Airworthiness Directives; Turboméca ARRIEL 1B, 1D, 1D1, 2B, and 2B1 Turboshaft Engines, 68194-68196 [E9-30511]

Download as PDF 68194 Federal Register / Vol. 74, No. 245 / Wednesday, December 23, 2009 / Proposed Rules Federal Aviation Administration • 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. ´ Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for the service information identified in this proposed AD. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2009–0302; Directorate Identifier 2009–NE–09–AD] 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 regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (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: Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117, fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238– 7199, for more information about this AD. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–30508 Filed 12–22–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 ´ Airworthiness Directives; Turbomeca ARRIEL 1B, 1D, 1D1, 2B, and 2B1 Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to revise an existing airworthiness directive (AD) for the products listed above. This proposed 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: cprice-sewell on DSKHWCL6B1PROD with PROPOSALS-1 During production of Arriel 1 and Arriel 2 Power Turbine (PT) wheels, geometric nonconformances on blade fir tree roots have ´ been detected by Turbomeca. Potentially non-conforming PT blades have been traced as having been installed on Module M04 (PT) listed in Mandatory Service Bulletin (MSB) A292 72 0827 for Arriel 1 engines and A292 72 2833 for Arriel 2 engines. The geometric non-conformities of the blades may potentially lead to a reduction in the fatigue resistance of PT blades to a lower level than their authorized in service use limit. This reduction of fatigue resistance can potentially result in blade release, which could cause an uncommanded in-flight shutdown. We are proposing this AD to prevent release of PT blades, which could result in an uncommanded in-flight shutdown and emergency autorotation landing. DATES: We must receive comments on this proposed AD by January 22, 2010. 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. VerDate Nov<24>2008 13:33 Dec 22, 2009 Jkt 220001 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–2009–0302; Directorate Identifier 2009–NE–09–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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Discussion On April 6, 2009, the FAA issued AD 2009–08–08, Amendment 39–15881 (74 FR 17075, April 14, 2009). That AD requires: • For engines with an affected Module M04 (PT module) which has accumulated 1,000 total PT cycles or more on the effective date of that AD, remove the PT blades from service before further flight. • For engines with an affected Module M04 (PT module) which has accumulated fewer than 1,000 total PT cycles on the effective date of that AD, remove the PT blades from service before accumulating 1,000 total PT cycles. • After the effective date of that AD, do not install any PT blades removed as specified in paragraph (e)(1) or (e)(2) of that AD, into any engine. Actions Since AD 2009–08–08 Was Issued Since that AD was issued, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0112R1, dated July 30, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Since issuance of initial version of AD 2009–0112 additional information is available: —The list of Modules M04 concerned by the restriction of the cycle use limit of these PT blades has been updated again: The serial numbers of Modules M04 which have been retrofitted are crossed out. However no new affected Modules M04 have been identified. See figure 1 of the referenced ´ Turbomeca MSB. —Additional testing and analysis had been ´ carried out by Turbomeca which allows increasing the cyclic use limit of these PT blades to 5 000 flight cycles. Therefore this AD revises AD 2009–0112 and requires establishing the cyclic use limit of these PT blades to 5 000 flight cycles. For PT blades having reached a number of flight cycles superior or equal to 5 000, removal of Module M04, or PT wheel assembly, or PT blades is required prior to next flight. You may obtain further information by examining the MCAI in the AD docket. E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 74, No. 245 / Wednesday, December 23, 2009 / Proposed Rules Relevant Service Information ´ Turbomeca has issued Alert MSB No. A292 72 0827, Version C, dated July 15, 2009, for Arriel 1 series turboshaft engines, and issued Alert MSB No. A292 72 2833, Version C, dated July 15, 2009, for Arriel 2 series turboshaft engines. The power turbine modules M04 having the affected PT blades are listed by serial number (S/N) in Figure 1 of these MSBs, as applicable. We have incorporated by reference these MSBs to identify the affected parts. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a separate paragraph of the AD. These requirements take precedence over the actions copied from the MCAI. cprice-sewell on DSKHWCL6B1PROD with PROPOSALS-1 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 France, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing 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 AD requires removing the affected PT blades from service before exceeding 5,000 flight cycles. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 10 products of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $43,000 per product. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $436,400. 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. VerDate Nov<24>2008 13:33 Dec 22, 2009 Jkt 220001 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); 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 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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 removing amendment 39–15881, and adding the following new AD: ´ Turbomeca S.A.: Docket No. FAA–2009– 0302; Directorate Identifier 2009–NE– 09–AD. