Airworthiness Directives; Eurocopter France Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters, 36482-36484 [05-12418]

Download as PDF 36482 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations in the AD docket shortly after the DMS receives them. PART 39—AIRWORTHINESS DIRECTIVES Authority for This Rulemaking I 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 the 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. 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 by sending a request to us 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 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 VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 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: I 2005–13–25 Turbomeca S.A.: Amendment 39–14162. Docket No. FAA–2005–21624; Directorate Identifier 2005–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 11, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arriel 2B turboshaft engines with Modification TU62A incorporated. These engines are installed on, but not limited to, Eurocopter AS350B3 helicopters. 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 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/code_of_federal_regulations/ ibr_locations.html. Issued in Burlington, Massachusetts, on June 16, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–12415 Filed 6–23–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Unsafe Condition (d) This AD results from several reports of the hydromechanical unit (HMU) acceleration controller axle sticking. We are issuing this AD to prevent loss of control of engine fuel flow in the manual control mode or mixed control mode, leading to engine overspeed and in-flight engine shutdown, or uncommanded in-flight engine shutdown. Federal Aviation Administration 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. (f) Within 20 operating hours after the effective date of this AD, inspect, clean, lubricate, and check for proper operation of the HMU acceleration controller axle. Use paragraph 2 of Instructions to be Incorporated of Turbomeca Alert Mandatory Service Bulletin No. A292 73 2814, Update No. 1, dated January 11, 2005, to do these actions. (g) Thereafter, repeat the actions specified in paragraph (f) of this AD within every 210 operating hours. Airworthiness Directives; Eurocopter France Model EC 155B, EC155B1, SA– 365N, SA–365N1, AS–365N2, and AS 365 N3 Helicopters Alternative Methods of Compliance (h) 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 (i) DGAC airworthiness directive F–2004– 139, dated August 18, 2004, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Alert Mandatory Service Bulletin (ASB) No. A292 73 2814, Update No. 1, dated January 11, 2005, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2005–20512; Directorate Identifier 2004–SW–35–AD; Amendment 39– 14160; AD 2005–13–23] RIN 2120–AA64 Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, SA–365N and N1, AS– 365N2, and AS 365 N3 helicopters. That AD currently requires inspecting the hydraulic brake hose (hose) for crazing, pinching, distortion, or leaks at the torque link hinge and replacing the hose, if necessary. That AD also requires inspecting the hose and the emergency flotation gear pipe to ensure adequate clearance, and adjusting the landing gear leg, if necessary. This amendment requires the same actions as the existing AD and adds another model helicopter to the applicability. This amendment is prompted by notification by the manufacturer and the European Authority that another affected model helicopter, the Model EC155B1, may have the same unsafe condition and should be added to the existing AD. The actions specified by this AD are intended to prevent failure of a hose, E:\FR\FM\24JNR1.SGM 24JNR1 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel, and subsequent loss of control of the helicopter during a runon landing. DATES: Effective July 29, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 29, 2005. ADDRESSES: You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. Examining the Docket You may examine the docket that contains this AD, any comments, and other information on the Internet at https://dms.dot.gov, or at the Docket Management System (DMS), U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, on the plaza level of the Nassif Building, Washington, DC. FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by superseding AD 2003–18–03, Amendment 39–13294 (68 FR 52832, September 8, 2003), for the specified model helicopters was published in the Federal Register on March 8, 2005 (70 FR 11166). The action proposed to add the Eurocopter Model EC155B1 helicopters to the applicability and continue to require, within the next 10 hours time-in-service (TIS), inspecting the hose for crazing, pinching, distortion, or leaks at the torque link hinge and replacing the hose before further flight, if necessary. Also proposed was continuing to require, at the next 100-hour TIS inspection, inspecting the hose and the emergency flotation gear pipe to ensure adequate clearance, and adjusting the landing gear leg, if necessary. ´ ´ The Direction Generale De L’Aviation Civile (DGAC), the airworthiness authority for France, notified us that an unsafe condition may exist on Eurocopter Model EC 155 B1 helicopters as well as the other affected model helicopters that are included in AD 2003–18–03. The DGAC has advised in their AD No. F–2004–099, dated July 7, 2004, that a report of a wheel brake hose compression due to interference with a clamp that attaches the emergency VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 flotation gear pipe led to the issue of AD No. 2002–475–007, which defined measures applicable to EC 155 version B aircraft. DGAC AD No. 2002–475–007 was cancelled by its Revision 1, and the DGAC issued AD No. F–2004–099, dated July 7, 2004, which supersedes and covers the requirements of AD 2002–475–007, extends its affectivity to EC 155 version B1 aircraft, and refers to revised service information, with no change to the technical content. The DGAC issued that AD after Eurocopter issued Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004. The revised service bulletin added the Eurocopter Model EC155B1 to it’s applicability but didn’t change any technical content. Eurocopter has also replaced Alert Telex No. 32.00.09, dated July 31, 2002, with Alert