Airworthiness Directives; Eurocopter Canada Limited Model BO 105 LS A-3 Helicopters, 25787-25789 [E6-6589]

Download as PDF Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules 25787 Compliance Procedures (1) For Model SR20, serial numbers (S/Ns) 1005 through 1600, and Model SR22, S/Ns 0002 through 1727, do the following actions: (i) At the lower back of the crew seat, release the reclosable fasteners to expose the lower seat frame. (ii) Replace the crew seat break-over bolt with the new crew seat break-over pin, part number 17063–002. (iii) Recover the seat frame, refastening the reclosable fasteners. (iv) Inspect the crew seat. (v) Repeat the above actions for the opposite crew seat. Within 50 hours time-in-service (TIS) or within 180 days, whichever occurs first, after the effective date of this AD. Follow Cirrus Design Corporation Service Bulletin SB 2X–25–17 R1, Issued: December 15, 2005; Revised: January 20, 2006. (2) For Models SR20, S/Ns 1005 through 1455, and SR22, S/Ns 0002 through 1044, do the following actions: (i) Identify whether the recline lock is secured with two bolts or three bolts. (ii) If the recline locks are secured with two bolts, remove the existing recline locks and replace with the new recline locks kit, Kit Number 70084–001. (iii) If the recline locks are secured with three bolts, remove existing recline locks and replace with the new recline locks kit, Kit Number 70084–002. (iv) Check break-over pin alignment and adjust as necessary. (v) Check that the locks engage with the break-over bolts with the seat in the full recline position. If full seat recline is not possible or difficult to engage, grinding of the lower aft seat frame is necessary. (vi) Repeat the above actions for the opposite crew seat. Within 50 hours TIS or within 180 days, whichever occurs first after October 13, 2005 (the effective date of AD 2005–17– 19), unless already accomplished. Follow Cirrus Design Corporation Service Bulletin SB 2X–25–06 R4, Issued: August 13, 2004; Revised: May 5, 2005. Alternative Methods of Compliance (AMOCs) (f) The Manager, Chicago Aircraft Certification Office, FAA, ATTN: Wess Rouse, Small Airplane Project Manager, ACE–117C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294–8113; facsimile: (847) 294–7834; e-mail: wess.rouse@faa.gov; or Angie Kostopoulos, Composite Technical Specialist, ACE–116C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294–7426; facsimile: (847) 294–7834; e-mail: evangelia.kostopoulos@faa.gov, have the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. rmajette on PROD1PC67 with PROPOSALS Actions Issued in Kansas City, Missouri, on April 25, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–6590 Filed 5–1–06; 8:45 am] helicopters. This proposal would require replacing certain fixed bolts and nuts, reidentifying certain main rotor nuts, and revising the Airworthiness Limitations—Time Change Items (TCI) list to reflect the new life limits and new part numbers. This proposal is prompted by a re-evaluation of certain fatigue-critical parts, which resulted in establishing new life limits for certain like-numbered parts and reidentifying a certain existing part with a different part number, or in some cases, replacing them with new parts. The actions specified by this proposed AD are intended to prevent fatigue failure of the fixed bolts and nuts, and subsequent loss of control of the helicopter. Related Information (g) To get copies of the documents referenced in this AD, contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727–2737; Internet address: https:// www.cirrusdesign.com. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–24254; Directorate Identifier 2006–CE–24–AD. VerDate Aug<31>2005 14:31 May 01, 2006 Jkt 208001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24632; Directorate Identifier 2005–SW–31–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter Canada Limited Model BO 105 LS A–3 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A–3 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Comments must be received on or before July 3, 2006. DATES: 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 ADDRESSES: E:\FR\FM\02MYP1.SGM 02MYP1 25788 Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules 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 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: rmajette on PROD1PC67 with PROPOSALS 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–2006–24632, Directorate Identifier 2005–SW–31–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 VerDate Aug<31>2005 14:31 May 01, 2006 Jkt 208001 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 Eurocopter Model BO 105 LS A–3 helicopters. Transport Canada advises that changes to the TCI list must be incorporated, and affected parts must be replaced and reidentified in accordance with the manufacturer’s service information. Eurocopter has issued Alert Service Bulletin No. ASB BO 105 LS 10–11, dated May 11, 2005, which specifies changes to and introduction of life limits, and reidentification of certain life-limited parts. Transport Canada classified this alert service bulletin as mandatory and issued AD No. CF– 2005–17, dated June 6, 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. We have examined the findings of the Transport 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. Therefore, the proposed AD would require, within 30 days, incorporating revised life limits and part numbers into the list of life-limited parts, or TCI list, which is