[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13514-13516]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7248]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-31-AD; Amendment 39-10414; AD 98-06-35]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA-366G1
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Eurocopter France Model SA-366G1 helicopters. This
action requires initial and repetitive inspections of the tail rotor
blade Kevlar tie-bar (Kevlar tie-bar) for delaminations. This amendment
is prompted by a report of delamination of a Kevlar tie-bar. The
actions specified in this AD are intended to detect delaminations of
the Kevlar tie-bar, that could result in loss of anti-torque function
and subsequent loss of control of the helicopter.
DATES: Effective April 6, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 6, 1998.
Comments for inclusion in the Rules Docket must be received on or
before May 19, 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-31-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: 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 Model SA-366G1
helicopters. The DGAC advises that delamination outside certain
tolerance limits may occur on Kevlar tie-bars.
Eurocopter France has issued Eurocopter France Telex Service
Bulletin No. 05.19, dated August 19, 1992, which specifies visually
checking the condition of the Kevlar tie-bar assembly for delamination
around the blade-to-hub attachment point within 10 flying hours, and if
delamination exists that is outside certain tolerance limits, removing
the tail rotor blade and replacing it with an airworthy blade.
Eurocopter France also issued Eurocopter France SA 366 Service Bulletin
No. 05.20, Revision 3, dated November 14, 1996, which specifies
repetitive visual inspections of the Kevlar tie-bar for delamination,
and if delamination exists that is outside certain tolerance limits,
removing the tail rotor blade and replacing it with an airworthy tail
rotor blade at intervals of 250 flying hours. The DGAC classified these
service bulletins as mandatory and issued DGAC AD 92-186-014(B)R4,
dated December 4, 1996, in order to assure 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.
The FAA estimates that 91 helicopters of U.S. registry will be
affected by this AD, that it will take 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 helicopter.
Based on these figures, the total cost impact of this AD on U.S.
operators is estimated to be $294,840.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model SA-366G1 helicopters
of the same type design registered in the United States, this AD is
being issued to detect delaminations of the Kevlar tie-bar, that could
result in loss of anti-
[[Page 13515]]
torque function and subsequent loss of control of the helicopter. The
actions are required to be accomplished in accordance with the service
bulletins described previously. The short compliance time involved is
required because the previously described critical unsafe condition can
adversely affect the controllability of the helicopter. Therefore, an
initial inspection within 10 hours time-in-service is required and this
AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-SW-31-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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 98-06-35 Eurocopter France: Amendment 39-10414. Docket No. 97-
SW-31-AD.
Applicability: Model SA-366G1 helicopters, with tail rotor
blades, part numbers (P/N) 365A12-0010-all dash numbers, 365A12-
0020-01, 365A33-2131-all dash numbers, or 365A12-0020-03, 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 (d) 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 delaminations of the tail rotor blade Kevlar tie-bar
(Kevlar tie-bar), that could result in loss of anti-torque function
and subsequent loss of control of the helicopter, accomplish the
following:
(a) Within 10 hours time-in-service (TIS), inspect each Kevlar
tie-bar in accordance with paragraph CC of Eurocopter France Telex
Service Bulletin 05.19, dated August 19, 1992. This initial
inspection is not required for blade P/N 365A12-0020-03.
Note 2: Twisting the Kevlar tie-bar slightly when inspecting
will make it easier to identify any faults.
(b) Within 250 hours TIS, and thereafter at intervals not to
exceed 250 hours TIS, inspect each Kevlar tie-bar in accordance with
paragraph 2.B of Eurocopter France Service Bulletin 05.20, Revision
3, dated November 14, 1996.
(c) If any delamination is found during any of the inspections
required by paragraphs (a) or (b) of this AD, remove the blade and
replace it with an airworthy blade before further flight.
(d) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(e) 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.
(f) The inspections shall be done in accordance with Eurocopter
France Telex SB 05.19, dated August 19, 1992 and Eurocopter France
SB 05.20, Revision 3, dated November 14, 996. 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.,
[[Page 13516]]
Room 663, Fort Worth, Texas 76137; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on April 6, 1998.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 92-186-014(B)R4, dated
December 4, 1996.
Issued in Fort Worth, Texas, on March 12, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-7248 Filed 3-19-98; 8:45 am]
BILLING CODE 4910-13-U
