Airworthiness Directives; Eurocopter France Model AS350B, BA, B1, B2, B3, C, D, D1, AS355E, F, F1, F2, and N Helicopters, 54501-54503 [E9-25440]

Download as PDF Federal Register / Vol. 74, No. 203 / Thursday, October 22, 2009 / Proposed Rules a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI Civil Aviation Safety Authority of Australia, AD number AD/GAF– N22/69 Amdt 6, dated September 10, 2009, Nomad Alert Service Bulletin ANMD–27–53, dated February 20, 2008, and Nomad Alert Service Bulletin ANMD–57–18, Rev 1, dated August 14, 2006, for related information. Issued in Kansas City, Missouri, on October 15, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–25443 Filed 10–21–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0951; Directorate Identifier 2007–SW–52–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS350B, BA, B1, B2, B3, C, D, D1, AS355E, F, F1, F2, and N Helicopters dcolon on DSK2BSOYB1PROD with PROPOSALS AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. This proposed AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The AD MCAI states ‘‘EASA issued Airworthiness Directive (AD) 2006– 0251 and its revisions following a case of total failure and a case of a crack discovered on the support shaft of the sliding door rear roller. Metallurgical and metallographic analyses revealed a nonconformity concerning the heat treatment of the material. Since then, VerDate Nov<24>2008 15:06 Oct 21, 2009 Jkt 220001 other cases of cracks and failures of the roller support shaft rear attach fitting had been reported. This condition, if not corrected, could lead to the loss of the sliding door in flight.’’ Separation of a sliding door in flight creates an unsafe condition because the door could come into contact with the rotor system. The proposed AD would require actions that are intended to address this unsafe condition. DATES: We must receive comments on this proposed AD by November 23, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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. Examining the Docket: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Gary Roach, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5130, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 54501 FAA–2009–0951; Directorate Identifier 2007–SW–52–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion EASA, which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2007–0236, dated August 31, 2007, to correct an unsafe condition for specified Eurocopter model helicopters. The MCAI AD states that EASA issued AD 2006–0251 and its revisions following a case of total failure and a case of a crack discovered on the support shaft of the sliding door rear roller. Metallurgical and metallographic analyses revealed a nonconformity concerning the heat treatment of the material. Since then, other cases of cracks and failures of the roller support shaft rear attach fitting had been reported. EASA AD No. 2007– 0236 supersedes EASA AD No. 2006– 0251R2 but retains the requirements for repetitive inspections until replacement of current parts with improved parts. EASA AD No. 2007–0236 also prohibits installation of another roller support fitting part number (P/N) 350A25–1270– 22 on any AS350 or AS355 helicopter. You may obtain further information by examining the MCAI AD and service information in the AD docket. Related Service Information On July 18, 2006, Eurocopter issued Alert Service Bulletin (ASB) No. 52.00.30 for modifying the AS350 series helicopters and ASB No. 52.00.23 for modifying the AS355 series helicopters. These ASBs contained modifications 073298 and 073308. The following day, Eurocopter issued ASB No. 05.00.45 for the AS355 model helicopters and No. 05.00.47 for the AS350 model helicopters, both dated July 19, 2006. Later, Eurocopter issued Revision 1 to ASB No. 52.00.23 for the AS355 model helicopters and No. 52.00.30 for the AS350 model helicopters, both dated June 29, 2007, to modify the sliding door medium roller and fitting. The actions described in the MCAI AD are intended to correct the same unsafe condition as that identified in the service information. E:\FR\FM\22OCP1.SGM 22OCP1 54502 Federal Register / Vol. 74, No. 203 / Thursday, October 22, 2009 / Proposed Rules FAA’s Evaluation and Unsafe Condition Determination This product has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, their technical agent, has notified us of the unsafe condition described in the MCAI AD. We are proposing this AD because we evaluated all information provided by EASA and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Differences Between This AD and the MCAI AD This AD differs from EASA AD No. 2007–0236 as follows: • We use the word ‘‘inspect’’ to describe the actions required by a mechanic versus the word ‘‘check,’’ which is how we describe the actions allowed by a pilot. • We refer to the compliance time as ‘‘hours time-in-service (TIS)’’ rather than ‘‘flying hours.’’ • We do not require an operator to tell the manufacturer if a crack is found in the shaft. • We are not including the Model L1, which is a military model helicopter; but we are including the Models 350C and D1 helicopters. dcolon on DSK2BSOYB1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect about 725 products of U.S. registry. We also estimate that it would take about 4 work-hours per helicopter to inspect and modify the sliding doors. The average labor rate is $80 per workhour. Required parts would cost about $7,000 per helicopter. