[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
