Airworthiness Directives; Eurocopter France (ECF) Model SA-365N1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 Helicopters, 20931-20932 [2010-9292]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 75, Number 77 (Thursday, April 22, 2010)]
[Proposed Rules]
[Pages 20931-20932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-9292]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

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

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Federal Register / Vol. 75, No. 77 / Thursday, April 22, 2010 / 
Proposed Rules

[[Page 20931]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0426; Directorate Identifier 2009-SW-34-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (ECF) Model SA-365N1, 
AS-365N2, AS 365 N3, EC 155B, and EC155B1 Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
specified ECF 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 MCAI AD reports 
the separation and loss of a stainless steel ring (75 millimeter (mm) 
in diameter) from a tail rotor blade (blade) sleeve resulting in 
severe, high-frequency vibrations, which can lead to damage to the 
fenestron blades, loss of yaw control, and subsequent loss of control 
of the helicopter.

DATES: We must receive comments on this proposed AD by May 24, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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, 
TX 75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
https://www.eurocopter.com.
    Examining the Docket: You may examine the AD docket on the Internet 
at https://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 
stated in the ADDRESSES section of this proposal. 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 data, views, or arguments about 
this proposed AD. Send your comments to an address listed in the 
ADDRESSES section of this proposal. Include ``Docket No. FAA-2010-0426; 
Directorate Identifier 2009-SW-34-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 https://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

    The EASA, which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD No. 2006-0099, dated April 24, 
2006, to correct an unsafe condition for the specified ECF model 
helicopters. EASA issued an AD following a case of separation and loss 
of a stainless steel ring (75 mm in diameter) from a blade sleeve 
resulting in severe, high-frequency vibrations, which can lead to 
damage to the fenestron blades, loss of yaw control, and subsequent 
loss of control of the helicopter.
    You may obtain further information by examining the MCAI AD and any 
related service information in the AD docket.

Related Service Information

    Eurocopter has issued Alert Service Bulletin No. 05A011 for the 
Model EC 155B and B1 helicopters and No. 05.00.49 for the Model SA-
365N1, AS-365N2, and AS 365 N3 helicopters. Both service bulletins are 
dated March 1, 2006. The service information specifies checking the 
blade sleeve for slippage of the stainless steel ring (75 mm in 
diameter) and replacing the blade if the stainless steel ring has 
slipped. The actions described in the MCAI AD are intended to correct 
the unsafe condition identified in the service information.

FAA's Evaluation and Unsafe Condition Determination

    These helicopters have been approved by the aviation authority of 
France and are 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 the unsafe condition exists and is likely to exist or 
develop on other helicopters of these same type designs. This proposed 
AD would require:
     For the Model SA-365N1, AS-365N2, and AS 365 N3 
helicopters, within 50 hours time-in-service (TIS), unless done 
previously, and thereafter at intervals not to exceed 10 hours TIS, 
inspect each blade of the fenestron tail rotor to determine whether 
there has been any outward slippage (toward the shroud) of the 
stainless steel ring that is

[[Page 20932]]

around the sleeve of each blade where the blade enters the fenestron 
hub.
     For the Model EC 155B or B1 helicopters, within 50 hours 
time-in-service (TIS), unless done previously, and thereafter at 
intervals not to exceed 15 hours TIS, inspect each blade for slippage 
of the fenestron tail rotor to determine whether there has been any 
outward slippage (toward the shroud) of the stainless steel ring that 
is around the sleeve of each blade where the blade enters the fenestron 
hub.
     If the stainless steel ring has slipped outward, before 
further flight, replace the blade with an airworthy blade.

Differences Between This AD and the MCAI AD

    We refer to flying hours as hours time-in-service. Also, we use 
``inspect'' rather than ``check'' to describe the actions required by 
this AD. We use a different initial compliance time.

Costs of Compliance

    We estimate that this proposed AD would affect about 33 helicopters 
of U.S. registry. We also estimate that it would take about 15 minutes 
per helicopter to inspect for slippage of the stainless steel ring of 
the blade sleeve. The average labor rate is $80 per work-hour. Based on 
these figures, we estimate the cost of the proposed AD on U.S. 
operators would be $660 assuming none of the blades would have to be 
replaced.

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 helicopters 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.
    Therefore, I certify this proposed AD:
    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-2010-0426; Directorate Identifier 
2009-SW-34-AD.

Comments Due Date

    (a) We must receive your comments by May 24, 2010.

Other Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model SA-365N1, AS-365N2, AS 365 N3, EC 
155B, and EC155B1 helicopters, with a fenestron tail rotor blade 
(blade), part number 365A12-0060-01 or 365A12-0070-00, installed, 
certificated in any category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) AD 
reports the separation and loss of a stainless steel ring (75 mm in 
diameter) from a blade sleeve resulting in severe, high-frequency 
vibrations, which can lead to damage to the fenestron blades, loss 
of yaw control, and subsequent loss of control of the helicopter.

Actions and Compliance

    (e) Required as indicated:
    (1) For the Model SA-365N1, AS-365N2, and AS 365 N3 helicopters, 
within 50 hours time-in-service (TIS), unless done previously, and 
thereafter at intervals not to exceed 10 hours TIS, inspect each 
blade of the fenestron tail rotor to determine whether there has 
been any outward slippage (toward the shroud) of the stainless steel 
ring that is around the sleeve of each blade where the blade enters 
the fenestron hub as depicted in Appendix 1 and by following the 
Accomplishment Instructions, paragraph 2.B.1., of Eurocopter Alert 
Service Bulletin No. 05.00.49, dated March 1, 2006.
    (2) For the Model EC 155B or B1 helicopters, within 50 hours 
time-in-service (TIS), unless done previously, and thereafter at 
intervals not to exceed 15 hours TIS, inspect each blade of the 
fenestron tail rotor to determine whether there has been any outward 
slippage (toward the shroud) of the stainless steel ring that is 
around the sleeve of each blade where the blade enters the fenestron 
hub as depicted in Appendix 1 and by following paragraph 2.B.1., of 
Eurocopter Alert Service Bulletin No. 05A011, dated March 1, 2006.
    (3) If the stainless steel ring has slipped outward, before 
further flight, replace the blade with an airworthy blade.

Differences Between This AD and the MCAI AD

    (f) We refer to flying hours as hours time-in-service. Also, we 
use ``inspect'' rather than ``check'' to describe the action to be 
taken in the AD. We use a different initial compliance time.

Other Information

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Rotorcraft Directorate, Safety Management Group, 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) European Aviation Safety Agency MCAI Airworthiness Directive 
No. 2006-0099, dated April 24, 2006, contains related information.

Joint Aircraft System/Component (JASC) Code

    (i) The JASC Code is 6400: Tail Rotor.

    Issued in Fort Worth, Texas, on April 14, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-9292 Filed 4-21-10; 8:45 am]
BILLING CODE 4910-13-P