AD 2006-09-10

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25930-25932]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-4108]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24588; Directorate Identifier 2006-SW-07-AD; 
Amendment 39-14581; AD 2006-09-10]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365 N1, AS-
365 N2, N3, SA 366 G1, and EC-155B and B1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) Model SA-365 N1, AS-365 
N2, N3, SA 366 G1, and EC-155B and B1 helicopters. This action requires 
a one-time inspection for end play in the pitch control rod assembly 
double bearing (bearing) using the tail rotor (T/R) hub control plate, 
and before further flight, replacing the bearing if end play is 
present. This amendment is prompted by one incident in which a pilot 
lost T/R pitch control of a helicopter while landing. The actions 
specified in this AD are intended to detect damage to the bearing, 
resulting in end play and prevent loss of T/R pitch control and 
subsequent loss of control of the helicopter.

DATES: Effective May 18, 2006.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 18, 2006.
    Comments for inclusion in the Rules Docket must be received on or 
before July 3, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    <bullet> DOT Docket Web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically;
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically;
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
    <bullet> Fax: (202) 493-2251; or
    <bullet> 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 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 docket that contains the AD, any comments, and 
other information on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>, or in person 
at the Docket Management System (DMS) Docket Offices between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The Docket 
Office (telephone (800) 647-5227) is located on the plaza level of the 
Department of Transportation Nassif Building at the street address 
stated in the ADDRESSES section. Comments will be available in the AD 
docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort 
Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and 
B1 helicopters. This action requires, within 50 hours time-in-service 
(TIS), a one-time inspection of the T/R hub control plate for end play 
in the bearing, and if end play is present, replacing the bearing 
before further flight. This amendment is prompted by one incident in 
which a pilot lost T/R pitch control of a helicopter while landing. The 
loss of the T/R pitch control was due to significant damage to the 
bearing of the control rod in the tail gearbox. This condition, if not 
detected, could result in loss of T/R pitch control and subsequent loss 
of control of the helicopter.
    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on Eurocopter France Model AS 365 N, SA 366, 
and EC 155 helicopters. EASA advises that the loss of pitch control is 
due to significant damage to the bearing of the control rod in the tail 
gearbox.
    Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.52, 
applicable to the Model 365 N1, N2, and N3 helicopters; ASB No. 05.36, 
applicable to Model 366 G1 helicopters; and ASB No. 05A013, applicable 
to Model EC-155B and B1 helicopters, all dated February 15, 2006, and 
all of which specify a check at regular intervals to ensure there is no 
end play in the bearing of the T/R pitch control rod. EASA classified 
this ASB as mandatory and issued AD No. 2006-0051-E, dated February 20, 
2006, to ensure the continued airworthiness of these helicopters in 
France. This AD does not require repetitive inspections because 
helicopters in this fleet do not normally accrue enough flight hours in 
a short period of time to justify issuing an immediately adopted final 
rule requiring repetitive inspections without allowing the public time 
to first comment on such a proposal. We may issue further AD action at 
a later date to propose repetitive 110-hours TIS inspections.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral agreement. Under this agreement, EASA has kept the 
FAA informed of the situation described above. We have examined EASA's 
findings, evaluated all pertinent information, and determined that AD 
action is necessary for products of this type design that are

[[Page 25931]]

certificated for operation in the United States.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type designs. Therefore, this AD is being 
issued to detect damage to the bearing, resulting in end play and 
prevent loss of T/R pitch control and subsequent loss of control of the 
helicopter. This AD requires, within 50 hours TIS, a one-time 
inspection of the T/R hub control plate for end play in the bearing, 
and if end play is present, replacing the bearing before further 
flight. Accomplish the actions by following the specified portions of 
the ASB described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, inspecting for end play 
in the bearing is required within 50 hours TIS and replacing the 
bearing, if necessary, is required before further flight and this AD 
must be issued immediately. This AD is an interim action until 
Eurocopter completes bench tests to analyze the effect of the oil 
level, associated with pitch control loads, on the behavior of the 
bearing.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 137 helicopters. The one-time 
inspection will take approximately 1 work hour, and replacing the 
bearing, if needed, will take approximately 8 work hours to accomplish 
at an average labor rate of $80 per work hour. Required parts will cost 
approximately $2,026 per helicopter. Based on these figures, the total 
cost impact of the AD on U.S. operators is $365,242, assuming the 
bearing is replaced on the entire fleet.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-24588; 
Directorate Identifier 2006-SW-07-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to <a href="http://dms.dot.gov">http://dms.dot.gov</a>, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. 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 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 <a href="http://dms.dot.gov">http://dms.dot.gov</a>.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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 AD. See the DMS 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.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2006-09-10 Eurocopter France: Amendment 39-14581. Docket No. FAA-
2006-24588; Directorate Identifier 2006-SW-07-AD.

    Applicability: Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and 
EC-155B and B1 helicopters, with a tail rotor (T/R) pitch control 
rod assembly double bearing (bearing) installed, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect damage to the bearing resulting in end play and to 
prevent loss of T/R pitch control and subsequent loss of control of 
the helicopter:
    (a) Within 50 hours time-in-service, inspect the T/R hub control 
plate for end play in the bearing in accordance with paragraph 2.B., 
Operational Procedure, in Eurocopter Alert Service Bulletin No. 
05.00.52, applicable to Model SA-365 N1 and AS-365 N2 and N3 
helicopters; No. 05.36, applicable to Model SA 366 G1 helicopters; 
and No. 05A013, applicable to Model EC-155B and B1 helicopters, 
dated February 15, 2006 (ASBs).
    (b) If end play is present, before further flight, replace the 
bearing with an airworthy bearing. You are not required to contact 
the manufacturer to meet the requirements of this AD.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Regulations Group, Rotorcraft Directorate, FAA, 
ATTN: Uday Garadi, 2601 Meacham Blvd., Fort Worth, Texas, 76193, 
telephone (817) 222-5123, fax (817) 222-5961, for information about 
previously approved alternative methods of compliance.
    (d) Special flight permits will not be issued.
    (e) The inspection and replacement, if necessary, shall be done 
in accordance with the specified portions of Eurocopter Alert 
Service Bulletin No. 05.00.52, applicable to

[[Page 25932]]

Model SA-365 N1 and SA-365 N2 and N3 helicopters; No. 05.36, 
applicable to Model SA 366 G1 helicopters; and No. 05A013, 
applicable to Model EC-155B and B1 helicopters, dated February 15, 
2006. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, 
telephone (972) 641-3460, fax (972) 641-3527. Copies may be 
inspected at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.
    (f) This amendment becomes effective on May 18, 2006.

    Note: The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2006-0051-E, dated February 20, 2006.


    Issued in Fort Worth, Texas, on April 17, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-4108 Filed 5-2-06; 8:45 am]
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