[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