Service Bulletin No. 32.00.09, dated October 27, 2003 that contained no technical changes. The service bulletin applies to Eurocopter Model AS365N, N1, N2, and N3 helicopters. The DGAC classified this service bulletin as mandatory and issued AD No. F–2002–474–058 R1, dated March 3, 2004. This superseding AD contains references to both of these revised documents. These helicopter models are manufactured in France and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the DGAC has kept us informed of the situation described above. We have examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or on our determination of the cost to the public. We have determined that air safety and the public interest require the adoption of the rule as proposed. We estimate that this AD will affect 48 helicopters of U.S. registry. It will take approximately 5 work hours per helicopter to accomplish each inspection and 5 work hours to replace any parts, as necessary. The average labor rate is $65 per work hour. Required parts will cost approximately $459 for the hose; if replacing the hose on two sides is required, the cost is approximately $918. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $1,568 per helicopter, or $56,448 for the PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 36483 entire fleet, assuming 75 percent of the fleet (36 helicopters) is equipped with emergency flotation gear, that one inspection is done, and that the hose on two sides is replaced on those 36 helicopters). 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 the 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. 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 an economic evaluation of the estimated costs to comply with this AD. See the DMS to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration I E:\FR\FM\24JNR1.SGM 24JNR1 36484 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39–13294 (68 FR 52832, September 8, 2003), and by adding a new airworthiness directive (AD), Amendment 39–14160, to read as follows: I 2005–13–23 Eurocopter France: Amendment 39–14160. Docket No. FAA–2005–20512; Directorate Identifier 2004–SW–35–AD. Supersedes AD 2003– 18–03, Amendment 39–13294, Docket No. 2002–SW–53–AD. Applicability: Model EC 155B, EC155B1, SA–365N, SA–365N1, AS–365N2, and AS 365 N3 helicopters, with emergency flotation gear installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of a hydraulic brake hose (hose), resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel and subsequent loss of control of the helicopter during a run-on landing, accomplish the following: (a) Within 10 hours time-in-service (TIS), inspect the hose for crazing, pinching, distortion, or leaks as illustrated in Area A of Figure 1 of Eurocopter Alert Service Bulletin No. 32.00.09, dated October 27, 2003 (ASB No. 32.00.09), for Model SA–365N and N1, AS–365N2, and AS 365 N3 helicopters, and Eurocopter Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004 (ASB No. 32A004R1), for Model EC 155B and EC155B1 helicopters. (b) If crazing, pinching, distortion, or leaks exist, replace the hose with an airworthy hose before further flight. (c) At the next 100-hour TIS inspection, inspect the hose and the emergency flotation gear pipe to ensure adequate clearance and adjust the landing gear leg, if necessary, in accordance with the Operational Procedure, paragraph 2.B.2., of ASB No. 32.00.09 or ASB No. 32A004R1, as applicable. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (e) The inspections and adjustments shall be done in accordance with the specified portions of Eurocopter Alert Service Bulletin No. 32.00.09, dated October 27, 2003, or Eurocopter Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 Forum Drive, Grand Prairie, Texas 75053– 4005, telephone (972) 641–3460, fax (972) 641–3527. Copies may be inspected at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. (f) This amendment becomes effective on July 29, 2005. Note: The subject of this AD is addressed ´ ´ in Direction Generale De L’Aviation Civile (France) AD No. F–2002–474–058 R1, dated March 3, 2004 and AD No. F–2004–099, dated July 7, 2004. Issued in Fort Worth, Texas, on June 10, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–12418 Filed 6–23–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21589; Directorate Identifier 2004–SW–44–AD; Amendment 39– 14154; AD 2005–13–17] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Model AB412 Series Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for the Agusta S.p.A. (Agusta) Model AB412 Series helicopters. This action requires inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids, and removing any blade with an excessive void from service. This AD also requires modifying certain blades by installing shear pins and tip closure rivets on all affected blades. This amendment is prompted by reports of in-flight loss of tip blocks and tip closures resulting in minor to substantial damage. The actions specified in this AD are intended to prevent loss of the tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter. DATES: Effective July 11, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 of the Federal Register as of July 11, 2005. Comments for inclusion in the Rules Docket must be received on or before August 23, 2005. ADDRESSES: Use one of the following addresses to submit comments on this 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; • Fax: (202) 493–2251; or • 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. You may get the service information identified in this AD from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605–222595. Examining the Docket You may examine the docket that contains the AD, any comments, and other information on the Internet at https://dms.dot.gov, or in person at the Docket Management System (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 located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Agusta Model AB412 Series helicopters. This action requires inspecting the tip block and the tip closure for adhesive bond voids and removing any blade with an excessive void from service. This action also requires modifying certain blades by installing shear pins and tip closure rivets in the tip area of all affected blades. This amendment is prompted by reports of in-flight loss of tip blocks and tip closures resulting in minor to E:\FR\FM\24JNR1.SGM 24JNR1

