Airworthiness Directives; Turbomeca S.A. ARRIUS 1A Turboshaft Engines, 53153-53154 [E9-24853]

Download as PDF Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations January 28, 2009; or 328 Support Services Service Bulletin SB–328J–25–235, dated January 28, 2009, as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (Only the odd-numbered pages of these documents contain the issue dates of the documents.) (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Global Support Center, P.O. Box 1252, D–82231 Wessling, Federal Republic of Germany; telephone +49 8153 88111 6666; fax +49 8153 88111 6565; e-mail gsc.op@328support.de; Internet https:// www.328support.de. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 30, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–24448 Filed 10–15–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0348; Directorate Identifier 2008–NE–39–AD; Amendment 39– 16050; AD 2009–21–11] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. ARRIUS 1A Turboshaft Engines CPrice-Sewell on DSKDVH8Z91PROD with RULES AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Cycle life limit value for ARRIUS 1A balancing piston Part Number (P/N) 0 319 20 VerDate Nov<24>2008 15:49 Oct 15, 2009 Jkt 220001 152 0, initially set at 40 000 cycles, has been reduced to 16 000 cycles, following the discovery of a calculation error during a recent review of the ARRIUS 1 engine family files. We are issuing this AD to prevent failure of the balancing piston, which could result in an engine in-flightshutdown and the release of high-energy debris and damage to the helicopter. DATES: This AD becomes effective November 20, 2009. 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. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 17, 2009 (74 FR 17797). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: 53153 received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information The MCAI requires modifying the cyclic life limit value of the balancing piston in the engine log book as specified in Turbomeca Mandatory Service Bulletin 319 72 0811, dated April 30, 2008, and updating the approved operator’s maintenance program. We are requiring removing from service ARRIUS 1A engines containing a balancing piston, P/N 0 319 20 152 0, before the balancing piston meets or exceeds the new, reduced cyclic life limit value of 16,000 cycles-since-new. Costs of Compliance Based on the service information, we estimate that this AD would affect about 33 products of U.S. registry. We also estimate that it would take about 0.5 work-hour per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts would cost about $5,280 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $175,560. Authority for This Rulemaking Cycle life limit value for ARRIUS 1A balancing piston Part Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has been reduced to 16 000 cycles, following the discovery of a calculation error during a recent review of the ARRIUS 1 engine family files. As of the publication date of this Airworthiness Directive, no ARRIUS 1A engines in service are fitted with a balancing piston that has logged more than 16 000 cycles, and the outlook for the consumption of cycles on the ARRIUS 1A fleet indicates that no balancing pistons will exceed this new limit for a few years’ time. Moreover, this new cycle life limit value for the balancing piston has been incorporated since the end of 2007 in ARRIUS 1A Maintenance documentation. Failure to comply with the new life limits provided in the Airworthiness Limitations Section of ARRIUS 1A Maintenance documentation could potentially result in an engine in-flight-shutdown and the release of high energy debris. 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. You may obtain further information by examining the MCAI in the AD docket. Regulatory Findings Comments We gave the public the opportunity to participate in developing this AD. We PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on E:\FR\FM\16OCR1.SGM 16OCR1 53154 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 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); and 3. 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ CPrice-Sewell on DSKDVH8Z91PROD with RULES 2009–21–11 Turbomeca S.A.: Amendment 39–16050. Docket No. FAA–2009–0348; Directorate Identifier 2008–NE–39–AD. Applicability (c) This AD applies to Turbomeca S.A. ARRIUS 1A turboshaft engines with VerDate Nov<24>2008 15:49 Oct 15, 2009 Jkt 220001 14 CFR Part 39 (d) Cycle life limit value for ARRIUS 1A balancing piston Part Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has been reduced to 16 000 cycles, following the discovery of a calculation error during a recent review of the ARRIUS 1 engine family files. We are issuing this AD to prevent failure of the balancing piston, which could result in an engine in-flight-shutdown and the release of high-energy debris and damage to the helicopter. [Docket No. FAA–2009–1369; Directorate Identifier 2003–NE–03–AD; Amendment 39– 16048; AD 2009–21–09] Actions and Compliance (e) Unless already done, for ARRIUS 1A engines with a balancing piston, P/N 0 319 20 152 0, installed, remove the engine from service before the balancing piston accumulates 16,000 cycles-since-new (CSN). Installation Prohibition (f) After the effective date of this AD, don’t return to service any engine that has a balancing piston that has accumulated 16,000 or more CSN. FAA AD Differences (g) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) or service information as follows: (1) This AD requires removing from service, any ARRIUS 1A engine that has a balancing piston, P/N 0 319 20 152 0, with 16,000 CSN installed. (2) We prohibit returning to service any ARRIUS 1A engine that has a balancing piston, P/N 0 319 20 152 0, with 16,000 or more CSN. Related Information ■ Affected Airworthiness Directives (ADs) (b) None. Reason (h) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. PART 39—AIRWORTHINESS DIRECTIVES Effective Date (a) This airworthiness directive (AD) becomes effective November 20, 2009. DEPARTMENT OF TRANSPORTATION Other FAA AD Provisions Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ § 39.13 balancing pistons, part number (P/N) 0 319 20 152 0, installed. These engines are installed on, but not limited to, Eurocopter AS355N helicopters. (i) Refer to MCAI Airworthiness Directive 2008–0133, dated July 17, 2008 for related information. (j) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (k) None. Issued in Burlington, Massachusetts, on October 8, 2009. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–24853 Filed 10–15–09; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 892– 17, Trent 892B–17, and Trent 895–17 turbofan engines with high-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. That AD currently requires removal from service of these HP compressor rotor rear stage 5 and 6 discs and cone shafts before reaching newly reduced life limits. This AD requires removing these parts at new reduced cycle limits. This AD results from Rolls-Royce plc reducing the lives of these parts and changing the life calculating method to use ‘‘Standard Duty Cycles’’ with ‘‘Multiple Flight Profile Monitoring’’ and ‘‘Flight Cycles’’ with ‘‘Heavy Flight Profile Monitoring’’. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation that might lead to uncontained disc failure and damage to the airplane. DATES: This AD becomes effective November 20, 2009. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936. 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. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803, e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by E:\FR\FM\16OCR1.SGM 16OCR1

