[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.
[[Page 11118]]
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