contained in the helicopter delivery file, and within 150 hours timein-service (TIS), replacing 4 fixed bolts, part number (P/N) LN 9038 K08018, with fixed bolts, P/N 105–101021.17. It would also require replacing 4 main rotor nuts, P/N 105–142241.01, within 30 days if they have less than 150 hours TIS remaining, or reidentifying those main rotor nuts within 150 hours TIS if they have 150 or more hours TIS remaining. The actions would be PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 required to be accomplished by following specified portions of the alert service bulletin described previously. We estimate that this proposed AD would affect 7 helicopters of U.S. registry and the proposed actions would take approximately: • 1 work hour per helicopter to remove and replace 4 fixed bolts; • 16 work hours per helicopter to remove, replace, and reidentify four nuts; and • 1 work hour per helicopter to create component history cards at an average labor rate of $65 per work hour. Required parts would cost approximately $3.80 for each fixed bolt, P/N 105–101021.17, and $882.67 for each nut, P/N 105–142241.01. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $33,011, assuming all nuts and bolts on the entire fleet are replaced. 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 E:\FR\FM\02MYP1.SGM 02MYP1 Federal Register / Vol. 71, No. 84 / Tuesday, May 2, 2006 / Proposed Rules 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 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: Accordingly, pursuant to the authority delegated to me by the Part name 105–101021.17 (Formerly P/N LN 9038– K08018). 105–142241.01 ................................................. Eurocopter Canada Limited: Docket No. FAA–2006–24632; Directorate Identifier 2005–SW–31–AD. Applicability: Model BO 105 LS A–3 helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue failure of a fixed bolt and main rotor nut, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 30 days: (1) Modify the Airworthiness Limitation section, Time Change Items (TCI) list, or table of life-limited components, with their revised life limits by adding part number (P/N) 105– 142241.01 and by changing P/N LN 9038 K08018 to P/N 105–101021.17, as shown in the following table. P/N Fixed Bolt (Bolt) ................................................. Main Rotor Nut (Nut) ......................................... 25789 Life limit 6,000 hours time-in-service (TIS). 122,850 flights or 18,900 hours TIS, whichever occurs first. rmajette on PROD1PC67 with PROPOSALS The number of flights equals the number of landings (i.e., ground contacts). (2) Create a historical or equivalent record for each of the parts listed in the preceding table. (3) Review the aircraft records and determine the TIS and landings on each nut, P/N 105–142241.01. If the number of flights (i.e., landings) is unknown, the initial life limit is 18,900 hours TIS. Thereafter, record the number of flights for use when determining the retirement life. (b) Before further flight, replace any nut that has less than 150 hours TIS remaining before reaching its life limit. Unless accomplished previously, prior to replacing a nut, reidentify the nut in accordance with paragraph (c)(2) of this AD. (c) Within 150 hours TIS: (1) Replace the 4 bolts, P/N LN 9038 K08018, with bolts, P/N 105–101021.17, as shown in Figure 1 of Eurocopter Alert Service Bulletin No. ASB BO 105 LS 10–11, dated May 11, 2005 (ASB). (2) For those nuts with 150 or more hours TIS remaining on their life, remove and reidentify those nuts, P/N 105–142241.01, by adding the serial number of the main rotor head, followed by a dash and a consecutive number, in accordance with the procedures stated in Figure 2 of the ASB. (d) Before further flight, remove any lifelimited part on which the life limit has been equaled or exceeded. (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 Manager, Regulations and Policy Group, Rotorcraft Directorate, FAA, ATTN: 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, for information about previously approved alternative methods of compliance. VerDate Aug<31>2005 14:31 May 01, 2006 Jkt 208001 Note: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF– 2005–17, dated June 6, 2005. Issued in Fort Worth, Texas, on April 24, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6–6589 Filed 5–1–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–18850; Directorate Identifier 2004–SW–19–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N, N1, and SA–366G1 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes to revise an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N, N1, and SA–366G1 helicopters. That AD currently requires inspecting the main gearbox (MGB) base plate for a crack and replacing the MGB if a crack is found. This action would increase the PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 time intervals for inspecting the MGB base plate. This action would also include minor editorial changes throughout the AD. This proposal is prompted by crack growth tests that indicate that the inspection intervals can be increased without affecting safety. The actions specified by the proposed AD are intended to detect a crack in an MGB base plate and prevent failure of one of the MGB attachment points to the frame, which could result in severe vibration and subsequent loss of control of the helicopter. DATES: Comments must be received by July 3, 2006. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas E:\FR\FM\02MYP1.SGM 02MYP1