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $5,307,000. 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 VerDate Nov<24>2008 15:06 Oct 21, 2009 Jkt 220001 because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. 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 this 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 an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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. The FAA amends § 39.13 by adding the following new AD: Eurocopter France: Docket No. FAA–2009– 0951; Directorate Identifier 2007–SW– 52–AD. Comments Due Date (a) We must receive comments by November 23, 2009. Other Affected ADs (b) None. Applicability (c) This AD applies to Eurocopter France Model AS350B, BA, B1, B2, B3, C, D, D1, AS355E, F, F1, F2, and N helicopters, with sliding door pre-MOD 073298 or pre-MOD 073308, installed, certificated in any category. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Reason (d) The mandatory continuing airworthiness information (MCAI) AD states ‘‘EASA issued Airworthiness Directive (AD) 2006–0251 and its revisions following a case of total failure and a case of a crack discovered on the support shaft of the sliding door rear roller. Metallurgical and metallographic analyses revealed a nonconformity concerning the heat treatment of the material. Since then, other cases of cracks and failures of the roller support shaft rear attach fitting had been reported. This condition, if not corrected, could lead to the loss of the sliding door in flight.’’ Separation of a sliding door in flight creates an unsafe condition because the door could come into contact with the rotor system. This AD requires actions that are intended to address this unsafe condition. Actions and Compliance (e) Required as indicated. (1) For a sliding door with less than 90 hours time-in-service (TIS), on or before accumulating a total of 110 hours TIS, unless already done, conduct the visual and dye penetrant inspections of the support shaft of the rear roller and the rear fitting (fitting) of the sliding door for a crack by reference to Figure 1 and by following the Operational Procedure, paragraph 2.B.1 and 2.B.2, of Eurocopter Alert Service Bulletin (ASB) No. 05.00.47 dated July 19, 2006, for the Model AS350 helicopters (ASB 05.00.47) or ASB No. 05.00.45 dated July 19, 2006, for the Model AS355 helicopters (ASB 05.00.45), except you are not required to contact the manufacturer. (i) If no crack is found in the shaft or fitting, reinstall the shaft on the fitting, fit the spring pins, and plug the pin holes by following the Operational Procedure, paragraph 2.B.2. of ASB 05.00.47 or 05.00.45, whichever is appropriate for your model helicopter. (ii) If you find a crack in the fitting, replace the fitting with an airworthy fitting before further flight. (iii) If you find a crack in the shaft, replace the shaft with an airworthy shaft before further flight, by reference to Figure 1 and following paragraph 2.B.3. of ASB 05.00.47 or 05.00.45, whichever is appropriate for your model helicopter. (2) For a sliding door with 90 or more hours TIS, within the next 20 hours TIS, unless already done, and thereafter at intervals not to exceed 110 hours TIS, conduct the visual and dye penetrant inspections of the support shaft of the rear roller and the fitting of the sliding door for a crack by reference to Figure 1 and by following the Operational Procedure, paragraph 2.B.1 and 2.B.2, of ASB 05.00.47 or ASB 05.00.45, whichever is appropriate for your model helicopter, except you are not required to contact the manufacturer. (i) If no crack is found in the shaft and fitting, reinstall the shaft or fitting, fit the spring pins, and plug the pin holes by following the Operational Procedure, paragraph 2.B.2. of ASB 05.00.47 or 05.00.45, whichever is appropriate for your model helicopter. E:\FR\FM\22OCP1.SGM 22OCP1 Federal Register / Vol. 74, No. 203 / Thursday, October 22, 2009 / Proposed Rules (ii) If you find a crack in the fitting, replace the fitting with an airworthy fitting before further flight. (iii) If you find a crack in the shaft, replace the shaft with an airworthy shaft before further flight by reference to Figure 1 and by following paragraph 2.B.3. of ASB 05.00.47 or 05.45, whichever is appropriate for your model helicopter. (3) After the effective date of this AD, do not install any of the following parts on any helicopter: (i) Left-hand sliding door, part number (P/N) 350A25–0030–00XX, 350A25–0120– 00XX, and 350AMR–0227–0052; (ii) Right-hand sliding door, P/N 350A25– 0030–01XX, 350A25–0120–01XX, 350A25– 0120–03XX, and 350AMR–0227–0051; (iii) Rail roller pin, P/N 350A25–1275–20; and (iv) Cast roller support fittings, P/N 350A25–1270–20 and P/N 350A25–1270–22. Differences Between This AD and the MCAI AD (f) This AD differs from EASA AD No. 2007–0236 as follows: (1) We use the word ‘‘inspect’’ to describe the actions required by a mechanic versus the word ‘‘check,’’ which is how we describe the actions allowed by a pilot. (2) We refer to the compliance time as hours time-in-service (TIS) rather than flying hours. (3) We do not require an operator to inform the manufacturer if a crack is found in the shaft as specified in the service