Airworthiness Directives; Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E Helicopters, 37515-37517 [06-5880]

Download as PDF Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules Applicability (c) This AD applies to all Airbus Model A300 and A310 airplanes; and all Airbus Model A300 B4–601, B4–603, B4–620, B4– 622, B4–605R, B4–622R, F4–605R, and F4– 622R airplanes, and A300 C4–605R Variant F airplanes; certificated in any category. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the following service bulletins, as applicable: (1) For Model A300 airplanes: Airbus Service Bulletin A300–24–0102, including Appendix 01, dated December 15, 2005; (2) For Model A310 airplanes: Airbus Service Bulletin A310–24–2095, including Appendix 01, dated December 15, 2005; and (3) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, and F4–622R airplanes, and A300 C4–605R Variant F airplanes: Airbus Service Bulletin A300–24–6092, including Appendix 01, dated December 15, 2005. days after the effective date of the AD, whichever is later: Submit a report of the findings (both positive and negative) of the inspections required by paragraph (g) of this AD to Airbus Engineering, c/o SE–E54, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the airplane serial number or registration number, the number of flight cycles and flight hours on the airplane, the date of the inspection, the location of the defect, the conditions found, and the type of repair. Submitting Appendix 01 of the service bulletin to Airbus is acceptable for compliance with this requirement. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) EASA’s airworthiness directive 2006– 0076, dated April 3, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on June 22, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5872 Filed 6–29–06; 8:45 am] Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ mstockstill on PROD1PC61 with PROPOSALS Inspections and Corrective Actions (g) Within 44 months after the effective date of this AD, perform detailed inspections for discrepancies of all electrical bundles located in the leading and trailing edges of the wings, and all applicable corrective actions, by doing all of the actions in the service bulletin, except as provided by paragraph (h) of this AD. All corrective actions must be done before further flight. DEPARTMENT OF TRANSPORTATION Exception to Corrective Action Instructions (h) If inadequate clearance is found between any electrical wire harness and adjacent components or structure: Before further flight, correct the inadequate clearance using a method approved by either the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Reporting (i) Within 30 days after doing the inspections required by this AD, or within 30 VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25085; Directorate Identifier 2006–SW–02–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E 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 Eurocopter France PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 37515 (Eurocopter) model helicopters. This proposal would require replacing a certain hydraulic drive belt (drive belt). Also proposed is reducing the lubrication time interval for a certain hydraulic pump drive shaft (drive shaft). This proposal is prompted by inflight failures of the drive belt and the drive shaft. The actions specified by this proposed AD are intended to prevent inflight failure of the drive belt or drive shaft, loss of hydraulic power to the flight control system, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before August 29, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: 202–493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this 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 http://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5130, 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–2006–25085, Directorate Identifier 2006–SW–02–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 E:\FR\FM\30JNP1.SGM 30JNP1 37516 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this 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 http://dms.dot.gov. mstockstill on PROD1PC61 with PROPOSALS 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 On May 4, 2004, a Eurocopter Model AS350BA helicopter lost hydraulic system power, resulting in a non-fatal accident. An investigation of the accident showed that the drive belt, part number (P/N) 704A33–690–004, failed in-flight, approximately 160 hours short of its 600-hour time-in-service (TIS) life limit. Further investigations showed that the drive belt had been installed inside out and the exterior surface, as installed, had numerous lateral cracks. Historical records from both the FAA’s Service Difficulty Report database and the National Transportation Safety Board’s Accidents and Incidents database showed that 43 failures or replacements of the affected P/Ned drive belts occurred between February 1995 and