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 68195 Comments Due Date (a) We must receive comments by January 22, 2010. Affected Airworthiness Directives (ADs) (b) This AD revises AD 2009–08–08, Amendment 39–15881. Applicability (c) This AD applies to: ´ (1) Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines with the power turbine (PT) modules M04 installed, as listed by ´ serial number (S/N) in Figure 1 of Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 72 0827, Version C, dated July 15, 2009; and ´ (2) Turbomeca Arriel 2B, and 2B1 turboshaft engines with the power turbine modules M04 installed, as listed by S/N in ´ Figure 1 of Turbomeca Alert MSB No. A292 72 2833, Version C, dated July 15, 2009. (3) These engines are installed on, but not limited to, Eurocopter AS 350 B, AS 350 BA, AS 350 B1, AS 350 B2, AS 350 B3, and EC 130 B4 helicopters. Reason (d) European Aviation Safety Agency (EASA) AD No. 2009–0112R1, dated July 30, 2009, states: Since issuance of initial version of AD 2009–0112 additional information is available: —The list of Modules M04 concerned by the restriction of the cycle use limit of these PT blades has been updated again: The serial numbers of Modules M04 which have been retrofitted are crossed out. However no new affected Modules M04 have been identified. See figure 1 of the referenced ´ Turbomeca MSB. —Additional testing and analysis had been ´ carried out by Turbomeca which allows increasing the cyclic use limit of these PT blades to 5 000 flight cycles. We are issuing this AD to prevent release of PT blades, which could result in an uncommanded in-flight shutdown and emergency autorotation landing. Actions and Compliance (e) Unless already done, do the following actions. (1) For engines with an affected Module M04 (PT module), which has accumulated 5,000 total PT cycles or more on the effective date of this AD, remove the PT blades from service before further flight. (2) For engines with an affected Module M04, which has accumulated fewer than 5,000 total PT cycles on the effective date of this AD, remove the PT blades from service before accumulating 5,000 total PT cycles. (3) After the effective date of this AD, do not install any PT blades removed as specified in paragraph (e)(1) or (e)(2) of this AD, into any engine. FAA AD Differences (f) Although the compliance section of EASA AD No. 2009–0112R1, dated July 30, 2009, states to replace the Module M04, or PT wheel assembly, or PT blades, this AD states to remove the PT blades from service. (g) Although EASA AD No. 2009–0112R1, dated July 30, 2009, applies to the Arriel E:\FR\FM\23DEP1.SGM 23DEP1 68196 Federal Register / Vol. 74, No. 245 / Wednesday, December 23, 2009 / Proposed Rules 2B1A engine, this AD does not apply to that model because it has no U.S. type certificate. Alternative Methods of Compliance (AMOCs) (h) 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 EASA Airworthiness Directive 2009–0112R1, dated July 30, 2009; ´ and Turbomeca Mandatory Service Bulletins (MSBs) A292 72 0827, Version C, dated July 15, 2009; and A292 72 2833, Version C, dated July 15, 2009; for related information. (j) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117, fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on December 17, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–30511 Filed 12–22–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0803; Directorate Identifier 2009–NE–34–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Auxiliary Power Units Models GTCP36–150(R) and GTCP36– 150(RR) cprice-sewell on DSKHWCL6B1PROD with PROPOSALS-1 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for Honeywell International Inc. auxiliary power units (APU) models GTCP36– 150(R) and GTCP36–150(RR). This proposed AD would require inspecting the fuel control unit (FCU) differential pressure (Delta P) sleeve bore for erosion, replacing the FCU if it fails the inspection, and installing a fuel deflector on the Delta P sleeve of the FCU. This proposed AD results from eight reports of fuel leakage from the fuel control unit. We are proposing this AD to prevent fuel leakage in the APU compartment, which could lead to ignition of fuel vapor, creating a fire and explosion hazard resulting in injury, VerDate Nov<24>2008 13:33 Dec 22, 2009 Jkt 220001 and damage to the APU and the airplane. DATES: We must receive any comments on this proposed AD by February 22, 2010. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • 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 FURTHER INFORMATION CONTACT: Roger Pesuit, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: roger.pesuit@faa.gov; telephone (562) 627–5251, fax (562) 627–5210. Contact Honeywell International Inc., 111 S. 34th Street, Phoenix, Arizona 85034–2802; Web site: http:// portal.honeywell.com/wps/portal/aero; telephone No. (800) 601–3099; international telephone No. (601) 365– 3099; for a copy of the service information identified in this proposed AD. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2009–0803; Directorate Identifier 2009– NE–34–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). 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 regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (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. Discussion Over a five-year period, we received eight reports of fuel leakage from the fuel control unit housing on APUs, models GTCP36–150(R) and GTCP36– 150(RR). Investigation has found that when the Delta P sleeve is incorrectly positioned inside the fuel control unit housing, a high-velocity stream of fuel can hit the housing. This high-velocity stream can cause cavitation, which is a rapid formation and collapse of vapor pockets in very low-pressure regions of the fuel stream exiting the Delta P sleeve. This condition accelerates erosion of the fuel control housing, eventually causing it to leak. Honeywell International Inc. conducted focused inspections on 228 fuel control unit housings, and found that 97 of them had evidence of erosion. This condition, if not corrected, could result in fuel leakage in the APU compartment, which could lead to ignition of fuel vapor, creating a fire and explosion hazard resulting in injury, and damage to the APU and the airplane. Relevant Service Information We have reviewed and approved the technical contents of Honeywell International Inc. Service Bulletin No. 3882840–49–7975, Revision 1, dated April 10, 2009, that describes procedures for inspecting the FCU Delta P sleeve bore for erosion, replacing the FCU if it fails the inspection, and installing a fuel deflector on the Delta P sleeve of the FCU. Installing this fuel deflector will prevent erosion and leakage of the fuel control unit housing. E:\FR\FM\23DEP1.SGM 23DEP1

