[Federal Register: November 24, 2003 (Volume 68, Number 226)]
[Proposed Rules]
[Page 65854-65856]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24no03-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-11-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS 365 N3
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes adopting a new airworthiness directive
(AD) for the specified Eurocopter France (Eurocopter) model
helicopters. This proposal would require installing a tail rotor blade
(blade)-to-torsion bar attachment tuning weight assembly on each blade
of the Quiet Fenestron tail rotor and replacing each blade attachment
bushing. This proposal is prompted by the discovery of tail rotor
induced vibrations during flight tests. The actions specified by this
proposed AD are intended to prevent vibration in the tail rotor and the
pilot's anti-torque pedals, blade pitch control failure, and subsequent
loss of control of the helicopter.
DATES: Comments must be received on or before January 23, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
[[Page 65855]]
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2003-SW-11-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
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: Richard Monschke, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort
Worth, Texas 76193-0110, telephone (817) 222-5116, 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. 2003-SW-11-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 N3 helicopters. The DGAC
advises of a report of the discovery of an increased level of vibration
felt by the crew in the pedal units.
Eurocopter has issued Alert Service Bulletin (ASB) No. 64.00.23,
dated October 30, 2002, which specifies installing a tuning weight
assembly, part number (P/N) 365A33-3546-00, on each blade of the Quiet
Fenestron tail rotor. Compliance with this ASB requires prior
compliance with Eurocopter Service Bulletin 64.00.21, dated November 8,
2000 (modification 0761B23, 0765B35, and 0764B39, 40, 41), which
specifies installing a Quiet Fenestron tail rotor, and with Eurocopter
Service Bulletin 65.00.14, dated January 7, 2002 (modification
0765B41), which specifies installing a reinforced control shaft on the
tail rotor hub control shaft assembly. The DGAC classified these
service bulletins as mandatory and issued AD No. 2002-622(A), dated
December 11, 2002, to ensure the continued airworthiness of these
helicopters in France.
This helicopter model is manufactured in France and is 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 this type design that are certificated for
operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type design registered in the
United States. Therefore, the proposed AD would require removing each
tail rotor attachment bushing, P/N 365A33-3530-20, and then installing
a blade-to-torsion bar attachment tuning weight assembly, P/N 365A33-
3546-00, on each blade of the Quiet Fenestron tail rotor at the same
time. Mixing the existing blade attachment bushings, P/N 365A33-3530-
20, and the new tuning weight assembly, P/N 365A33-3546-00, on the same
tail rotor hub would be prohibited. The actions would be required to be
accomplished in accordance with the service bulletin described
previously.
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The
regulation now includes material that relates to altered products,
special flight permits, and alternative methods of compliance. Because
we have now included this material in part 39, we no longer need to
include it in each individual AD.
The FAA estimates that this proposed AD would affect 6 helicopters
of U.S. registry and the proposed actions would take approximately 8
work hours per helicopter to accomplish at an average labor rate of $65
per work hour. Required parts would cost approximately $3,290, and
attaching hardware would cost $40. Based on these figures, we estimate
the total cost impact of the proposed AD on U.S. operators to be $3,850
per helicopter, or $23,100 for the entire fleet.
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. 2003-SW-11-AD.
Applicability: Model AS 365 N3 helicopters, with a Quiet
Fenestron tail rotor (tail rotor gearbox, part number (P/N) 365A33-
6005-06, and tail rotor hub, P/N
[[Page 65856]]
365A33-3500-02), tail rotor hub attachment bushings, part number (P/
N) 365A33-3530-20, and a reinforced control shaft, P/N 365A33-6214-
20, on the tail rotor hub control shaft assembly, installed,
certificated in any category.
Compliance: Within 3 months, unless accomplished previously.
To prevent vibration in the tail rotor attachments and the
pilot's anti-torque pedals, blade pitch control failure, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Install a tail rotor blade (blade)-to-torsion bar attachment
tuning weight assembly, P/N 365A33-3546-00, on each blade of the
Quiet Fenestron tail rotor in accordance with paragraph 2,
Accomplishment Instructions, of Eurocopter France Alert Service
Bulletin 64.00.23, dated October 30, 2002. Replace each of the 10
blade attachment bushings, P/N 365A33-3530-20, at the same time. Do
not mix the existing blade attachment bushings, P/N 365A33-3530-20,
and the new tuning weight assemblies, P/N 365A33-3546-00, on the
same tail rotor hub.
(b) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Safety Management Group, Rotorcraft Directortate, FAA,
for information about previously approved alternative methods of
compliance.
Note: The subject of this AD is addressed in Direction Generale
De L'Aviation Civile (France) AD 2002-622(A), dated December 11,
2002.
Issued in Fort Worth, Texas, on November 17, 2003.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-29221 Filed 11-21-03; 8:45 am]
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