[Federal Register Volume 62, Number 244 (Friday, December 19, 1997)]
[Rules and Regulations]
[Pages 66506-66508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-33145]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-50-AD; Amendment 39-10261; AD 97-26-18]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA-360C
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-360C helicopters. This
action requires replacement of the main gear box (MGB) input bevel
pinion (bevel pinion). This amendment is prompted by service reports of
bevel pinion fatigue cracking. This condition, if not corrected, could
result in failure of the MGB and a subsequent forced landing.
DATES: Effective January 5, 1998.
Comments for inclusion in the Rules Docket must be received on or
before January 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-SW-50-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, (817) 222-
5961.
SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation (DGAC),
which is the airworthiness authority for France, recently notified the
FAA that an unsafe condition may exist on Eurocopter France Model SA-
360C helicopters with MGB, part number (P/N) 360A32-2000--all dash
numbers, installed. The DGAC advises that replacement of the MGB bevel
pinion, P/N 360A32-1021-20, is necessary at 1,000 hours time-in-service
(TIS) intervals to prevent fatigue cracking of the bevel pinion,
failure of the MGB, and a subsequent forced landing.
Eurocopter France has issued Service Bulletin No. 01.35, dated
January 14, 1997, which specifies replacement of the MGB bevel pinion
at 1,000 hour TIS intervals. The DGAC classified this service bulletin
as mandatory and issued DGAC AD 97-027-041(B), dated February 12, 1997,
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.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model SA-360C helicopters
of the same type design registered in the United States, this AD is
being issued to prevent bevel pinion fatigue cracking, failure of the
MGB, and a subsequent forced landing. This AD requires replacement of
the bevel pinion at specified TIS intervals.
None of the Eurocopter France Model SA-360C helicopters affected by
this AD action are on the U.S. Register. All
[[Page 66507]]
helicopters included in the applicability of this rule are currently
operated by non-U.S. operators under foreign registry; therefore, they
are not directly affected by this AD action. However, the FAA considers
that this rule is necessary to ensure that the unsafe condition is
addressed in the event that any of these subject helicopters are
imported and placed on the U.S. Register in the future.
Should an affected helicopter be imported and placed on the U.S.
Register, it will require approximately 8.5 work hours to accomplish
the required actions, at an average labor rate of $60 per work hour.
Required parts will cost $17,000 per helicopter for each replacement.
Based on these figures, the cost impact of this AD will be $17,510 per
helicopter for each MGB bevel pinion replacement.
Since this AD action does not affect any helicopter that is
currently on the U.S. register, it has no adverse economic impact and
imposes no additional burden on any person. Therefore, notice and
public procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
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-50-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 notice and prior public comment are
unnecessary in promulgating this regulation and therefore, it can be
issued immediately to correct an unsafe condition in aircraft since
none of these model helicopters are registered in the United States,
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, 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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
97-26-18 Eurocopter France: Amendment 39-10261. Docket No. 97-SW-
50-AD.
Applicability: Model SA-360C helicopters with main gearbox
(MGB), part number (P/N) 360A32-2000--all dash numbers, 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 prevent fatigue cracking of the MGB bevel pinion, failure of
the MGB, and a subsequent forced landing, accomplish the following:
(a) Before further flight, and thereafter at intervals not to
exceed 1,000 hours time-in-service (TIS), replace the MGB bevel
pinion, P/N 360A32-1021-20, on MGBs that have accumulated 900 or
more hours TIS since first installed on any helicopter or since the
last MGB overhaul.
(b) On or before the accumulation of 1,000 hours TIS, and
thereafter at intervals not to exceed 1,000 hours TIS, replace the
bevel pinion, P/N 360A32-1021-20, on MGBs that have accumulated less
than 900 hours TIS since first installed on any helicopter or since
the last MGB overhaul. This AD revises the Airworthiness Limitations
section of the maintenance manual by establishing a new retirement
life for the bevel pinion, P/N 360A32-1021-20, of 1,000 hours TIS.
Note 2: Eurocopter France Mandatory Service Bulletin No. 01.35,
dated January 14, 1997, contains additional information concerning
the subject of this AD.
(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, FAA,
Rotorcraft Directorate. 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.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199
[[Page 66508]]
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) This amendment becomes effective on January 5, 1998.
Note 4: The subject of this AD is addressed in Direction
Generale de L'Aviation Civile (France) AD 97-027-041(B), dated
February 12, 1997.
Issued in Fort Worth, Texas, on December 12, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-33145 Filed 12-18-97; 8:45 am]
BILLING CODE 4910-13-P
