Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters, 38797-38800 [07-3434]

Download as PDF 38797 Proposed Rules Federal Register Vol. 72, No. 135 Monday, July 16, 2007 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28688; Directorate Identifier 2005–SW–21–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 430 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This document proposes adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters. This proposal would require replacing a certain servo actuator-to-actuator support attachment bolt (bolt) with an airworthy bolt. This proposal would also require establishing a retirement life for certain bolts and recording the retirement life on a component history card or equivalent record. This proposal is prompted by further evaluation of certain fatigue-critical parts, resulting in establishing a life limit of 5000 hours for the affected bolts. The actions specified by this proposed AD are intended to prevent fatigue failure of the bolt and subsequent loss of control of the helicopter. SUMMARY: Comments must be received on or before September 14, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: U.S. Department of Transportation, Docket Operations, M– ycherry on PRODPC74 with PROPOSALS DATES: VerDate Aug<31>2005 15:15 Jul 13, 2007 Jkt 211001 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590; • Fax: 202–493–2251, or • Hand Delivery: West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., 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 proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. 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: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–28688, Directorate Identifier 2005–SW–21–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. 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 or signed 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 https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5527) is located at the West Building Ground Floor, Room WL–140 at 1200 New Jersey Avenue, SE., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on BHTC Model 430 helicopters, serial numbers 49001 through 49106. Transport Canada advises of the need to establish a new airworthiness life limitation of 5000 hours for the three servo actuator support attachment bolts and to replace the three affected bolts. Bell Helicopter Textron has issued Alert Service Bulletin No. 430–05–33, dated February 16, 2005 (ASB). The ASB introduces a retirement life of 5000 hours for the bolts. The ASB states that since these bolts have not been listed in the Helicopter Component Replace record, it is difficult to determine with accuracy the actual number of hours accumulated on fielded bolts. Also, the ASB states that Bell has elected to replace all the fielded bolts, part number (P/N) 50–047C8–31. Transport Canada classified this ASB as mandatory and issued AD No. CF– 2005–09, dated April 14, 2005, to ensure the continued airworthiness of these helicopters in Canada. This helicopter model is manufactured in Canada and is 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, Transport Canada has kept us informed of the situation described above. The upper three bolts of the servo attaching to the collective and cyclic levers have a retirement life of 5000 hours. However, three identical bolts at the lower end of the servos attaching to the actuator support do not have an established life limit. These three bolts may be subject to premature failure due to fatigue causing failure of the actuators and subsequent loss of control of the helicopter. We have examined the findings of Transport E:\FR\FM\16JYP1.SGM 16JYP1 38798 Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules Canada, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Further evaluation of certain fatiguecritical parts resulted in establishing a life limit of 5000 hours for the affected bolts which is intended to prevent fatigue failure of the bolt and subsequent loss of control of the helicopter. Therefore, the proposed AD would require the following: • Within 150 hours time-in-service (TIS), replace all three bolts, P/N 50– 047C8–31, with airworthy, zero-time bolts, P/N 50–047C8–31. • Revise the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5000 hours TIS for each bolt. • Record a 5000-hour TIS life limit for each bolt on the component history card or equivalent record. We estimate that this proposed AD would affect 54 helicopters of U.S. registry. The proposed actions would take about 2 work hours per helicopter to replace 3 bolts at an average labor rate of $80 per work hour. Required parts would cost about $243 for each bolt. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $48,006, assuming that the recordkeeping cost would be negligible. Regulatory Findings ycherry on PRODPC74 with PROPOSALS We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would not have a substantial direct VerDate Aug<31>2005 15:15 Jul 13, 2007 Jkt 211001 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 proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. 