Agencies

[Federal Register Volume 70, Number 121 (Friday, June 24, 2005)]
[Rules and Regulations]
[Pages 36482-36484]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12418]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20512; Directorate Identifier 2004-SW-35-AD; 
Amendment 39-14160; AD 2005-13-23]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC 155B, 
EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Eurocopter France (Eurocopter) Model EC 155B, SA-365N and N1, 
AS-365N2, and AS 365 N3 helicopters. That AD currently requires 
inspecting the hydraulic brake hose (hose) for crazing, pinching, 
distortion, or leaks at the torque link hinge and replacing the hose, 
if necessary. That AD also requires inspecting the hose and the 
emergency flotation gear pipe to ensure adequate clearance, and 
adjusting the landing gear leg, if necessary. This amendment requires 
the same actions as the existing AD and adds another model helicopter 
to the applicability. This amendment is prompted by notification by the 
manufacturer and the European Authority that another affected model 
helicopter, the Model EC155B1, may have the same unsafe condition and 
should be added to the existing AD. The actions specified by this AD 
are intended to prevent failure of a hose,

[[Page 36483]]

resulting in failure of hydraulic pressure to the brakes on the 
affected landing gear wheel, and subsequent loss of control of the 
helicopter during a run-on landing.

DATES: Effective July 29, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 29, 2005.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.

Examining the Docket

    You may examine the docket that contains this AD, any comments, and 
other information on the Internet at https://dms.dot.gov, or at the 
Docket Management System (DMS), U.S. Department of Transportation, 400 
Seventh Street, SW., Room PL-401, on the plaza level of the Nassif 
Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2003-18-03, Amendment 39-13294 (68 FR 52832, September 
8, 2003), for the specified model helicopters was published in the 
Federal Register on March 8, 2005 (70 FR 11166). The action proposed to 
add the Eurocopter Model EC155B1 helicopters to the applicability and 
continue to require, within the next 10 hours time-in-service (TIS), 
inspecting the hose for crazing, pinching, distortion, or leaks at the 
torque link hinge and replacing the hose before further flight, if 
necessary. Also proposed was continuing to require, at the next 100-
hour TIS inspection, inspecting the hose and the emergency flotation 
gear pipe to ensure adequate clearance, and adjusting the landing gear 
leg, if necessary.
    The Direction G[eacute]n[eacute]rale De L'Aviation Civile (DGAC), 
the airworthiness authority for France, notified us that an unsafe 
condition may exist on Eurocopter Model EC 155 B1 helicopters as well 
as the other affected model helicopters that are included in AD 2003-
18-03. The DGAC has advised in their AD No. F-2004-099, dated July 7, 
2004, that a report of a wheel brake hose compression due to 
interference with a clamp that attaches the emergency flotation gear 
pipe led to the issue of AD No. 2002-475-007, which defined measures 
applicable to EC 155 version B aircraft. DGAC AD No. 2002-475-007 was 
cancelled by its Revision 1, and the DGAC issued AD No. F-2004-099, 
dated July 7, 2004, which supersedes and covers the requirements of AD 
2002-475-007, extends its affectivity to EC 155 version B1 aircraft, 
and refers to revised service information, with no change to the 
technical content. The DGAC issued that AD after Eurocopter issued 
Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004. The 
revised service bulletin added the Eurocopter Model EC155B1 to it's 
applicability but didn't change any technical content.
    Eurocopter has also replaced Alert Telex No. 32.00.09, dated July 
31, 2002, with Alert Service Bulletin No. 32.00.09, dated October 27, 
2003 that contained no technical changes. The service bulletin applies 
to Eurocopter Model AS365N, N1, N2, and N3 helicopters. The DGAC 
classified this service bulletin as mandatory and issued AD No. F-2002-
474-058 R1, dated March 3, 2004. This superseding AD contains 
references to both of these revised documents.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, the DGAC has kept us informed of the 
situation described above. We have examined the findings of the DGAC, 
reviewed all available information, and determined that AD action is 
necessary for products of these type designs that are certificated for 
operation in the United States.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or on our determination of the cost to the public. We have 
determined that air safety and the public interest require the adoption 
of the rule as proposed.
    We estimate that this AD will affect 48 helicopters of U.S. 
registry. It will take approximately 5 work hours per helicopter to 
accomplish each inspection and 5 work hours to replace any parts, as 
necessary. The average labor rate is $65 per work hour. Required parts 
will cost approximately $459 for the hose; if replacing the hose on two 
sides is required, the cost is approximately $918. Based on these 
figures, the total cost impact of this AD on U.S. operators is 
estimated to be $1,568 per helicopter, or $56,448 for the entire fleet, 
assuming 75 percent of the fleet (36 helicopters) is equipped with 
emergency flotation gear, that one inspection is done, and that the 
hose on two sides is replaced on those 36 helicopters).

