Airworthiness Directives; Turbomeca Artouste III Series Turboshaft Engines, 49182-49184 [05-16453]

Download as PDF 49182 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations Repair of the Spool Shaft (i) You may repair the spool if the CSR on the spool shaft are fewer than or equal to the limit in the column titled, Repair by (CSR), in Table 2 of this AD. Use 3.B. of the Accomplishment Instructions of GEAE SB No. CF6–80C2 S/B 72–1052, Revision 02, dated May 25, 2005, for the repair. CF6–80E1 Engines (j) For CF6–80E1 series engines with HPCR stage 11–14 spool shafts with SNs listed in 1.A.(2) of GEAE SB No. CF6–80E1 S/B 72– 0232, Revision 01, dated February 5, 2004, do the following: (1) Inspect the spool shaft for the location of the cut circumferential repair at the next piece-part exposure, but before exceeding 11,600 CSR. Use 3.A.(1) of the Accomplishment Instructions of GEAE SB No. CF6–80E1 S/B 72–0232, Revision 01, dated February 5, 2004 for the inspection. (2) For the purposes of this AD, CSR limit is defined as the current CSN minus the CSN at the time of the repair. (3) If the CSR limit cannot be determined from the engine records, then CSN must be used. (4) If the circumferential cut repair is in the Stage 14 forward location, and not in Area X, no further action is required by this AD. However, GEAE recommends that you repair these spools at the next exposure of the spool shaft. Table 2 of this AD, replace the spool shaft within 420 CIS or within the published part life limit, whichever occurs first. Repair of the Spool Shaft (l) You may repair the spool shaft if the CSR on the spool shaft are fewer than or equal to the limit in the column titled, Repair by (CSR), in Table 2 of this AD. Use 3.B. of the Accomplishment Instructions of GEAE SB CF6–80E1 S/B 72–0232, Revision 01, dated February 5, 2004, for the repair. Replacement of the Spool Shaft (k) After the effective date of this AD, replace spool shafts as follows: (1) If the spool shaft exceeds the CSR limit in the column titled, Repair by (CSR), in Table 2 of this AD, replace the spool shaft within 420 CIS or prior to exceeding the CSR limit in the column titled, Replace by (CSR), in Table 2 of this AD, whichever occurs later. (2) If the spool shaft exceeds the CSR limit in the column titled, Replace by (CSR), in Alternative Methods of Compliance (m) 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. Material Incorporated by Reference (n) You must use the service information specified in Table 3 of this AD to perform the actions required by this AD. TABLE 3.—INCORPORATION BY REFERENCE Service bulletin No. Page Revision Date CF6–80C2 S/B 72–1052 ........................................................................................................ ALL ................... 02 May 25, 2005. ALL ................... 01 February 5, 2004. Total Pages: 11 CF6–80E1 S/B 72–0232 ........................................................................................................ Total Pages: 9 The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 3 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672–8422, 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., Nassif Building, Room PL–401, Washington, DC 20590–0001, 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 NARA, call 202–741–6030, or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on August 12, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–16454 Filed 8–22–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 16:13 Aug 22, 2005 Jkt 205001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20849; Directorate Identifier 2005–NE–04–AD; Amendment 39– 14227; AD 2005–17–06] RIN 2120–AA64 Airworthiness Directives; Turbomeca Artouste III Series Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Artouste III series turboshaft engines. This AD requires modification of the engine air intake assembly. This AD results from a report of an in-flight shutdown and subsequent loss of control of the helicopter due to ice ingestion into the engine. We are issuing this AD to prevent ice ingestion into the engine, which could lead to an in-flight shutdown and subsequent loss of control of the helicopter. DATES: This AD becomes effective September 27, 2005. The Director of the Federal Register approved the incorporation by reference of certain PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 publications listed in the regulations as of September 27, 2005. ADDRESSES: Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 05 59 74 45 15, for the service information identified in this AD. 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 01803–5299; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to Turbomeca Artouste III series turboshaft engines. We published the proposed AD in the Federal Register on April 6, 2005 (70 FR 17368). That action proposed to require adding two additional water drain holes in the engine air intake assembly. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in E:\FR\FM\23AUR1.SGM 23AUR1 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations person at the Docket Management Facility Docket Offices 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 have considered the one comment received. One commenter, Turbomeca, states that we should change the compliance section to reference Update No. 1 of Mandatory Service Bulletin (MSB) No. 218 72 0104. Update No. 1 of the MSB corrects an error in the MSB original issue. The MSB original issue required only one hole to be drilled in each halfair intake assembly, preventing the halfair intake assemblies from being interchangeable. Update No. 1 of the MSB requires a second hole to be drilled in each half-air intake assembly to make them interchangeable. We agree, and have changed the compliance section of this AD to reference Turbomeca MSB No. 218 72 0104, Update No. 1, dated March 25, 2005. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,062 engines of the affected design in the worldwide fleet. We estimate that this AD will affect 59 engines installed on helicopters of U.S. registry. We also estimate that it will take about three work hours per engine to perform the actions, and that the average labor rate is $65 per work hour. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $11,505. 