Airworthiness Directives; Turbomeca Artouste III Series Turboshaft Engines, 17368-17370 [05-6774]

Download as PDF 17368 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules We prepared a summary of the costs to comply with this proposal and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. (number to be provided), the pilot must report a rough-running engine that cannot be cleared by adjustment of the engine controls; particularly the fuel mixture setting, to maintenance personnel, immediately after landing.’’ List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Starter Adapter Shaft Gear Needle Bearing Replacement (g) If, during an inspection required by paragraph (h), (i), (j), or (k) of this AD, you find needle bearing, part number (P/N) 537721, installed in the crankcase, replace it with bushing, P/N 654472, before reassembling components. Use the bushing installation procedure specified in Part 4 of TCM Mandatory Service Bulletin (MSB) No. MSB94–4E, dated January 24, 2005. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: Teledyne Continental Motors: Docket No. FAA–2005–20850; Directorate Identifier 2005–NE–05–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by June 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Teledyne Continental Motors (TCM) GTSIO–520 series reciprocating engines. These engines are installed on, but not limited to, Twin Commander (formerly Aero Commander) model 685, Cessna model 404, 411 series, and 421 series, British Aerospace, Aircraft Group, Scottish Division model B.206 series 2 and Aeronautica Macchi, model AM–3 airplanes. Unsafe Condition (d) This AD results from six service difficulty reports and one fatal accident report received related to failed starter adapter assemblies. We are issuing this AD to prevent failure of the starter adapter assembly and or crankshaft gear, resulting in failure of the engine and possible forced landing. 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. Aircraft Placard Installation and Compliance (f) Before further flight, install a placard to the instrument panel in 1⁄4 inch-high or higher characters, within plain view of the pilot that states: ‘‘In accordance with AD VerDate jul<14>2003 15:58 Apr 05, 2005 Jkt 205001 Unscheduled Inspections for Rough-Running Engines (h) For any engine that experiences rough running conditions regardless of time-inservice (TIS), do the following: (1) Before further flight, perform the inspection procedures specified in Part 1 and Part 3 of TCM MSB No. MSB94–4E, dated January 24, 2005, and replace components as necessary. (2) An engine is considered rough-running if there is a sudden increase in the perceived vibration levels that cannot be cleared by adjustment of the engine controls; particularly the fuel mixture setting. Information on a rough running engine can be found in the aircraft manufacturer’s Airplane Flight Manual, Pilot’s Operating Handbook, or Aircraft Owners Manual. 100-Hour and Annual Inspections (i) For any engine, at the next 100-hour or annual inspection, whichever occurs first, do the following: (1) Perform the inspection procedures specified in Part 2 of TCM MSB No. MSB94– 4E, dated January 24, 2005, and replace components as necessary. (2) Thereafter, at each 100-hour inspection, (plus or minus 10 hours), and annual inspection, perform repetitive inspections and component replacements as specified in paragraph (h)(1) of this AD. Starter Adapters With 400 Hours or More Time-In-Service (TIS) or Unknown TIS (j) For any starter adapter with 400 hours or more TIS or unknown TIS on the effective date of this AD, do the following: (1) Within 25 hours TIS, perform the inspection procedures specified in Part 3 of TCM MSB No. MSB94–4E, dated January 24, 2005, and replace components as necessary. (2) Thereafter, at 400-hour TIS intervals, (plus or minus 10 hours), perform repetitive inspections and component replacements as specified in Part 3 of TCM MSB No. MSB94– 4E, dated January 24, 2005, and replace components as necessary. Starter Adapters With Fewer Than 400 Hours TIS (k) For any starter adapter with fewer than 400 hours TIS on the effective date of this AD, do the following: (1) Upon accumulation of 400 hours TIS, (plus or minus 10 hours), perform the inspection procedures specified in Part 3 of PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 TCM MSB No. MSB94–4E, dated January 24, 2005, and replace components as necessary. (2) Thereafter, at 400-hour TIS intervals, (plus or minus 10 hours), perform repetitive inspections and component replacements, as specified in Part 3 of TCM MSB No. MSB94– 4E, dated January 24, 2005, and replace components as necessary. Installation of TCM Service Kit, EQ6642R (l) At the next engine overhaul or starter adapter replacement after the effective date of this AD, whichever occurs first, do the following: (1) Install TCM service kit, P/N EQ6642R. Use the service kit installation procedures specified in Part 5 of TCM MSB No. MSB94– 4E, dated January 24, 2005. (2) Continue performing the inspections and component replacements specified in paragraphs (i), (j), and (k) of this AD. Prohibition of Special Flight Permits for Rough-Running Engines (m) Special flight permits are prohibited for rough-running engines described in paragraph (h)(2) of this AD. Alternative Methods of Compliance (n) The Manager, Atlanta Aircraft 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 (o) European Aviation Safety Agency AD 2004–0006, dated December 15, 2004, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on March 30, 2005. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–6775 Filed 4–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20849; Directorate Identifier 2005–NE–04–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca Artouste III Series Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for Turbomeca Artouste III series turboshaft engines. This proposed AD would require modification of the engine air intake assembly. This proposed AD results from a report of an in-flight E:\FR\FM\06APP1.SGM 06APP1 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules shutdown and subsequent loss of control of the helicopter due to ice ingestion into the engine. We are proposing 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: We must receive any comments on this proposed AD by June 6, 2005. