[Federal Register Volume 65, Number 96 (Wednesday, May 17, 2000)]
[Rules and Regulations]
[Pages 31256-31259]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12354]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-34-AD; Amendment 39-11732; AD 2000-10-08]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N1, AS-
365N2, and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 
helicopters and requires conducting inspections of each tail rotor 
blade for bonding separation, measuring the clearance between the tip 
of each tail rotor blade and the circumference of the air duct, and 
replacing the blade if necessary. This amendment is prompted by an 
inflight incident in which the tail rotor blades were significantly 
damaged due to bonding separation. The actions specified by this AD are 
intended to prevent damage to a tail rotor blade, loss of tail rotor 
control, and subsequent loss of control of the helicopter.

EFFECTIVE DATE: June 21, 2000.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD for Eurocopter 
France Model SA-365N1, AS-365N2, and SA-366G1 helicopters was published 
in the Federal Register on February 29, 2000 (65 FR 10724). That action 
proposed to require conducting inspections of each tail rotor blade for 
bonding separation, measuring the clearance between the tip of each 
tail rotor blade and the circumference of the air duct, and replacing 
the blade if necessary.
    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 136 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$1,000 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $144,160.
    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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

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.

[[Page 31257]]

Sec. 39.13  [Amended]

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

AD 2000-10-08  Eurocopter France: Amendment 39-11732. Docket No. 99-
SW-34-AD.

    Applicability: Model SA-365N1, AS-365N2, and SA-366G1 
helicopters, with a tail rotor blade, part number (P/N) 365A33-2131, 
365A12-0010, or 365A12-0020, 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 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (f) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent damage to a tail rotor blade (blade), loss of tail 
rotor control, and subsequent loss of control of the helicopter:
    (a) Within 10 hours time-in-service (TIS) and thereafter prior 
to the first flight of each day, conduct the following visual 
inspection of each blade (see Figure 1):
    (1) Zone A: If a blister is detected on the blade suction face, 
conduct a tapping test inspection on the whole blade for bonding 
separation. If bonding separation or a crack is found, replace the 
blade with an airworthy blade before further flight.
    (2) Zone B: If a crack, wrinkling, or a blister is found, 
replace the blade with an airworthy blade before further flight.
    (b) Within 10 hours TIS, conduct a tapping test inspection on 
each blade. If there is bonding separation, replace the blade with 
an airworthy blade before further flight.

    Note 2: Revisions 5 of Eurocopter France Service Bulletins 05.09 
and 05.00.17, both dated December 18, 1998, pertain to the subject 
of this AD.

    (c) Thereafter, at intervals not to exceed 25 hours TIS or every 
50 cycles (each takeoff and landing equals 1 cycle), whichever 
occurs first, conduct a tapping test inspection for bonding 
separation on all blades with a serial number (S/N) less than 18912, 
and blades, P/N 365A12-0020-00 or 365A12-0020-01, with a S/N equal 
to or greater than 18912. If bonding separation or a crack is found, 
replace the blade with an airworthy blade before further flight.
    (d) Thereafter, at intervals not to exceed 100 hours TIS or 200 
cycles, whichever occurs first, conduct a tapping test inspection 
for bonding separation on blades, P/N 365A12-0020-02 or 365A12-0020-
03. If bonding separation or a crack is found, replace the blade 
with an airworthy blade before further flight.
    (e) Within 10 hours TIS, and thereafter at intervals not to 
exceed 100 hours TIS or 200 cycles, whichever occurs first, measure 
the blade-to-air duct clearance. If the clearance is less than 3 mm, 
replace the blade with an airworthy blade before further flight.
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    (f) 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, Regulations Group, 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, Regulations Group.

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

    (g) Special flight permits may be issued in accordance with 
Secs. 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.
    (h) This amendment becomes effective on June 21, 2000.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile AD's 88-152-010(A)R5 and 88-153-
023(A)R5, both dated December 30, 1998.


    Issued in Fort Worth, Texas, on May 9, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-12354 Filed 5-16-00; 8:45 am]
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