[Federal Register Volume 65, Number 47 (Thursday, March 9, 2000)]
[Proposed Rules]
[Pages 12489-12490]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-5734]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-45-AD]


Airworthiness Directives; Eurocopter France Model SA-365N1, AS-
365N2, and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to Eurocopter France Model SA-
365N1, AS-365N2, and SA-366G1 helicopters, that currently requires 
initial and repetitive inspections of the tail rotor blade Kevlar tie-
bar (Kevlar tie-bar) for cracks or delaminations. This action would 
require the same actions required by the existing AD, and would correct 
an incorrectly stated part number (P/N) in the existing AD. This 
proposal is prompted by a report of delamination of a Kevlar tie-bar. 
The actions specified by the proposed AD are intended to detect cracks 
that could lead to delamination of the Kevlar tie-bar, loss of tail 
rotor control, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before May 8, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-45-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 
76193-0111, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-SW-45-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-45-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Model SA-365N1, AS-365N2, and SA-366G1 
helicopters. The DGAC advises that delamination outside certain 
tolerance limits may occur on Kevlar tie-bars.
    On April 30, 1998, the FAA issued AD 98-10-04, Amendment 39-10515 
(63 FR 25158, May 7, 1998), to require, within 10 hours time-in-service 
(TIS), and thereafter at intervals not to exceed 250 hours TIS, 
inspecting the Kevlar tie-bar for a crack or delamination and replacing 
any blade in which a crack or delamination is found with an airworthy 
blade. That action was prompted by a report of delamination of a Kevlar 
tie-bar. That condition, if not corrected, could result in loss of tail 
rotor control and subsequent loss of control of the helicopter.
    Since the issuance of that AD, the FAA has discovered that a blade 
P/N was incorrectly stated in the existing AD. That P/N was incorrectly 
stated as 365A12-0020-20. The correct P/N is 365A12-0020-02.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of these type designs that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Model SA-365N1, AS-365N2, and SA-366G1 
helicopters of the same type design, the proposed AD would supersede AD 
98-10-04 to require, within 10 hours TIS, and thereafter at intervals 
not to exceed 250 hours TIS, inspecting the Kevlar tie-bar for a crack 
or delamination and replacing any blade in which a crack or 
delamination is found.
    The FAA estimates that 47 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $3,000 per blade. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be $152,280 
to replace one blade and perform one inspection on each helicopter.
    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that 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) if

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promulgated, 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. A copy of the draft regulatory 
evaluation prepared for this action is contained in the Rules Docket. A 
copy of it may be obtained by contacting the Rules Docket at the 
location provided under the caption ADDRESSES.

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 removing Amendment 39-10515 (63 FR 
25158, May 7, 1998), and by adding a new airworthiness directive (AD), 
to read as follows:

Eurocopter France: Docket No. 99-SW-45-AD. Supersedes AD 98-10-04, 
Amendment 39-10515, Docket No. 97-SW-49-AD.

    Applicability: Model SA-365N1, AS-365N2, and SA-366G1 
helicopters, with tail rotor blade (blade), Part Number 365A12-010-
all dash numbers, 365A12-0020-00, 365A33-2131-all dash numbers, or 
365A12-0020-02, installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect cracks that could lead to delamination of the tail 
rotor blade Kevlar tie-bar (Kevlar tie-bar), loss of tail rotor 
control, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within 10 hours time-in-service (TIS), and thereafter at 
intervals not to exceed 250 hours TIS, inspect each Kevlar tie-bar 
for a crack or delamination in accordance with paragraph B, 
Operational Procedure, of Eurocopter France Service Bulletin 
05.00.34, Revision 3, dated November 14, 1996.
    (b) If any delamination or cracking is found during any of the 
inspections required by paragraph (a) of this AD, remove the blade 
and replace it with an airworthy blade before further flight.
    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the helicopter to a location where the 
requirements of this AD can be accomplished.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 92-185-33(B)R4, dated 
December 4, 1996.


    Issued in Fort Worth, Texas, on March 1, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-5734 Filed 3-8-00; 8:45 am]
BILLING CODE 4910-13-P