January 2006. Twenty of the affected drive belts were replaced because they were found prematurely stretched or worn past their service limits and the remaining drive belts failed in-flight after averaging 277 hours TIS. These in-flight failures resulted in loss of hydraulic system pressure that required the pilots to make emergency landings; three of those in-flight failures, including the failure on May 4, 2004, resulted in accidents. VerDate Aug<31>2005 14:43 Jun 29, 2006 Jkt 208001 Prior to that May 2004 accident, the Transportation Safety Board of Canada (TSB) investigated a fatal accident in which a Eurocopter Model AS350B2 helicopter experienced hydraulic system failure and crashed. Examination of the installed drive belt showed that it had failed at the manufacturing seam, similar to the drive belt involved in the May 2004 accident. The TSB’s further examinations showed that similar inservice, intact drive belts had extensive cracking in the same location, but that the one improved ‘‘Poly-V’’ drive belt examined had no cracks. On April 22, 2004, Transport Canada issued a Canadian AD mandating the installation of the ‘‘Poly-V’’ drive belt. On January 9, 2006, the National Transportation Safety Board (NTSB) recommended that we: • Require operators of Eurocopter AS–350 series helicopters to comply with the provisions of Eurocopter Service Bulletin AS350, No. 63.00.08, Revision 1, dated May 7, 2004, or subsequent revision (NTSB Safety Recommendation No. A–05–36). • Identify an appropriate life limit or inspection interval for the existing Eurocopter AS–350 hydraulic pump flat drive belt and require Eurocopter AS– 350 operators to comply with this limit/ interval until they accomplish Eurocopter Service Bulletin AS350, No. 63.00.08, Revision 1, dated May 7, 2004 or subsequent revisions (NTSB Safety Recommendation No. A–05–37). Eurocopter has issued the following: • Service Bulletin No. 63.00.08, dated May 27, 2002, which specifies installing a poly-v type drive belt on the driving hydraulic pump; and • Service Bulletin No. 29.00.04, Revision 1, dated January 27, 2004, which specifies reducing the lubrication interval and installing an O-ring seal in the groove of the hydraulic pump drive shaft in order to prevent early wear of the splines. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type designs registered in the United States. Therefore, the proposed AD would require the following: • At or before the next 500-hour TIS inspection, replacing the drive belt with an airworthy drive belt that is not included in the applicability of this AD, and • Within 110 hours TIS or at the next scheduled lubrication interval for the drive shaft splines, and thereafter at intervals not to exceed 110 hours TIS or 6 months, whichever occurs first, lubricating the drive shaft splines. We estimate that this proposed AD would affect 700 helicopters of U.S. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 registry. Replacing each drive belt would take approximately 25 work hours and lubricating the drive shaft splines would take approximately 1 work hour. The average labor rate is $80 an hour. Each replacement drive belt would cost about $3,500. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $4,130,000, assuming no helicopter has been modified with the new drive shaft belt and the splines are lubricated 5 times in the first year. 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. E:\FR\FM\30JNP1.SGM 30JNP1 Federal Register / Vol. 71, No. 126 / Friday, June 30, 2006 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Issued in Fort Worth, Texas, on June 22, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–5880 Filed 6–29–06; 8:45 am] 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: BILLING CODE 4910–13–P PART 39—AIRWORTHINESS DIRECTIVES 15 CFR Parts 764 and 766 DEPARTMENT OF COMMERCE Bureau of Industry and Security [Docket No 060511128–6128–01] 1. The authority citation for part 39 continues to read as follows: RIN 0694–AD36 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 mstockstill on PROD1PC61 with PROPOSALS 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Eurocopter France: Docket No. FAA–2006– 25085; Directorate Identifier 2006–SW– 02–AD. Applicability: Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, and AS350D1 helicopters with a hydraulic drive belt (drive belt), part number (P/N) 704A33–690–004, or a hydraulic pump drive shaft (drive shaft), P/N 704A34–310– 006, installed, certificated in any category. Compliance: Required as indicated. To prevent loss of hydraulic power to the flight control system and subsequent loss of control of the helicopter, accomplish the following: (a) At or before the next 500-hour time-inservice (TIS) inspection, unless accomplished previously, replace the drive belt with an airworthy drive belt that is not included in the applicability of this AD. (b) Within 110 hours TIS or at the next scheduled lubrication interval for the