Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters, 37060-37063 [05-12690]

Download as PDF 37060 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Proposed Rules replace the stops and brackets at an average labor rate of $65 per work hour. Required parts would cost about $130 per helicopter. Based on these figures, the total cost impact of the proposed AD on U.S. operators would be $87,750, assuming one-half of the U.S. helicopters have the older partnumbered stops and brackets installed and would need to replace them. 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. The Proposed Amendment DEPARTMENT OF TRANSPORTATION 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: Federal Aviation Administration 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: Robinson Helicopter Company: Docket No. FAA–2005–21679; Directorate Identifier 2004–SW–33–AD. Applicability: Model R22 series helicopters, serial numbers (S/N) 0002 through 2519, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the main rotor blade (blade) droop and teeter stop (stop) and teeter stop bracket (bracket), blade contact with the airframe, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 3 months, replace the stops, brackets, and washers with redesigned, airworthy teeter stops, part number (P/N) B151–3, droop stops, P/N A150–1, Revision F, brackets, P/N B 226–2, and washers by following the Compliance Procedure, paragraphs 2, 3, 5, and 6, of Robinson Helicopter Company Service Bulletin SB– 78A, dated May 27, 2004. (b) Replacing the stops, brackets, and washers with redesigned, airworthy stops, brackets, and washers constitutes terminating action for 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 Los Angeles Aircraft Certification Office (LAACO), FAA, for information about previously approved alternative methods of compliance. Issued in Fort Worth, Texas, on June 20, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–12688 Filed 6–27–05; 8:45 am] BILLING CODE 4910–13–P List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. VerDate jul<14>2003 16:30 Jun 27, 2005 Jkt 205001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2005–21680; Directorate Identifier 2004–SW–48–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, A–1, B, B–1, L, L–1, L–3, L–4 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This proposal would require, before the first flight of each day, checking the tail rotor blade (blade) root doublers (doublers) for an edge void or de-bond on both sides of each blade, and if an edge void or de-bond is found, replacing the unairworthy blade with an airworthy blade. This proposal would also require replacing any affected serial-numbered blade with an airworthy blade. This proposal is prompted by reports of de-bond of the doublers due to inadequate surface preparation resulting in poor adherence of the doublers. The actions specified by this proposed AD are intended to prevent loss of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before August 29, 2005. 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: 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 proposed AD from Bell Helicopter Textron Canada, 12,800 Rue E:\FR\FM\28JNP1.SGM 28JNP1 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Proposed Rules de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272. 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–2005–21680, Directorate Identifier 2004–SW–48–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– 5227) is located at the plaza level of the Department of Transportation NASSIF Building in Room PL–401 at 400 Seventh Street, SW., 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 VerDate jul<14>2003 16:30 Jun 27, 2005 Jkt 205001 Model 206A, B, and L series helicopters. Transport Canada advises that an inadequate surface preparation on a limited number of blades resulted in two reported instances of blade root doubler de-bond. They also advise that to ensure blade integrity all suspected blades are to be checked daily until removed from service. BHTC has issued Alert Service Bulletin Nos. 206–04–101 and 206L–04– 131, both dated September 13, 2004, which specify a daily check of the doubler area to verify integrity of the doubler by a pilot as part of the daily pre-flight check. The service bulletins also specify a retirement from service of affected blades, which constitutes terminating action. Transport Canada classified these service bulletins as mandatory and issued AD No. CF– 2004–25, dated November 23, 2004, to ensure the continued airworthiness of these helicopters in Canada. These helicopter models are now manufactured in Canada and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, Transport Canada has kept us informed of the situation described above. We have examined the findings of Transport Canada, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of these same type designs registered in the United States. Therefore, the proposed AD would require the following: • Before the first flight of each day, clean each blade and check the doublers for an edge void or de-bond on both sides of each blade. An owner/operator (pilot) holding at least a private pilot certificate may perform the checks. Pilots may perform these checks because they require no tools, can be done by observation, and can be done equally well by a pilot or a mechanic. However, the pilot must enter compliance with these requirements into the helicopter maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v). • If an edge void or de-bond is found, before further flight, replace the affected blade with an airworthy blade with a serial number other than those to which this AD applies. • Within 100 hours time-in-service, replace all affected blades with airworthy blades with a serial number PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 37061 other than those to which this AD applies. We estimate that this proposed AD would affect 2194 helicopters of U.S. registry. The proposed actions would: • Take about 1⁄4 work hour to do a daily check for blade edge voids and debonds; and • Take about 4 work hours to replace a blade at an average labor rate of $65 per work hour. • Cost about $5848 for a replacement blade. