Airworthiness Directives; Turbomeca S.A. ARRIUS 2F Turboshaft Engines, 16809-16811 [E9-8310]

Download as PDF Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules Removing LPCR Discs from Service (f) For engines with a second and third stage LPCR disc that has a serial number (SN) listed in Table 5 of Honeywell International Inc. Alert Service Bulletins (ASBs) TFE731–72– A3748, dated August 21, 2008, or TFE731–72–A3749, dated August 21, 2008, remove the second and third stage LPCR disc from service within 100 cycles-in-service (CIS) after the effective date of this AD. (g) For engines with a second and third stage LPCR disc that has an SN listed in Table 6 of Honeywell International Inc. ASBs TFE731–72– A3748, dated August 21, 2008, or TFE731–72–A3749, dated August 21, 2008, do the earlier of the following: (1) Remove the second and third stage LPCR disc from service within 2,000 CIS after the effective date of this AD, or (2) Remove the second and third stage LPCR disc from service the next time the intermediate case is removed from the LPC case. Installation Prohibition (h) After the effective date of this AD, don’t install any second and third stage LPCR disc removed as required in paragraphs (f) or (g) of this AD. Alternative Methods of Compliance (i) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (j) Contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; email: joseph.costa@faa.gov; telephone: (562) 627–5246; fax: (562) 627–5210, for more information about this AD. (k) Honeywell International Inc. ASBs TFE731–72–A3748, dated August 21, 2008, and TFE731–72–A3749, dated August 21, 2008, pertain to the subject of this AD. Contact Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101–201, P.O. Box 52170, Phoenix, AZ 85072–2170, telephone: Global Customer Care toll free (800) 601–3099; International callers (602) 365–3099, for a copy of this service information. VerDate Nov<24>2008 18:52 Apr 10, 2009 Jkt 217001 Issued in Burlington, Massachusetts, on April 6, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–8309 Filed 4–10–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0330; Directorate Identifier 2008–NE–43–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. ARRIUS 2F Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new 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: Rubs between the pipe and the bulkhead may lead to premature wearing and finally rupture of the P3 air pipe. The loss of P3 air pressure would then force the fuel control system to idle which could have a detrimental effect in critical phases of flight. We are proposing this AD to prevent an uncommanded power loss, which could result in an emergency autorotation landing or accident. DATES: We must receive comments on this proposed AD by May 13, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 16809 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: 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: 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–2009–0330; Directorate Identifier 2008–NE–43–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 https:// 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008–0134R1, dated February 17, 2009, (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: E:\FR\FM\13APP1.SGM 13APP1 16810 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules On several ARRIUS 2F engines, the clearance between the P3 air pipe P/N 0319719180 and the rear right bulkhead P/N 0319998240 has been found to be too small. Investigations have shown that both P3 air pipe and rear right bulkhead were compliant to the design. The Turbomeca Engineering Department concluded that the tolerance of assembly established during the design could result in some rubbing between parts. Rubs between the pipe and the bulkhead may lead to premature wearing and finally rupture of the P3 air pipe. The loss of P3 air pressure would then force the fuel control system to idle which could have a detrimental effect in critical phases of flight. For the reason stated above, this Airworthiness Directive (AD) requires the inspection of the P3 air pipe (first section) and RH rear half-wall and, in case it is found damaged or non-compliant (idem), the replacement or readjustment of parts. 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 Relevant Service Information Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319 75 4810, dated May 14, 2008. The actions described in this service information are intended to correct the unsafe condition identified in 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 proposing this AD because we evaluated all information provided by France and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 94 engines installed on helicopters of U.S. registry. We also estimate that it would take about 1 work-hour per engine to comply with this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $705 per engine. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $73,790. Our cost estimate is exclusive of possible warranty coverage. 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 VerDate Nov<24>2008 18:52 Apr 10, 2009 Jkt 217001 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 by adding the following new AD: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Turbomeca S.A.: Docket No. FAA–2009– 0330; Directorate Identifier 2008–NE– 43–AD. Comments Due Date (a) We must receive comments by May 13, 2009. Affected Airworthiness Directives (ADs) (b) None. Applicability (c) This AD applies to Turbomeca S.A. ARRIUS 2F turboshaft engines with P3 air pipe, part number 0319719180, installed. