[Federal Register Volume 68, Number 62 (Tuesday, April 1, 2003)]
[Proposed Rules]
[Pages 15687-15688]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7596]



[[Page 15687]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-61-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS 365 N3 and 
EC 155B Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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

SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD) for Eurocopter France (Eurocopter) Model AS 365 N3 and 
EC 155B helicopters that would have revised the Airworthiness 
Limitations section of the maintenance manuals by establishing a new 
service life limit for the Fenestron pitch change control rod (control 
rod). That proposal was prompted by a failure of a control rod on a 
prototype helicopter that led to a precautionary landing. This action 
revises the proposed rule by requiring replacement of the control rod 
with an improved reinforced steel airworthy control rod. The actions 
specified by this proposed AD are intended to prevent failure of the 
control rod, loss of control of the tail rotor, and subsequent loss of 
control of the helicopter.

DATES: Comments must be received on or before June 2, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-61-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: 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:

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 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. 2001-SW-61-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    A proposal to amend 14 CFR part 39 to add an AD for Eurocopter 
Model AS 365 N3 and EC 155B helicopters was published a notice of 
proposed rulemaking (NPRM) in the Federal Register on October 2, 2002 
(67 FR 61843). That NPRM proposed to reduce the current service life 
limit of 1,500 hours time in service (TIS) to 300 hours TIS for the 
control rod, part number (P/N) 365A33-6161-21, and proposed to require 
removing the control rod:
    [sbull] Before further flight for helicopters with control rods 
having 700 or more hours TIS;
    [sbull] Within 20 hours TIS for helicopters with control rods 
having 500 or more hours TIS, but less than 700 hours TIS; and
    [sbull] Within 30 hours TIS for helicopters with control rods 
having more than 270 hours TIS and less than 500 hours TIS.

The proposed AD would also have required revising the Airworthiness 
Limitations section of the maintenance manuals to reflect the new 
retirement life of 300 hours TIS for the control rod. That NPRM was 
prompted by a failure of a control rod on a prototype helicopter that 
led to a precautionary landing. That condition, if not corrected, could 
result in loss of control of the tail rotor and subsequent loss of 
control of the helicopter.
    Since issuing that NPRM, the manufacturer has made available a 
newly designed, reinforced steel control rod. Therefore, based upon the 
adoption of the improved-design control rod by the airworthiness 
authority of the country in which the product was manufactured, we are 
proposing to adopt a one-time replacement of the control rod rather 
than our original proposal to replace the control rod initially and 
thereafter at 300 hours TIS intervals. In addition, we have made other 
changes to the proposal.
    Since these changes expand the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.
    The Direction G[eacute]n[eacute]rale 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 and Model EC 155B 
helicopters. The DGAC advises that a control rod failure occurred on a 
prototype aircraft and mandates removing control rod, P/N 365A33-6161-
21, at certain times depending on the number of helicopter flight 
hours, and replacing it with a reinforced steel control rod, P/N 
365A33-6214-20.
    Eurocopter has issued Alert Telex No. 04A005 for Model EC 155B 
helicopters, and Alert Telex No. 01.00.55 for Model AS 365 N3 
helicopters, both dated July 4, 2002. The alert telexes specify 
removing the control rod, P/N 365A33-6161-21, and replacing it with a 
reinforced steel control rod, P/N 365A33-6214-20. The DGAC classified 
these alert telexes as mandatory and issued AD No. 2002-472-057(A) for 
Model AS 365 N3 helicopters, and AD No. 2002-473-006(A) for Model EC 
155B helicopters. Both AD's are dated September 18, 2002, and were 
issued 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.
    An unsafe condition is likely to exist or develop on other 
helicopters of these same type designs registered in the United States. 
Therefore, the proposed

[[Page 15688]]

AD would require removing the control rod, P/N 365A33-6161-21, and 
replacing it with a reinforced steel control rod, P/N 365A33-6214-20.
    The FAA estimates that 3 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per helicopter to remove and replace the control rod, and that 
the average labor rate is $60 per work hour. Required parts would cost 
approximately $2,677. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $8,391.
    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 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. 2001-SW-61-AD.

    Applicability: Model AS 365 N3 helicopters with MOD 0764B39 
(Quiet Fenestron) and Model EC 155B helicopters with tail rotor 
pitch change control rod (control rod), part number (P/N) 365A33-
6161-21, 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 failure of the control rod, loss of control of the 
tail rotor, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Remove the control rod, P/N 365A33-6161-21, and replace it 
with a reinforced steel control rod, P/N 365A33-6214-20, in 
accordance with the following table:

--------------------------------------------------------------------------------------------------------------------------------------------------------
            Remove the control rod:                                                       For control rods with:
--------------------------------------------------------------------------------------------------------------------------------------------------------
Before further flight..........................  700 or more hours TIS.
Within 20 hours TIS............................  500 or more hours TIS but less than 700 hours TIS.
Within 30 hours TIS............................  More than 270 hours TIS and less than 500 hours TIS.
--------------------------------------------------------------------------------------------------------------------------------------------------------


    Note 2: Eurocopter Alert Telex No. 04A005, for Model EC 155B 
helicopters, and Alert Telex No. 01.00.55, for Model AS 365 N3 
helicopters, both dated July 4, 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 
Generale De L'Aviation Civile (France) AD No. 2002-472-057(A) for 
Model AS 365 N3 helicopters, and AD No. 2002-473-006(A) for Model EC 
155B helicopters. Both AD's are dated September 18, 2002.


    Issued in Fort Worth, Texas, on March 24, 2003.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 03-7596 Filed 3-31-03; 8:45 am]
BILLING CODE 4910-13-P