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $201,058, assuming 26 blades are affected and replaced and assuming 100 daily checks are done. 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 E:\FR\FM\28JNP1.SGM 28JNP1 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Proposed Rules 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 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. Air transportation, Aircraft, Aviation safety, Safety. § 39.13 [Amended] 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: 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Bell Helicopter Textron Canada: Docket No. FAA–2005–21680; Directorate Identifier 2004–SW–48–AD. Applicability: Model 206A, A–1, B, B–1, L, L–1, L–3, L–4 helicopters, with tail rotor blade (blade), part number (P/N) 206–016– (b) If an edge void or a de-bond is found, before further flight, replace the blade with an airworthy blade with a serial number other than those to which this AD applies. (c) Within 100 hours time-in-service, replace all affected, serial-numbered blades with airworthy blades with a serial number other than those to which this AD applies. Note 1: Bell Helicopter Textron Alert Service Bulletin Nos. 206–04–101 and 206L– 04–131, both dated September 13, 2004, pertain to the subject of this AD. VerDate jul<14>2003 16:30 Jun 27, 2005 Jkt 205001 (d) Replacing an affected, serialnumbered blade with an airworthy blade without an affected serial number contained in the applicability section of this AD constitutes terminating action for the requirements of this AD for that blade. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 201–131, serial numbers with a prefix of ‘‘CS’’ and 4820 through 4845, installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Before the first flight of each day, clean each blade and visually check the blade root doublers for an edge void or de-bond on both sides of each blade as depicted in Figure 1 of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). previously approved alternative methods of compliance. (f) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the blade may be replaced provided that no doubler edge void or de-bond is found during any check or inspection. Note 2: The subject of this AD is addressed in Transport Canada, Canada AD No. CF– 2004–25, dated November 23, 2004. E:\FR\FM\28JNP1.SGM 28JNP1 EP28JN05.000</GPH> 37062 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Proposed Rules Issued in Fort Worth, Texas, on June 20, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–12690 Filed 6–27–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21242; Directorate Identifier 2005–NE–09–AD] 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 05 59 74 45 15, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7175, fax (781) 238–7199. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Comments Invited Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1 and 1S1 Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a new airworthiness directive (AD) that is applicable to certain Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines. This proposal would require initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines, and replacement of 2nd stage turbines on 1B and 1D1 engines only. This proposal is prompted by the release of gas generator 2nd stage turbine blades while in service, with full containment of debris. We are proposing this AD to prevent an uncommanded engine in flight shutdown. We must receive any comments on this proposed AD by August 29, 2005. DATES: Use one of the following addresses to comment on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, ADDRESSES: VerDate jul<14>2003 16:30 Jun 27, 2005 Jkt 205001 We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21242; Directorate Identifier 2005–NE–09–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https:// dms.dot.gov. Examining the AD Docket You may examine the docket that contains the proposal, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647– 5227) is on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 37063 Discussion The Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition might exist on Turbomeca, Arriel 1B (modified per TU 148), 1D, 1D1 and 1S1 turboshaft engines. The DGAC advises that sixteen cases of release of gas generator 2nd stage turbine blades occurred in service, with full containment of debris. These events resulted in uncommanded engine in flight shutdown. Although terminating action is still unavailable, mandatory checks of the turbine blades and replacement of the turbine are being required in order to reduce the probability of an uncommanded engine in flight shutdown. Relevant Service Information We have reviewed and approved the technical contents of the following Turbomeca Alert Service Bulletins (ASBs), all dated March 24, 2004: ASB A292 72 0807, for Arriel 1B post TU 148; ASB A292 72 0808, for Arriel 1D; ASB A292 72 0809, for Arriel 1D1; and ASB A292 72 0810, for Arriel 1S1, that describe procedures for initial and repetitive position checks of the 2nd stage turbine blades, and replacement of 2nd stage turbines on 1B and 1D1 engines only. The DGAC classified these ASBs as mandatory and issued airworthiness directive F–2004–047, dated March 31, 2004, in order to ensure the airworthiness of these Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines in France. FAA’s Determination and Requirements of the Proposed AD These engines, manufactured in France, are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. In keeping with this bilateral airworthiness agreement, the DGAC kept us informed of the situation described above. We have examined the DGAC’s findings, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. For this reason, we are proposing this AD, which would require initial and repetitive position checks of the 2nd stage turbine blades on Turbomeca Arriel 1B, 1D, 1D1 and 1S1 turboshaft engines, and replacement of 2nd stage turbines on 1B and 1D1 engines only. The proposed AD would require you to E:\FR\FM\28JNP1.SGM 28JNP1