information. (4) We do not include the Model L1, which is a military model helicopter; but we are including the Models 350C and D1 helicopters. Other Information (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, Rotorcraft Directorate, ATTN: DOT FAA, Southwest Region, Gary Roach, ASW– 111, Aviation Safety Engineer, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5130, fax (817) 222–5961, has the authority to approve AMOCs for this AD, if requested, using the procedures found in 14 CFR 39.19. Related Information (h) MCAI EASA AD No. 2007–0236, dated August 31, 2007, contains related information. dcolon on DSK2BSOYB1PROD with PROPOSALS Joint Aircraft System Component (JASC) Code (i) JASC Code 5344: Fuselage Door Hinges. Issued in Fort Worth, Texas, on October 8, 2009. Larry M. Kelly, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E9–25440 Filed 10–21–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 15:06 Oct 21, 2009 Jkt 220001 DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Parts 131 and 292 [Docket No. RM09–23–000] Revisions to Form, Procedures, and Criteria for Certification of Qualifying Facility Status for a Small Power Production or Cogeneration Facility October 15, 2009. AGENCY: Federal Energy Regulatory Commission, DOE. ACTION: Notice of proposed rulemaking. SUMMARY: In this Notice of Proposed Rulemaking, the Federal Energy Regulatory Commission (Commission) proposes to revise its regulations, which currently provide the FERC Form No. 556 (Form 556) that is used in the certification of qualifying status for an existing or proposed small power production or cogeneration facility. The Commission proposes to revise its regulations to remove the contents of the Form No. 556 from the regulations, and, in their place, to provide that an applicant seeking to certify qualifying facility (QF) status of a small power production or cogeneration facility must complete, and electronically file, the Form No. 556 that is in effect at the time of filing. We propose to revise and reformat the Form No. 556 to clarify the content of the form and to take advantage of newer technologies that will reduce both the filing burden for applicants and the processing burden for the Commission. We also propose to exempt generating facilities with net power production capacities of 1 MW or less from the QF certification requirement, and to codify the Commission’s authority to waive the QF certification requirement for good cause. Finally, we propose to clarify, simplify or correct certain sections of the regulations. DATES: Comments must be filed on or before December 21, 2009. ADDRESSES: You may submit comments, identified by Docket No. RM09–23–000, by one of the following methods: Agency Web site: http://www.ferc.gov. Follow the instructions for submitting comments via the eFiling link found in the Comment Procedures Section of the preamble. Mail: Commenters unable to file comments electronically must mail or hand deliver an original and 14 copies of their comments to: Federal Energy Regulatory Commission, Secretary of the Commission, 888 First Street, NE., PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 54503 Washington, DC 20426. Please refer to the Comment Procedures Section of the preamble for additional information on how to file paper comments. FOR FURTHER INFORMATION CONTACT: Tom Dautel (Technical Information), Division of Economic and Technical Analysis, Office of Energy Policy and Innovation, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, Telephone: (202) 502–6196, E-mail: thomas.dautel@ferc.gov. Paul Singh (Technical Information), Division of Tariffs and Market Development—West, Office of Energy Market Regulation, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, Telephone: (202) 502–8576, E-mail: paul.singh@ferc.gov. S.L. Higginbottom (Legal Information), Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street, NE., Washington, DC 20426, Telephone: (202) 502–8561, Email: samuel.higginbottom@ferc.gov. SUPPLEMENTARY INFORMATION: I. Introduction 1. The Commission proposes to revise § 131.80 of its regulations,1 which currently sets forth the FERC Form No. 556 (Form 556) that is used in the certification of qualifying status for an existing or proposed small power production or cogeneration facility. Section 131.80 now contains Form No. 556 and general instructions for completing the form. The Commission proposes to revise § 131.80 of its regulations to remove the contents of the Form No. 556 and, in their place, provide that an applicant seeking to certify qualifying facility (QF) status of a small power production or cogeneration facility must complete and file the Form No. 556 that is in effect at the time of filing, which will be made available for download from the Commission’s QF Web site.2 The Commission also proposes to require that the Form No. 556 be submitted to the Commission electronically. 2. The Commission proposes to revise and reformat the Form No. 556 to clarify the content of the form and to take advantage of newer technologies that will reduce both the filing burden for applicants and the processing burden for the Commission. 3. The Commission also proposes revisions to the procedures, standards and criteria for QF status provided in Part 292 of its regulations to accomplish 1 18 CFR 131.80. 2 http://www.ferc.gov/QF. E:\FR\FM\22OCP1.SGM 22OCP1

