Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 71483-71484 [2012-28839]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 77, Number 232 (Monday, December 3, 2012)]
[Rules and Regulations]
[Pages 71483-71484]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28839]



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Federal Register / Vol. 77, No. 232 / Monday, December 3, 2012 / 
Rules and Regulations

[[Page 71483]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0520; Directorate Identifier 2002-NE-43-AD; 
Amendment 39-17273; AD 2012-24-03]
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 superseding an existing airworthiness directive (AD) 
for all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 
1E, 1E2, 1K, 1K1, 1S, and 1S1 turboshaft engines. That AD currently 
requires initial and repetitive visual inspections for erosion caused 
by dust ingestion and, if necessary, cleaning of the gas generator 
(module M03). This new AD requires determining the engine history; 
performing a one-time visual inspection of the axial compressor for 
erosion; performing initial and repetitive cleaning of the gas 
generator hollow shaft; and replacing the rear bearing if the amount of 
dust collected during cleaning exceeds 8 grams. This AD also includes 
an optional terminating action. This AD was prompted by in-service 
experience which has shown that dust inside the gas generator hollow 
shaft may be found when the axial compressor wheel has less erosion 
than initially assessed. We are issuing this AD to prevent an unbalance 
of the gas generator rotating assembly, which may lead to gas generator 
rear bearing failure, and uncommanded engine shutdown.

DATES: This AD is effective January 7, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 7, 
2013.

ADDRESSES: For service information identified in this AD, contact 
Turbomeca S.A., 40220 Tarnos, France; phone: 33 05 59 74 40 00; telex: 
570 042; fax: 33 05 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 https://www.regulations.gov; 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 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.

FOR FURTHER INFORMATION CONTACT: Rose Len, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7772; fax: 
781-238-7199; email: rose.len@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2003-12-14, Amendment 39-13199 (68 FR 36900, 
June 20, 2003). That AD applies to the specified products. The NPRM 
published in the Federal Register on July 25, 2012 (77 FR 43550). That 
NPRM proposed to require determining the engine history; performing a 
one-time visual inspection of the axial compressor for erosion; 
performing initial and repetitive cleaning of the gas generator hollow 
shaft; and replacing the rear bearing if the amount of dust collected 
during cleaning exceeds 8 grams. That NPRM also included an optional 
terminating action. That NPRM also removed Turbomeca S.A. Arriel 1E and 
1K turboshaft engines from the applicability section of the AD. The 1E 
engine is no longer in service. The 1K engine is not an FAA validated 
engine.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Request To Ease Requirements When Barrier Filters Used Continuously

    Charles E. Greenberg requested that the FAA consider modifying the 
AD to accommodate operators of helicopters with barrier filter 
installations for the engine intakes. If operator records can show that 
specific serial number engines have always operated with filtered air, 
the requirement for cleaning the gas generator hollow shaft should be 
superseded by a requirement to maintain records of operation with 
barrier filter protection. The commenter stated that no dirt can be 
ingested by an engine downstream of the filter, as long as the barrier 
filter has never gone into bypass mode.
    We disagree. The FAA cannot anticipate all of the available barrier 
filter designs installed on helicopter models. Each barrier filter 
design and helicopter combination would require its own assessment of 
the filter's use and effectiveness. We did not change the AD.
    However, the substantiated continuous use of a barrier filter may 
be proposed as an alternative method of compliance (AMOC) to this AD, 
using the standard AMOC request procedure.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    We estimate that this AD will affect about 1,421 engines installed 
on helicopters of U.S. registry. We also estimate that it will take 
about 24 work-hours per engine to inspect and clean the gas generator 
module. The average labor rate is $85 per work-hour. A replacement gas 
generator rear bearing would cost about $4,128 per engine and take 
about 8 work-hours to replace. Based on these figures, we estimate the 
cost of the AD on U.S. operators to be $2,898,840.

[[Page 71484]]

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 have 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 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, 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 removing airworthiness directive (AD) 
2003-12-14, Amendment 39-13199 (68 FR 36900, June 20, 2003), and adding 
the following new AD:

2012-24-03 Turbomeca S.A.: Amendment 39-17273; Docket No. FAA-2012-
0520; Directorate Identifier 2002-NE-43-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective January 7, 2013.

(b) Affected ADs

    This AD supersedes AD 2003-12-14, Amendment 39-13199 (68 FR 
36900, June 20, 2003).

(c) Applicability

    This AD applies to all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 1B, 
1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines that 
have not incorporated Turbomeca S.A. Modification TU360.

(d) Unsafe Condition

    This AD was prompted by in-service experience showing that dust 
inside the gas generator hollow shaft may be found when the axial 
compressor wheel has less erosion than initially assessed. We are 
issuing this AD to prevent an unbalance of the gas generator 
rotating assembly, which may lead to deterioration of the gas 
generator rear bearing and uncommanded engine shutdown.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 50 engine hours after the effective date of this AD, 
determine the engine history and perform the maintenance actions at 
the specified schedules. Use paragraphs 1.A. and 2.A. through 2.C. 
of Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. A292 72 
0230, Version C, dated February 29, 2012 to perform the maintenance 
actions and to establish the cleaning schedule.
    (2) If during any of the cleanings, the dust weight collected 
inside the gas generator hollow shaft is more than 8 grams, replace 
the gas generator rear bearing before further flight.
    (3) After the effective date of this AD, if there are any 
changes in accordance with paragraph 1.A.(1)(a)1.3 of Turbomeca S.A. 
Alert MSB No. A292 72 0230, Version C, dated February 29, 2012, 
within 50 engine hours time-in-service after such a change, 
accomplish the actions as specified in paragraphs (e)(1) and (e)(2) 
of this AD.
    (4) After the effective date of this AD, do not install any gas 
generator (module M03) on an engine unless it is in compliance with 
this AD.
    (5) After the effective date of this AD, do not install any gas 
generator rear bearing that has operated on an engine with a hollow 
shaft that has been found to have a dust weight more than 8 grams.

(f) Optional Terminating Action

    As optional terminating action to the repetitive actions in this 
AD, modify the engine by incorporating Turbomeca S.A. Modification 
TU360.

(g) Alternative Methods of Compliance (AMOCs)

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

(h) Related Information

    (1) For more information about this AD, contact Rose Len, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7772; fax: 781-238-7199; email: 
rose.len@faa.gov.
    (2) Refer to European Aviation Safety Agency AD 2012-0071, dated 
April 26, 2012, and Turbomeca S.A. Alert MSB No. A292 72 0230, 
Version C, dated February 29, 2012, for related information.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Turbomeca S.A. Alert Mandatory Service Bulletin No. A292 72 
0230, Version C, dated February 29, 2012.
    (ii) Reserved.
    (3) For Turbomeca S.A. service information identified in this 
AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 05 59 74 
40 00; telex: 570 042; fax: 33 05 59 74 45 15.
    (4) You may view this service information at 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.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 20, 2012.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-28839 Filed 11-30-12; 8:45 am]
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