Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines, 4121-4123 [E8-31396]

Download as PDF Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations III.B. of PZL Service Bulletin No. E/62.020/ 2008, dated October 30, 2008. (3) If in the inspection required in paragraph (f)(1) of this AD any damage is found on the flight control systems other than the pulleys and cables of the aileron control system, before further flight, repair the damage with an FAA-approved repair solution (see paragraph (g)(2) of this AD). Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES FAA AD Differences 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: ■ 2009–02–02 Polskie Zaklady Lotnicze Spolka zo.o: Amendment 39–15792; Docket No. FAA–2009–0010; Directorate Identifier 2009–CE–001–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 12, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Models PZL M26 01 airplanes, serial numbers 1APP01–01 and 1AP002–01 through 1AP002–06, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. rwilkins on PROD1PC63 with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: ‘‘A detailed inspection in a M26 airplane revealed a significant chafing of the aileron control cable against the wing rib in the fuselage-to-wing area of transition and an abnormal wearing of pulleys’ gorges as well.’’ ‘‘Such damage can only be evidenced on control cables which travel in pulleys either limited in rotation or seized.’’ ‘‘If left uncorrected, this condition, which could also occur on the elevator or rudder control system, could lead to loss of one or more primary flight controls and consequent reduced controllability of the airplane.’’ ‘‘For the reason stated above, this Airworthiness Directive requires a detailed inspection of flight controls and the correction of any discrepancy that could be found as a result of the inspection.’’ Actions and Compliance (f) Unless already done, do the following actions. (1) Before further flight, after the effective date of this AD, inspect the airplane’s flight control systems as instructed in paragraph III.A. of Polskie Zaklady Lotnicze Spolka zo.o. (PZL) Service Bulletin No. E/62.020/ 2008, dated October 30, 2008. (2) If in the inspection required in paragraph (f)(1) of this AD any damage is found on the pulleys and cables of the aileron control system, before further flight, repair the damage as instructed in paragraph VerDate Nov<24>2008 16:34 Jan 22, 2009 Jkt 217001 Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Attn: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to European Aviation Safety Agency (EASA) AD No. 2008–0220, dated December 19, 2008, and Polskie Zaklady Lotnicze Spolka zo.o. (PZL) Service Bulletin No. E/62.020/2008, dated October 30, 2008, for related information. Material Incorporated by Reference (i) You must use Polskie Zaklady Lotnicze Spolka zo.o. (PZL) Service Bulletin No. E/ 62.020/2008, dated October 30, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Polskie Zaklady Lotnicze Sp. z.o.o., ul. Wojska Polskiego 3, 39–300 Mielec, Poland; telephone: +48 17 788 7574; fax: +48 17 788 6365; e-mail: pzl@pzlmielec.com.pl; Internet: https://www.pzlmielec.pl/biuletyn/ E62–020–2008_e.pdf. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 4121 (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, Missouri on January 8, 2009. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–776 Filed 1–22–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0935; Directorate Identifier 2008–NE–28–AD; Amendment 39– 15790; AD 2009–01–11] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: 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. E:\FR\FM\23JAR1.SGM 23JAR1 4122 Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations DATES: This AD becomes effective February 27, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 27, 2009. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 30, 2008 (73 FR 64566). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: 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. rwilkins on PROD1PC63 with RULES Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. VerDate Nov<24>2008 16:34 Jan 22, 2009 Jkt 217001 Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. We are not referencing 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 AD. Costs of Compliance Based on the service information, we estimate that this AD will affect about 414 products installed on helicopters of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $256 per product. Based on these figures, we estimate the cost of the 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 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: ■ 2009–01–11 Turbomeca: Amendment 39– 15790. Docket No. FAA–2008–0935; Directorate Identifier 2008–NE–28–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 27, 2009. Affected 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. E:\FR\FM\23JAR1.SGM 23JAR1 Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations 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. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (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. Federal Aviation Administration 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. Material Incorporated by Reference (k) You must use Turbomeca Mandatory Service Bulletin No. 292 73 2826, dated March 13, 2008, to do the low fuel pressure switch installation inspection required by this AD. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax (33) 05 59 74 45 15. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on December 30, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–31396 Filed 1–22–09; 8:45 am] BILLING CODE 4910–13–P Definition (f) 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. rwilkins on PROD1PC63 with RULES FAA AD Difference (g) 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. VerDate Nov<24>2008 16:34 Jan 22, 2009 Jkt 217001 4123 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2008–0420; Directorate Identifier 2008–NE–10–AD; Amendment 39– 15793; AD 2009–02–03] RIN 2120–AA64 Airworthiness Directives; Lycoming Engines IO, (L)IO, TIO, (L)TIO, AEIO, AIO, IGO, IVO, and HIO Series Reciprocating Engines, Teledyne Continental Motors (TCM) LTSIO–360– RB and TSIO–360–RB Reciprocating Engines, and Superior Air Parts, Inc. IO–360 Series Reciprocating Engines With Certain Precision Airmotive LLC RSA–5 and RSA–10 Series, and Bendix RSA–5 and RSA–10 Series, Fuel Injection Servos AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Lycoming Engines IO, (L)IO, TIO, (L)TIO, AEIO, AIO, IGO, IVO, and HIO series reciprocating engines, TCM TSIO–360–RB reciprocating engines, and Superior Air Parts, Inc. IO–360 series reciprocating engines with certain Precision Airmotive LLC RSA–5 and RSA–10 series fuel injection servos. That AD currently requires inspecting servo plugs for looseness and damage on fuel injection servos that have a servo plug gasket, part number (P/N) 365533, installed, and if loose, inspecting the servo regulator cover threads for damage, inspecting the gasket for damage, reinstalling acceptable parts, and torquing the servo plug to a new, higher torque to maintain the proper clamp-up force between the plug and cover. This AD requires the same inspections, except if the plug is found loose, servo plug gasket, P/N 365533, must be replaced with a new, improved gasket, P/N 2577258. This AD also requires replacement by December 31, 2009, of servo plug gaskets, P/N 365533, manufactured and made available on or after August 22, 2006, as mandatory terminating action to the repetitive inspections required by this AD. This AD also prohibits the installation of any servo plug gasket, P/N 365533. This AD also clarifies the TCM engine model applicability, and adds Bendix RSA–5 and RSA–10 series fuel injection servos to the applicability. This AD results from Precision Airmotive LLC E:\FR\FM\23JAR1.SGM 23JAR1

