Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines, 6925-6927 [E7-2425]

Download as PDF Federal Register / Vol. 72, No. 30 / Wednesday, February 14, 2007 / Rules and Regulations corrective actions before further flight. Repeat the test thereafter at intervals not to exceed 2,000 flight hours. (1) For airplanes modified before the effective date of this AD in accordance with Airbus Service Bulletin A300–22–0117, dated September 7, 2004: Do the initial test within 2,000 flight hours after the effective date of this AD. (2) For airplanes modified in accordance with Airbus Service Bulletin A300–22–0117, Revision 01, dated April 20, 2005; or Revision 02, dated September 14, 2005: Do the initial test within 2,000 flight hours after the modification required by paragraph (f) of this AD, or within 2,000 flight hours after the effective date of this AD, whichever occurs later. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. 6925 (3) AMOCs approved previously in accordance with AD 2005–13–33 are not approved as AMOCs with this AD. Related Information (i) French airworthiness directive F–2005– 107, dated July 6, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level A300–22–0117 ............................................................................ A300–22–0117 ............................................................................ A300–22–0117 ............................................................................ A300–22–0118, excluding Appendix 01 ..................................... Original 01 02 Original (1) The Director of the Federal Register approved the incorporation by reference of the documents identified in Table 2 of this Date September 7, 2004. April 20, 2005. September 14, 2005. May 18, 2005. AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 2.—NEW MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level A300–22–0117 ............................................................................ A300–22–0117 ............................................................................ A300–22–0118, excluding Appendix 01 ..................................... 01 02 Original rmajette on PROD1PC67 with RULES (2) On August 1, 2005 (70 FR 36833, June 27, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–22–0117, dated September 7, 2004. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 5, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–2412 Filed 2–13–07; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:01 Feb 13, 2007 Jkt 211001 Date April 20, 2005. September 14, 2005. May 18, 2005. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22039; Directorate Identifier 2005–NE–33–AD; Amendment 39– 14940; AD 2005–17–17R1] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is revising an existing airworthiness directive (AD) for Turbomeca S.A. Arrius 2F turboshaft engines. That AD currently requires replacing certain O-rings on the check valve piston in the lubrication unit, at repetitive intervals. This AD requires the same actions except it reduces the applicability from all Turbomeca S.A. Arrius 2F turboshaft engines, to Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated modification Tf75. This AD results from Turbomeca S.A. introducing a check PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 valve piston design requiring no O-ring. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter. DATES: This AD becomes effective March 21, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of March 21, 2007. ADDRESSES: You can get the service information identified in this AD from Turbomeca S.A., 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, telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with E:\FR\FM\14FER1.SGM 14FER1 6926 Federal Register / Vol. 72, No. 30 / Wednesday, February 14, 2007 / Rules and Regulations a proposed AD. The proposed AD applies to Turbomeca S.A. Arrius 2F turboshaft engines. We published the proposed AD in the Federal Register on November 8, 2006 (71 FR 65430). That action proposed to require replacing certain O-rings on the check valve piston in the lubrication unit, at repetitive intervals. This AD requires the same actions except it reduces the applicability from all Turbomeca S.A. Arrius 2F turboshaft engines, to Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated modification Tf75. 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 Office 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 about 124 engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per engine to perform the actions, and that the average labor rate is $80 per work-hour. Required parts will cost about $100 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators, for one O-ring replacement to be $22,320 for the fleet, or $180 per engine. Authority for This Rulemaking Adoption of the Amendment 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. I 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, Incorporation by reference, Safety. 