Airworthiness Directives; Bell Helicopter Textron Canada Model 206A and 206B Helicopters, 65443-65445 [E7-22415]

Download as PDF Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations their immediate family member has not made a referral. (3) Business associates and family members. All transactions under this section with business associates or family members not specifically prohibited by paragraph (g)(1) of this section must be conducted at arm’s length and in the interest of the federal credit union. (4) Definitions. The definitions in § 701.21(c)(8)(ii) of this part apply to this section. [FR Doc. E7–22709 Filed 11–20–07; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0176; Directorate Identifier 2007–SW–14–AD; Amendment 39–15263; AD 2007–23–17] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 206A and 206B Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206A and 206B helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The aviation authority of Canada, with which we have a bilateral agreement, states in the MCAI: rmajette on PROD1PC64 with RULES Reevaluation of the structural analysis indicates the need for the removal from service of bolts in this application. The removal of certain main rotor latch bolts is required because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of control of the helicopter. We are issuing this AD to require actions to correct this unsafe condition on these products. DATES: This AD becomes effective December 6, 2007. We must receive comments on this AD by January 22, 2008. ADDRESSES: You may send comments by any of the following methods: VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Deliver to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590 between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD may contain text copied from the MCAI and for this reason might not follow our plain language principles. Discussion Transport Canada, which is the aviation authority for Canada, has issued Airworthiness Directive No. CF– 2006–23R1, dated March 12, 2007 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 65443 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for these Canadian-certificated products. The MCAI states: Reevaluation of the structural analysis indicates the need for the removal from service of bolts in this application. The removal of certain main rotor latch bolts is required because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of control of the helicopter. We are issuing this AD to require actions to correct this unsafe condition on these products. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bell Helicopter Textron has issued Alert Service Bulletin No. 206–06–109, dated July 25, 2006. The actions described in this MCAI are intended to correct the same unsafe condition identified in the service information. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of Canada, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, we have been notified of the unsafe condition described in the MCAI and the referenced service information. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. The removal of certain bolts is required within 30 days because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of the helicopter. We are issuing this AD to require actions to correct this unsafe condition on these products. Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. E:\FR\FM\21NOR1.SGM 21NOR1 65444 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations Authority for This Rulemaking § 39.13 An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the affected bolts may fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of the helicopter. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. I Comments Invited Regulatory Findings This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0176; Directorate Identifier 2007–SW–14–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. We 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 this AD: 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 and placed it in the AD docket. Cost of Compliance Air transportation, Aircraft, Aviation safety, Safety. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in the ‘‘Differences Between the FAA AD and the MCAI’’ section within the AD. rmajette on PROD1PC64 with RULES FAA’s Determination of the Effective Date We estimate this proposed AD would affect about 1463 products of U.S. registry. We also estimate that it would take about 6 work hours per helicopter to replace affected bolts if not done as part of the scheduled main rotor hub disassembly. The average labor rate is $80 per work-hour. Required parts would cost about $1414 per helicopter. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $2,770,992, or $1894 per helicopter. VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 List of Subjects in 14 CFR Part 39 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: 2007–23–17 Bell Helicopter Textron Canada: Amendment 39–15263. Docket No. FAA–2007–0176; Directorate Identifier 2007–SW–14–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 6, 2007. Other Affected ADs (b) None. Applicability (c) This AD applies to Model 206A and 206B helicopters, up to and including serial number 3216, with a main rotor latch bolt, part number 206–010–169–001, 206–010– 169–003, or 206–011–122–003, certificated in any category. Reason (d) The mandatory continued airworthiness information (MCAI) states: Reevaluation of the structural analysis indicates the need for the removal from service of bolts in this application. The removal of certain main rotor latch bolts is required because these bolts do not have a mandatory retirement life. Further evaluation has shown that these bolts fail prematurely due to fatigue. This fatigue failure may result in failure of the main rotor and subsequent loss of the helicopter. Actions and Compliance (e) Within 30 days, remove from service each main rotor latch bolt that has a P/N that is included in the applicability of this AD and replace it with an airworthy bolt. Differences Between the FAA AD and the MCAI (f) None. Subject (g) Air Transport Association of America (ATA) Code: 6200 Main Rotor System. Other Information (h) The following information also applies to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Rotorcraft Directorate, Safety Management Group, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Sharon Miles, Aviation Safety Engineer, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5122, fax (817) 222–5961. (2) Airworthy Product: Use only FAA approved corrective actions. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent) if the State of Design has an appropriate bilateral agreement with the United States. You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, E:\FR\FM\21NOR1.SGM 21NOR1 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (i) Mandatory continuing Airworthiness Information (MCAI) Transport Canada Airworthiness Directive No. CF–2006–23–R1, dated March 12, 2007, and Bell Helicopter Textron Alert Service Bulletin No. 206–06– 109, dated July 25, 2006, contain related information. Issued in Fort Worth, Texas, on November 2, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–22415 Filed 11–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD; Amendment 39–15270; AD 2007–24–04] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. CFM56–5C4/1 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. rmajette on PROD1PC64 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for CFM International, S.A. CFM56–5C4/1 series turbofan engines. That AD currently requires that the low pressure turbine (LPT) conical support, part number (P/N) 337–002–407–0, be removed from service at or before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). This AD requires that the same P/N LPT conical support be removed from service before reaching the new, relaxed cyclic life limit of 20,000 CSN. This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337–002–407–0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. DATES: Effective December 6, 2007. We must receive any comments on this AD by January 22, 2008. ADDRESSES: Use one of the following addresses to comment on this AD: VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Docket Management Facility, Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On August 15, 2001, we issued AD 2001–17–14, Amendment 39–12405 (66 FR 44297, August 23, 2001). That AD requires that the CFM56–5C4/1 series turbofan engine LPT conical support, P/N 337–002–407–0, be removed from service at or before reaching the cyclic life limit of 9,350 CSN. That AD was the result of the discovery of an error in the Time Limits Section of Chapter 5 of the CFM56–5C Engine Shop Manual. The manual incorrectly listed the published cyclic life limit of the CFM56–5C4/1 turbofan engine LPT conical support, P/N 337–002–407–0, as 15,000 CSN, rather than the certified value of 9,350 CSN. Actions Since We Issued AD 2001–17– 14 Since we issued AD 2001–17–14, CFM International, S.A. performed a life extension study of the CFM56–5C4/1 engine LPT conical support, P/N 337– 002–407–0. The results of the study show that the calculated cyclic life limit is above 20,000 CSN. Based on the study, CFM International, S.A. has now established a relaxed certified cyclic life limit of 20,000 CSN for this part. FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these CFM56–5C4/1 turbofan engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other turbofan engines of the same type design. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 65445 certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. This AD requires that the CFM56–5C4/1 series turbofan engine LPT conical support, P/N 337–002–407–0, be removed from service at or before reaching the new, relaxed cyclic life limit of 20,000 CSN. Applicability Paragraph Correction In AD 2001–17–14, we incorrectly stated that the engines were installed on, but not limited to, Airbus A320 series airplanes. In this AD we corrected the airplane model to A340 series airplanes. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. Therefore, a situation exists that allows the immediate adoption of this regulation. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to https:// www.regulations.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 the Federal Docket Management System 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 19477–19478). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, E:\FR\FM\21NOR1.SGM 21NOR1

