[Federal Register Volume 71, Number 90 (Wednesday, May 10, 2006)]
[Proposed Rules]
[Pages 27215-27216]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7096]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24733; Directorate Identifier 2005-SW-08-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This amendment proposes superseding an existing airworthiness 
directive (AD) for the specified Eurocopter France (ECF) model 
helicopters that currently requires replacing each affected main rotor 
head torsion tie bar (tie bar) with an airworthy tie bar and revising 
the limitations section of the maintenance manual by adding life limits 
for certain tie bars. This action would retain the current requirements 
and reduce life limits of another part-numbered tie bar. This proposal 
is prompted by the FAA determination, after reviewing the 
manufacturer's data, that another part-numbered tie bar should be 
included in the applicability of the AD. The actions specified by the 
proposed 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: Comments must be received on or before July 10, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: 202-493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains this AD, any comments, and 
other information on the Internet at http://dms.dot.gov, or at the 
Docket Management System (DMS), U.S. Department of Transportation, 400 
Seventh Street SW., Room PL-401, on the plaza level of the Nassif 
Building, Washington, DC.

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: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2006-
24733, Directorate Identifier 2005-SW-08-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of our docket Web site, you can find and read the comments to 
any of our dockets, including the name of the individual who sent or 
signed the comment. You may review the DOT's complete Privacy Act 
Statement in the Federal Register published on April 11, 2000 (65 FR 
19477-78) or you may visit http://dms.dot.gov.

Discussion

    On April 11, 2002, we issued AD 2002-08-16 (67 FR 19640, April 23, 
2002), Amendment 39-12725, to supersede AD 2001-19-51 (66 FR 58663, 
November 23, 2001), Amendment 39-12508. AD 2001-19-51 was published 
after we issued Emergency AD 2001-19-51 on September 21, 2001. AD 2001-
19-51 requires removal of certain part-numbered tie bars and adds a 
life limit for other part-numbered tie bars. AD 2002-08-16 retained 
requirements removing certain part-numbered tie bars and further 
reduced the life of the tie bars. 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. 
The requirements of the current AD are intended to prevent failure of a 
tie bar, loss of a main rotor blade, and subsequent loss of control of 
the helicopter.
    Since issuing that AD, the Direction Generale De L'Aviation Civile 
(DGAC), the airworthiness authority for France, notified the FAA of 
another affected tie-bar, part number (P/N) 704A33-633-270, and 
additional flight restrictions for the new-affected tie bar.
    Also, since issuing that AD, ECF has issued Alert Service Bulletin 
No. 01.29, dated December 4, 2002 (ASB), for the Models SA341G and 
SA342J helicopters. The ASB cancels Alert Telex (AT) No. 01.28, dated 
August 7, 2001, and supersedes AT 01.29 R1, dated December 11, 2001. 
The ASB specifies additional flight restrictions for the affected tie 
bars and adds tie bar, P/N 704A33-633-270, to the ASB effectivity. The 
DGAC classified this ASB as mandatory and issued AD 2001-587-041(A) R2, 
dated January 8, 2003, for the Model SA341/342 helicopters 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.

[[Page 27216]]

    This previously described unsafe condition is likely to exist or 
develop on other helicopters of these same type designs. Therefore, the 
proposed AD would supersede AD 2002-08-16 to retain the same 
requirements and would add tie bar, P/N 704A33-633-270, to the 
applicability, remove it from service within 600 hours TIS or 2 years, 
whichever occurs first, and revise the limitations section of the 
maintenance manual accordingly.
    We estimate that this proposed AD would affect 33 helicopters of 
U.S. registry. The proposed actions would take about 8 work hours per 
helicopter to replace the tie bars at an average labor rate of $65 per 
work hour. Required parts would cost about $13,335 per helicopter, 
assuming all 3 tie bars are replaced. Based on these figures, we 
estimate the total cost impact of the proposed AD on U.S. operators to 
be $457,215 ($13,855 per helicopter).

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD 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 and responsibilities among the various levels of 
government.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 39-12725 (67 FR 
19640, April 23, 2002), and by adding a new airworthiness directive 
(AD), to read as follows:

Eurocopter France: Docket No. FAA-2006-24733; Directorate Identifier 
2005-SW-08-AD. Supersedes AD 2002-08-16, Amendment 39-12725, Docket 
No. 2001-SW-72-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, 
-03; or 704A33-633-270, installed, certificated in any category.
    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, do the following:
    (a) Before further flight, remove each tie bar, P/N 341A31-4904-
00, -01, -02, or -03; and 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 since initial 
installation, within 600 hours TIS, or within 2 years, whichever 
occurs first.

    Note 1: Eurocopter France (ECF) Alert Telex AT 01.39 R1, dated 
December 11, 2001, pertains to the subject of this AD for the Model 
SA-360C helicopters.


    (c) Remove each tie bar, P/N 704A33-633-270, within 600 hours 
TIS, or within 2 years, whichever occurs first.

    Note 2: ECF Alert Service Bulletin 01.29, dated December 4, 
2002, pertains to the subject of this AD for the Models SA341G and 
SA342J helicopters.


    (d) This AD revises the Limitations section of the maintenance 
manual by adding to the current life limit of 5000 hours TIS for tie 
bars, P/N 341A31-4933-00 and -01 the following additional 
alternative life limits:
    (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 P/N 341A31-4933-00 and -01, for tie bars manufactured in 
1995 or subsequent years, a life limit of 600 hours TIS or 2 years, 
whichever occurs first.
    (e) This AD revises the Limitations section of the maintenance 
manual by reducing the current life limit of 1000 hours TIS for tie 
bar, P/N 704A33-633-270, to a life limit of 600 hours TIS or 2 
years, whichever occurs first.
    (f) Special flight permits will not be issued.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) ADs 2001-588-047(A) R1, dated 
December 26, 2001, and 2001-587-041(A) R2, dated January 8, 2003.


    Issued in Fort Worth, Texas, on April 28, 2006.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E6-7096 Filed 5-9-06; 8:45 am]
BILLING CODE 4910-13-P