AD 2004-05-29

AD Final Rules - 040529.pdf
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AD Number:
2004-05-29
Document Type:
AD Final Rules
Docket Number:
2003-SW-12-AD
Subject Heading:
Airworthiness Directives; Eurocopter France Model EC 155B Helicopters
Subject:
Tail rotor blade (blade) -to-torsion bar attachment
Status:
Current
Citation:
Federal Register: March 15, 2004 (Volume 69, Number 50)
Citation Publish Date:
03/15/2004
Effective Date:
04/19/2004
Make:
Airbus Helicopters
Model:
EC 155B
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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FR Doc 04-5332


[Federal Register: March 15, 2004 (Volume 69, Number 50)]


[Rules and Regulations]


[Page 12064-12065]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr15mr04-6]


–––––––––––––––––––––––––––––––––––-


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.


–––––––––––––––––––––––––––––––––––-


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) 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
2


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


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


1. The authority citation for part 39 continues to read as follows:


Authority:
 
49 U.S.C. 106(g), 40113, 44701.