[Federal Register Volume 64, Number 131 (Friday, July 9, 1999)]
[Proposed Rules]
[Pages 37046-37049]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-17487]


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 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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  Federal Register / Vol. 64, No. 131 / Friday, July 9, 1999 / Proposed 
Rules  

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-75-AD]


Airworthiness Directives; Eurocopter France Model SA-365C, C1, 
C2, N, and N1; AS-365N2; and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) applicable to Eurocopter France Model SA-365C, C1, C2, 
N, and N1; AS-365N2; and SA-366G1 helicopters. This proposal would 
require inspecting the tightening torque of the main rotor hub blade 
attach beam spherical thrust bearing bolts (bolts). The proposal would 
then require either applying the specified torque or, if necessary, 
conducting a dye penetrant inspection for cracks in the metal 
components. If a crack is found, the proposal would require replacing 
the spherical thrust bearing (bearing) with an airworthy bearing. This 
proposal is prompted by reports of cracks in the metal components of 
the bearing attachment joint. The actions specified by the proposed AD 
are intended to prevent loosening of bearing bolts in flight, which may 
cause cracks in the metal components, failure of the bearing, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 7, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-75-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas. Comments may be inspected at this location between 9 
a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Mike Mathias, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 
76193-0111, telephone (817) 222-5123, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 98-SW-75-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-75-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    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-365C, C1, C2, N, and 
N1; AS-365N2; and SA-366G1 helicopters. The DGAC advises of the 
formation of cracks in the metal components of the bearing joint due to 
increased stress resulting from possible loosening of the bearing 
bolts.
    Eurocopter France has issued Service Bulletins 05.22, 05.24, and 
05.00.39, all dated July 17, 1998 (SB's). The SB's specify inspecting 
the bearing bolts for the specified tightening torque and applying a 
greater torque or, if necessary, performing a dye penetrant inspection 
of the metal components of the bearing joint for cracks and replacing 
any bolt in which a crack is found. The DGAC classified these SB's as 
mandatory and issued AD's 98-383-044(A), 98-382-024(A), 98-384-047(A), 
all dated September 23, 1998, to ensure the continued airworthiness of 
these helicopters in France.
    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 these type designs 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-365C, C1, C2, N, 
and N1; AS-365N2; and SA-366G1 helicopters of the same type designs 
registered in the United States, the proposed AD would require 
inspecting to determine the torque applied to the bearing bolts and 
replacing the bearing if a crack is found.
    The FAA estimates that 100 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.5 work 
hour and approximately 3,000 inspections over the life of the fleet per 
helicopter to accomplish the proposed actions, and that the average 
labor rate is $60 per work hour. Required parts would cost 
approximately $3,000 per

[[Page 37047]]

helicopter. Based on these figures, the total cost impact of the 
proposed AD on U.S. operators is estimated to be $9,030,000, assuming 
10 ship sets of bearings would need to be replaced on the fleet.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) Is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Eurocopter France: Docket No. 98-SW-75-AD.

    Applicability: Model SA-365C, C1, C2, N, and N1; 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 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required within 550 hours time-in-service (TIS), 
unless accomplished previously, and thereafter at intervals not to 
exceed 550 hours TIS.
    To prevent loosening of the main rotor hub blade attach beam 
spherical thrust bearing bolts (bolts), cracks in the metal 
components, failure of a spherical thrust bearing (bearing), and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Inspect the tightening torque of the bolts as indicated by 
``A'' in Figure 1.
    (1) If tightening torque is equal to or less than 12 m.daN (88.4 
lb-ft), remove the bearing and conduct a dye penetrant inspection 
for cracks on the two contact surfaces identified as ``H'' in Figure 
1.
    (i) If a crack is detected, replace the bearing with an 
airworthy bearing.
    (ii) If no crack is detected, reinstall the bearing.

    Note 2: Eurocopter France Service Bulletins 05.22, 05.24, and 
05.00.39, all dated July 17, 1998, pertain to the subject of this 
AD.

    (2) If the tightening torque is greater than 12 m.daN (88.4 lb-
ft), then tighten to 19-22 m.daN (140-162.2 lb-ft).

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    (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 3: 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.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD's 98-383-044(A) for the 
Model SA-365C, 98-382-024-(A) for the Model SA-366, and 98-384-
047(A) for the Model AS-365N helicopters. These AD's are all dated 
September 23, 1998.

    Issued in Fort Worth, Texas, on July 2, 1999.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-17487 Filed 7-8-99; 8:45 am]
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