Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines, 64566-64568 [E8-25887]

Download as PDF 64566 Proposed Rules Federal Register Vol. 73, No. 211 Thursday, October 30, 2008 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. 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. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration 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: 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: 14 CFR Part 39 [Docket No. FAA–2008–0935; Directorate Identifier 2008–NE–28–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: pwalker on PROD1PC71 with PROPOSALS Several cases of loss of internal components from the Hydro Mechanical Unit (HMU) low fuel pressure switch HydraElectric part number (P/N) 9 550 17 956 0 into the fuel system, have been reported on Arriel 2 engines. The loss of internal components from the low fuel pressure switch into the fuel system may lead to a rupture of the HP–LP pumps drive shaft shear pin, and thus to a possible uncommanded in-flight shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD results in an emergency autorotation landing and in certain conditions may lead to an accident. We are proposing this AD to prevent forced autorotation landing, or an accident. DATES: We must receive comments on this proposed AD by December 1, 2008. 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 VerDate Aug<31>2005 16:41 Oct 29, 2008 Jkt 217001 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–2008–0935; Directorate Identifier 2008–NE–28–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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 AD 2008– 0077, dated April 28, 2008 (and corrected May 6, 2008) (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Several cases of loss of internal components from the HMU low fuel pressure switch Hydra-Electric P/N 9 550 17 956 0 into the fuel system, have been reported on Arriel 2 engines. The loss of internal components from the low fuel pressure switch into the fuel system may lead to a rupture of the HP–LP pumps drive shaft shear pin, and thus to a possible uncommanded IFSD. On a single-engine helicopter, an uncommanded IFSD results in an emergency autorotation landing and in certain conditions may lead to an accident. The evaluation of this condition prompts the issuance of this AD, which requires the following actions for the HMUs installed on Arriel 2 single-engine applications in order to: • Verify the part number of the low fuel pressure switch; • If installed, replace the Hydra-Electric low fuel pressure switch P/N 9 550 17 956 0 (with either of two different P/N low fuel pressure switches, referenced in the MCAI). • In case a Hydra-Electric switch P/N 9 550 17 956 0 is installed or may have been installed on the HMU, verify that no parts are found in the chamber of the HMU body where the base of the low fuel pressure switch has been installed. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Turbomeca has issued Mandatory Service Bulletin No. 292 73 2826, dated March 13, 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 E:\FR\FM\30OCP1.SGM 30OCP1 Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 / Proposed Rules agreement with France, they have notified us of the unsafe condition described in the EASA AD and service information referenced above. We are proposing 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 proposed AD would require a one-time inspection for affected low fuel pressure switches, for evidence of an affected switch previously installed and inspection for switch parts missing or fallen into the HMU well. Difference Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. We have proposed to not reference the P/Ns of the serviceable low pressure switch as the MCAI does, in order to follow FAA policies. This difference is described in a separate paragraph of the proposed AD. This requirement, if ultimately adopted, will take precedence over the actions in the MCAI. pwalker on PROD1PC71 with PROPOSALS Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 414 products installed on helicopters of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $256 per product. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $139,104. 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 VerDate Aug<31>2005 16:41 Oct 29, 2008 Jkt 217001 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 by adding the following new AD: Turbomeca: Docket No. FAA–2008–0935; Directorate Identifier 2008–NE–28–AD. Comments Due Date (a) We must receive comments by December 1, 2008. Affected Airworthiness Directives (ADs) (b) None. Applicability (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft engines. These engines are installed on, but not limited to, Eurocopter France AS350B3 and EC130 B4 helicopters. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 64567 Reason (d) European Aviation Safety Agency (EASA) AD No. 2008–0077, dated March 13, 2006 (and corrected May 6, 2008), states: Several cases of loss of internal components from the Hydro Mechanical Unit (HMU) low fuel pressure switch HydraElectric part number (P/N) 9 550 17 956 0 into the fuel system, have been reported on Arriel 2 engines. The loss of internal components from the low fuel pressure switch into the fuel system may lead to a rupture of the HP–LP pumps drive shaft shear pin, and thus to a possible uncommanded in-flight shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD results in an emergency autorotation landing and in certain conditions may lead to an accident. We are issuing this AD to prevent forced autorotation landing, or an accident. Actions and Compliance (e) Unless already done, do the following actions. (1) No later than September 30, 2009, perform a one-time inspection of the HMU, using paragraph 2 of Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2826, dated March 13, 2008, to identify the low fuel pressure switch installed on the adjusted HMU. (2) If a Hydra-Electric low fuel pressure switch, part number (P/N) 9 550 17 956 0 is installed: (i) Inspect the low fuel pressure switch and chamber of the HMU body. (ii) If any parts from the low fuel pressure switch are missing or found in the HMU chamber, replace the HMU with a new or overhauled HMU equipped with a serviceable low fuel pressure switch. (iii) If not, replace only the low fuel pressure switch with a serviceable low fuel pressure switch. (3) If a low fuel pressure switch other than a Hydra-Electric low fuel pressure switch, P/ N 9 550 17 956 0 is installed, and that is the only type of low fuel pressure switch that has been installed since new, repair, or overhaul, no further action is required. (4) If a Hydra-Electric switch, P/N 9 550 17 956 0, has been or may have been installed previously, and the conditions of paragraph (e)(3) of this AD are not met: (i) Inspect the chamber of the HMU body. (ii) If any parts are found in the HMU chamber, replace the HMU with a new or overhauled HMU equipped with a serviceable low fuel pressure switch. FAA AD Difference (f) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and/or service information, by not referencing the P/Ns of the serviceable low fuel pressure switch, and, defining a serviceable low fuel pressure switch, for the purpose of this AD. Definition (g) For the purpose of this AD, a serviceable low fuel pressure switch is a switch that has a P/N other than P/N 9 550 17 956 0. E:\FR\FM\30OCP1.SGM 30OCP1 64568 Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 / Proposed Rules 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 AD 2008–0077, dated April 28, 2008 (and corrected May 6, 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. Issued in Burlington, Massachusetts, on October 23, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–25887 Filed 10–29–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1118; Directorate Identifier 2007–NM–318–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800, and –900 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). pwalker on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. The existing AD currently requires reviewing the airplane maintenance records to determine whether an engine has been removed from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, the existing AD also requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. This proposed AD would require the same actions for airplanes on which the engine has not been previously removed. This proposed AD results from reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes that had not had an engine removed VerDate Aug<31>2005 16:41 Oct 29, 2008 Jkt 217001 since delivery. We are proposing this AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane. DATES: We must receive comments on this proposed AD by December 15, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6432; fax (425) 917–6590. 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–2008–1118; Directorate Identifier 2007–NM–318–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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 consider all comments received by the closing date and may amend this proposed AD because 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 we receive about this proposed AD. Discussion On January 21, 2003, we issued AD 2003–03–01, amendment 39–13025 (68 FR 4367, January 29, 2003), for all Boeing Model 737–600, –700, –700C, –800, and –900 series airplanes. That AD requires reviewing the airplane maintenance records to determine whether an engine has been removed from the airplane since the airplane was manufactured. For airplanes on which an engine has been removed, that AD requires an inspection of the aft engine mount to determine if the center link assembly is correctly installed, and follow-on actions if necessary. That AD resulted from reports indicating that operators found that the center link assembly for the aft engine mount was reversed on several airplanes. We issued that AD to prevent increased structural loads on the aft engine mount, which could result in failure of the aft engine mount and consequent separation of the engine from the airplane. Actions Since Existing AD Was Issued Since we issued AD 2003–03–01, the manufacturer informed us that it is possible that some center links were incorrectly installed in an aft engine mount before the airplane was delivered. In AD 2003–03–01 inspection of the aft engine mounts was required only for airplanes that had an engine change after the airplane was delivered to the operator. The inspection is now necessary for all airplanes, line numbers 1 through 1277 inclusive. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 737–71A1462, Revision 3, dated May 20, 2004. The procedures in Revision 3 of the service bulletin are essentially the same as those in Boeing Alert Service Bulletin 737–71A1462, Revision 1, dated November 7, 2002. We referred to Revision 1 of the service bulletin as the appropriate source of service information for accomplishing the actions required by AD 2003–03–01. However, Revision 3 of the service bulletin also specifies inspecting to determine if the center link assembly is installed correctly on any installed engine that has not been removed from E:\FR\FM\30OCP1.SGM 30OCP1

