Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines, 28589-28591 [E7-9721]

Download as PDF Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, 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: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4138; 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) AMOCs approved for AD 2003–07–06 are not approved for this AD. (3) 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 FAAapproved 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. (4) 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. cprice-sewell on PRODPC61 with RULES Related Information (i) Refer to MCAI Civil Aviation Authority AD No. G–2004–0029, dated December 20, 2004; BAE Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JA030644, dated October 6, 2003; BAE Systems British Aerospace Jetstream Mandatory Service Bulletin 32–JA020741, Original Issue: November 2, 2002; APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003; and APPH Ltd. Service Bulletin 32–76, pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002, for related information. Material Incorporated by Reference (j) You must use APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003; as referenced in BAE Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JA030644, dated October 6, 2003; and APPH Ltd. Service Bulletin 32– 76, pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002; as referenced in BAE Systems British Aerospace Jetstream Mandatory Service Bulletin 32–JA020741, Original Issue: November 2, 2002; 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 APPH Ltd. Service Bulletin 32–76, Revision 1, dated August 2003; as referenced in BAE Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JA030644, dated October 6, 2003, under 5 U.S.C. 552(a) and 1 CFR part 51. VerDate Aug<31>2005 15:01 May 21, 2007 Jkt 211001 (2) On May 22, 2003 (68 FR 16195, April 3, 2003), the Director of the Federal Register approved the incorporation by reference of APPH Ltd. Service Bulletin 32–76, pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002, as referenced in BAE Systems British Aerospace Jetstream Mandatory Service Bulletin 32– JA020741, Original Issue: November 2, 2002. (3) For service information identified in this AD, contact BAE Systems, Prestwick International Airport, Ayshire, KA9 2RW, Scotland; telephone: (01292) 675207; fax: (01292) 675704. (4) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 Kansas City, Missouri, on May 9, 2007. Charles L. Smalley, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 07–2522 Filed 5–21–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2006–26112; Directorate Identifier 2006–NE–35–AD; Amendment 39– 14837; AD 2006–24–08] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada (P&WC) PW535A Turbofan Engines; Correction Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; correction. AGENCY: SUMMARY: The FAA is correcting airworthiness directive (AD) 2006–24– 08. That AD applies to Pratt & Whitney Canada (P&WC) PW535A turbofan engines. We published that AD in the Federal Register on December 4, 2006 (71 FR 70284). The fuel manifold part number (P/N) 3025267–01 listed in paragraph (c) is incorrect. This document corrects that P/N. In all other respects, the original document remains the same. EFFECTIVE DATE: Effective May 22, 2007. FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New EnglandExecutive Park, Burlington, MA, 01803; telephone (781) 238–7178; fax (781) 238–7199. Frm 00003 Fmt 4700 On December 4, 2006 (71 FR 70284), we published a final rule AD, FR Doc, E6– 20204, in the Federal Register. That AD applies to P&WC PW535A turbofan engines. We need to make the following correction: SUPPLEMENTARY INFORMATION: § 39.13 [Corrected] On page 70286, in the second column, in paragraph (c), in the fourth line, ‘‘3025267–01’’ is corrected to read ‘‘3052627–01’’. Issued in Burlington, Massachusetts, on May 14, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–9719 Filed 5–21–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22430; Directorate Identifier 2005–NE–34–AD; Amendment 39– 15063; AD 2007–11–06] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines 14 CFR Part 39 PO 00000 28589 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. That AD currently requires removing from service certain serial number (SN) fuel control units (FCUs) or replacing the constant delta pressure (delta P) diaphragm in those FCUs. This AD requires replacing all FCUs not incorporating modification Tf 55 with FCUs that incorporate modification Tf 55. This AD results from the European Aviation Safety Agency (EASA) and Turbomeca expanding the applicability to the full population of FCUs installed on Arrius 2F turboshaft engines. FCUs not incorporating modification Tf 55 are susceptible to having an improperly assembled constant delta P diaphragm. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident. DATES: This AD becomes effective June 26, 2007. ADDRESSES: You can get the service information identified in this AD from E:\FR\FM\22MYR1.SGM 22MYR1 28590 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 05 59 74 45 15. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Turbomeca Arrius 2F turboshaft engines. We published the proposed AD in the Federal Register on January 17, 2007 (72 FR 1947). That action proposed to require replacing all FCUs not incorporating modification Tf 55, with FCUs that incorporate modification Tf 55. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. cprice-sewell on PRODPC61 with RULES Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 15:01 May 21, 2007 Jkt 211001 Regulatory Findings We have 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Costs of Compliance We estimate that this AD will affect 46 Arrius 2F turboshaft engines installed on helicopters of U.S. registry. We also estimate that it will take about 3 work-hours per engine to perform the FCU replacement and that the average labor rate is $80 per work-hour. Required parts will cost about $25,480 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $1,183,120. VerDate Aug<31>2005 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14275 (70 FR 54622, September 16, 2005) and by adding a new airworthiness directive, Amendment 39–15063, to read as follows: I 2007–11–06 Turbomeca: Amendment 39– 15063. Docket No. FAA–2005–22430; Directorate Identifier 2005–NE–34–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 26, 2007. Affected ADs (b) This AD supersedes AD 2005–19–10, Amendment 39–14275. Applicability (c) This AD applies to Turbomeca Arrius 2F turboshaft engines with fuel control units (FCUs) not incorporating modification Tf 55. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Unsafe Condition (d) This AD results from the European Aviation Safety Agency (EASA) and Turbomeca expanding the applicability to the full population of FCUs installed on Arrius 2F turboshaft engines. FCUs not incorporating modification Tf 55 are susceptible to having an improperly assembled constant delta pressure (delta P) diaphragm. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident. Compliance (e) You are responsible for having the actions required by this AD performed as soon as practicable after the effective date of this AD but no later than July 31, 2007, unless the actions have already been done. (f) Replace all FCUs not incorporating modification Tf 55 with FCUs that incorporate modification Tf 55. Alternative Methods of Compliance (g) The Manager, Engine 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 (h) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238–7175, fax (781) 238–7199; for more information about this AD. (i) EASA AD No. 2006–0237, dated August 9, 2006, addresses the subject of this AD. (j) Turbomeca Mandatory Service Bulletin No. 319 73 4055, Update No. 1, dated March 17, 2006, pertains to the subject of this AD. E:\FR\FM\22MYR1.SGM 22MYR1 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations Issued in Burlington, Massachusetts, on May 15, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–9721 Filed 5–21–07; 8:45 am] SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27295 Directorate Identifier 2007–CE–013–AD; Amendment 39–15060; AD 2007–11–03] RIN 2120–AA64 Airworthiness Directives; Dornier Luftfahrt GmbH Model 228 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: Discussion 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: SUMMARY: cprice-sewell on PRODPC61 with RULES During a maintenance inspection, cracks were found on the centre section of fuselage frame 19. The investigation on the root cause is still in progress. Fuselage frame 19 supports the rear side of the main landing gear (MLG). This condition, if not corrected, could cause collapse of frame 19, leading to subsequent collapse of a MLG. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 26, 2007. On June 26, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. VerDate Aug<31>2005 15:01 May 21, 2007 Jkt 211001 The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. The streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. 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 March 16, 2007 (72 FR 12574). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: 28591 general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the AD. Costs of Compliance We estimate that this AD will affect 19 products of U.S. registry. We also estimate that it will take about 6 workhours per product to comply with basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $9,120 or $480 per product. In addition, this AD may require follow-on actions. Because each followon action is based on the damage found on the affected airplane, we have no way of determining the cost of those follow-on actions or the number of products that may need these actions. Authority for This Rulemaking 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. 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. Conclusion Regulatory Findings We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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. During a maintenance inspection, cracks were found on the centre section of fuselage frame 19. The investigation on the root cause is still in progress. Fuselage frame 19 supports the rear side of the main landing gear (MLG). This condition, if not corrected, could cause collapse of frame 19, leading to subsequent collapse of a MLG. Since an unsafe condition has been identified that may exist or develop on other aircraft of this type design, this Airworthiness Directive (AD) requires a visual inspection of the affected fuselage frame and, if discrepancies are found, reporting the results to the TC holder. This is considered to be an interim action. Comments Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\22MYR1.SGM 22MYR1

