Airworthiness Directives; Eurocopter France Model AS 350 B, BA, B1, B2, B3, and D, and Model AS355 E, F, F1, F2, and N Helicopters, 34062-34063 [2010-14540]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 75, Number 115 (Wednesday, June 16, 2010)]
[Proposed Rules]
[Pages 34062-34063]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-14540]


========================================================================
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.

========================================================================


Federal Register / Vol. 75, No. 115 / Wednesday, June 16, 2010 / 
Proposed Rules

[[Page 34062]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0611; Directorate Identifier 2009-SW-18-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS 350 B, BA, 
B1, B2, B3, and D, and Model AS355 E, F, F1, F2, and N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
Eurocopter France Model AS 350 B, BA, B1, B2, B3, and D, and Model 
AS355 E, F, F1, F2, and N helicopters, with certain main rotor servo-
controls and tail rotor servo-controls. This proposed AD would require 
replacing all servo-controls that are identified in the Applicability 
section of this proposed AD. This proposed AD is prompted by an 
internal review conducted by the manufacturer which revealed that some 
main and tail rotor servo-controls do not conform to the approved 
design. The actions specified by this proposed AD are intended to 
prevent the distributor slide valve jamming in its sleeve, leading to 
reduced controllability of the rotors and subsequent loss of control of 
the helicopter.

DATES: Comments must be received on or before August 16, 2010.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     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, 
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://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: J.R. Holton, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, ASW-111, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-4964, 
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-2010-0611, 
Directorate Identifier 2009-SW-18-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://www.regulations.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 the 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).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency AD No. 2007-0141-E, dated May 21, 2007, to correct an unsafe 
condition for certain Eurocopter France Model AS 350 B, BA, BB, B1, B2, 
B3, and D, and Model AS355 E, F, F1, F2, and N helicopters. EASA 
advises that an internal review revealed that some main and tail rotor 
servo-controls do not conform to the approved design. This results in a 
greater play in the input lever bearing which could lead to off-
centered lever/distributor slide valve. If not corrected, this 
condition could jam the distributor slide valve in its sleeve, 
contributing to reduced controllability of the rotors and subsequent 
loss of control of the helicopter.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin (EASB) No. 
01.00.58, applicable to Model AS 350 B, BA, BB, B1, B2, B3, and D 
helicopters, and EASB No. 01.00.53, applicable to Model AS355 E, F, F1, 
F2, and N helicopters, both Revision 1 and both dated April 19, 2007, 
``to preclude the risk of jamming of the distributor slide valve in its 
sleeve, due to excessive play in the bearing of the servo-control input 
lever.'' Both EASB 01.00.58 and 01.00.53, along with 01.00.22 and 
01.00.23 for various military model helicopters are contained in the 
same EASB document. The EASA classified these EASBs as mandatory and 
issued EASA Emergency AD No. 2007-0141-E, dated May 21, 2007, to ensure 
the continued airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition Determination

    These products have been approved by the aviation authority of 
France and are approved for operation in the United

[[Page 34063]]

States. Pursuant to our bilateral agreement with France, EASA, their 
technical representative, 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 products of these 
same type designs. This proposed AD would require replacing all servo-
controls with serial numbers that are in the Applicability section of 
this proposed AD.

Differences Between This Proposed AD and the EASA AD

    This proposed AD does not require returning servo-controls to the 
manufacturer for return to conformity. The proposed AD does not require 
inspecting for the existence of ``hard points'' in the flight controls.

Costs of Compliance

    We estimate that this proposed AD would affect 56 helicopters of 
U.S. registry and the proposed actions would take approximately 1.5 
work hours per helicopter to accomplish at an average labor rate of $85 
per work hour. Required parts would cost approximately $16,500 per 
helicopter. Based on these figures, we estimate the total cost impact 
of the proposed AD on U.S. operators to be $931,140 for the entire 
fleet.

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 an economic evaluation of the estimated costs to comply 
with this proposed AD. See the AD docket to examine the 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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-2010-0611; Directorate Identifier 
2009-SW-18-AD.
    Applicability: Model AS 350 B, BA, B1, B2, B3, and D, and Model 
AS355 E, F, F1, F2, and N helicopters, with a main rotor or tail 
rotor servo-control identified in Table 1, installed, certificated 
in any category.

                                 Table 1
------------------------------------------------------------------------
            Component               Part No. (P/N)     Serial No. (S/N)
------------------------------------------------------------------------
Main rotor servo-control........  P/N SC5083........  S/N 270M, 272M,
                                                       409M, 423M, 452M,
                                                       or 1573.
                                  P/N SC5083-1......  S/N 2902 through
                                                       2921, inclusive.
                                  P/N 5084..........  S/N 30, 84, 104,
                                                       186, 438, 575, or
                                                       695.
                                  P/N 5084-1........  S/N 1462 through
                                                       1481, inclusive.
Tail rotor servo-control........  P/N SC5072........  S/N 222M, 306M, or
                                                       309.
------------------------------------------------------------------------

    Compliance: Required as indicated.
    To prevent the distributor slide valve jamming in its sleeve, 
leading to reduced controllability of the rotors and subsequent loss 
of control of the helicopter, accomplish the following:
    (a) Within 50 hours time-in-service (TIS), or when a ``hard 
point'' is detected in the flight controls, whichever occurs 
earlier, replace each installed servo control that has a serial 
number listed in Table 1 of this AD, with an airworthy servo 
control.

    Note 1:  Eurocopter EASB 01.00.58 and 01.00.53 have guidance 
which pertains to the subject of this AD.

    (b) 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, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: J.R. Holton, Aviation Safety Engineer, 
Regulations and Policy Group, ASW-111, 2601 Meacham Blvd., Fort 
Worth, Texas 76137, telephone (817) 222-4964, fax (817) 222-5961, 
for information about previously approved alternative methods of 
compliance.
    (c) The Joint Aircraft System/Component (JASC) Code is 6730: 
Rotorcraft Servo System.

    Note 2: The subject of this AD is addressed in Eurocopter 
Aviation Safety Agency (France) Emergency AD No. 2007-0141-E, dated 
May 21, 2007.


    Issued in Fort Worth, Texas, on June 9, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-14540 Filed 6-15-10; 8:45 am]
BILLING CODE 4910-13-P