Airworthiness Directives; Eurocopter France Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and B1 Helicopters, 25930-25932 [06-4108]

Download as PDF 25930 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference (j) You must use Boeing Special Attention Service Bulletin 767–53–0118, dated September 8, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http://www. archives.gov/federal_register/code_of_ federal_regulations/ibr_locations.html. is present. This amendment is prompted by one incident in which a pilot lost T/ R pitch control of a helicopter while landing. The actions specified in this AD are intended to detect damage to the bearing, resulting in end play and prevent loss of T/R pitch control and subsequent loss of control of the helicopter. [Docket No. FAA–2006–24588; Directorate Identifier 2006–SW–07–AD; Amendment 39– 14581; AD 2006–09–10] Effective May 18, 2006. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 18, 2006. Comments for inclusion in the Rules Docket must be received on or before July 3, 2006. ADDRESSES: Use one of the following addresses to submit comments on this 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 http://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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. RIN 2120–AA64 Examining the Docket Issued in Renton, Washington, on April 21, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–4055 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Eurocopter France Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 helicopters. This action requires a one-time inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/ R) hub control plate, and before further flight, replacing the bearing if end play VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 DATES: You may examine the docket that contains the AD, any comments, and other information on the Internet at http://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: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 This amendment adopts a new AD for Eurocopter Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 helicopters. This action requires, within 50 hours time-in-service (TIS), a one-time inspection of the T/R hub control plate for end play in the bearing, and if end play is present, replacing the bearing before further flight. This amendment is prompted by one incident in which a pilot lost T/R pitch control of a helicopter while landing. The loss of the T/R pitch control was due to significant damage to the bearing of the control rod in the tail gearbox. This condition, if not detected, could result in loss of T/R pitch control and subsequent loss of control of the helicopter. The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on Eurocopter France Model AS 365 N, SA 366, and EC 155 helicopters. EASA advises that the loss of pitch control is due to significant damage to the bearing of the control rod in the tail gearbox. Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.52, applicable to the Model 365 N1, N2, and N3 helicopters; ASB No. 05.36, applicable to Model 366 G1 helicopters; and ASB No. 05A013, applicable to Model EC– 155B and B1 helicopters, all dated February 15, 2006, and all of which specify a check at regular intervals to ensure there is no end play in the bearing of the T/R pitch control rod. EASA classified this ASB as mandatory and issued AD No. 2006–0051–E, dated February 20, 2006, to ensure the continued airworthiness of these helicopters in France. This AD does not require repetitive inspections because helicopters in this fleet do not normally accrue enough flight hours in a short period of time to justify issuing an immediately adopted final rule requiring repetitive inspections without allowing the public time to first comment on such a proposal. We may issue further AD action at a later date to propose repetitive 110-hours TIS inspections. This helicopter model is manufactured in France and is type certificated for operation in the United States under the provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral agreement. Under this agreement, EASA has kept the FAA informed of the situation described above. We have examined EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for products of this type design that are SUPPLEMENTARY INFORMATION: E:\FR\FM\03MYR1.SGM 03MYR1 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations certificated for operation in the United States. This unsafe condition is likely to exist or develop on other helicopters of the same type designs. Therefore, this AD is being issued to detect damage to the bearing, resulting in end play and prevent loss of T/R pitch control and subsequent loss of control of the helicopter. This AD requires, within 50 hours TIS, a one-time inspection of the T/R hub control plate for end play in the bearing, and if end play is present, replacing the bearing before further flight. Accomplish the actions by following the specified portions of the ASB described previously. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. Therefore, inspecting for end play in the bearing is required within 50 hours TIS and replacing the bearing, if necessary, is required before further flight and this AD must be issued immediately. This AD is an interim action until Eurocopter completes bench tests to analyze the effect of the oil level, associated with pitch control loads, on the behavior of the bearing. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. We estimate that this AD will affect 137 helicopters. The one-time inspection will take approximately 1 work hour, and replacing the bearing, if needed, will take approximately 8 work hours to accomplish at an average labor rate of $80 per work hour. Required parts will cost approximately $2,026 per helicopter. Based on these figures, the total cost impact of the AD on U.S. operators is $365,242, assuming the bearing is replaced on the entire fleet. sroberts on PROD1PC70 with RULES Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–24588; Directorate Identifier 2006–SW–07–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 amend the AD in light of those comments. We will post all comments we receive, without change, to http:// 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 AD. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. 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 http://dms.dot.gov. 