Agencies

[Federal Register Volume 74, Number 245 (Wednesday, December 23, 2009)]
[Proposed Rules]
[Pages 68194-68196]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-30511]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0302; Directorate Identifier 2009-NE-09-AD]
RIN 2120-AA64


Airworthiness Directives; Turbom[eacute]ca ARRIEL 1B, 1D, 1D1, 
2B, and 2B1 Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to revise an existing airworthiness directive (AD) 
for the products listed above. This proposed 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:

    During production of Arriel 1 and Arriel 2 Power Turbine (PT) 
wheels, geometric non-conformances on blade fir tree roots have been 
detected by Turbom[eacute]ca. Potentially non-conforming PT blades 
have been traced as having been installed on Module M04 (PT) listed 
in Mandatory Service Bulletin (MSB) A292 72 0827 for Arriel 1 
engines and A292 72 2833 for Arriel 2 engines.
    The geometric non-conformities of the blades may potentially 
lead to a reduction in the fatigue resistance of PT blades to a 
lower level than their authorized in service use limit. This 
reduction of fatigue resistance can potentially result in blade 
release, which could cause an uncommanded in-flight shutdown.

    We are proposing this AD to prevent release of PT blades, which 
could result in an uncommanded in-flight shutdown and emergency 
autorotation landing.

DATES: We must receive comments on this proposed AD by January 22, 
2010.

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.
    Contact Turbom[eacute]ca, 40220 Tarnos, France; telephone 33 05 59 
74 40 00, fax 33 05 59 74 45 15, for the service information identified 
in this proposed AD.

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 regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (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: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199.

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-2009-0302; 
Directorate Identifier 2009-NE-09-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 review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    On April 6, 2009, the FAA issued AD 2009-08-08, Amendment 39-15881 
(74 FR 17075, April 14, 2009). That AD requires:
     For engines with an affected Module M04 (PT module) which 
has accumulated 1,000 total PT cycles or more on the effective date of 
that AD, remove the PT blades from service before further flight.
     For engines with an affected Module M04 (PT module) which 
has accumulated fewer than 1,000 total PT cycles on the effective date 
of that AD, remove the PT blades from service before accumulating 1,000 
total PT cycles.
     After the effective date of that AD, do not install any PT 
blades removed as specified in paragraph (e)(1) or (e)(2) of that AD, 
into any engine.

Actions Since AD 2009-08-08 Was Issued

    Since that AD was issued, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2009-
0112R1, dated July 30, 2009 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    Since issuance of initial version of AD 2009-0112 additional 
information is available:

--The list of Modules M04 concerned by the restriction of the cycle 
use limit of these PT blades has been updated again: The serial 
numbers of Modules M04 which have been retrofitted are crossed out. 
However no new affected Modules M04 have been identified. See figure 
1 of the referenced Turbom[eacute]ca MSB.
--Additional testing and analysis had been carried out by 
Turbom[eacute]ca which allows increasing the cyclic use limit of 
these PT blades to 5 000 flight cycles.

Therefore this AD revises AD 2009-0112 and requires establishing the 
cyclic use limit of these PT blades to 5 000 flight cycles.
    For PT blades having reached a number of flight cycles superior 
or equal to 5 000, removal of Module M04, or PT wheel assembly, or 
PT blades is required prior to next flight.