Agencies

[Federal Register Volume 70, Number 123 (Tuesday, June 28, 2005)]
[Proposed Rules]
[Pages 37060-37063]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12690]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21680; Directorate Identifier 2004-SW-48-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for the specified Bell Helicopter Textron Canada (BHTC) model 
helicopters. This proposal would require, before the first flight of 
each day, checking the tail rotor blade (blade) root doublers 
(doublers) for an edge void or de-bond on both sides of each blade, and 
if an edge void or de-bond is found, replacing the unairworthy blade 
with an airworthy blade. This proposal would also require replacing any 
affected serial-numbered blade with an airworthy blade. This proposal 
is prompted by reports of de-bond of the doublers due to inadequate 
surface preparation resulting in poor adherence of the doublers. The 
actions specified by this proposed AD are intended to prevent loss of a 
blade, loss of tail rotor control, and subsequent loss of control of 
the helicopter.

DATES: Comments must be received on or before August 29, 2005.

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: 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 proposed AD 
from Bell Helicopter Textron Canada, 12,800 Rue

[[Page 37061]]

de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 
363-8023, fax (450) 433-0272.
    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-2005-
21680, Directorate Identifier 2004-SW-48-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-
647-5227) is located at the plaza level of the Department of 
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street, 
SW., 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 Model 206A, B, and L 
series helicopters. Transport Canada advises that an inadequate surface 
preparation on a limited number of blades resulted in two reported 
instances of blade root doubler de-bond. They also advise that to 
ensure blade integrity all suspected blades are to be checked daily 
until removed from service.
    BHTC has issued Alert Service Bulletin Nos. 206-04-101 and 206L-04-
131, both dated September 13, 2004, which specify a daily check of the 
doubler area to verify integrity of the doubler by a pilot as part of 
the daily pre-flight check. The service bulletins also specify a 
retirement from service of affected blades, which constitutes 
terminating action. Transport Canada classified these service bulletins 
as mandatory and issued AD No. CF-2004-25, dated November 23, 2004, to 
ensure the continued airworthiness of these helicopters in Canada.
    These helicopter models are now manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept us informed 
of the situation described above. We have examined the findings of 
Transport Canada, reviewed all available information, and determined 
that AD action is necessary for products of these type designs that are 
certificated for operation in the United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of these same type designs registered in 
the United States. Therefore, the proposed AD would require the 
following:
     Before the first flight of each day, clean each blade and 
check the doublers for an edge void or de-bond on both sides of each 
blade. An owner/operator (pilot) holding at least a private pilot 
certificate may perform the checks. Pilots may perform these checks 
because they require no tools, can be done by observation, and can be 
done equally well by a pilot or a mechanic. However, the pilot must 
enter compliance with these requirements into the helicopter 
maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v).
     If an edge void or de-bond is found, before further 
flight, replace the affected blade with an airworthy blade with a 
serial number other than those to which this AD applies.
     Within 100 hours time-in-service, replace all affected 
blades with airworthy blades with a serial number other than those to 
which this AD applies.
    We estimate that this proposed AD would affect 2194 helicopters of 
U.S. registry. The proposed actions would:
     Take about \1/4\ work hour to do a daily check for blade 
edge voids and de-bonds; and
     Take about 4 work hours to replace a blade at an average 
labor rate of $65 per work hour.
     Cost about $5848 for a replacement blade.
    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $201,058, assuming 26 blades are 
affected and replaced and assuming 100 daily checks are done.

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

[[Page 37062]]

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-2005-21680; 
Directorate Identifier 2004-SW-48-AD.

    Applicability: Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 
helicopters, with tail rotor blade (blade), part number (P/N) 206-
016-201-131, serial numbers with a prefix of ``CS'' and 4820 through 
4845, installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of a blade, loss of tail rotor control, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Before the first flight of each day, clean each blade and 
visually check the blade root doublers for an edge void or de-bond 
on both sides of each blade as depicted in Figure 1 of this AD. An 
owner/operator (pilot), holding at least a private pilot 
certificate, may perform this visual check and must enter compliance 
with this paragraph into the helicopter maintenance records by 
following 14 CFR sections 43.11 and 91.417(a)(2)(v).
[GRAPHIC] [TIFF OMITTED] TP28JN05.000

    (b) If an edge void or a de-bond is found, before further flight, 
replace the blade with an airworthy blade with a serial number other 
than those to which this AD applies.
    (c) Within 100 hours time-in-service, replace all affected, serial-
numbered blades with airworthy blades with a serial number other than 
those to which this AD applies.

    Note 1: Bell Helicopter Textron Alert Service Bulletin Nos. 206-
04-101 and 206L-04-131, both dated September 13, 2004, pertain to 
the subject of this AD.

    (d) Replacing an affected, serial-numbered blade with an airworthy 
blade without an affected serial number contained in the applicability 
section of this AD constitutes terminating action for the requirements 
of this AD for that blade.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, for 
information about previously approved alternative methods of 
compliance.
    (f) Special flight permits may be issued in accordance with 14 CFR 
21.197 and 21.199 to operate the helicopter to a location where the 
blade may be replaced provided that no doubler edge void or de-bond is 
found during any check or inspection.

    Note 2: The subject of this AD is addressed in Transport Canada, 
Canada AD No. CF-2004-25, dated November 23, 2004.



[[Page 37063]]


    Issued in Fort Worth, Texas, on June 20, 2005.
S. Frances Cox,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-12690 Filed 6-27-05; 8:45 am]
BILLING CODE 4910-13-P

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