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 draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft 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. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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: 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: Bell Helicopter Textron Canada: Docket No. FAA–2007–28688; Directorate Identifier 2005–SW–21–AD. Applicability Model 430 helicopters, serial numbers 49001 through 49106, with a servo actuatorto-actuator support attachment bolt (bolt), part number (P/N) 50–047C8–31, installed, which attaches the lower two cyclic servo actuators and the lower collective servo actuator to the three lower actuator supports, certificated in any category. Compliance Required as indicated, unless accomplished previously. To prevent fatigue failure of the bolt and subsequent loss of control of the helicopter, do the following: (a) Within 150 hours time-in-service (TIS), replace all three affected bolts, as depicted for one of these bolts in Figure 1 of this AD, with airworthy, zero-time bolts, P/N 50– 047C8–31. BILLING CODE 4910–13–P E:\FR\FM\16JYP1.SGM 16JYP1 (b) This AD revises the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5000 hours TIS for each bolt. VerDate Aug<31>2005 15:15 Jul 13, 2007 Jkt 211001 (c) Record a 5000-hour TIS life limit for each bolt on the component history card or equivalent record. (d) To request a different method of compliance or a different compliance time PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 38799 for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas E:\FR\FM\16JYP1.SGM 16JYP1 EP16JY07.009</GPH> ycherry on PRODPC74 with PROPOSALS Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules 38800 Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules 76193–0111, telephone (817) 222–5122, fax (817) 222–5961 for information about previously approved alternative methods of compliance. Note: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF 2005–09, dated April 14, 2005. Issued in Fort Worth, Texas, on July 5, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 07–3434 Filed 7–13–07; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27975; Directorate Identifier 2007–CE–041–AD] RIN 2120–AA64 Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A. Model P–180 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: ycherry on PRODPC74 with PROPOSALS Several aircraft, at the factory, presented some debris in the hydraulic fluid of the steering system. Investigations revealed that some components of the steering system can be responsible for the fluid contamination because of an initial pollution on their manufacturing. If not corrected, a contaminated fluid could cause malfunction and a possible jamming of the steering system. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by August 15, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. VerDate Aug<31>2005 15:15 Jul 13, 2007 Jkt 211001 • 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: 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. • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4145; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–27975; Directorate Identifier 2007–CE–041–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Emergency Airworthiness Directive EAD No: 2007– 0147–E, dated May 22, 2007 (referred to PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Several aircraft, at the factory, presented some debris in the hydraulic fluid of the steering system. Investigations revealed that some components of the steering system can be responsible for the fluid contamination because of an initial pollution on their manufacturing. If not corrected, a contaminated fluid could cause malfunction and a possible jamming of the steering system. The superseded Airworthiness Directive (AD) 2007–0088–E was previously issued to address the unsafe condition. The present Airworthiness Directive expands applicability of this AD to all P.180 ‘Avanti’ series aircraft and the list of defective components as listed in revision 1 of Piaggio Aero Industries Mandatory Service Bulletin No 80–0236. This AD also requires Temporary Changes to the respective Airplane Flight Manual (AFM) and Aircraft Maintenance Manual (AMM) and introduces procedures to recondition defective units. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Piaggio Aero Industries S.p.A. has issued Service Bulletin (Mandatory) N.: 80–0236 Rev. 1, dated May 15, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed 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. We might also have proposed different actions in this AD from those E:\FR\FM\16JYP1.SGM 16JYP1