Agencies

[Federal Register Volume 74, Number 199 (Friday, October 16, 2009)]
[Rules and Regulations]
[Pages 53153-53154]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-24853]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0348; Directorate Identifier 2008-NE-39-AD; 
Amendment 39-16050; AD 2009-21-11]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. ARRIUS 1A Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.

We are issuing this AD to prevent failure of the balancing piston, 
which could result in an engine in-flight-shutdown and the release of 
high-energy debris and damage to the helicopter.

DATES: This AD becomes effective November 20, 2009.

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.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 17, 2009 (74 
FR 17797). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.
    As of the publication date of this Airworthiness Directive, no 
ARRIUS 1A engines in service are fitted with a balancing piston that 
has logged more than 16 000 cycles, and the outlook for the 
consumption of cycles on the ARRIUS 1A fleet indicates that no 
balancing pistons will exceed this new limit for a few years' time.
    Moreover, this new cycle life limit value for the balancing 
piston has been incorporated since the end of 2007 in ARRIUS 1A 
Maintenance documentation.
    Failure to comply with the new life limits provided in the 
Airworthiness Limitations Section of ARRIUS 1A Maintenance 
documentation could potentially result in an engine in-flight-
shutdown and the release of high energy debris.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

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

Differences Between This AD and the MCAI or Service Information

    The MCAI requires modifying the cyclic life limit value of the 
balancing piston in the engine log book as specified in Turbomeca 
Mandatory Service Bulletin 319 72 0811, dated April 30, 2008, and 
updating the approved operator's maintenance program.
    We are requiring removing from service ARRIUS 1A engines containing 
a balancing piston, P/N 0 319 20 152 0, before the balancing piston 
meets or exceeds the new, reduced cyclic life limit value of 16,000 
cycles-since-new.

Costs of Compliance

    Based on the service information, we estimate that this AD would 
affect about 33 products of U.S. registry. We also estimate that it 
would take about 0.5 work-hour per product to comply with this AD. The 
average labor rate is $80 per work-hour. Required parts would cost 
about $5,280 per product. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $175,560.

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

[[Page 53154]]

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); and
    3. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
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 AD:

2009-21-11 Turbomeca S.A.: Amendment 39-16050. Docket No. FAA-2009-
0348; Directorate Identifier 2008-NE-39-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
20, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. ARRIUS 1A turboshaft 
engines with balancing pistons, part number (P/N) 0 319 20 152 0, 
installed. These engines are installed on, but not limited to, 
Eurocopter AS355N helicopters.

Reason

    (d) Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.
    We are issuing this AD to prevent failure of the balancing 
piston, which could result in an engine in-flight-shutdown and the 
release of high-energy debris and damage to the helicopter.

Actions and Compliance

    (e) Unless already done, for ARRIUS 1A engines with a balancing 
piston, P/N 0 319 20 152 0, installed, remove the engine from 
service before the balancing piston accumulates 16,000 cycles-since-
new (CSN).

Installation Prohibition

    (f) After the effective date of this AD, don't return to service 
any engine that has a balancing piston that has accumulated 16,000 
or more CSN.

FAA AD Differences

    (g) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) or service information as follows:
    (1) This AD requires removing from service, any ARRIUS 1A engine 
that has a balancing piston, P/N 0 319 20 152 0, with 16,000 CSN 
installed.
    (2) We prohibit returning to service any ARRIUS 1A engine that 
has a balancing piston, P/N 0 319 20 152 0, with 16,000 or more CSN.

Other FAA AD Provisions

    (h) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (i) Refer to MCAI Airworthiness Directive 2008-0133, dated July 
17, 2008 for related information.
    (j) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (k) None.

    Issued in Burlington, Massachusetts, on October 8, 2009.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-24853 Filed 10-15-09; 8:45 am]
BILLING CODE 4910-13-P