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

[[Page 68195]]

Relevant Service Information

    Turbom[eacute]ca has issued Alert MSB No. A292 72 0827, Version C, 
dated July 15, 2009, for Arriel 1 series turboshaft engines, and issued 
Alert MSB No. A292 72 2833, Version C, dated July 15, 2009, for Arriel 
2 series turboshaft engines. The power turbine modules M04 having the 
affected PT blades are listed by serial number (S/N) in Figure 1 of 
these MSBs, as applicable. We have incorporated by reference these MSBs 
to identify the affected parts.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we required different actions 
in this AD from those in the MCAI in order to follow FAA policies. Any 
such differences are described in a separate paragraph of the AD. These 
requirements take precedence over the actions copied from 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 France, they have notified us of the unsafe 
condition described in the MCAI and service information referenced 
above. We are issuing 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 AD requires removing the affected PT blades from service before 
exceeding 5,000 flight cycles.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 10 products of U.S. registry. We also estimate that 
it would take about 8 work-hours per product to comply with this 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $43,000 per product. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be $436,400.

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); 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 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

    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]

    2. The FAA amends Sec.  39.13 removing amendment 39-15881, and 
adding the following new AD:

Turbom[eacute]ca S.A.: Docket No. FAA-2009-0302; Directorate 
Identifier 2009-NE-09-AD.

Comments Due Date

    (a) We must receive comments by January 22, 2010.

Affected Airworthiness Directives (ADs)

    (b) This AD revises AD 2009-08-08, Amendment 39-15881.

Applicability

    (c) This AD applies to:
    (1) Turbom[eacute]ca Arriel 1B, 1D, and 1D1 turboshaft engines 
with the power turbine (PT) modules M04 installed, as listed by 
serial number (S/N) in Figure 1 of Turbom[eacute]ca Alert Mandatory 
Service Bulletin (MSB) No. A292 72 0827, Version C, dated July 15, 
2009; and
    (2) Turbom[eacute]ca Arriel 2B, and 2B1 turboshaft engines with 
the power turbine modules M04 installed, as listed by S/N in Figure 
1 of Turbom[eacute]ca Alert MSB No. A292 72 2833, Version C, dated 
July 15, 2009.
    (3) These engines are installed on, but not limited to, 
Eurocopter AS 350 B, AS 350 BA, AS 350 B1, AS 350 B2, AS 350 B3, and 
EC 130 B4 helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2009-0112R1, 
dated July 30, 2009, states:
    Since issuance of initial version of AD 2009-0112 additional 
information is available:

--The list of Modules M04 concerned by the restriction of the cycle 
use limit of these PT blades has been updated again: The serial 
numbers of Modules M04 which have been retrofitted are crossed out. 
However no new affected Modules M04 have been identified. See figure 
1 of the referenced Turbom[eacute]ca MSB.
--Additional testing and analysis had been carried out by 
Turbom[eacute]ca which allows increasing the cyclic use limit of 
these PT blades to 5 000 flight cycles.

We are issuing this AD to prevent release of PT blades, which could 
result in an uncommanded in-flight shutdown and emergency 
autorotation landing.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) For engines with an affected Module M04 (PT module), which 
has accumulated 5,000 total PT cycles or more on the effective date 
of this AD, remove the PT blades from service before further flight.
    (2) For engines with an affected Module M04, which has 
accumulated fewer than 5,000 total PT cycles on the effective date 
of this AD, remove the PT blades from service before accumulating 
5,000 total PT cycles.
    (3) After the effective date of this AD, do not install any PT 
blades removed as specified in paragraph (e)(1) or (e)(2) of this 
AD, into any engine.

FAA AD Differences

    (f) Although the compliance section of EASA AD No. 2009-0112R1, 
dated July 30, 2009, states to replace the Module M04, or PT wheel 
assembly, or PT blades, this AD states to remove the PT blades from 
service.
    (g) Although EASA AD No. 2009-0112R1, dated July 30, 2009, 
applies to the Arriel

[[Page 68196]]

2B1A engine, this AD does not apply to that model because it has no 
U.S. type certificate.

Alternative Methods of Compliance (AMOCs)

    (h) 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 EASA Airworthiness Directive 2009-0112R1, 
dated July 30, 2009; and Turbom[eacute]ca Mandatory Service 
Bulletins (MSBs) A292 72 0827, Version C, dated July 15, 2009; and 
A292 72 2833, Version C, dated July 15, 2009; for related 
information.
    (j) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on December 17, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-30511 Filed 12-22-09; 8:45 am]
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