Agencies

[Federal Register Volume 72, Number 135 (Monday, July 16, 2007)]
[Proposed Rules]
[Pages 38797-38800]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-3434]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / 
Proposed Rules

[[Page 38797]]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28688; Directorate Identifier 2005-SW-21-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters. 
This proposal would require replacing a certain servo actuator-to-
actuator support attachment bolt (bolt) with an airworthy bolt. This 
proposal would also require establishing a retirement life for certain 
bolts and recording the retirement life on a component history card or 
equivalent record. This proposal is prompted by further evaluation of 
certain fatigue-critical parts, resulting in establishing a life limit 
of 5000 hours for the affected bolts. The actions specified by this 
proposed AD are intended to prevent fatigue failure of the bolt and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 14, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590;
     Fax: 202-493-2251, or
     Hand Delivery: West Building Ground Floor, Room W12-140, 
1200 New Jersey Avenue, SE., 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 proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

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: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28688, Directorate Identifier 2005-SW-21-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. 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 or 
signed 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 https://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5527) is located at the West Building Ground Floor, Room WL-140 at 
1200 New Jersey Avenue, SE., Washington, DC. Comments will be available 
in the AD docket shortly after the DMS receives them.

Discussion

    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on BHTC Model 430 
helicopters, serial numbers 49001 through 49106. Transport Canada 
advises of the need to establish a new airworthiness life limitation of 
5000 hours for the three servo actuator support attachment bolts and to 
replace the three affected bolts.
    Bell Helicopter Textron has issued Alert Service Bulletin No. 430-
05-33, dated February 16, 2005 (ASB). The ASB introduces a retirement 
life of 5000 hours for the bolts. The ASB states that since these bolts 
have not been listed in the Helicopter Component Replace record, it is 
difficult to determine with accuracy the actual number of hours 
accumulated on fielded bolts. Also, the ASB states that Bell has 
elected to replace all the fielded bolts, part number (P/N) 50-047C8-
31. Transport Canada classified this ASB as mandatory and issued AD No. 
CF-2005-09, dated April 14, 2005, to ensure the continued airworthiness 
of these helicopters in Canada.
    This helicopter model is manufactured in Canada and is 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, Transport Canada has kept us informed 
of the situation described above. The upper three bolts of the servo 
attaching to the collective and cyclic levers have a retirement life of 
5000 hours. However, three identical bolts at the lower end of the 
servos attaching to the actuator support do not have an established 
life limit. These three bolts may be subject to premature failure due 
to fatigue causing failure of the actuators and subsequent loss of 
control of the helicopter. We have examined the findings of Transport

[[Page 38798]]

Canada, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design registered in the 
United States. Further evaluation of certain fatigue-critical parts 
resulted in establishing a life limit of 5000 hours for the affected 
bolts which is intended to prevent fatigue failure of the bolt and 
subsequent loss of control of the helicopter. Therefore, the proposed 
AD would require the following:
     Within 150 hours time-in-service (TIS), replace all three 
bolts, P/N 50-047C8-31, with airworthy, zero-time bolts, P/N 50-047C8-
31.
     Revise the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 5000 hours TIS 
for each bolt.
     Record a 5000-hour TIS life limit for each bolt on the 
component history card or equivalent record.
    We estimate that this proposed AD would affect 54 helicopters of 
U.S. registry. The proposed actions would take about 2 work hours per 
helicopter to replace 3 bolts at an average labor rate of $80 per work 
hour. Required parts would cost about $243 for each bolt. Based on 
these figures, we estimate the total cost impact of the proposed AD on 
U.S. operators to be $48,006, assuming that the recordkeeping cost 
would be negligible.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD would not have a substantial direct effect on the States, on the 
relationship between the national Government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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 draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

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


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron Canada: Docket No. FAA-2007-28688; 
Directorate Identifier 2005-SW-21-AD.

Applicability

    Model 430 helicopters, serial numbers 49001 through 49106, with 
a servo actuator-to-actuator support attachment bolt (bolt), part 
number (P/N) 50-047C8-31, installed, which attaches the lower two 
cyclic servo actuators and the lower collective servo actuator to 
the three lower actuator supports, certificated in any category.

Compliance

    Required as indicated, unless accomplished previously.
    To prevent fatigue failure of the bolt and subsequent loss of 
control of the helicopter, do the following:
    (a) Within 150 hours time-in-service (TIS), replace all three 
affected bolts, as depicted for one of these bolts in Figure 1 of 
this AD, with airworthy, zero-time bolts, P/N 50-047C8-31.

BILLING CODE 4910-13-P

[[Page 38799]]

[GRAPHIC] [TIFF OMITTED] TP16JY07.009

    (b) This AD revises the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 5000 hours 
TIS for each bolt.
    (c) Record a 5000-hour TIS life limit for each bolt on the 
component history card or equivalent record.
    (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, FAA, ATTN: Sharon Miles, 
Aviation Safety Engineer, Rotorcraft Directorate, Regulations and 
Guidance Group, Fort Worth, Texas

[[Page 38800]]

76193-0111, telephone (817) 222-5122, fax (817) 222-5961 for 
information about previously approved alternative methods of 
compliance.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF 2005-09, dated April 14, 2005.


    Issued in Fort Worth, Texas, on July 5, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 07-3434 Filed 7-13-07; 8:45 am]
BILLING CODE 4910-13-C
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