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. VerDate jul<14>2003 16:13 Aug 22, 2005 Jkt 205001 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. 49183 Effective Date (a) This airworthiness directive (AD) becomes effective September 27, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to Turbomeca Artouste III B, B1, and D turboshaft engines. These engines are installed on, but not limited to, Aerospatiale (Eurocopter—France) SA–315B LAMA, and Alouette III SA3160, SA–316B, and SA–316C helicopters. Unsafe Condition (d) This AD results from a report of an inflight shutdown and subsequent loss of control of the helicopter, due to ice ingestion into the engine. We are issuing this AD to prevent ice ingestion into the engine, which could lead to an in-flight shutdown and subsequent loss of control of the helicopter. Compliance: (e) You are responsible for having the actions required by this AD performed within nine months after the effective date of this AD, unless the actions have already been done. Addition of Water Drain Holes (Turbomeca Modification TU 171A) (f) Within nine months from the effective date of this AD, drill two additional water drain holes in each engine air intake assembly half-cover, using paragraph 2.B. and the air intake assembly dimensional flat view of Turbomeca Artouste III Mandatory Service Bulletin No. 218 72 0104, Update No. 1, dated March 25, 2005. 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 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (h) DGAC airworthiness directive F–2003– 455, dated December 24, 2003, also addresses the subject of this AD. Adoption of the Amendment (i) You must use Turbomeca Artouste III Mandatory Service Bulletin No. 218 72 0104, Update No. 1, dated March 25, 2005, to perform the actions 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, 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 Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–0001, 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 NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2005–17–06 Turbomeca: Amendment 39– 14227. Docket No. FAA–2005–20849; Directorate Identifier. 2005–NE–04–AD. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 Material Incorporated by Reference E:\FR\FM\23AUR1.SGM 23AUR1 49184 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations Issued in Burlington, Massachusetts, on August 12, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–16453 Filed 8–22–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–19473; Directorate Identifier 2004–CE–35–AD; Amendment 39– 14146; AD 2005–13–09] RIN 2120–AA64 Airworthiness Directives; GROB– WERKE Model G120A Airplanes Federal Aviation Administration, DOT. ACTION: Final rule; correction. AGENCY: This document incorporates corrections to add service information to Airworthiness Directive (AD) 2005–13– 09, which was published in the Federal Register on June 22, 2005 (70 FR 35993). AD 2005–13–09 applies to certain GROB–WERKE Model G120A airplanes. This action adds GROB–WERKE Service Bulletin No. MSB1121–052/2, dated February 14, 2005, to paragraphs (e)(1), (e)(2), and (h) of AD 2005–13–09. This service information was included in the notice of proposed rulemaking (NPRM) for this AD, but we inadvertently omitted it in the final rule request for comments. We are re-issuing the AD in its entirety to help eliminate any confusion that this AD may have created. SUMMARY: The effective date of this AD remains July 26, 2005. As of July 26, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. DATES: To get the service information identified in this AD, contact GROB–WERKE, Burkart Grob e.K., Unternehmenbereich Luft-und Raumfahrt, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany; telephone: 011 49 8268 998 105; facsimile: 011 49 8268 998 200. To review this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741– 6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2004–19473. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, ACE–112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816–329– 4146; facsimile: 816–329–4090. SUPPLEMENTARY INFORMATION: ADDRESSES: Discussion On June 14, 2005, FAA issued AD 2005–13–09, Amendment 39–14146 (70 FR 35993, June 22, 2005), which applies to certain GROB–WERKE Model G120A airplanes. That AD requires you to replace the main landing gear (MLG) uplock hook assembly. Need for This Action GROB–WERKE Service Bulletin No. MSB1121–052/2, dated February 14, 2005, was included in the NPRM, but we inadvertently omitted it from AD 2005–13–09. We are adding it paragraphs (e)(1), (e)(2), and (h) of this AD. We are clarifying and re-issuing the AD in its entirety to help eliminate any confusion that this AD may have created. 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. § 39.13 [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: I 2005–13–09 GROB–WERKE: Amendment 39–14146; Docket No. FAA–2005–19473; Directorate Identifier 2004-CE–35-AD. When Does This AD Become Effective? (a) The effective date of this AD (2005–13– 09) remains July 26, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model G120A, all serial numbers beginning with 85001. What Is the Unsafe Condition Presented in This AD? (d) This AD results from a report that the main landing gear (MLG) may not extend because of contamination or misalignment of the assembly. The actions specified in this AD are intended to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Remove MLG up-lock hook assembly and replace with the new MLG up-lock hook assembly. Within 100 hours time-in-service after July 26, 2005 (the effective date of this AD), unless already done. (2) For all serial numbers: Do not install any elevator and aileron hinge pins that are not part number SY991A hinge pins. After July 26, 2005 (the effective date of this AD). Follow GROB–WERKE Service Bulletin No. MSB1121–052/2, dated February 14, 2005; and GROB–WERKE Service Bulletin No.MSB1121– 060, dated March 7, 2005. Follow GROB–WERKE Service Bulletin No. MSB1121–052/2, datedFebruary 14, 2005; and GROB–WERKE Service Bulletin No. MSB1121– 060, dated March 7, 2005. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time VerDate jul<14>2003 16:13 Aug 22, 2005 Jkt 205001 for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 comments and will send your request to the Manager, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact E:\FR\FM\23AUR1.SGM 23AUR1