Agencies

[Federal Register Volume 72, Number 224 (Wednesday, November 21, 2007)]
[Rules and Regulations]
[Pages 65443-65445]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22415]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0176; Directorate Identifier 2007-SW-14-AD; 
Amendment 39-15263; AD 2007-23-17]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206A and 206B Helicopters

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Bell 
Helicopter Textron Canada (BHTC) Model 206A and 206B helicopters. This 
AD results from mandatory continuing airworthiness information (MCAI) 
originated by an aviation authority to identify and correct an unsafe 
condition on an aviation product. The aviation authority of Canada, 
with which we have a bilateral agreement, states in the MCAI:

    Reevaluation of the structural analysis indicates the need for 
the removal from service of bolts in this application.

The removal of certain main rotor latch bolts is required because these 
bolts do not have a mandatory retirement life. Further evaluation has 
shown that these bolts fail prematurely due to fatigue. This fatigue 
failure may result in failure of the main rotor and subsequent loss of 
control of the helicopter. We are issuing this AD to require actions to 
correct this unsafe condition on these products.

DATES: This AD becomes effective December 6, 2007.
    We must receive comments on this AD by January 22, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: https://www.regulations.gov. 
Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590 between 
9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the economic evaluation, any 
comments received, and other information. The street address for the 
Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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: 

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This streamlined process will allow us to adopt 
MCAI safety requirements in a more efficient manner and will reduce 
safety risks to the public. This process continues to follow all FAA AD 
issuance processes to meet legal, economic, Administrative Procedure 
Act, and Federal Register requirements. We also continue to meet our 
technical decision-making responsibilities to identify and correct 
unsafe conditions on U.S.-certificated products.
    This AD references the MCAI and related service information that we 
considered in forming the engineering basis to correct the unsafe 
condition. The AD may contain text copied from the MCAI and for this 
reason might not follow our plain language principles.

