AD 2001-19-51

[Federal Register Volume 66, Number 226 (Friday, November 23, 2001)]
[Rules and Regulations]
[Pages 58663-58665]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-29189]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-48-AD; Amendment 39-12508; AD 2001-19-51]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA341G, SA342J, 
and SA-360C Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2001-19-51, which was sent 
previously to all known U.S. owners and operators of Eurocopter France 
(ECF) Model SA341G, SA342J, and SA-360C helicopters by individual 
letters. This AD requires, before further flight, replacing a certain 
unairworthy main rotor head torsion tie bar (tie bar) with an airworthy 
tie bar. This AD also requires revising the limitations section of the 
maintenance manual by adding a life limit for certain tie bars. This AD 
is prompted by an accident involving an ECF Model SA341G helicopter due 
to the failure of a tie bar. The actions specified by this AD are 
intended to prevent failure of a tie bar, loss of a main rotor blade, 
and subsequent loss of control of the helicopter.

DATES: Effective December 10, 2001, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2001-19-51, 
issued on September 21, 2001, which contained the requirements of this 
amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before January 22, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-48-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#380115594b4f15595c5b5755555d564c4b785e5959165f574e"><span class="__cf_email__" data-cfemail="053c28647672286461666a6868606b7176456364642b626a73">[email&#160;protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On September 21, 2001, the FAA issued

[[Page 58664]]

Emergency AD 2001-19-51 for ECF Model SA341G, SA342J, and SA-360C 
helicopters which requires, before further flight, replacing certain 
unairworthy tie bars with airworthy tie bars. The AD also requires 
revising the limitations section of the maintenance manual by adding a 
life limit for certain tie bars and specifies that certain tie bars are 
not approved for installation on any helicopter. That action was 
prompted by an accident involving an ECF Model SA341G helicopter due to 
the failure of a tie bar. The ECF Model SA342J and SA-360C helicopters 
are equipped with tie bars identical to the one that failed on the ECF 
Model SA341G helicopter. Failure of a tie bar could result in loss of a 
main rotor blade and subsequent loss of control of the aircraft.
    ECF has issued Telex Alert Nos. 01.28 and 01.38, both dated August 
7, 2001, which declare certain tie bars unairworthy and impose a 20-
year life limit for certain other tie bars. The Direction Generale De 
L'Aviation Civile (DGAC), which is the airworthiness authority for 
France, classified these telex alerts as mandatory and issued AD Nos. 
2001-374-040(A) and 2001-375-046(A), both dated August 22, 2001, 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 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral 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 the unsafe condition described is likely to exist or develop 
on other ECF Model SA341G, SA342J, and SA-360C helicopters of the same 
type designs, the FAA issued Emergency AD 2001-19-51 to prevent failure 
of a tie bar, loss of a main rotor blade, and subsequent loss of 
control of the helicopter. The AD requires, before further flight, 
replacing certain unairworthy tie bars with airworthy tie bars. The AD 
also requires revising the limitations section of the maintenance 
manual by adding a life limit for tie bars, P/N 341A31-4933-00 and 
341A31-4933-01, of 20 years from initial installation on any 
helicopter. The existing 5,000 hours TIS life limit on those tie bars 
remains the same. Tie bars, P/N 341A31-4933-00 and 341A31-4933-01, are 
to be removed from service when either the years or hours life limit is 
reached, whichever occurs first. The AD also specifies that tie bars, 
P/N 341A31-4904-00, -01, -02, -03, and 360A31-1097-02 and -03, are not 
approved for installation on any helicopter. The short compliance time 
involved is required because the previously described critical unsafe 
condition can adversely affect the structural integrity and 
controllability of the helicopter. Therefore, the actions previously 
mentioned are required before further flight, and this AD must be 
issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on September 21, 2001 to all known U.S. owners and operators of 
ECF Model SA341G, SA342J, and SA-360C helicopters. These conditions 
still exist, and the AD is hereby published in the Federal Register as 
an amendment to 14 CFR 39.13 to make it effective to all persons.
    The FAA estimates that 33 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 8 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$13,335 per helicopter, assuming all 3 tie bars are replaced. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $445,895 ($13,815 per helicopter).

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 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 mailed 
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. 2001-SW-48-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will 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 and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, 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 
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas.

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:

[[Page 58665]]

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:

2001-19-51  Eurocopter France: Amendment 39-12508. Docket No. 2001-
SW-48-AD.

    Applicability: Model SA341G, SA342J, and SA-360C helicopters 
with the following main rotor head torsion tie bar (tie bar), part 
number (P/N):
      341A31-4904-00, -01, -02, -03;
      341A31-4933-00, -01; or
      360A31-1097-02, or -03;
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 (d) 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 before further flight, unless accomplished 
previously.
    To prevent failure of a tie bar, loss of a main rotor blade, and 
subsequent loss of control of the aircraft, accomplish the 
following:
    (a) Remove each tie bar, P/N 341A31-4904-00, -01, -02, or -03; 
360A31-1097-02 or -03, from service and replace with an airworthy 
tie bar, P/N 341A31-4933-00 or 341A31-4933-01.

    Note 2: Eurocopter France Telex Alert Nos. 01.28 and 01.38, both 
dated August 7, 2001, pertain to the subject of this AD.

    (b) Replace each tie bar, P/N 341A31-4933-00 or 341A31-4933-01, 
if 20 or more years have elapsed since initial installation on any 
helicopter, with an airworthy tie bar, P/N 341A31-4933-00 or 341A31-
4933-01. If the date of initial installation on any helicopter 
cannot be determined, use the date of manufacture of the tie bar as 
the date of initial installation.
    (c) This AD revises the limitations section of the maintenance 
manual by adding a life limit for tie bars, P/N 341A31-4933-00 and 
341A31-4933-01, of 20 years from initial installation on any 
helicopter and retains the existing 5,000 hours time-in-service 
(TIS) life limit on those tie bars. Tie bars, P/N 341A31-4933-00 and 
341A31-4933-01, are to be removed from service when either the years 
or hours TIS life limit is reached, whichever occurs first. Tie 
bars, P/N 341A31-4904-00, -01, -02, and -03, and 360A31-1097-02 and 
-03, are not approved for installation on any helicopter.
    (d) 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.

    (e) Special flight permits will not be issued.
    (f) This amendment becomes effective on December 10, 2001, to 
all persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-19-51, issued September 21, 2001, 
which contained the requirements of this amendment.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France), AD's 2001-374-040(A) and 
2001-375-046(A), both dated August 22, 2001.


    Issued in Fort Worth, Texas, on November 9, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-29189 Filed 11-21-01; 8:45 am]
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