. 298 73 2818, 
Version F, dated March 5, 2014, which is not incorporated by 
reference in this AD, can be obtained from Turbomeca S.A., using the 
contact information in paragraph (g)(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.

[[Page 48030]]

    (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.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 6, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-19228 Filed 8-14-14; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:46:21.599794+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

1c690db730def2a2b9103a0f0d9f8aa1e2c6a967753a20811864c79105c74bcb

Text SHA-256

902234604187194ed28e4b94f189885e2e25f6ed00da82b17ddc9ec884865070