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 25931 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 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2006–09–10 Eurocopter France: Amendment 39–14581. Docket No. FAA–2006–24588; Directorate Identifier 2006–SW–07–AD. Applicability: Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 helicopters, with a tail rotor (T/R) pitch control rod assembly double bearing (bearing) installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect damage to the bearing resulting in end play and to prevent loss of T/R pitch control and subsequent loss of control of the helicopter: (a) Within 50 hours time-in-service, inspect the T/R hub control plate for end play in the bearing in accordance with paragraph 2.B., Operational Procedure, in Eurocopter Alert Service Bulletin No. 05.00.52, applicable to Model SA–365 N1 and AS–365 N2 and N3 helicopters; No. 05.36, applicable to Model SA 366 G1 helicopters; and No. 05A013, applicable to Model EC–155B and B1 helicopters, dated February 15, 2006 (ASBs). (b) If end play is present, before further flight, replace the bearing with an airworthy bearing. You are not required to contact the manufacturer to meet the requirements of this AD. (c) 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 Manager, Regulations Group, Rotorcraft Directorate, FAA, ATTN: Uday Garadi, 2601 Meacham Blvd., Fort Worth, Texas, 76193, telephone (817) 222– 5123, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) The inspection and replacement, if necessary, shall be done in accordance with the specified portions of Eurocopter Alert Service Bulletin No. 05.00.52, applicable to E:\FR\FM\03MYR1.SGM 03MYR1 25932 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations Model SA–365 N1 and SA–365 N2 and N3 helicopters; No. 05.36, applicable to Model SA 366 G1 helicopters; and No. 05A013, applicable to Model EC–155B and B1 helicopters, dated February 15, 2006. 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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. (f) This amendment becomes effective on May 18, 2006. Note: The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2006–0051–E, dated February 20, 2006. Issued in Fort Worth, Texas, on April 17, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–4108 Filed 5–2–06; 8:45 am] regulations is approved by the Director of the Federal Register as of May 3, 2006. Availability of matter incorporated by reference in the amendment is as follows: ADDRESSES: For Examination 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Ave, SW., Washington, DC 20591; 2. The FAA Regional Office of the region in which affected airport is located; or 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. 4. The National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/ federal_register/ code_of_federal_regulations/ ibr_locations.html. For Purchase 14 CFR Part 97 Individual SIAP copies may be obtained from: 1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue, SW., Washington, DC 20591; or 2. The FAA Regional Office of the region in which the affected airport is located. [Docket No. 30492; Amdt. No. 3165] By Subscription BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Standard Instrument Approach Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: This amendment amends Standard Instrument Approach Procedures (SIAPs) for operations at certain airports. These regulatory actions are needed because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, addition of new obstacles, or changes in air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. DATES: This rule is effective May 3, 2006. The compliance date for each SIAP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 Copies of all SIAPs, mailed once every 2 weeks, are for sale by the Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402. FOR FURTHER INFORMATION CONTACT: Donald P. Pate, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd. Oklahoma City, OK. 73169 (Mail Address: P.O. Box 25082 Oklahoma City, OK. 73125) telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This amendment to Title 14, Code of Federal Regulations, part 97 (14 CFR part 97) amends Standard Instrument Approach Procedures (SIAPs). The complete regulatory description of each SIAP is contained in the appropriate FAA Form 8260, as modifiedby the the National Flight Data Center (FDC)/Permanent Notice to Airmen (P-NOTAM), which is incorporated by reference in the amendment under 5 U.S.C. 552(a), 1 CFR part 51, and § 97.20 of the Code of PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Federal Regulations. Materials incorporated by reference are available for examination or purchase as stated above. The large number of SIAPs, their complex nature, and the need for a special format make their verbatim publication in the Federal Register expensive and impractical. Further, airmen do not use the regulatory text of the SIAPs, but refer to their graphic depiction on charts printed by publishers of aeronautical materials. Thus, the advantages of incorporation by reference are realized and publication of the complete description of each SIAP contained in FAA form documents is unnecessary. The provisions of this amendment state the affected CFR sections, with the types and effective dates of the SIAPs. This amendment also identifies the airport, its location, the procedure identification and the amendment number. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP as amended in the transmittal. For safety and timeliness of change considerations, this amendment incorporates only specific changes contained for each SIAP as modified by FDC/P–NOTAMs. The SIAPs, as modified by FDC P– NOTAM, and contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these chart changes to SIAPs, the TERPS criteria were applied to only these specific conditions existing at the affected airports. All SIAP amendments in this rule have been previously issued by the FAA in a FDC NOTAM as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances which created the need for all these SIAP amendments requires making them effective in less than 30 days. Further, the SIAPs contained in this amendment are based on the criteria contained in TERPS. Because of the close and immediate relationship between these SIAPs and safety in air commerce, I find that notice and public procedure before adopting these SIAPs are impracticable and contrary to the public interest and, where applicable, that good cause exists for making these SIAPs effective in less than 30 days. Conclusion The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are E:\FR\FM\03MYR1.SGM 03MYR1

