AD 2002-08-16

[Federal Register Volume 67, Number 78 (Tuesday, April 23, 2002)]
[Rules and Regulations]
[Pages 19640-19641]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-9728]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-72-AD; Amendment 39-12725; AD 2002-08-16]
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 amendment supersedes an existing airworthiness directive 
(AD) for the specified Eurocopter France (ECF) model helicopters. That 
AD currently requires replacing each affected unairworthy main rotor 
head torsion tie bar (tie bar) with an airworthy tie bar and revising 
the limitations section of the maintenance manual by adding a life 
limit for certain tie bars. This amendment requires additional 
revisions to the limitations section of the maintenance manual by 
further reducing the life limit for certain tie bars. This amendment 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 May 8, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before June 24, 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-72-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#3d04105c4e4a105c595e5250505853494e7d5b5c5c135a524b"><span class="__cf_email__" data-cfemail="4a73672b393d672b2e292527272f243e390a2c2b2b642d253c">[email&#160;protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5130, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On September 21, 2001, the FAA issued an 
Emergency AD (EAD) 2001-19-51 to require replacing each affected 
unairworthy tie bar, revising the limitations section of the 
maintenance manual by adding a life limit for certain tie bars, and 
specifying that certain tie bars are not approved for installation on 
any helicopter. That EAD was published in the Federal Register on 
November 23, 2001 (66 FR 58663) as Amendment 39-12508. Those actions 
were 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 have 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 helicopter.
    Since the issuance of that AD, the Direction Generale De L'Aviation 
Civile (DGAC), the airworthiness authority for France, notified the FAA 
of another accident involving a Model SA341G helicopter due to failure 
of the tie bar.
    ECF has issued Alert Telex Nos. 01.29R1 and 01.39R1, both dated 
December 11, 2001, which declare certain tie bars unairworthy and 
impose a 7-year life limit for certain other tie bars as a 
precautionary measure pending further investigation. The DGAC 
classified these telex alerts as mandatory and issued AD Nos. 2001-587-
041(A) R1 and 2001-588-047(A) R1, both dated December 26, 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.
    This unsafe condition is likely to exist or develop on other ECF 
model helicopters of these same type designs. Therefore, this AD 
supersedes AD 2001-19-51 to retain the requirement to remove certain 
part-numbered tie bars, to add the requirement to remove certain other 
tie bars at specified intervals, and to revise the limitations section 
of the maintenance manual by further reducing the life limit. 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 a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 33 helicopters will be affected by this AD, 
that it will take approximately 8 work hours to replace the tie bars, 
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

[[Page 19641]]

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-72-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 
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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-12508, Docket 
No. 2001-SW-48-AD (66 FR 58663) and by adding a new airworthiness 
directive (AD), Amendment 39-12725, to read as follows:

2002-08-16  Eurocopter France: Amendment 39-12725. Docket No. 2001-
SW-72-AD. Supersedes AD No. 2001-19-51, Amendment 39-12508, Docket 
No. 2001-SW-48-AD.

    Applicability: Model SA341G, SA342J, and SA-360C helicopters 
with a main rotor head torsion tie bar (tie bar), part number (P/N):

341A31-4904-00, -01, -02, -03;
341A31-4933-00, -01;
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 as indicated, 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) Before further flight, remove each tie bar, P/N 341A31-4904-
00, -01, -02, or -03; or 360A31-1097-02 or -03, from service.
    (b) For each tie bar, P/N 341A31-4933-00 or -01:
    (1) Before further flight, determine the date of initial 
installation on any helicopter using the date of manufacture if the 
date of installation cannot be determined.
    (2) For each tie bar with 7 or more years time-in-service (TIS) 
since initial installation on any helicopter, remove within 5 hours 
TIS.
    (3) For each tie bar manufactured before 1995 with less than 7 
years TIS since initial installation on any helicopter, remove 
before accumulating 7 years TIS, within 300 hours TIS, or within 1 
year, whichever occurs first.
    (4) For each tie bar manufactured in 1995 or subsequent years 
with less than 7 years TIS since initial installation on any 
helicopter, remove before accumulating 7 years TIS, within 600 hours 
TIS, or within 2 years, whichever occurs first.

    Note 2: Eurocopter France (ECF) Alert Telex Nos. 01.29R1 and 
01.39R1, both dated December 11, 2001, pertain to the subject of 
this AD.

    (c) This AD revises the limitations section of the maintenance 
manual by adding to the current life limit of 5000 hours TIS, the 
following additional alternative life limits for tie bars, P/N 
341A31-4933-00 or 341A31-4933-01:
    (1) Seven years TIS from initial installation on any helicopter 
or
    (2) For tie bars manufactured before 1995, a life limit of 300 
hours TIS or 1 year, or
    (3) For tie bars manufactured in 1995 or subsequent years, a 
life limit of 600 hours TIS or 2 years, whichever occurs first.
    (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 May 8, 2002.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) ADs 2001-587-041(A) R1 and 
2001-588-047(A) R1, both dated December 26, 2001.


    Issued in Fort Worth, Texas, on April 11, 2002.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-9728 Filed 4-22-02; 8:45 am]
BILLING CODE 4910-13-P