drive shaft splines, and thereafter at intervals not to exceed 110 hours TIS or 6 months, whichever occurs first, lubricate the drive shaft splines. (c) This action reduces the interval for lubricating the drive shaft splines from 550 hours TIS or 2 years, whichever occurs first, to 110 hours TIS or 6 months, whichever occurs first. Note: Eurocopter Service Bulletin No. 63.00.08, dated May 27, 2002, and No. 29.00.04, Revision 1, dated January 27, 2004, pertain to the subject of this AD. (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 Manager, Rotorcraft Directorate, Regulations and Guidance Group, FAA, ATTN: Gary Roach, Aviation Safety Engineer, Fort Worth, Texas 76193– 0111, telephone (817) 222–5130, fax (817) 222–5961, for information about previously approved alternative methods of compliance. 14:43 Jun 29, 2006 Bureau of Industry and Security, Commerce. ACTION: Proposed rule. AGENCY: [Amended] VerDate Aug<31>2005 Antiboycott Penalty Guidelines Jkt 208001 SUMMARY: This proposed rule would set forth BIS policy concerning voluntary self disclosures of violations of part 760 (Restrictive Trade Practices or Boycotts) of the Export Administration Regulations (EAR) and violations of part 762 (Recordkeeping) of the EAR that relate to part 760. This proposed rule also would set forth the factors that the Bureau of Industry and Security (BIS) considers when deciding whether to pursue administrative charges or settle allegations of such violations as well as the factors that BIS considers when deciding what level of penalty to seek in administrative cases. DATES: Comments must be received by August 29, 2006. ADDRESSES: Comments may be made via the Federal e-Rulemaking portal at, http://www.regulations.gov, by e-mail directly to BIS at publiccomments@bis.doc.gov, via fax at (202) 482–3355 or to U.S. Department of Commerce, Bureau of Industry and Security, Regulatory Policy Division, Room 2703, 14th Street and Pennsylvania Avenue, NW., Washington, DC 20230. Please refer to RIN 0694–AD36 in all comments. FOR FURTHER INFORMATION CONTACT: Edward O. Weant III, Acting Director, Office of Antiboycott Compliance, Bureau of Industry and Security, United States Department of Commerce, at (202) 482–2381. SUPPLEMENTARY INFORMATION: Background Part 760 of the EAR—Restrictive Trade Practices or Boycotts—prohibits U.S. persons from taking or knowingly agreeing to take certain actions with intent to comply with, further, or PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 37517 support an unsanctioned foreign boycott. Part 760 of the EAR also requires U.S. persons who are recipients of requests ‘‘* * * to take any action which has the effect of furthering or supporting a restrictive trade practice or boycott fostered or imposed by a foreign country against a country friendly to the United States or against any United States person * * *’’ to report receipt of those requests and whether they took the requested action. Part 762 of the EAR—Recordkeeping—requires, inter alia, retention of certain documents that contain information related to the prohibitions or reporting requirements of part 760. Collectively these provisions of the EAR are referred to in this notice as the antiboycott provisions. BIS administers and enforces the antiboycott provisions through its Office of Antiboycott Compliance (OAC). This proposed rule would: Set forth specific procedures for voluntary self disclosures of violations to OAC, provide guidance about how OAC responds to violations of the antiboycott provisions, and describe how OAC makes penalty determinations in the settlement of administrative enforcement cases related to the antiboycott provisions. This rule would not address disclosure provisions or penalty determination factors in any other matters such as criminal prosecutions for violations of the antiboycott provisions or tax penalties that the Department of Treasury may impose for antiboycott violations that arise pursuant to the Ribicoff Amendment to the Tax Reform Act of 1976, as implemented by Section 999 of the Internal Revenue Code. Voluntary selfdisclosure provisions and guidance on charging and penalty determinations in settlement of administrative enforcement cases that are not related to the antiboycott provisions are stated elsewhere in the EAR. Proposed Changes to the EAR in This Rule This rule would create a new § 764.8 setting forth the procedures for voluntary self-disclosure of violations of the antiboycott provisions. It would also create a new supplement No. 2 to part 764 that would describe how BIS responds to violations of the antiboycott provisions and how BIS makes penalty determinations in the settlement of administrative enforcement cases. The rule would also make technical and conforming changes to part 766. This rule would provide specific criteria with respect to what constitutes a voluntary self-disclosure and how voluntary self-disclosures relate to other E:\FR\FM\30JNP1.SGM 30JNP1