Agencies

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25930-25932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4108]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24588; Directorate Identifier 2006-SW-07-AD; 
Amendment 39-14581; AD 2006-09-10]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365 N1, AS-
365 N2, N3, SA 366 G1, and EC-155B and B1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) Model SA-365 N1, AS-365 
N2, N3, SA 366 G1, and EC-155B and B1 helicopters. This action requires 
a one-time inspection for end play in the pitch control rod assembly 
double bearing (bearing) using the tail rotor (T/R) hub control plate, 
and before further flight, replacing the bearing if end play is 
present. This amendment is prompted by one incident in which a pilot 
lost T/R pitch control of a helicopter while landing. The actions 
specified in this AD are intended to detect damage to the bearing, 
resulting in end play and prevent loss of T/R pitch control and 
subsequent loss of control of the helicopter.

DATES: Effective May 18, 2006.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 18, 2006.
    Comments for inclusion in the Rules Docket must be received on or 
before July 3, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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 http://
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 
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 the AD, any comments, and 
other information on the Internet at http://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: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and 
B1 helicopters. This action requires, within 50 hours time-in-service 
(TIS), a one-time inspection of the T/R hub control plate for end play 
in the bearing, and if end play is present, replacing the bearing 
before further flight. This amendment is prompted by one incident in 
which a pilot lost T/R pitch control of a helicopter while landing. The 
loss of the T/R pitch control was due to significant damage to the 
bearing of the control rod in the tail gearbox. This condition, if not 
detected, could result in loss of T/R pitch control and subsequent loss 
of control of the helicopter.
    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on Eurocopter France Model AS 365 N, SA 366, 
and EC 155 helicopters. EASA advises that the loss of pitch control is 
due to significant damage to the bearing of the control rod in the tail 
gearbox.
    Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.52, 
applicable to the Model 365 N1, N2, and N3 helicopters; ASB No. 05.36, 
applicable to Model 366 G1 helicopters; and ASB No. 05A013, applicable 
to Model EC-155B and B1 helicopters, all dated February 15, 2006, and 
all of which specify a check at regular intervals to ensure there is no 
end play in the bearing of the T/R pitch control rod. EASA classified 
this ASB as mandatory and issued AD No. 2006-0051-E, dated February 20, 
2006, to ensure the continued airworthiness of these helicopters in 
France. This AD does not require repetitive inspections because 
helicopters in this fleet do not normally accrue enough flight hours in 
a short period of time to justify issuing an immediately adopted final 
rule requiring repetitive inspections without allowing the public time 
to first comment on such a proposal. We may issue further AD action at 
a later date to propose repetitive 110-hours TIS inspections.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral agreement. Under this agreement, EASA has kept the 
FAA informed of the situation described above. We have examined EASA's 
findings, evaluated all pertinent information, and determined that AD 
action is necessary for products of this type design that are