Agencies

[Federal Register Volume 74, Number 203 (Thursday, October 22, 2009)]
[Proposed Rules]
[Pages 54501-54503]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-25440]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0951; Directorate Identifier 2007-SW-52-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS350B, BA, B1, 
B2, B3, C, D, D1, AS355E, F, F1, F2, and N Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
specified Eurocopter France (Eurocopter) model helicopters. This 
proposed AD results from a mandatory continuing airworthiness 
information (MCAI) AD issued by the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community. The AD MCAI states ``EASA issued Airworthiness 
Directive (AD) 2006-0251 and its revisions following a case of total 
failure and a case of a crack discovered on the support shaft of the 
sliding door rear roller. Metallurgical and metallographic analyses 
revealed a nonconformity concerning the heat treatment of the material. 
Since then, other cases of cracks and failures of the roller support 
shaft rear attach fitting had been reported. This condition, if not 
corrected, could lead to the loss of the sliding door in flight.''
    Separation of a sliding door in flight creates an unsafe condition 
because the door could come into contact with the rotor system. The 
proposed AD would require actions that are intended to address this 
unsafe condition.

DATES: We must receive comments on this proposed AD by November 23, 
2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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.
    Examining the Docket: You may examine the AD docket on the Internet 
at http://www.regulations.gov or in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the economic 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: DOT/FAA Southwest Region, Gary Roach, 
ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations 
and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, 
telephone (817) 222-5130, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0951; 
Directorate Identifier 2007-SW-52-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD No. 2007-0236, dated August 31, 
2007, to correct an unsafe condition for specified Eurocopter model 
helicopters. The MCAI AD states that EASA issued AD 2006-0251 and its 
revisions following a case of total failure and a case of a crack 
discovered on the support shaft of the sliding door rear roller. 
Metallurgical and metallographic analyses revealed a nonconformity 
concerning the heat treatment of the material. Since then, other cases 
of cracks and failures of the roller support shaft rear attach fitting 
had been reported. EASA AD No. 2007-0236 supersedes EASA AD No. 2006-
0251R2 but retains the requirements for repetitive inspections until 
replacement of current parts with improved parts. EASA AD No. 2007-0236 
also prohibits installation of another roller support fitting part 
number (P/N) 350A25-1270-22 on any AS350 or AS355 helicopter. You may 
obtain further information by examining the MCAI AD and service 
information in the AD docket.