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 the 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. 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 an economic evaluation of the estimated costs to comply 
with this AD. See the DMS to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration

[[Page 36484]]

amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-13294 (68 FR 
52832, September 8, 2003), and by adding a new airworthiness directive 
(AD), Amendment 39-14160, to read as follows:

2005-13-23 Eurocopter France: Amendment 39-14160. Docket No. FAA-
2005-20512; Directorate Identifier 2004-SW-35-AD. Supersedes AD 
2003-18-03, Amendment 39-13294, Docket No. 2002-SW-53-AD.

    Applicability: Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-
365N2, and AS 365 N3 helicopters, with emergency flotation gear 
installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of a hydraulic brake hose (hose), resulting 
in failure of hydraulic pressure to the brakes on the affected 
landing gear wheel and subsequent loss of control of the helicopter 
during a run-on landing, accomplish the following:
    (a) Within 10 hours time-in-service (TIS), inspect the hose for 
crazing, pinching, distortion, or leaks as illustrated in Area A of 
Figure 1 of Eurocopter Alert Service Bulletin No. 32.00.09, dated 
October 27, 2003 (ASB No. 32.00.09), for Model SA-365N and N1, AS-
365N2, and AS 365 N3 helicopters, and Eurocopter Alert Service 
Bulletin No. 32A004, Revision 1, dated June 16, 2004 (ASB No. 
32A004R1), for Model EC 155B and EC155B1 helicopters.
    (b) If crazing, pinching, distortion, or leaks exist, replace 
the hose with an airworthy hose before further flight.
    (c) At the next 100-hour TIS inspection, inspect the hose and 
the emergency flotation gear pipe to ensure adequate clearance and 
adjust the landing gear leg, if necessary, in accordance with the 
Operational Procedure, paragraph 2.B.2., of ASB No. 32.00.09 or ASB 
No. 32A004R1, as applicable.
    (d) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.
    (e) The inspections and adjustments shall be done in accordance 
with the specified portions of Eurocopter Alert Service Bulletin No. 
32.00.09, dated October 27, 2003, or Eurocopter Alert Service 
Bulletin No. 32A004, Revision 1, dated June 16, 2004, as applicable. 
The Director of the Federal Register approved this incorporation by 
reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Copies may be obtained from American Eurocopter Corporation, 2701 
Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-
3460, fax (972) 641-3527. Copies may be inspected at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
    (f) This amendment becomes effective on July 29, 2005.

    Note: The subject of this AD is addressed in Direction 
G[eacute]n[eacute]rale De L'Aviation Civile (France) AD No. F-2002-
474-058 R1, dated March 3, 2004 and AD No. F-2004-099, dated July 7, 
2004.


    Issued in Fort Worth, Texas, on June 10, 2005.
S. Frances Cox,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-12418 Filed 6-23-05; 8:45 am]
BILLING CODE 4910-13-P
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