Discussion

    Transport Canada, which is the aviation authority for Canada, has 
issued Airworthiness Directive No. CF-2006-23R1, dated March 12, 2007 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for these Canadian-certificated products.
    The MCAI states:

    Reevaluation of the structural analysis indicates the need for 
the removal from service of bolts in this application.

The removal of certain main rotor latch bolts is required because these 
bolts do not have a mandatory retirement life. Further evaluation has 
shown that these bolts fail prematurely due to fatigue. This fatigue 
failure may result in failure of the main rotor and subsequent loss of 
control of the helicopter. We are issuing this AD to require actions to 
correct this unsafe condition on these products.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bell Helicopter Textron has issued Alert Service Bulletin No. 206-
06-109, dated July 25, 2006. The actions described in this MCAI are 
intended to correct the same unsafe condition identified in the service 
information.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of Canada, 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with this State of Design Authority, we have been 
notified of the unsafe condition described in the MCAI and the 
referenced service information. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design. The removal of certain bolts is required within 30 days 
because these bolts do not have a mandatory retirement life. Further 
evaluation has shown that these bolts fail prematurely due to fatigue. 
This fatigue failure may result in failure of the main rotor and 
subsequent loss of the helicopter. We are issuing this AD to require 
actions to correct this unsafe condition on these products.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.

[[Page 65444]]

    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in the ``Differences Between the FAA AD and the MCAI'' 
section within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because the 
affected bolts may fail prematurely due to fatigue. This fatigue 
failure may result in failure of the main rotor and subsequent loss of 
the helicopter. Therefore, we determined that notice and opportunity 
for public comment before issuing this AD are impracticable and that 
good cause exists for making this amendment effective in fewer than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-0176; Directorate 
Identifier 2007-SW-14-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Cost of Compliance

    We estimate this proposed AD would affect about 1463 products of 
U.S. registry. We also estimate that it would take about 6 work hours 
per helicopter to replace affected bolts if not done as part of the 
scheduled main rotor hub disassembly. The average labor rate is $80 per 
work-hour. Required parts would cost about $1414 per helicopter. Based 
on these figures, we estimate the cost of the proposed AD on U.S. 
operators to be $2,770,992, or $1894 per helicopter.

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 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 this AD:
    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 and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2007-23-17 Bell Helicopter Textron Canada: Amendment 39-15263. 
Docket No. FAA-2007-0176; Directorate Identifier 2007-SW-14-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
6, 2007.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 206A and 206B helicopters, up to 
and including serial number 3216, with a main rotor latch bolt, part 
number 206-010-169-001, 206-010-169-003, or 206-011-122-003, 
certificated in any category.

Reason

    (d) The mandatory continued airworthiness information (MCAI) 
states:

    Reevaluation of the structural analysis indicates the need for 
the removal from service of bolts in this application.

The removal of certain main rotor latch bolts is required because 
these bolts do not have a mandatory retirement life. Further 
evaluation has shown that these bolts fail prematurely due to 
fatigue. This fatigue failure may result in failure of the main 
rotor and subsequent loss of the helicopter.

Actions and Compliance

    (e) Within 30 days, remove from service each main rotor latch 
bolt that has a P/N that is included in the applicability of this AD 
and replace it with an airworthy bolt.

Differences Between the FAA AD and the MCAI

    (f) None.

Subject

    (g) Air Transport Association of America (ATA) Code: 6200 Main 
Rotor System.

Other Information

    (h) The following information also applies to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Rotorcraft Directorate, Safety Management Group, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Sharon 
Miles, Aviation Safety Engineer, Regulations and Guidance Group, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 
222-5961.
    (2) Airworthy Product: Use only FAA approved corrective actions. 
Corrective actions are considered FAA-approved if they are approved 
by the State of Design Authority (or their delegated agent) if the 
State of Design has an appropriate bilateral agreement with the 
United States. You are required to assure the product is airworthy 
before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act,

[[Page 65445]]

the Office of Management and Budget (OMB) has approved the 
information collection requirements and has assigned OMB Control 
Number 2120-0056.

Related Information

    (i) Mandatory continuing Airworthiness Information (MCAI) 
Transport Canada Airworthiness Directive No. CF-2006-23-R1, dated 
March 12, 2007, and Bell Helicopter Textron Alert Service Bulletin 
No. 206-06-109, dated July 25, 2006, contain related information.

    Issued in Fort Worth, Texas, on November 2, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-22415 Filed 11-20-07; 8:45 am]
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