Related Service Information

    On July 18, 2006, Eurocopter issued Alert Service Bulletin (ASB) 
No. 52.00.30 for modifying the AS350 series helicopters and ASB No. 
52.00.23 for modifying the AS355 series helicopters. These ASBs 
contained modifications 073298 and 073308. The following day, 
Eurocopter issued ASB No. 05.00.45 for the AS355 model helicopters and 
No. 05.00.47 for the AS350 model helicopters, both dated July 19, 2006. 
Later, Eurocopter issued Revision 1 to ASB No. 52.00.23 for the AS355 
model helicopters and No. 52.00.30 for the AS350 model helicopters, 
both dated June 29, 2007, to modify the sliding door medium roller and 
fitting. The actions described in the MCAI AD are intended to correct 
the same unsafe condition as that identified in the service 
information.

[[Page 54502]]

FAA's Evaluation and Unsafe Condition Determination

    This product has been approved by the aviation authority of France 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with France, EASA, their technical agent, has 
notified us of the unsafe condition described in the MCAI AD. We are 
proposing this AD because we evaluated all information provided by EASA 
and determined an unsafe condition exists and is likely to exist or 
develop on other products of these same type designs.

Differences Between This AD and the MCAI AD

    This AD differs from EASA AD No. 2007-0236 as follows:
     We use the word ``inspect'' to describe the actions 
required by a mechanic versus the word ``check,'' which is how we 
describe the actions allowed by a pilot.
     We refer to the compliance time as ``hours time-in-service 
(TIS)'' rather than ``flying hours.''
     We do not require an operator to tell the manufacturer if 
a crack is found in the shaft.
     We are not including the Model L1, which is a military 
model helicopter; but we are including the Models 350C and D1 
helicopters.

Costs of Compliance

    We estimate that this proposed AD would affect about 725 products 
of U.S. registry. We also estimate that it would take about 4 work-
hours per helicopter to inspect and modify the sliding doors. The 
average labor rate is $80 per work-hour. Required parts would cost 
about $7,000 per helicopter. Based on these figures, we estimate the 
cost of the proposed AD on U.S. operators to be $5,307,000.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. 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 this 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 an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new AD:

Eurocopter France: Docket No. FAA-2009-0951; Directorate Identifier 
2007-SW-52-AD.

Comments Due Date

    (a) We must receive comments by November 23, 2009.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Eurocopter France Model AS350B, BA, B1, 
B2, B3, C, D, D1, AS355E, F, F1, F2, and N helicopters, with sliding 
door pre-MOD 073298 or pre-MOD 073308, installed, certificated in 
any category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) AD 
states ``EASA issued Airworthiness Directive (AD) 2006-0251 and its 
revisions following a case of total failure and a case of a crack 
discovered on the support shaft of the sliding door rear roller. 
Metallurgical and metallographic analyses revealed a nonconformity 
concerning the heat treatment of the material. Since then, other 
cases of cracks and failures of the roller support shaft rear attach 
fitting had been reported. This condition, if not corrected, could 
lead to the loss of the sliding door in flight.'' Separation of a 
sliding door in flight creates an unsafe condition because the door 
could come into contact with the rotor system. This AD requires 
actions that are intended to address this unsafe condition.