Agencies

[Federal Register Volume 74, Number 14 (Friday, January 23, 2009)]
[Rules and Regulations]
[Pages 4121-4123]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-31396]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-28-AD; 
Amendment 39-15790; AD 2009-01-11]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

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

    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.

[[Page 4122]]


DATES: This AD becomes effective February 27, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of February 27, 2009.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on October 30, 2008 (73 
FR 64566). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    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.

Comments

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

Conclusion

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

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. We are not referencing 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 AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 414 products installed on helicopters of U.S. registry. We 
also estimate that it will take about 1 work-hour per product to comply 
with this AD. The average labor rate is $80 per work-hour. Required 
parts will cost about $256 per product. Based on these figures, we 
estimate the cost of the 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-01-11 Turbomeca: Amendment 39-15790. Docket No. FAA-2008-0935; 
Directorate Identifier 2008-NE-28-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
27, 2009.

Affected 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.

[[Page 4123]]

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.

Definition

    (f) 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.

FAA AD Difference

    (g) 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.

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.

Material Incorporated by Reference

    (k) You must use Turbomeca Mandatory Service Bulletin No. 292 73 
2826, dated March 13, 2008, to do the low fuel pressure switch 
installation inspection required by this AD.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax 
(33) 05 59 74 45 15.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on December 30, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-31396 Filed 1-22-09; 8:45 am]
BILLING CODE 4910-13-P
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