[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
