[Federal Register Volume 65, Number 40 (Tuesday, February 29, 2000)]
[Proposed Rules]
[Pages 10724-10727]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-4796]


 ========================================================================
 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. 65, No. 40 / Tuesday, February 29, 2000 / 
Proposed Rules  

[[Page 10724]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-34-AD]


Airworthiness Directives; Eurocopter France Model SA-365N1, 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-365N1, AS-
365N2, and SA-366G1 helicopters. This proposal would require conducting 
inspections of each tail rotor blade for bonding separation, measuring 
the clearance between the tip of each tail rotor blade and the 
circumference of the air duct, and replacing the blade if necessary. 
This proposal is prompted by an inflight incident in which the tail 
rotor blades were significantly damaged due to bonding separation. The 
actions specified by the proposed AD are intended to prevent damage to 
a tail rotor blade, loss of tail rotor control, 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-34-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: Sharon Miles, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 
76193-0111, telephone (817) 222-5122, 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-34-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-34-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter France Model SA-365N1, AS-365N2, and 
SA-366G1 helicopters. The DGAC advises of an inflight incident of 
bonding separation of a tail rotor blade on a Model SA-366G1 
helicopter.
    Eurocopter France issued Service Bulletins 05.09, Revision 5, 
applicable to the Model SA-366G1, and 05.00.17, Revision 5, applicable 
to the Models SA-365N1 and AS-365N2 dated December 18, 1998 (SB). The 
SB's specify inspecting the Model SA-365N1, AS-365N2, and SA-366G1 
helicopters to detect bonding separation of tail rotor blade part 
number (P/N) 365A33-2131, 365A12-0010, and 365A12-0020, all dash 
numbers; measuring the blade-to-air duct for a clearance of less than 3 
mm; and replacing each tail rotor blade with an airworthy blade if 
necessary. The DGAC classified these SB's as mandatory and issued AD's 
88-152-010(A)R5 and 88-153-023(A)R5, both dated December 30, 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 
Sec. 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-365N1, AS-365N2, 
and SA366G1 helicopters with tail rotor blades, P/N 365A33-2131, 
365A12-0010, or 365A12-0020, all dash numbers, installed, of the same 
type designs registered in the United States, the proposed AD would 
require conducting inspections of each tail rotor blade for bonding 
separation, measuring for a blade-to-air duct clearance of less than 3 
mm, and replacing any unairworthy blade with an airworthy blade if 
necessary.
    The FAA estimates that 136 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $1,000 per helicopter. Based on these figures, the total 
cost

[[Page 10725]]

impact of the proposed AD on U.S. operators is estimated to be 
$144,160.
    The regulations proposed herein would not impose substantial direct 
compliance costs on states or local governments or 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 13132, the FAA has not consulted with 
States or local authorities prior to the publication of this notice.
    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. 99-SW-34-AD.

    Applicability: Model SA-365N1, AS-365N2, and SA-366G1 
helicopters, with a tail rotor blade, part number (P/N) 365A33-2131, 
365A12-0010, or 365A12-0020, 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 
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 (f) 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 as indicated, unless accomplished 
previously.
    To prevent damage to a tail rotor blade (blade), loss of tail 
rotor control, and subsequent loss of control of the helicopter:
    (a) Within 10 hours time-in-service (TIS) and thereafter prior 
to the first flight of each day, conduct the following visual 
inspection of each blade (see Figure 1):
    (1) Zone A: If a blister is detected on the blade suction face, 
conduct a tapping test inspection on the whole blade for bonding 
separation. If bonding separation or a crack is found, replace the 
blade with an airworthy blade before further flight.
    (2) Zone B: If a crack, wrinkling, or a blister is found, 
replace the blade with an airworthy blade before further flight.
    (b) Within 10 hours TIS, conduct a tapping test inspection on 
each blade. If there is bonding separation, replace the blade with 
an airworthy blade before further flight.

    Note 2: Revisions 5, of Eurocopter France Service Bulletins 
05.09 and 05.00.17, both dated December 18, 1998, pertain to the 
subject of this AD.

    (c) Thereafter, at intervals not to exceed 25 hours TIS or every 
50 cycles (each takeoff and landing equals 1 cycle), whichever 
occurs first, conduct a tapping test inspection for bonding 
separation on all blades with a serial number (S/N) less than 18912, 
and blades, P/N 365A12-0020-00 or 365A12-0020-01, with a S/N equal 
to or greater than 18912. If bonding separation or a crack is found, 
replace the blade with an airworthy blade before further flight.
    (d) Thereafter, at intervals not to exceed 100 hours TIS or 200 
cycles, whichever occurs first, conduct a tapping test inspection 
for bonding separation on blades, P/N 365A12-0020-02 or 365A12-0020-
03. If bonding separation or a crack is found, replace the blade 
with an airworthy blade before further flight.
    (e) Within 10 hours TIS, and thereafter at intervals not to 
exceed 100 hours TIS or 200 cycles, whichever occurs first, measure 
the blade-to-air duct clearance. If the clearance is less than 3 mm, 
replace the blade with an airworthy blade before further flight.
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[[Page 10726]]

[GRAPHIC] [TIFF OMITTED] TP29FE00.000

    (f) 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.

    (g) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197

[[Page 10727]]

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 AD's 88-152-010(A)R5 and 88-153-
023(A)R5, both dated December 30, 1998.


    Issued in Fort Worth, Texas, on February 22, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-4796 Filed 2-28-00; 8:45 am]
BILLING CODE 4910-13-C