[Federal Register Volume 63, Number 44 (Friday, March 6, 1998)]
[Rules and Regulations]
[Pages 11116-11118]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-5733]



[[Page 11116]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-53-AD; Amendment 39-10378; AD 98-05-17]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, SA-
365N1, AS-365N2, and 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-365N, SA-365N1, AS-365N2, 
and SA-366G1 helicopters. This action requires inspecting for 
rotational play or looseness of the outboard fin attachment studs 
(studs) and washers (if washers are present); inspecting each stud for 
incremental rotational movement or pure rotation; and if there is 
rotational play or looseness of any individual stud, performing a dye-
penetrant inspection for cracks on each stud utilized in the 
installation. This amendment is prompted by a report of an outboard fin 
separating from the helicopter during flight, and several reports of 
loose outboard fins in service. This condition, if not corrected, could 
result in an outboard fin separating and contacting the rotor blades 
during flight, and subsequent loss of control of the helicopter.

DATES: Effective March 23, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 23, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before May 5, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 97-W-53-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, has notified 
the FAA that an unsafe condition may exist on Eurocopter France Model 
SA-365N, SA-365N1, AS-365N2, and AS-366G1 helicopters. The DGAC advises 
that, due to the loss of an outboard fin in flight and the discovery of 
some loose outboard fins in service, within 50 flying hours, the 
directives stated in paragraphs B1, B2, and B3 of Eurocopter France AS 
365 Service Bulletin No. 01.00.40, Revision No. 1, and Eurocopter 
France AS 366 Service Bulletin No. 01.20, Revision No. 1, both dated 
October 24, 1996, must be accomplished.
    Eurocopter France has issued Eurocopter France AS 365 Service 
Bulletin No. 01.00.40, Revision No. 1, which is applicable to Model SA-
365N, SA-365N1, and AS-365N2 helicopters, and Eurocopter France AS 366 
Service Bulletin No. 01.20, Revision No. 1, which is applicable to 
Model SA-366G1 helicopters, both dated October 24, 1996, which specify 
checking the tightening torque value on studs on which MOD 0755B08 has 
not been incorporated. The DGAC classified this service bulletin as 
mandatory and issued AD 94-076-036(B)R1, dated December 4, 1996, 
applicable to Model SA-365N, SA-365N1, and AS-365N2 helicopters, and AD 
94-077-016(B)R1, dated December 4, 1996, applicable to Model SA-366G1 
helicopters, in order to assure the continued airworthiness of these 
helicopters in France. According to the type certificate data sheet for 
Eurocopter France helicopters listed in the U.S. Register, the model 
designation is SA-366G1 instead of AS 366.
    These helicopter models are manufactured in France and are 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-365N, SA-365N1, 
AS-365N2, and SA-366G1 helicopters of the same type design registered 
in the United States, this AD is being issued to prevent an outboard 
fin separating and contacting the rotor blades during flight, and 
subsequent loss of control of the helicopter. This AD requires 
inspecting for rotational play or looseness of the studs and the 
washers used to attach the outboard fin to the helicopter (if washers 
are present); inspecting each stud for incremental rotational movement 
or pure rotation; and if there is rotational play or looseness of any 
individual stud, performing a dye-penetrant inspection for cracks on 
each stud utilized in the installation. If a crack is found, 
replacement of the cracked stud with an airworthy stud is required. The 
actions are required to be accomplished in accordance with the service 
bulletins described previously. The outboard fin is a major component 
of the flight control system. If the outboard fin separated from the 
helicopter, it could contact the rotor blades during flight, resulting 
in subsequent loss of control of the helicopter. Due to the criticality 
of the outboard fin's retention to the continued safe flight of the 
affected helicopters, this rule must be issued immediately to correct 
an unsafe condition in the affected helicopters.
    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.
    The FAA estimates that 37 helicopters of U.S. Registry will be 
affected by this AD, that it will take approximately 2 work hours per 
helicopter to accomplish the proposed actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$100 per helicopter. Based on these figures, the total cost impact of 
the this AD on U.S. operators is estimated to be $8,140.

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.

[[Page 11117]]

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-53-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 98-05-17  Eurocopter France: Amendment 39-10378. Docket No. 97-
SW-53-AD.

    Applicability: Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 
helicopters, 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 (b) 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 within 50 hours time-in-service, unless 
accomplished previously.
    To prevent an outboard fin from separating and contacting the 
rotor blades during flight, resulting in loss of control of the 
helicopter, accomplish the following:
    (a) For helicopters with outboard fins that are secured with 
outboard fin attachment studs (studs), part number (P/N) 365A13-
3017-24, which have not been modified in accordance with MOD 
0755B08, remove the outboard fins and inspect for the presence of 
washers in the seating plane of the outboard fins.
    (1) If washers are present, inspect for rotational play or 
looseness of the washers.
    (2) If washers are not present, use shims to inspect for play or 
looseness between the stud and the seating plane.
    (3) With each outboard fin removed, inspect each stud to ensure 
there is no incremental rotational movement or pure rotation when 
the tightening torque load specified in paragraph B.1) of the 
Accomplishment Instructions of both Eurocopter France AS 365 Service 
Bulletin No. 01.00.40, Revision No. 1, which is applicable to Model 
SA-365N, SA-365N1, and AS-365N2 helicopters, and Eurocopter France 
AS 366 Service Bulletin No. 01.20, Revision No. 1, which is 
applicable to Model SA-366G1 helicopters, both dated October 24, 
1996, is applied.
    (4) If no play or looseness between the stud and the seating 
plane and no incremental rotational movement or pure rotation is 
discovered, reinstall the outboard fins as specified in paragraph 
B.2) of the Accomplishment Instructions in the applicable service 
bulletins specified in paragraph (3) of this AD.
    (5) If play or looseness between the stud and the seating plane 
and incremental movement or rotation is discovered, remove the 
washers (if present) and studs and perform a dye-penetrant 
inspection of the stud for cracks in accordance with paragraph B.3) 
of the Accomplishment Instructions in the applicable service 
bulletins specified in paragraph (3) of this AD.
    (6) If a crack is discovered as a result of the inspection 
required by paragraph (5) of this AD, replace the stud with an 
airworthy stud. Reinstall the outboard fin in accordance with Note I 
in the applicable service bulletins specified in paragraph (3) of 
this AD.
    (b) 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.

    (c) 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.
    (d) The inspections shall be done in accordance with Eurocopter 
France AS 365 Service Bulletin No. 01.00.40, Revision No. 1, and 
Eurocopter France AS 366 Service Bulletin No. 01.20, Revision No. 1, 
both dated October 24, 1996. These incorporations by reference were 
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 
76137; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on March 23, 1998.


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    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 94-077-016(B)R1 and AD 94-
076-036(B)R1, both dated December 4, 1996.

    Issued in Fort Worth, Texas, on February 26, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-5733 Filed 3-5-98; 8:45 am]
BILLING CODE 4910-13-P