[Federal Register Volume 63, Number 88 (Thursday, May 7, 1998)]
[Rules and Regulations]
[Pages 25158-25160]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-12114]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-49-AD; Amendment 39-10515; AD 98-10-04]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.


[[Page 25159]]


ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Eurocopter France (Eurocopter) Model SA-365N1, AS-365N2, 
and SA-366G1 helicopters, that requires initial and repetitive 
inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for 
cracks or delaminations. This amendment is prompted by a report of 
delamination of a Kevlar tie-bar. The actions specified by this 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: Effective June 11, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 11, 1998.

ADDRESSES: The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Eurocopter Model SA-365N1, AS-
365N2, and SA-366G1 helicopters was published in the Federal Register 
on March 13, 1998 (63 FR 12419). That action proposed to require 
initial and repetitive inspections of the tail rotor blade Kevlar tie-
bar for cracks or delaminations.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.
    The sole commenter states that the proposed AD is more restrictive 
than either Eurocopter France Service Bulletin 05.00.34R3, dated 
November 14, 1996, or Direction Generale De L'Aviation Civile (DGAC) AD 
92-185-033(B)R4, dated December 4, 1996, which allow operation of a 
helicopter having cracks that are within a certain tolerance. The 
commenter states that not all cracks warrant replacement of the part, 
and that the proposed AD should give the same parameters for the cracks 
as given in the Eurocopter France service bulletin and the DGAC AD. The 
FAA does not concur. Any crack or delamination of the Kevlar tie-bar 
could initiate a failure and lead to loss of control of the helicopter. 
The FAA considers any crack in a flight critical part to be unsafe, and 
the part must be replaced prior to further flght.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 47 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
helicopter to accomplish the actions, and that the average labor rate 
is $60 per work hour. Required parts will cost approximately $3,000 per 
blade. Based on these figures, the total cost impact of the 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 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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

    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:

AD 98-10-04  Eurocopter France: Amendment 39-10515. 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 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, perational 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

[[Page 25160]]

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.
    (e) The inspections and replacement, if necessary, shall be done 
in accordance with Eurocopter France Service Bulletin 05.00.34, 
Revision 3, dated November 14, 1996. This incorporation by reference 
was approved by the Director of the Federal Register 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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (f) This amendment becomes effective on June 11, 1998.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 92-185-033(B)R4 dated 
December 4, 1996.

    Issued in Fort Worth, Texas, on April 30, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-12114 Filed 5-6-98; 8:45 am]
BILLING CODE 4910-13-P