Actions and Compliance

    (e) Required as indicated.
    (1) For a sliding door with less than 90 hours time-in-service 
(TIS), on or before accumulating a total of 110 hours TIS, unless 
already done, conduct the visual and dye penetrant inspections of 
the support shaft of the rear roller and the rear fitting (fitting) 
of the sliding door for a crack by reference to Figure 1 and by 
following the Operational Procedure, paragraph 2.B.1 and 2.B.2, of 
Eurocopter Alert Service Bulletin (ASB) No. 05.00.47 dated July 19, 
2006, for the Model AS350 helicopters (ASB 05.00.47) or ASB No. 
05.00.45 dated July 19, 2006, for the Model AS355 helicopters (ASB 
05.00.45), except you are not required to contact the manufacturer.
    (i) If no crack is found in the shaft or fitting, reinstall the 
shaft on the fitting, fit the spring pins, and plug the pin holes by 
following the Operational Procedure, paragraph 2.B.2. of ASB 
05.00.47 or 05.00.45, whichever is appropriate for your model 
helicopter.
    (ii) If you find a crack in the fitting, replace the fitting 
with an airworthy fitting before further flight.
    (iii) If you find a crack in the shaft, replace the shaft with 
an airworthy shaft before further flight, by reference to Figure 1 
and following paragraph 2.B.3. of ASB 05.00.47 or 05.00.45, 
whichever is appropriate for your model helicopter.
    (2) For a sliding door with 90 or more hours TIS, within the 
next 20 hours TIS, unless already done, and thereafter at intervals 
not to exceed 110 hours TIS, conduct the visual and dye penetrant 
inspections of the support shaft of the rear roller and the fitting 
of the sliding door for a crack by reference to Figure 1 and by 
following the Operational Procedure, paragraph 2.B.1 and 2.B.2, of 
ASB 05.00.47 or ASB 05.00.45, whichever is appropriate for your 
model helicopter, except you are not required to contact the 
manufacturer.
    (i) If no crack is found in the shaft and fitting, reinstall the 
shaft or fitting, fit the spring pins, and plug the pin holes by 
following the Operational Procedure, paragraph 2.B.2. of ASB 
05.00.47 or 05.00.45, whichever is appropriate for your model 
helicopter.

[[Page 54503]]

    (ii) If you find a crack in the fitting, replace the fitting 
with an airworthy fitting before further flight.
    (iii) If you find a crack in the shaft, replace the shaft with 
an airworthy shaft before further flight by reference to Figure 1 
and by following paragraph 2.B.3. of ASB 05.00.47 or 05.45, 
whichever is appropriate for your model helicopter.
    (3) After the effective date of this AD, do not install any of 
the following parts on any helicopter:
    (i) Left-hand sliding door, part number (P/N) 350A25-0030-00XX, 
350A25-0120-00XX, and 350AMR-0227-0052;
    (ii) Right-hand sliding door, P/N 350A25-0030-01XX, 350A25-0120-
01XX, 350A25-0120-03XX, and 350AMR-0227-0051;
    (iii) Rail roller pin, P/N 350A25-1275-20; and
    (iv) Cast roller support fittings, P/N 350A25-1270-20 and P/N 
350A25-1270-22.

Differences Between This AD and the MCAI AD

    (f) This AD differs from EASA AD No. 2007-0236 as follows:
    (1) We use the word ``inspect'' to describe the actions required 
by a mechanic versus the word ``check,'' which is how we describe 
the actions allowed by a pilot.
    (2) We refer to the compliance time as hours time-in-service 
(TIS) rather than flying hours.
    (3) We do not require an operator to inform the manufacturer if 
a crack is found in the shaft as specified in the service 
information.
    (4) We do not include the Model L1, which is a military model 
helicopter; but we are including the Models 350C and D1 helicopters.

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Safety Management Group, Rotorcraft Directorate, ATTN: DOT FAA, 
Southwest Region, Gary Roach, ASW-111, Aviation Safety Engineer, 
Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, 
Texas 76137, telephone (817) 222-5130, fax (817) 222-5961, has the 
authority to approve AMOCs for this AD, if requested, using the 
procedures found in 14 CFR 39.19.

Related Information

    (h) MCAI EASA AD No. 2007-0236, dated August 31, 2007, contains 
related information.

Joint Aircraft System Component (JASC) Code

    (i) JASC Code 5344: Fuselage Door Hinges.

    Issued in Fort Worth, Texas, on October 8, 2009.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-25440 Filed 10-21-09; 8:45 am]
BILLING CODE 4910-13-P