[Federal Register Volume 63, Number 49 (Friday, March 13, 1998)]
[Proposed Rules]
[Pages 12419-12421]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6496]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-49-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 adoption of a new airworthiness 
directive (AD) that is applicable to Eurocopter France (Eurocopter) 
Model SA-365N1, AS-365N2, and SA-366G1 helicopters. This proposal would 
require initial and repetitive inspections of the tail rotor blade 
Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. 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 by April 13, 1998.

addresses: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-SW-49-AD, 2601 Meacham Blvd, Room 663, 
Fort Worth, Texas 76197. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    This service information referenced in the proposed rule may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas

[[Page 12420]]

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: Mr. Mike Mathias, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5123, 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. 97-SW-49-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. 97-SW-49-AD, 2601 Meacham Blvd, Fort Worth, 
Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on SA-365N1, AS-365N2, and SA-366G1 model 
helicopters. The DGAC advises that delamination outside certain 
tolerance limits may occur on Kevlar tie-bars.
    Eurocopter France issued Telex Service Bulletin (SB) 05.33, dated 
August 19, 1992, that specifies visually checking the condition of the 
Kevlar tie-bar assembly for delamination around the blade-to-hub 
attachment point within 10 flying hours. If delamination exists that is 
outside certain tolerance limits, SB 05.33 specifies removing the rail 
rotor blade (blade) and replacing it with an airworthy blade. 
Eurocopter France also issued SB 05.00.34, Revision 3, dated November 
14, 1996, that specifies repetitive visual inspections at intervals of 
250 flying hours of the Kevlar tie-bar for delaminations. If certain 
cracks exist, SB 05.00.34, Revision 3, specifies removing the blade 
from service. The DGAC classified these service bulletins as mandatory 
and issued DGAC AD 92-185-033(B)R4, dated December 4, 1996, to ensure 
the continued airworthiness of these helicopters in France.
    This helicopter model is manufactured in France and is 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 this type design 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 Eurocopter France Model SA-365N1, AS-365N2, 
and SA-366G1, helicopters of the same type design registered in the 
United States, the proposed AD would require within 10 hours time-in-
service (TIS), and thereafter at intervals not to exceed 250 hours TIS, 
inspections of the Kevlar tie-bar for a crack of delamination and 
replacement of any balde in which a crack or delamination is found with 
an airworthy blade. The actions would be required to be accomplished in 
accordance with the service bulletin described previously.
    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 proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 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 adding a new airworthiness directive 
to read as follows:

Eurocopter France: Docket No. 97-SW-49-AD.

    Applicability: SA-365N1, AS-365N2, and SA-366G1 model 
helicopters, with tail rotor blade (blade), Part Number 365A12-010-
all dash numbers, 365A12-0020-00, 365A33-2131-all dash numbers, or 
365A12-0020-20, 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 
modified, altered, or repaired in the area

[[Page 12421]]

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 use the 
authority provided in paragraph (c) to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition, or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    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) after the effective 
date of this AD, 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, Rotorcraft Standards Staff, 
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, Rotorcraft Standards Staff.

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

    (d) Special flight permits may be issued in accordance with 
sections 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 February 28, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-6496 Filed 3-12-98; 8:45 am]
BILLING CODE 4910-13-M