Agencies

[Federal Register Volume 70, Number 162 (Tuesday, August 23, 2005)]
[Rules and Regulations]
[Pages 49182-49184]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16453]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20849; Directorate Identifier 2005-NE-04-AD; 
Amendment 39-14227; AD 2005-17-06]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Artouste III Series 
Turboshaft Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Turbomeca Artouste III series turboshaft engines. This AD requires 
modification of the engine air intake assembly. This AD results from a 
report of an in-flight shutdown and subsequent loss of control of the 
helicopter due to ice ingestion into the engine. We are issuing this AD 
to prevent ice ingestion into the engine, which could lead to an in-
flight shutdown and subsequent loss of control of the helicopter.

DATES: This AD becomes effective September 27, 2005. The Director of 
the Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of September 27, 2005.

ADDRESSES: Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 
74 40 00, fax +33 05 59 74 45 15, for the service information 
identified in this AD.
    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 01803-5299; 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to Turbomeca Artouste III series turboshaft engines. We published the 
proposed AD in the Federal Register on April 6, 2005 (70 FR 17368). 
That action proposed to require adding two additional water drain holes 
in the engine air intake assembly.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in

[[Page 49183]]

person at the Docket Management Facility Docket Offices 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 have considered the one comment received.
    One commenter, Turbomeca, states that we should change the 
compliance section to reference Update No. 1 of Mandatory Service 
Bulletin (MSB) No. 218 72 0104. Update No. 1 of the MSB corrects an 
error in the MSB original issue. The MSB original issue required only 
one hole to be drilled in each half-air intake assembly, preventing the 
half-air intake assemblies from being interchangeable. Update No. 1 of 
the MSB requires a second hole to be drilled in each half-air intake 
assembly to make them interchangeable. We agree, and have changed the 
compliance section of this AD to reference Turbomeca MSB No. 218 72 
0104, Update No. 1, dated March 25, 2005.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,062 engines of the affected design in the 
worldwide fleet. We estimate that this AD will affect 59 engines 
installed on helicopters of U.S. registry. We also estimate that it 
will take about three work hours per engine to perform the actions, and 
that the average labor rate is $65 per work hour. Based on these 
figures, we estimate the total cost of the AD to U.S. operators to be 
$11,505.

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 adding the following new airworthiness 
directive:

2005-17-06 Turbomeca: Amendment 39-14227. Docket No. FAA-2005-20849; 
Directorate Identifier. 2005-NE-04-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 27, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to Turbomeca Artouste III B, 
B1, and D turboshaft engines. These engines are installed on, but 
not limited to, Aerospatiale (Eurocopter--France) SA-315B LAMA, and 
Alouette III SA3160, SA-316B, and SA-316C helicopters.

Unsafe Condition

    (d) This AD results from a report of an in-flight shutdown and 
subsequent loss of control of the helicopter, due to ice ingestion 
into the engine. We are issuing this AD to prevent ice ingestion 
into the engine, which could lead to an in-flight shutdown and 
subsequent loss of control of the helicopter.
    Compliance: (e) You are responsible for having the actions 
required by this AD performed within nine months after the effective 
date of this AD, unless the actions have already been done.

Addition of Water Drain Holes (Turbomeca Modification TU 171A)

    (f) Within nine months from the effective date of this AD, drill 
two additional water drain holes in each engine air intake assembly 
half-cover, using paragraph 2.B. and the air intake assembly 
dimensional flat view of Turbomeca Artouste III Mandatory Service 
Bulletin No. 218 72 0104, Update No. 1, dated March 25, 2005.

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) DGAC airworthiness directive F-2003-455, dated December 24, 
2003, also addresses the subject of this AD.

Material Incorporated by Reference

    (i) You must use Turbomeca Artouste III Mandatory Service 
Bulletin No. 218 72 0104, Update No. 1, dated March 25, 2005, to 
perform the actions 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, 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 Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-0001, 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 NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.


[[Page 49184]]


    Issued in Burlington, Massachusetts, on August 12, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-16453 Filed 8-22-05; 8:45 am]
BILLING CODE 4910-13-P

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