Agencies

[Federal Register Volume 72, Number 98 (Tuesday, May 22, 2007)]
[Rules and Regulations]
[Pages 28589-28591]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-9721]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22430; Directorate Identifier 2005-NE-34-AD; 
Amendment 39-15063; AD 2007-11-06]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Turbomeca Arrius 2F turboshaft engines. That AD currently 
requires removing from service certain serial number (SN) fuel control 
units (FCUs) or replacing the constant delta pressure (delta P) 
diaphragm in those FCUs. This AD requires replacing all FCUs not 
incorporating modification Tf 55 with FCUs that incorporate 
modification Tf 55. This AD results from the European Aviation Safety 
Agency (EASA) and Turbomeca expanding the applicability to the full 
population of FCUs installed on Arrius 2F turboshaft engines. FCUs not 
incorporating modification Tf 55 are susceptible to having an 
improperly assembled constant delta P diaphragm. We are issuing this AD 
to prevent an uncommanded engine in-flight shutdown on a single-engine 
helicopter, resulting in a forced autorotation landing or an accident.

DATES: This AD becomes effective June 26, 2007.

ADDRESSES: You can get the service information identified in this AD 
from

[[Page 28590]]

Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 
05 59 74 45 15.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Turbomeca Arrius 2F 
turboshaft engines. We published the proposed AD in the Federal 
Register on January 17, 2007 (72 FR 1947). That action proposed to 
require replacing all FCUs not incorporating modification Tf 55, with 
FCUs that incorporate modification Tf 55.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in ADDRESSES. Comments will be 
available in the AD docket shortly after the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

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

Costs of Compliance

    We estimate that this AD will affect 46 Arrius 2F turboshaft 
engines installed on helicopters of U.S. registry. We also estimate 
that it will take about 3 work-hours per engine to perform the FCU 
replacement and that the average labor rate is $80 per work-hour. 
Required parts will cost about $25,480 per engine. Based on these 
figures, we estimate the total cost of the AD to U.S. operators to be 
$1,183,120.

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 removing Amendment 39-14275 (70 FR 
54622, September 16, 2005) and by adding a new airworthiness directive, 
Amendment 39-15063, to read as follows:

2007-11-06 Turbomeca: Amendment 39-15063. Docket No. FAA-2005-22430; 
Directorate Identifier 2005-NE-34-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 26, 
2007.

Affected ADs

    (b) This AD supersedes AD 2005-19-10, Amendment 39-14275.

Applicability

    (c) This AD applies to Turbomeca Arrius 2F turboshaft engines 
with fuel control units (FCUs) not incorporating modification Tf 55. 
These engines are installed on, but not limited to, Eurocopter 
EC120B helicopters.

Unsafe Condition

    (d) This AD results from the European Aviation Safety Agency 
(EASA) and Turbomeca expanding the applicability to the full 
population of FCUs installed on Arrius 2F turboshaft engines. FCUs 
not incorporating modification Tf 55 are susceptible to having an 
improperly assembled constant delta pressure (delta P) diaphragm. We 
are issuing this AD to prevent an uncommanded engine in-flight 
shutdown on a single-engine helicopter, resulting in a forced 
autorotation landing or an accident.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed as soon as practicable after the effective date of this 
AD but no later than July 31, 2007, unless the actions have already 
been done.
    (f) Replace all FCUs not incorporating modification Tf 55 with 
FCUs that incorporate modification Tf 55.

Alternative Methods of Compliance

    (g) The Manager, Engine 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

    (h) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
christopher.spinney@faa.gov; telephone (781) 238-7175, fax (781) 
238-7199; for more information about this AD.
    (i) EASA AD No. 2006-0237, dated August 9, 2006, addresses the 
subject of this AD.
    (j) Turbomeca Mandatory Service Bulletin No. 319 73 4055, Update 
No. 1, dated March 17, 2006, pertains to the subject of this AD.


[[Page 28591]]


    Issued in Burlington, Massachusetts, on May 15, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-9721 Filed 5-21-07; 8:45 am]
BILLING CODE 4910-13-P
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