[[Page 25931]]

certificated for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs. Therefore, this AD is being 
issued to detect damage to the bearing, resulting in end play and 
prevent loss of T/R pitch control and subsequent loss of control of the 
helicopter. This AD requires, within 50 hours TIS, a one-time 
inspection of the T/R hub control plate for end play in the bearing, 
and if end play is present, replacing the bearing before further 
flight. Accomplish the actions by following the specified portions of 
the ASB described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, inspecting for end play 
in the bearing is required within 50 hours TIS and replacing the 
bearing, if necessary, is required before further flight and this AD 
must be issued immediately. This AD is an interim action until 
Eurocopter completes bench tests to analyze the effect of the oil 
level, associated with pitch control loads, on the behavior of the 
bearing.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 137 helicopters. The one-time 
inspection will take approximately 1 work hour, and replacing the 
bearing, if needed, will take approximately 8 work hours to accomplish 
at an average labor rate of $80 per work hour. Required parts will cost 
approximately $2,026 per helicopter. Based on these figures, the total 
cost impact of the AD on U.S. operators is $365,242, assuming the 
bearing is replaced on the entire fleet.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-24588; 
Directorate Identifier 2006-SW-07-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://
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 AD. Using the search function of our docket 
Web site, you can find and read the comments to any of our dockets, 
including the name of the individual who sent the comment. 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 http://
dms.dot.gov.

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 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 adding a new airworthiness directive to 
read as follows:

2006-09-10 Eurocopter France: Amendment 39-14581. Docket No. FAA-
2006-24588; Directorate Identifier 2006-SW-07-AD.

    Applicability: Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and 
EC-155B and B1 helicopters, with a tail rotor (T/R) pitch control 
rod assembly double bearing (bearing) installed, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect damage to the bearing resulting in end play and to 
prevent loss of T/R pitch control and subsequent loss of control of 
the helicopter:
    (a) Within 50 hours time-in-service, inspect the T/R hub control 
plate for end play in the bearing in accordance with paragraph 2.B., 
Operational Procedure, in Eurocopter Alert Service Bulletin No. 
05.00.52, applicable to Model SA-365 N1 and AS-365 N2 and N3 
helicopters; No. 05.36, applicable to Model SA 366 G1 helicopters; 
and No. 05A013, applicable to Model EC-155B and B1 helicopters, 
dated February 15, 2006 (ASBs).
    (b) If end play is present, before further flight, replace the 
bearing with an airworthy bearing. You are not required to contact 
the manufacturer to meet the requirements of this AD.
    (c) 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 Manager, Regulations Group, Rotorcraft Directorate, FAA, 
ATTN: Uday Garadi, 2601 Meacham Blvd., Fort Worth, Texas, 76193, 
telephone (817) 222-5123, fax (817) 222-5961, for information about 
previously approved alternative methods of compliance.
    (d) Special flight permits will not be issued.
    (e) The inspection and replacement, if necessary, shall be done 
in accordance with the specified portions of Eurocopter Alert 
Service Bulletin No. 05.00.52, applicable to

[[Page 25932]]

Model SA-365 N1 and SA-365 N2 and N3 helicopters; No. 05.36, 
applicable to Model SA 366 G1 helicopters; and No. 05A013, 
applicable to Model EC-155B and B1 helicopters, dated February 15, 
2006. 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: http://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html.
    (f) This amendment becomes effective on May 18, 2006.

    Note: The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2006-0051-E, dated February 20, 2006.


    Issued in Fort Worth, Texas, on April 17, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-4108 Filed 5-2-06; 8:45 am]
BILLING CODE 4910-13-P