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 proposed AD. 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: Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20849; Directorate Identifier 2005–NE–04–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA VerDate jul<14>2003 17:48 Apr 05, 2005 Jkt 205001 personnel concerning this proposed AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https:// dms.dot.gov. Examining the AD Docket You may examine the docket that contains the proposal, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647– 5227) is 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. Discussion The Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Turbomeca Artouste III B, B1, and D turboshaft engines. The DGAC advises that an Artouste III B1 turboshaft engine installed in an Aerospatiale (Eurocopter—France) SA–315B LAMA helicopter, ingested a block of ice, causing an in-flight shutdown and subsequent loss of control of the helicopter. Turbomeca believes the block of ice formed at the rear of the engine air intake assembly while the helicopter was not running and parked on sloping ground. Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Artouste III Service Bulletin (SB) No 218 72 0104, dated December 24, 2003, that describes procedures for adding two additional water drain holes in the engine air intake assembly. The DGAC classified this SB as mandatory and issued AD F–2003–455, dated December 24, 2003, in order to assure the airworthiness of these Turbomeca Artouste III series engines in France. FAA’s Determination and Requirements of the Proposed AD These Turbomeca Artouste III series turboshaft engines, manufactured in France, are type-certificated for operation in the United States under the PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 17369 provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. In keeping with this bilateral airworthiness agreement, the DGAC kept us informed of the situation described above. We have examined the DGAC’s findings, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. For this reason, we are proposing this AD, which would require adding two additional water drain holes to the engine air intake assembly. The proposed AD would require you to use the service information described previously to perform these actions. Costs of Compliance There are about 1,062 engines of the affected design in the worldwide fleet. We estimate that this proposed AD would affect 59 engines installed on helicopters of U.S. registry. We also estimate that it would take about two work hours per engine to perform the proposed actions, and that the average labor rate is $65 per work hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $7,670. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and E:\FR\FM\06APP1.SGM 06APP1 17370 Federal Register / Vol. 70, No. 65 / Wednesday, April 6, 2005 / Proposed Rules responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would 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 proposal and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. 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 an additional water drain hole in each engine air intake assembly half-cover, using paragraphs 2.B.(1) through 2.B.(5) of Turbomeca Artouste III Service Bulletin (SB) No. 218 72 0104, dated December 24, 2003. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Related Information (h) DGAC airworthiness directive F–2003– 455, dated December 24, 2003, also addresses the subject of this AD. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: Issued in Burlington, Massachusetts, on March 30, 2005. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–6774 Filed 4–5–05; 8:45 am] PART 39—AIRWORTHINESS DIRECTIVES BILLING CODE 4910–13–P 1. The authority citation for part 39 continues to read as follows: DEPARTMENT OF TRANSPORTATION Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Federal Aviation Administration 14 CFR Part 39 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: [Docket No. FAA–2005–20869; Directorate Identifier 2004–NM–09–AD] Turbomeca: Docket No. FAA–2005–20849; Directorate Identifier 2005–NE–04–AD. RIN 2120–AA64 Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by June 6, 2005. Airworthiness Directives; Dornier Model 328–100 and –300 Series Airplanes 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 VerDate jul<14>2003 17:48 Apr 05, 2005 Jkt 205001 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Dornier Model 328–100 and -300 series airplanes. This proposed AD would require operators to install colored identification strips on the pulley brackets, fairlead bracket assemblies, operational assemblies, and flight control cables. This proposed AD is prompted by a report that the flight control systems do not have elements that are distinctively identified. We are proposing this AD to prevent the incorrect re-assembly of the flight control system during maintenance, which could result in reduced controllability of the airplane. PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 We must receive comments on this proposed AD by May 6, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http:/ /dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact AvCraft Aerospace GmbH, P.O. Box 1103, D– 82230 Wessling, Germany. You can examine the contents of this 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., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20869; the directorate identifier for this docket is 2004–NM–09–AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20869; Directorate Identifier 2004NM–09-AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each E:\FR\FM\06APP1.SGM 06APP1

