Airworthiness Directives; Eurocopter France Model SA 330F, G, and J Helicopters

[Federal Register Volume 63, Number 217 (Tuesday, November 10, 1998)]
[Rules and Regulations]
[Pages 62935-62936]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30045]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-38-AD; Amendment 39-10875; AD 98-23-09]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA 330F, G, and 
J Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Eurocopter France Model SA 330F, G, and J helicopters, 
that requires an initial and repetitive inspections of each tail rotor 
shaft flapping hinge retainer (retainer) for cracks and replacement of 
a retainer if a crack is discovered. This amendment is prompted by a 
report of high vibrations due to a cracked retainer occurring on a 
helicopter while it was in service. The actions specified by this AD 
are intended to detect cracks in the retainers that, if left 
undetected, could lead to high tail rotor vibrations, loss of tail 
rotor control, and subsequent loss of control of the helicopter.

EFFECTIVE DATE: December 15, 1998.

FOR FURTHER INFORMATION CONTACT: Mr. Mike Mathias, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Eurocopter France Model SA 330F, 
G, and J helicopters was published in the Federal Register on April 21, 
1998 (63 FR 19672). That action proposed to require an initial and 
repetitive inspections of each retainer for cracks and replacement of a 
retainer if a crack is discovered.
    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 4 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 0.5 work hour per 
helicopter to accomplish each dye-penetrant inspection, 2.0 work hours 
to replace the retainers on each helicopter, if necessary, and that the 
average labor rate is $60 per work hour. Required parts will cost 
approximately $56,900. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $252,080, assuming that the 
retainers on the tail rotor blades are replaced on all 4 helicopters 
and each helicopter is dye-penetrant inspected 200 times per year.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 Office of the Regional Counsel, Southwest 
Region, Attention: Rules Docket No. 97-SW-38-AD, 2601 Meacham Blvd., 
Room 663, Fort Worth, Texas 76137.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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:


[[Page 62936]]


    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:
AD 98-23-09  Eurocopter France: Amendment 39-10875. Docket No. 97-
SW-38-AD.

    Applicability: Model SA 330F, G, and J helicopters with tail 
rotor head assembly, part number 330 A 33 0000 all dash numbers, or 
330 A 33 0001 all dash numbers, 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 
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 use the authority 
provided in paragraph (c) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect cracks on a tail rotor shaft flapping hinge retainer 
(retainer) that could lead to high tail rotor vibrations, loss of 
tail rotor control, and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Before further flight, and thereafter before the first 
flight of each day, perform a dye-penetrant inspection of each 
retainer for cracks.
    (b) If a crack is found on any retainer, replace it with an 
airworthy retainer before further flight.

    Note 2: Eurocopter Service Bulletin No. 05.84, Revision No. 1, 
dated January 29, 1996, pertains to the subject of this AD.

    (c) 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, Rotorcraft Standards Staff, 
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, Rotorcraft Standards Staff.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (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 96-076-075(AB)R1, dated 
November 5, 1997.

    (e) This amendment becomes effective on December 15, 1998.

    Issued in Fort Worth, Texas, on November 2, 1998.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-30045 Filed 11-9-98; 8:45 am]
BILLING CODE 4910-13-U

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