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Reason (d) Rubs between the pipe and the bulkhead may lead to premature wearing and finally rupture of the P3 air pipe. The loss of P3 air pressure would then force the fuel control system to idle which could have a detrimental effect in critical phases of flight. We are issuing this AD to prevent an uncommanded power loss, which could result in an emergency autorotation landing or accident. Actions and Compliance (e) Unless already done, do the following actions within 100 operating hours after the effective date of this AD. Use paragraphs 2.B.(1) through 2.C.(2) of Turbomeca Mandatory Service Bulletin No. 319 75 4810, dated May 14, 2008. (1) Visually inspect P3 air pipe (first section) and RH rear half-wall. (2) Inspect play between P3 air pipe (first section) and RH rear half-wall. (3) Replace P3 air pipe (first section) if any damage is found. (4) Readjust the first section of the P3 air pipe if the inspected clearance is found to be not compliant. (5) If the play after readjusting the first section of the P3 air pipe is still less than 0.5 mm, repeat paragraphs (e)(1) through (e)(4) of this AD within intervals of 100 hours timesince-last inspection. (6) Replace RH rear half-wall if any damage is found. FAA AD Differences (f) None. Other FAA AD Provisions (g) 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 (h) Refer to MCAI EASA Airworthiness Directive 2008–0134R1, dated February 17, 2009, and Turbomeca S.A. Mandatory Service Bulletin No. 319 75 4810, dated May 14, 2008, for related information. Contact Turbomeca, 40220 Tarnos, France; telephone 33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5 59 74 45 15, for a copy of this service information. (i) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New E:\FR\FM\13APP1.SGM 13APP1 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules 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. Issued in Burlington, Massachusetts, on April 6, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–8310 Filed 4–10–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: Roger Pesuit, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712; e-mail: roger.pesuit@faa.gov; telephone (562) 627–5251, fax (562) 627–5210. Contact Hamilton Sundstrand Technical Publications, One Hamilton Road, Mail Stop: 1A–3–Z63, Windsor Locks, CT 06096–1010; telephone (860) 654–3575, for a copy of the service information identified in this proposed AD. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 Comments Invited [Docket No. FAA–2009–0247; Directorate Identifier 2009–NE–07–AD] 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– 2009–0247; Directorate Identifier 2009– NE–07–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 https:// 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). RIN 2120–AA64 Airworthiness Directives; Hamilton Sundstrand Power Systems T–62T– 46C12 Auxiliary Power Units AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for Hamilton Sundstrand Power Systems T–62T–46C12 auxiliary power units (APUs). This proposed AD would require upgrading the software in the APU full-authority digital controller (FADEC), from software version 02.01.000 to version 03.00.000. This proposed AD results from two reports of APU compartment explosions due to over-fueling of the APU at low rpm during the start sequence. We are proposing this AD to prevent overfueling of the APU during the start sequence, which could lead to fuel explosions, injury, and damage to the APU and the airplane. DATES: We must receive any comments on this proposed AD by June 12, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://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. VerDate Nov<24>2008 18:52 Apr 10, 2009 Jkt 217001 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 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. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 16811 Discussion We received two reports of APU compartment explosions of Hamilton Sundstrand Power Systems T–62T– 46C12 APUs, related to attempted start of the APU. In both events, the APU compartment was damaged, and the compartment doors were blown off the airplane. The APUs are ground operational only, and the airplanes were parked at the time of explosion. Investigation has revealed that the APU could receive an excessively rich fuel mixture at low rpm during the start sequence, due to the APU FADEC version 02.01.000 software, that can allow over-fueling of the APU during starting. This condition, if not corrected, could result in over-fueling of the APU during the start sequence, which could lead to fuel explosion, injury, and damage to the APU and the airplane. Relevant Service Information We have reviewed and approved the technical contents of Hamilton Sundstrand Power Systems Service Bulletin No. 4503067–49–12, Revision 1, dated December 23, 2008, that describes procedures for upgrading the APU FADEC software to version 03.00.000. This upgrade eliminates the potential for over-fueling the APU during the start sequence. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would require upgrading the APU FADEC software to version 03.00.000. The proposed AD would require you to use the service information described previously to perform these actions. Costs of Compliance We estimate that this proposed AD would affect 59 Hamilton Sundstrand Power Systems T–62T–46C12 APUs installed on airplanes of U.S. registry. We also estimate that it would take about three work-hours per APU to perform the proposed actions, and that the average labor rate is $80 per workhour. There is no required part cost. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $14,160. 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, E:\FR\FM\13APP1.SGM 13APP1

