[Federal Register Volume 63, Number 123 (Friday, June 26, 1998)]
[Rules and Regulations]
[Pages 34789-34790]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17041]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-39-AD; Amendment 39-10630; AD 98-13-39]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS 332C, L, and
L1 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 AS 332C, L, and L1 helicopters
that requires initial and repetitive inspections of the tail rotor
shaft flapping hinge retainers (retainers) for cracks. This amendment
is prompted by a report of high vibrations occurring on a helicopter
while in service due to a cracked retainer. The actions specified by
this AD are intended to detect cracks on the retainers that could lead
to high tail rotor vibrations, loss of tail rotor control, and
subsequent loss of control of the helicopter.
EFFECTIVE DATE: July 31, 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 AS 332C,
L, and L1 helicopters was published in the Federal Register on April 1,
1998 (63 FR 15791). That action proposed to require initial and
repetitive inspections of the retainers for cracks.
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 hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Required parts, if replacement of the
retainers on the tail rotor blades is necessary, would cost
approximately $56,900 per helicopter. 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
[[Page 34790]]
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 location provided under the caption
ADDRESSES.
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:
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 98-13-39 Eurocopter France: Amendment 39-10630. Docket No. 97-
SW-39-AD.
Applicability: AS 332C, L, and L1 helicopters, with tail rotor
shaft flapping hinge retainer, part number 330A33.3165.00,
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) Prior to 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.
Note 2: Eurocopter Service Bulletin No. 05.00.41, 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.
(e) This amendment becomes effective on July 31, 1998.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 96-074-057(B), dated March
27, 1996.
Issued in Fort Worth, Texas, on June 18, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-17041 Filed 6-25-98; 8:45 am]
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