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 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 14238 (70 FR 50164, August 26, 2005), and by adding a new airworthiness directive, Amendment 39–14940, to read as follows: I 2005–17–17R1 Turbomeca S.A.: Amendment 39–14940; Docket No. FAA–2005–22039; Directorate Identifier 2005–NE–33–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 21, 2007. Affected ADs (b) This AD revises AD 2005–17–17, Amendment 39–14238. Applicability (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated modification Tf75. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Unsafe Condition (d) This AD results from Turbomeca S.A. introducing a check valve piston design requiring no O-ring. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. O-ring Replacement (f) Replace the O-ring on the check valve piston in the lubrication unit at the intervals specified in Table 1 of this AD. Use the ‘‘Instructions to be Incorporated,’’ 2.A. through 2.C. (2) of Turbomeca Alert Service Bulletin No. A319 79 4802, Update No. 1, dated April 3, 2006, to replace the O-ring. TABLE 1.—COMPLIANCE TIMES FOR O-RING REPLACEMENT rmajette on PROD1PC67 with RULES If the class of oil is: Then replace the O-ring by the later of: Thereafter, replace the O-ring within: (1) HTS or unknown .......................................... 300 hours time-since-new (TSN) or 50 hours after the effective date of this AD. 450 hours TSN or 50 hours after the effective date of this AD. 300 hours time-since-last replacement (TSR). (2) STD .............................................................. VerDate Aug<31>2005 15:01 Feb 13, 2007 Jkt 211001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 500 hours TSR. E:\FR\FM\14FER1.SGM 14FER1 Federal Register / Vol. 72, No. 30 / Wednesday, February 14, 2007 / Rules and Regulations 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; telephone (781) 238– 7175, fax (781) 238–7199; e-mail: christopher.spinney@faa.gov for more information about this AD. European Aviation Safety Agency AD No. 2006–0141, dated May 29, 2006, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Turbomeca Alert Service Bulletin No. A319 79 4802, Update No. 1, dated April 3, 2006, to perform the replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of this service information. You may review copies 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 February 7, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–2425 Filed 2–13–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26241; Directorate Identifier 2006–NM–155–AD; Amendment 39–14938; AD 2007–04–07] RIN 2120–AA64 Airworthiness Directives; Bombardier Model DHC–8–400 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rmajette on PROD1PC67 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC–8–400 series airplanes. This AD requires inspecting to determine the manufacturer’s date of certain V-band clamps on the engine exhaust shroud assembly, and doing VerDate Aug<31>2005 15:01 Feb 13, 2007 Jkt 211001 related investigative/corrective actions if necessary. This AD results from a report of a discrepancy found during a maintenance inspection on a V-band clamp located on the engine exhaust duct shroud. The clamp ends were touching (although the correct fastener torque had been applied), resulting in reduced clamp force on the flanges. We are issuing this AD to prevent vibration in the duct shroud and fretting of the Vband clamp and flanges, which could result in cracking of the flanges and consequent release of hot exhaust gases from the engine tailpipe and damage to adjacent structure. This situation could trigger the fire warning system and result in an in-flight emergency, such as the flightcrew shutting down the engine and activating the fire suppression system. DATES: This AD becomes effective March 21, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 21, 2007. 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. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Richard Fiesel, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7304; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Bombardier Model DHC–8–400 series airplanes. That PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 6927 NPRM was published in the Federal Register on November 3, 2006 (71 FR 64651). That NPRM proposed to require inspecting to determine the manufacturer’s date of certain V-band clamps on the engine exhaust shroud assembly, and doing related investigative/corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM 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 This AD affects about 21 airplanes of U.S. registry. The required actions take about 3 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost is minimal. Based on these figures, the estimated cost of this AD for U.S. operators is $5,040, or $240 per airplane. 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. E:\FR\FM\14FER1.SGM 14FER1

