AD Amdt-39-13524

[Federal Register Volume 69, Number 50 (Monday, March 15, 2004)]
[Rules and Regulations]
[Pages 12064-12065]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-5332]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-12-AD; Amendment 39-13524, AD 2004-05-29]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC 155B 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) model helicopters that 
requires 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 amendment 
is prompted by the discovery of tail rotor induced vibrations during 
flight tests. The actions specified by this 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: Effective April 19, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 19, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand 
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on November 24, 2003 (68 FR 65856). That action 
proposed to require removing each tail rotor attachment bushing, part 
number (P/N)

[[Page 12065]]

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 Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model EC 155B 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 64A001, dated October 
30, 2002 (ASB), which specifies installing a tuning weight assembly, P/
N 365A33-3546-00, on each blade of the Fenestron tail rotor. Compliance 
with this ASB requires prior compliance with Eurocopter Service 
Bulletin 64-002, dated December 19, 2002 (modifications 0765B35 and 
0764B39), which specifies upgrading the Quiet Fenestron tail rotor hub 
and tail rotor gearbox for embodiment of the tuning weight 
modification, or Eurocopter Service Bulletin 65-003, dated December 10, 
2001 (modification 0765B41), which specifies installing a reinforced 
control shaft on the tail rotor hub control shaft assembly or both. The 
DGAC classified service bulletin ASB 64A001, dated October 30, 2002, as 
mandatory and issued AD No. 2002-621(A), dated December 11, 2002, to 
ensure the continued airworthiness of these helicopters in France.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 3 helicopters of U.S. 
registry and the actions will take approximately 8 work hours per 
helicopter to accomplish at an average labor rate of $65 per work hour. 
Required parts will cost approximately $3,290 and $40 for attaching 
hardware. Based on these figures, we estimate the total cost impact of 
the AD on U.S. operators to be $3,850 for each helicopter, or $11,550 
for the entire fleet.
    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.
    For the reasons discussed above, I certify that this action (1) Is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2004-05-29 Eurocopter France: Amendment 39-13524. Docket No. 2003-
SW-12-AD.

    Applicability: Model EC 155B helicopters with an upgraded Quiet 
Fenestron tail rotor hub, part number (P/N) 365A33-3501-02, with 
tail rotor attachment bushing, P/N 365A33-3530-20, and tail rotor 
gearbox, P/N 365A33-6005-04 (without the reinforced control shaft, 
P/N 365A33-6161-21) or tail rotor gearbox, P/N 365A33-6005-06 (with 
reinforced control shaft, P/N 365A33-6214-20), 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 356A33-3546-00, on each blade of the 
Quiet Fenestron tail rotor in accordance with paragraph 2, 
Accomplishment Instructions, of Eurocopter France Alert Service 
Bulletin 64A001, 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.
    (c) The installations shall be done in accordance with 
Eurocopter France Alert Service Bulletin 64A001, dated October 30, 
2002. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, 
telephone (972) 641-3460, fax (972) 641-3527. Copies may be 
inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (d) This amendment becomes effective on April 19, 2004.

    Note: The subject of this AD is addressed in Direction Generale 
De L'Aviation Civile (France) AD 2002-621(A), dated December 11, 
2002.


    Issued in Fort Worth, Texas, on March 3, 2004.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-5332 Filed 3-12-04; 8:45 am]
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