[Federal Register Volume 68, Number 31 (Friday, February 14, 2003)]
[Proposed Rules]
[Pages 7451-7453]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-3774]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-49-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, N1, 
AS-365N2, AS 365 N3, SA-366G1, AS355F, F1, F2, N, and EC130 B4 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

[[Page 7452]]


ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Eurocopter France (Eurocopter) Model SA-365N, N1, AS-365N2, AS 
365 N3, SA-366G1, AS355 F, F1, F2, N, and EC130 B4 helicopters with 
certain TRW-SAMM main servocontrols (servocontrols) installed. This 
proposal would require removing the servocontrol and replacing it with 
a servocontrol that does not fall within the ``Applicability'' of this 
AD at specified intervals. This proposal is prompted by the discovery 
of an incorrect tightening torque load found on servocontrols that were 
overhauled by Hawker Pacific Aerospace. The actions specified by this 
proposed AD are intended to prevent thread failure, separation of the 
upper end fitting that attaches the servocontrol cylinder to the upper 
ball end-fitting, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before April 15, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-49-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5123, 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 will 
be considered before taking action on the proposed rule. The proposals 
contained in this document 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 mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2002-SW-49-AD.'' The postcard will be date 
stamped and returned to the commenter.

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 Model AS 365 N, EC 130, AS 355, and 
SA 366 helicopters. The DGAC advises of a report of incorrect 
tightening torque load found in service on servocontrols that were 
overhauled by Hawker Pacific Aerospace.
    Eurocopter has issued the following alert telexes, all dated April 
29, 2002, which specify removing the servocontrols and returning them 
to the Hawker Pacific Aerospace:
    [sbull] Alert Telex No. 67.00.08 for Model AS-365N, N1, N2, and N3 
helicopters;
    [sbull] Alert Telex No. 67.03 for Model AS-366G1 helicopters;
    [sbull] Alert Telex No. 67.00.23 for Model AS355F, F1, F2, and N 
helicopters;
    [sbull] Alert Telex No. 67A001 for Model EC130 B4 helicopters.
    The DGAC classified these alert telexes as mandatory and issued AD 
No's. 2002-312-056(A), 2002-313-027(A), 2002-315-069(A), and 2002-316-
004(A), all dated June 12, 2002, 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.
    Incorrect torquing of the critical end fitting on the main 
servocontrol creates an unsafe condition. This unsafe condition is 
likely to exist or develop on other helicopters of the same type 
designs registered in the United States. Therefore, the proposed AD 
would require removing the servocontrols, part number SC8031, SC8031A, 
SC8031-1, SC8031-2, SC8032-1, SC8032-2, SC8033-1, SC8033-2, SC8034-1, 
SC8034-2, SC8042, or SC8043, that were overhauled or repaired at Hawker 
Pacific Aerospace before March 1, 2002, and replacing them with 
servocontrols that do not fall within the ``Applicability'' of this AD 
at specified intervals.
    The FAA estimates that 252 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 8 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $6,853, but the manufacturer has stated in the service 
information that it will rework the servocontrols at no cost to the 
owner/operator. Based on these figures, the total cost impact of the 
proposed AD on U.S. operators is estimated to be $1,847,916, assuming 
no costs are covered by the manufacturer's warranty.
    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 and 
responsibilities 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'' 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

[[Page 7453]]

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. 2002-SW-49-AD.

    Applicability: Model SA-365N, N1, AS-365N2, N3, SA-366 G1, 
AS355F, F1, F2, N and EC130 B4 helicopters, with TRW-SAMM main 
servocontrols, part number SC8031, SC8031A, SC8031-1, SC8031-2, 
SC8032-1, SC8032-2, SC8033-1, SC8033-2, SC8034-1, SC8034-2, SC8042 
or SC8043, overhauled or repaired at Hawker Pacific Aerospace before 
March 1, 2002, 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 (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 as indicated, unless accomplished 
previously.
    To prevent thread failure, separation of the upper end-fitting 
that attaches the servocontrol cylinder to the upper ball end-
fitting, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Replace each servocontrol with a servocontrol that does not 
fall within the ``Applicability'' of this AD in accordance with the 
following table:

------------------------------------------------------------------------
  For servocontrols that have been in
              service for:                  Replace the servocontrols:
------------------------------------------------------------------------
(1) Less than 1,000 hours time-in-       Within the next 550 hours TIS
 service (TIS).                           or 12 months, whichever occurs
                                          first.
(2) 1,000 or more hours TIS, and less    Before the servocontrols reach
 than 1,300 hours TIS.                    1,550 hours TIS or within 9
                                          months, whichever occurs
                                          first.
(3) 1,300 or more hours TIS............  Within the next 250 hours TIS
                                          or 6 months, whichever occurs
                                          first.
------------------------------------------------------------------------


    Note 2: Eurocopter Alert Telex No. 67.00.08 for Model AS 365 N, 
N1, N2, and N3 helicopters; Alert Telex No. 67.03 for Model AS 366 
G1 helicopters; Alert Telex No. 67.00.23 for Model AS 355 F, F1, F2, 
and N helicopters; and Alert Telex No. 67A001 for Model EC 130 B4 
helicopters, all dated April 29, 2002, pertain to the subject of 
this AD.

    (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 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 De 
L'Aviation Civile (France) AD No's. 2002-312-056(A), 2002-313-
027(A), 2002-315-069(A), and 2002-316-004(A), all dated June 12, 
2002.


    Issued in Fort Worth, Texas, on January 30, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-3774 Filed 2-13-03; 8:45 am]
BILLING CODE 4910-13-P