Agencies

[Federal Register Volume 70, Number 65 (Wednesday, April 6, 2005)]
[Proposed Rules]
[Pages 17368-17370]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6774]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20849; Directorate Identifier 2005-NE-04-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Artouste III Series 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Turbomeca Artouste III series turboshaft engines. This proposed AD 
would require modification of the engine air intake assembly. This 
proposed AD results from a report of an in-flight

[[Page 17369]]

shutdown and subsequent loss of control of the helicopter due to ice 
ingestion into the engine. We are proposing 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: We must receive any comments on this proposed AD by June 6, 
2005.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    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 proposed AD.

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:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20849; 
Directorate Identifier 2005-NE-04-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DMS Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78) or you 
may visit https://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is 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.

Discussion

    The Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Turbomeca Artouste III B, B1, and D turboshaft 
engines. The DGAC advises that an Artouste III B1 turboshaft engine 
installed in an Aerospatiale (Eurocopter--France) SA-315B LAMA 
helicopter, ingested a block of ice, causing an in-flight shutdown and 
subsequent loss of control of the helicopter. Turbomeca believes the 
block of ice formed at the rear of the engine air intake assembly while 
the helicopter was not running and parked on sloping ground.

Relevant Service Information

    We have reviewed and approved the technical contents of Turbomeca 
Artouste III Service Bulletin (SB) No 218 72 0104, dated December 24, 
2003, that describes procedures for adding two additional water drain 
holes in the engine air intake assembly. The DGAC classified this SB as 
mandatory and issued AD F-2003-455, dated December 24, 2003, in order 
to assure the airworthiness of these Turbomeca Artouste III series 
engines in France.

FAA's Determination and Requirements of the Proposed AD

    These Turbomeca Artouste III series turboshaft engines, 
manufactured in France, are type-certificated for operation in the 
United States under the provisions of section 21.29 of the Federal 
Aviation Regulations (14 CFR 21.29) and the applicable bilateral 
airworthiness agreement. In keeping with this bilateral airworthiness 
agreement, the DGAC kept us informed of the situation described above. 
We have examined the DGAC's findings, reviewed all available 
information, and determined that AD action is necessary for products of 
this type design that are certificated for operation in the United 
States. For this reason, we are proposing this AD, which would require 
adding two additional water drain holes to the engine air intake 
assembly. The proposed AD would require you to use the service 
information described previously to perform these actions.

Costs of Compliance

    There are about 1,062 engines of the affected design in the 
worldwide fleet. We estimate that this proposed AD would affect 59 
engines installed on helicopters of U.S. registry. We also estimate 
that it would take about two work hours per engine to perform the 
proposed actions, and that the average labor rate is $65 per work hour. 
Based on these figures, we estimate the total cost of the proposed AD 
to U.S. operators to be $7,670.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and

[[Page 17370]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Would 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 proposal 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.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 14 CFR part 39 as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

Turbomeca: Docket No. FAA-2005-20849; Directorate Identifier 2005-
NE-04-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by June 6, 
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 
an additional water drain hole in each engine air intake assembly 
half-cover, using paragraphs 2.B.(1) through 2.B.(5) of Turbomeca 
Artouste III Service Bulletin (SB) No. 218 72 0104, dated December 
24, 2003.

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.

    Issued in Burlington, Massachusetts, on March 30, 2005.
Diane Cook,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-6774 Filed 4-5-05; 8:45 am]
BILLING CODE 4910-13-P
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