Agencies

[Federal Register Volume 72, Number 30 (Wednesday, February 14, 2007)]
[Rules and Regulations]
[Pages 6925-6927]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-2425]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22039; Directorate Identifier 2005-NE-33-AD; 
Amendment 39-14940; AD 2005-17-17R1]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
for Turbomeca S.A. Arrius 2F turboshaft engines. That AD currently 
requires replacing certain O-rings on the check valve piston in the 
lubrication unit, at repetitive intervals. This AD requires the same 
actions except it reduces the applicability from all Turbomeca S.A. 
Arrius 2F turboshaft engines, to Turbomeca S.A. Arrius 2F turboshaft 
engines that have not incorporated modification Tf75. This AD results 
from Turbomeca S.A. introducing a check valve piston design requiring 
no O-ring. We are issuing this AD to prevent an uncommanded in-flight 
shutdown of the engine, which could result in a forced autorotation 
landing and damage to the helicopter.

DATES: This AD becomes effective March 21, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 21, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Turbomeca S.A., 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, 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with

[[Page 6926]]

a proposed AD. The proposed AD applies to Turbomeca S.A. Arrius 2F 
turboshaft engines. We published the proposed AD in the Federal 
Register on November 8, 2006 (71 FR 65430). That action proposed to 
require replacing certain O-rings on the check valve piston in the 
lubrication unit, at repetitive intervals. This AD requires the same 
actions except it reduces the applicability from all Turbomeca S.A. 
Arrius 2F turboshaft engines, to Turbomeca S.A. Arrius 2F turboshaft 
engines that have not incorporated modification Tf75.

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 Office 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 about 124 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
work-hour per engine to perform the actions, and that the average labor 
rate is $80 per work-hour. Required parts will cost about $100 per 
engine. Based on these figures, we estimate the cost of the AD on U.S. 
operators, for one O-ring replacement to be $22,320 for the fleet, or 
$180 per engine.

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, Incorporation by 
reference, 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 14238 (70 FR 50164, 
August 26, 2005), and by adding a new airworthiness directive, 
Amendment 39-14940, to read as follows:
2005-17-17R1 Turbomeca S.A.: Amendment 39-14940; Docket No. FAA-
2005-22039; Directorate Identifier 2005-NE-33-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
21, 2007.

Affected ADs

    (b) This AD revises AD 2005-17-17, Amendment 39-14238.

Applicability

    (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft 
engines that have not incorporated modification Tf75. These engines 
are installed on, but not limited to, Eurocopter EC120B helicopters.

Unsafe Condition

    (d) This AD results from Turbomeca S.A. introducing a check 
valve piston design requiring no O-ring. We are issuing this AD to 
prevent an uncommanded in-flight shutdown of the engine, which could 
result in a forced autorotation landing and damage to the 
helicopter.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

O-ring Replacement

    (f) Replace the O-ring on the check valve piston in the 
lubrication unit at the intervals specified in Table 1 of this AD. 
Use the ``Instructions to be Incorporated,'' 2.A. through 2.C. (2) 
of Turbomeca Alert Service Bulletin No. A319 79 4802, Update No. 1, 
dated April 3, 2006, to replace the O-ring.

            Table 1.--Compliance Times for O-ring Replacement
------------------------------------------------------------------------
                                  Then replace the O-     Thereafter,
     If the class of oil is:       ring by the later  replace the O-ring
                                          of:               within:
------------------------------------------------------------------------
(1) HTS or unknown..............  300 hours time-     300 hours time-
                                   since-new (TSN)     since-last
                                   or 50 hours after   replacement
                                   the effective       (TSR).
                                   date of this AD.
(2) STD.........................  450 hours TSN or    500 hours TSR.
                                   50 hours after
                                   the effective
                                   date of this AD.
------------------------------------------------------------------------


[[Page 6927]]

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; telephone (781) 238-
7175, fax (781) 238-7199; e-mail: christopher.spinney@faa.gov for 
more information about this AD. European Aviation Safety Agency AD 
No. 2006-0141, dated May 29, 2006, also addresses the subject of 
this AD.

Material Incorporated by Reference

    (i) You must use Turbomeca Alert Service Bulletin No. A319 79 
4802, Update No. 1, dated April 3, 2006, to perform the replacements 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca 
S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 
59 74 45 15, for a copy of this service information. You may review 
copies 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 February 7, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-2425 Filed 2-13-07; 8:45 am]
BILLING CODE 4910-13-P

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