Agencies

[Federal Register Volume 74, Number 69 (Monday, April 13, 2009)]
[Proposed Rules]
[Pages 16809-16811]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8310]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0330; Directorate Identifier 2008-NE-43-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. ARRIUS 2F Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new 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: Rubs between the pipe and the bulkhead may lead to 
premature wearing and finally rupture of the P3 air pipe. The loss of 
P3 air pressure would then force the fuel control system to idle which 
could have a detrimental effect in critical phases of flight. We are 
proposing this AD to prevent an uncommanded power loss, which could 
result in an emergency autorotation landing or accident.

DATES: We must receive comments on this proposed AD by May 13, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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.

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 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: 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:

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-2009-0330; 
Directorate Identifier 2008-NE-43-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 https://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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2008-0134R1, dated February 17, 2009, (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:


[[Page 16810]]


    On several ARRIUS 2F engines, the clearance between the P3 air 
pipe P/N 0319719180 and the rear right bulkhead P/N 0319998240 has 
been found to be too small.
    Investigations have shown that both P3 air pipe and rear right 
bulkhead were compliant to the design. The Turbomeca Engineering 
Department concluded that the tolerance of assembly established 
during the design could result in some rubbing between parts.
    Rubs between the pipe and the bulkhead may lead to premature 
wearing and finally rupture of the P3 air pipe. The loss of P3 air 
pressure would then force the fuel control system to idle which 
could have a detrimental effect in critical phases of flight.
    For the reason stated above, this Airworthiness Directive (AD) 
requires the inspection of the P3 air pipe (first section) and RH 
rear half-wall and, in case it is found damaged or non-compliant 
(idem), the replacement or readjustment of parts.

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

Relevant Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319 
75 4810, dated May 14, 2008. The actions described in this service 
information are intended to correct the unsafe condition identified in 
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 proposing this AD because we evaluated all information 
provided by France and determined the unsafe condition exists and is 
likely to exist or develop on other products of the same type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 94 engines installed on helicopters of U.S. 
registry. We also estimate that it would take about 1 work-hour per 
engine to comply with this proposed AD. The average labor rate is $80 
per work-hour. Required parts would cost about $705 per engine. Based 
on these figures, we estimate the cost of the proposed AD on U.S. 
operators to be $73,790. Our cost estimate is exclusive of possible 
warranty coverage.

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 by adding the following new AD:

Turbomeca S.A.: Docket No. FAA-2009-0330; Directorate Identifier 
2008-NE-43-AD.

Comments Due Date

    (a) We must receive comments by May 13, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. ARRIUS 2F turboshaft 
engines with P3 air pipe, part number 0319719180, installed. These 
engines are installed on, but not limited to, Eurocopter EC120B 
helicopters.

Reason

    (d) Rubs between the pipe and the bulkhead may lead to premature 
wearing and finally rupture of the P3 air pipe. The loss of P3 air 
pressure would then force the fuel control system to idle which 
could have a detrimental effect in critical phases of flight. We are 
issuing this AD to prevent an uncommanded power loss, which could 
result in an emergency autorotation landing or accident.

Actions and Compliance

    (e) Unless already done, do the following actions within 100 
operating hours after the effective date of this AD. Use paragraphs 
2.B.(1) through 2.C.(2) of Turbomeca Mandatory Service Bulletin No. 
319 75 4810, dated May 14, 2008.
    (1) Visually inspect P3 air pipe (first section) and RH rear 
half-wall.
    (2) Inspect play between P3 air pipe (first section) and RH rear 
half-wall.
    (3) Replace P3 air pipe (first section) if any damage is found.
    (4) Readjust the first section of the P3 air pipe if the 
inspected clearance is found to be not compliant.
    (5) If the play after readjusting the first section of the P3 
air pipe is still less than 0.5 mm, repeat paragraphs (e)(1) through 
(e)(4) of this AD within intervals of 100 hours time-since-last 
inspection.
    (6) Replace RH rear half-wall if any damage is found.

FAA AD Differences

    (f) None.

Other FAA AD Provisions

    (g) 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

    (h) Refer to MCAI EASA Airworthiness Directive 2008-0134R1, 
dated February 17, 2009, and Turbomeca S.A. Mandatory Service 
Bulletin No. 319 75 4810, dated May 14, 2008, for related 
information. Contact Turbomeca, 40220 Tarnos, France; telephone 33 
(0)5 59 74 40 00; telex 570 042; fax 33 (0)5 59 74 45 15, for a copy 
of this service information.
    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New

[[Page 16811]]

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.

    Issued in Burlington, Massachusetts, on April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-8310 Filed 4-10-09; 8:45 am]
BILLING CODE 4910-13-P
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