Agencies

[Federal Register Volume 71, Number 84 (Tuesday, May 2, 2006)]
[Proposed Rules]
[Pages 25787-25789]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-6589]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24632; Directorate Identifier 2005-SW-31-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter Canada Limited Model BO 105 
LS A-3 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Eurocopter Canada Limited (Eurocopter) Model BO 105 LS A-3 
helicopters. This proposal would require replacing certain fixed bolts 
and nuts, reidentifying certain main rotor nuts, and revising the 
Airworthiness Limitations--Time Change Items (TCI) list to reflect the 
new life limits and new part numbers. This proposal is prompted by a 
re-evaluation of certain fatigue-critical parts, which resulted in 
establishing new life limits for certain like-numbered parts and 
reidentifying a certain existing part with a different part number, or 
in some cases, replacing them with new parts. The actions specified by 
this proposed AD are intended to prevent fatigue failure of the fixed 
bolts and nuts, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before July 3, 2006.

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

[[Page 25788]]

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 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-2006-
24632, Directorate Identifier 2005-SW-31-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 Eurocopter Model BO 105 
LS A-3 helicopters. Transport Canada advises that changes to the TCI 
list must be incorporated, and affected parts must be replaced and 
reidentified in accordance with the manufacturer's service information.
    Eurocopter has issued Alert Service Bulletin No. ASB BO 105 LS 10-
11, dated May 11, 2005, which specifies changes to and introduction of 
life limits, and reidentification of certain life-limited parts. 
Transport Canada classified this alert service bulletin as mandatory 
and issued AD No. CF-2005-17, dated June 6, 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. We have examined the findings of the 
Transport 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. Therefore, the proposed AD would require, within 30 
days, incorporating revised life limits and part numbers into the list 
of life-limited parts, or TCI list, which is contained in the 
helicopter delivery file, and within 150 hours time-in-service (TIS), 
replacing 4 fixed bolts, part number (P/N) LN 9038 K08018, with fixed 
bolts, P/N 105-101021.17. It would also require replacing 4 main rotor 
nuts, P/N 105-142241.01, within 30 days if they have less than 150 
hours TIS remaining, or reidentifying those main rotor nuts within 150 
hours TIS if they have 150 or more hours TIS remaining. The actions 
would be required to be accomplished by following specified portions of 
the alert service bulletin described previously.
    We estimate that this proposed AD would affect 7 helicopters of 
U.S. registry and the proposed actions would take approximately:
     1 work hour per helicopter to remove and replace 4 fixed 
bolts;
     16 work hours per helicopter to remove, replace, and 
reidentify four nuts; and
     1 work hour per helicopter to create component history 
cards at an average labor rate of $65 per work hour. Required parts 
would cost approximately $3.80 for each fixed bolt, P/N 105-101021.17, 
and $882.67 for each nut, P/N 105-142241.01. Based on these figures, we 
estimate the total cost impact of the proposed AD on U.S. operators to 
be $33,011, assuming all nuts and bolts on the entire fleet are 
replaced.

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

[[Page 25789]]

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:

Eurocopter Canada Limited: Docket No. FAA-2006-24632; Directorate 
Identifier 2005-SW-31-AD.

    Applicability: Model BO 105 LS A-3 helicopters, certificated in 
any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue failure of a fixed bolt and main rotor nut, 
and subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 30 days:
    (1) Modify the Airworthiness Limitation section, Time Change 
Items (TCI) list, or table of life-limited components, with their 
revised life limits by adding part number (P/N) 105-142241.01 and by 
changing P/N LN 9038 K08018 to P/N 105-101021.17, as shown in the 
following table.

------------------------------------------------------------------------
            Part name                     P/N             Life limit
------------------------------------------------------------------------
Fixed Bolt (Bolt)...............  105-101021.17       6,000 hours time-
                                   (Formerly P/N LN    in-service (TIS).
                                   9038-K08018).
Main Rotor Nut (Nut)............  105-142241.01.....  122,850 flights or
                                                       18,900 hours TIS,
                                                       whichever occurs
                                                       first.
------------------------------------------------------------------------
The number of flights equals the number of landings (i.e., ground
  contacts).

    (2) Create a historical or equivalent record for each of the 
parts listed in the preceding table.
    (3) Review the aircraft records and determine the TIS and 
landings on each nut, P/N 105-142241.01. If the number of flights 
(i.e., landings) is unknown, the initial life limit is 18,900 hours 
TIS. Thereafter, record the number of flights for use when 
determining the retirement life.
    (b) Before further flight, replace any nut that has less than 
150 hours TIS remaining before reaching its life limit. Unless 
accomplished previously, prior to replacing a nut, reidentify the 
nut in accordance with paragraph (c)(2) of this AD.
    (c) Within 150 hours TIS:
    (1) Replace the 4 bolts, P/N LN 9038 K08018, with bolts, P/N 
105-101021.17, as shown in Figure 1 of Eurocopter Alert Service 
Bulletin No. ASB BO 105 LS 10-11, dated May 11, 2005 (ASB).
    (2) For those nuts with 150 or more hours TIS remaining on their 
life, remove and reidentify those nuts, P/N 105-142241.01, by adding 
the serial number of the main rotor head, followed by a dash and a 
consecutive number, in accordance with the procedures stated in 
Figure 2 of the ASB.
    (d) Before further flight, remove any life-limited part on which 
the life limit has been equaled or exceeded.
    (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 Manager, Regulations and Policy Group, Rotorcraft 
Directorate, FAA, ATTN: 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, for 
information about previously approved alternative methods of 
compliance.

    Note: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-2005-17, dated June 6, 2005.


    Issued in Fort Worth, Texas, on April 24, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E6-6589 Filed 5-1-06; 8:45 am]
BILLING CODE 4910-13-P
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