Agencies

[Federal Register Volume 73, Number 211 (Thursday, October 30, 2008)]
[Proposed Rules]
[Pages 64566-64568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25887]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 / 
Proposed Rules

[[Page 64566]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-28-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B and 2B1 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:

    Several cases of loss of internal components from the Hydro 
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part 
number (P/N) 9 550 17 956 0 into the fuel system, have been reported 
on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded in-flight 
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD 
results in an emergency autorotation landing and in certain 
conditions may lead to an accident.

    We are proposing this AD to prevent forced autorotation landing, or 
an accident.

DATES: We must receive comments on this proposed AD by December 1, 
2008.

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.

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: 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:

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-2008-0935; 
Directorate Identifier 2008-NE-28-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2008-0077, dated April 28, 2008 (and corrected May 6, 2008) 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    Several cases of loss of internal components from the HMU low 
fuel pressure switch Hydra-Electric P/N 9 550 17 956 0 into the fuel 
system, have been reported on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded IFSD. On a 
single-engine helicopter, an uncommanded IFSD results in an 
emergency autorotation landing and in certain conditions may lead to 
an accident.
    The evaluation of this condition prompts the issuance of this 
AD, which requires the following actions for the HMUs installed on 
Arriel 2 single-engine applications in order to:
     Verify the part number of the low fuel pressure switch;
     If installed, replace the Hydra-Electric low fuel 
pressure switch P/N 9 550 17 956 0 (with either of two different P/N 
low fuel pressure switches, referenced in the MCAI).
     In case a Hydra-Electric switch P/N 9 550 17 956 0 is 
installed or may have been installed on the HMU, verify that no 
parts are found in the chamber of the HMU body where the base of the 
low fuel pressure switch has been installed.

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

Relevant Service Information

    Turbomeca has issued Mandatory Service Bulletin No. 292 73 2826, 
dated March 13, 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

[[Page 64567]]

agreement with France, they have notified us of the unsafe condition 
described in the EASA AD and service information referenced above. We 
are proposing 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 proposed AD 
would require a one-time inspection for affected low fuel pressure 
switches, for evidence of an affected switch previously installed and 
inspection for switch parts missing or fallen into the HMU well.

Difference Between This Proposed AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. We have proposed to not reference 
the P/Ns of the serviceable low pressure switch as the MCAI does, in 
order to follow FAA policies. This difference is described in a 
separate paragraph of the proposed AD. This requirement, if ultimately 
adopted, will take precedence over the actions in the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 414 products installed on helicopters of U.S. 
registry. We also estimate that it would take about 1 work-hour per 
product to comply with this proposed AD. The average labor rate is $80 
per work-hour. Required parts would cost about $256 per product. Based 
on these figures, we estimate the cost of the proposed AD on U.S. 
operators to be $139,104. 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: Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-
28-AD.

Comments Due Date

    (a) We must receive comments by December 1, 2008.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft 
engines. These engines are installed on, but not limited to, 
Eurocopter France AS350B3 and EC130 B4 helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2008-0077, 
dated March 13, 2006 (and corrected May 6, 2008), states:

    Several cases of loss of internal components from the Hydro 
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part 
number (P/N) 9 550 17 956 0 into the fuel system, have been reported 
on Arriel 2 engines.
    The loss of internal components from the low fuel pressure 
switch into the fuel system may lead to a rupture of the HP-LP pumps 
drive shaft shear pin, and thus to a possible uncommanded in-flight 
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD 
results in an emergency autorotation landing and in certain 
conditions may lead to an accident.

    We are issuing this AD to prevent forced autorotation landing, 
or an accident.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) No later than September 30, 2009, perform a one-time 
inspection of the HMU, using paragraph 2 of Turbomeca Mandatory 
Service Bulletin (MSB) No. 292 73 2826, dated March 13, 2008, to 
identify the low fuel pressure switch installed on the adjusted HMU.
    (2) If a Hydra-Electric low fuel pressure switch, part number 
(P/N) 9 550 17 956 0 is installed:
    (i) Inspect the low fuel pressure switch and chamber of the HMU 
body.
    (ii) If any parts from the low fuel pressure switch are missing 
or found in the HMU chamber, replace the HMU with a new or 
overhauled HMU equipped with a serviceable low fuel pressure switch.
    (iii) If not, replace only the low fuel pressure switch with a 
serviceable low fuel pressure switch.
    (3) If a low fuel pressure switch other than a Hydra-Electric 
low fuel pressure switch, P/N 9 550 17 956 0 is installed, and that 
is the only type of low fuel pressure switch that has been installed 
since new, repair, or overhaul, no further action is required.
    (4) If a Hydra-Electric switch, P/N 9 550 17 956 0, has been or 
may have been installed previously, and the conditions of paragraph 
(e)(3) of this AD are not met:
    (i) Inspect the chamber of the HMU body.
    (ii) If any parts are found in the HMU chamber, replace the HMU 
with a new or overhauled HMU equipped with a serviceable low fuel 
pressure switch.

FAA AD Difference

    (f) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) and/or service information, by not referencing 
the P/Ns of the serviceable low fuel pressure switch, and, defining 
a serviceable low fuel pressure switch, for the purpose of this AD.

Definition

    (g) For the purpose of this AD, a serviceable low fuel pressure 
switch is a switch that has a P/N other than P/N 9 550 17 956 0.

[[Page 64568]]

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 AD 2008-0077, dated April 28, 2008 (and 
corrected May 6, 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.

    Issued in Burlington, Massachusetts, on October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-25887 Filed 10-29-08; 8:45 am]
BILLING CODE 4910-13-P