[Federal Register Volume 65, Number 40 (Tuesday, February 29, 2000)]
[Proposed Rules]
[Pages 10727-10730]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-4797]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-62-AD]


Airworthiness Directives; Eurocopter France Model SA-365C, C1, 
C2, N, and N1; AS-365N2 and N3; and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD) applicable to Eurocopter France Model SA-
365C, C1, C2, N, and N1; AS-365N2, and SA-366G1 helicopters. This 
proposal contains the same requirements as the existing AD but would 
add the Model AS-365N3 helicopter to the applicability. This proposal 
would require inspecting the tightening torque of the main rotor hub 
blade attach beam spherical thrust bearing bolts (bolts) and either 
applying a specified torque or, if necessary, inspecting for a crack in 
the metal components. This proposal would also require replacing the 
spherical thrust bearing (bearing) with an airworthy bearing if a crack 
is found. This proposal is prompted by reports of cracks in the metal 
components of the bearing attachment joint and the need to add the 
Eurocopter France Model AS 365 N3 helicopter to the applicability. 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 May 1, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-62-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, 2601 Meacham Blvd., 
Fort Worth, Texas 76137, telephone (817) 222-5296, 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. 99-SW-62-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. 99-SW-62-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    On October 5, 1999, the FAA issued AD 99-21-24, Amendment 39-11369 
(64 FR 55621), applicable to Eurocopter France Model SA-365C, C1, C2, 
N, and N1; AS-365N2; and SA-366G1 helicopters, to require inspecting 
the tightening torque of the bolts and either applying a specified 
torque or, if necessary, dye-penetrant inspecting for a crack in the 
metal components, and replacing any unairworthy bearing with an 
airworthy bearing. That action was prompted by reports of cracks in the 
metal components of the bearing attachment joint. The requirements of 
that AD were intended to prevent failure of the bearing and subsequent 
loss of control of the helicopter.
    Since the issuance of that AD, the FAA has discovered the 
inadvertent omission in the applicability of the Eurocopter France 
Model AS-365N3 helicopter. This proposal would add the Model AS 365 N3 
helicopter.
    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 N3; and SA-366G1 helicopters of the same type 
design, the proposed AD would supersede AD 99-21-24 but would contain 
the same requirements as AD 99-21-24 with the addition of the 
Eurocopter France Model AS-365N3 to the applicability.
    The FAA estimates that 101 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.5 work 
hour per helicopter and approximately 3,000 inspections per helicopter 
over the life of the fleet to accomplish the proposed actions, and that 
the average labor rate is $60 per work hour. Required parts would cost 
approximately $3,000 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$9,123,000, assuming 11 ship sets of bearings would need to be replaced 
on the fleet.
    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power among the 
various levels of government. Therefore, it is determined that this 
proposal would not have federalism implications under Executive Order 
13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) Is not a ``significant regulatory action''

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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 removing Amendment 39-11369 (64 FR 
55621, October 14, 1999) and by adding a new airworthiness directive 
(AD), to read as follows:

Eurocopter France: Docket No. 99-SW-62-AD. Supersedes AD 99-21-24, 
Docket 98-SW-75-AD, Amendment 39-11369.

    Applicability: Eurocopter France Model SA-365C, C1, C2, N, and 
N1; AS-365N2 and N3; 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 the torque to 19-22 m.daN (140-162.2 lb-ft).

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[GRAPHIC] [TIFF OMITTED] TP29FE00.001

    (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, Regulations Group, 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, Regulations Group.

    Note 3:  Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) Special flight permits may be issued in accordance with 
Secs. 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.



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    Issued in Fort Worth, Texas, on February 22, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-4797 Filed 2-28-00; 8:45 am]
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