[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