Agencies

[Federal Register Volume 71, Number 126 (Friday, June 30, 2006)]
[Proposed Rules]
[Pages 37515-37517]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5880]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25085; Directorate Identifier 2006-SW-02-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS350B, 
AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, and AS355E 
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 Eurocopter France (Eurocopter) model 
helicopters. This proposal would require replacing a certain hydraulic 
drive belt (drive belt). Also proposed is reducing the lubrication time 
interval for a certain hydraulic pump drive shaft (drive shaft). This 
proposal is prompted by in-flight failures of the drive belt and the 
drive shaft. The actions specified by this proposed AD are intended to 
prevent in-flight failure of the drive belt or drive shaft, loss of 
hydraulic power to the flight control system, and subsequent loss of 
control of the helicopter.

DATES: Comments must be received on or before August 29, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: 202-493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this 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 http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5130, 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-
25085, Directorate Identifier 2006-SW-02-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

[[Page 37516]]

and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this 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 http://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

    On May 4, 2004, a Eurocopter Model AS350BA helicopter lost 
hydraulic system power, resulting in a non-fatal accident. An 
investigation of the accident showed that the drive belt, part number 
(P/N) 704A33-690-004, failed in-flight, approximately 160 hours short 
of its 600-hour time-in-service (TIS) life limit. Further 
investigations showed that the drive belt had been installed inside out 
and the exterior surface, as installed, had numerous lateral cracks. 
Historical records from both the FAA's Service Difficulty Report 
database and the National Transportation Safety Board's Accidents and 
Incidents database showed that 43 failures or replacements of the 
affected P/Ned drive belts occurred between February 1995 and January 
2006. Twenty of the affected drive belts were replaced because they 
were found prematurely stretched or worn past their service limits and 
the remaining drive belts failed in-flight after averaging 277 hours 
TIS. These in-flight failures resulted in loss of hydraulic system 
pressure that required the pilots to make emergency landings; three of 
those in-flight failures, including the failure on May 4, 2004, 
resulted in accidents.
    Prior to that May 2004 accident, the Transportation Safety Board of 
Canada (TSB) investigated a fatal accident in which a Eurocopter Model 
AS350B2 helicopter experienced hydraulic system failure and crashed. 
Examination of the installed drive belt showed that it had failed at 
the manufacturing seam, similar to the drive belt involved in the May 
2004 accident. The TSB's further examinations showed that similar in-
service, intact drive belts had extensive cracking in the same 
location, but that the one improved ``Poly-V'' drive belt examined had 
no cracks. On April 22, 2004, Transport Canada issued a Canadian AD 
mandating the installation of the ``Poly-V'' drive belt.
    On January 9, 2006, the National Transportation Safety Board (NTSB) 
recommended that we:
     Require operators of Eurocopter AS-350 series helicopters 
to comply with the provisions of Eurocopter Service Bulletin AS350, No. 
63.00.08, Revision 1, dated May 7, 2004, or subsequent revision (NTSB 
Safety Recommendation No. A-05-36).
     Identify an appropriate life limit or inspection interval 
for the existing Eurocopter AS-350 hydraulic pump flat drive belt and 
require Eurocopter AS-350 operators to comply with this limit/interval 
until they accomplish Eurocopter Service Bulletin AS350, No. 63.00.08, 
Revision 1, dated May 7, 2004 or subsequent revisions (NTSB Safety 
Recommendation No. A-05-37).
    Eurocopter has issued the following:
     Service Bulletin No. 63.00.08, dated May 27, 2002, which 
specifies installing a poly-v type drive belt on the driving hydraulic 
pump; and
     Service Bulletin No. 29.00.04, Revision 1, dated January 
27, 2004, which specifies reducing the lubrication interval and 
installing an O-ring seal in the groove of the hydraulic pump drive 
shaft in order to prevent early wear of the splines.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type designs registered in the 
United States. Therefore, the proposed AD would require the following:
     At or before the next 500-hour TIS inspection, replacing 
the drive belt with an airworthy drive belt that is not included in the 
applicability of this AD, and
     Within 110 hours TIS or at the next scheduled lubrication 
interval for the drive shaft splines, and thereafter at intervals not 
to exceed 110 hours TIS or 6 months, whichever occurs first, 
lubricating the drive shaft splines.
    We estimate that this proposed AD would affect 700 helicopters of 
U.S. registry. Replacing each drive belt would take approximately 25 
work hours and lubricating the drive shaft splines would take 
approximately 1 work hour. The average labor rate is $80 an hour. Each 
replacement drive belt would cost about $3,500. Based on these figures, 
we estimate the total cost impact of the proposed AD on U.S. operators 
to be $4,130,000, assuming no helicopter has been modified with the new 
drive shaft belt and the splines are lubricated 5 times in the first 
year.

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.

[[Page 37517]]

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 France: Docket No. FAA-2006-25085; Directorate Identifier 
2006-SW-02-AD.
    Applicability: Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, 
AS350C, AS350D, and AS350D1 helicopters with a hydraulic drive belt 
(drive belt), part number (P/N) 704A33-690-004, or a hydraulic pump 
drive shaft (drive shaft), P/N 704A34-310-006, installed, 
certificated in any category.
    Compliance: Required as indicated.
    To prevent loss of hydraulic power to the flight control system 
and subsequent loss of control of the helicopter, accomplish the 
following:
    (a) At or before the next 500-hour time-in-service (TIS) 
inspection, unless accomplished previously, replace the drive belt 
with an airworthy drive belt that is not included in the 
applicability of this AD.
    (b) Within 110 hours TIS or at the next scheduled lubrication 
interval for the drive shaft splines, and thereafter at intervals 
not to exceed 110 hours TIS or 6 months, whichever occurs first, 
lubricate the drive shaft splines.
    (c) This action reduces the interval for lubricating the drive 
shaft splines from 550 hours TIS or 2 years, whichever occurs first, 
to 110 hours TIS or 6 months, whichever occurs first.

    Note: Eurocopter Service Bulletin No. 63.00.08, dated May 27, 
2002, and No. 29.00.04, Revision 1, dated January 27, 2004, pertain 
to the subject of this AD.

    (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 Manager, Rotorcraft Directorate, Regulations and 
Guidance Group, FAA, ATTN: Gary Roach, Aviation Safety Engineer, 
Fort Worth, Texas 76193-0111, telephone (817) 222-5130, fax (817) 
222-5961, for information about previously approved alternative 
methods of compliance.

    Issued in Fort Worth, Texas, on June 22, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-5880 Filed 6-29-06; 8:45 am]
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