AD Amdt-39-12452

[Federal Register Volume 66, Number 192 (Wednesday, October 3, 2001)]
[Rules and Regulations]
[Pages 50307-50310]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-24624]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-34-AD; Amendment 39-12452; AD 2000-10-08 R1]
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 revises an existing airworthiness directive 
(AD) for Eurocopter France (ECF) Model SA-365N1, AS-365N2, and SA-366G1 
helicopters. That AD currently requires inspecting 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 requires the same 
actions but allows the pilot to perform the daily visual check and 
contains a damage allowance for certain blades. This amendment is 
prompted by FAA determination that the pilot can

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check for a cracked, blistered, or wrinkled blade and that some 
debonding of the blade is acceptable. The actions specified by this AD 
are intended to allow a pilot check, to prevent unacceptable damage to 
a tail rotor blade, and to prevent loss of tail rotor control and 
subsequent loss of control of the helicopter.

EFFECTIVE DATE: November 7, 2001.

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 14 CFR part 39 by 
revising AD 2000-10-08, Amendment 39-11732 (65 FR 31256, May 17, 2000), 
for ECF Model SA-365N1, AS-365N2, and SA-366G1 helicopters, was 
published in the Federal Register on June 11, 2001 (66 FR 31189). The 
action proposed to revise AD 2000-10-08 to allow a ``visual'' check of 
each tail rotor blade for a crack, wrinkling, or a blister, within 10 
hours time-in-service (TIS) and thereafter before the first flight of 
each day. Also proposed was allowing some debonding in blades, part 
number 365A12-0020-02 and 365A12-0020-03.
    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. If a tapping inspection is required, it will take 
approximately 1 work hour per helicopter to conduct, and the average 
labor rate is $60 per work hour. If necessary, replacing a blade would 
take approximately 4 hours and required parts would cost approximately 
$1,000 per helicopter. Based on these figures, the total cost impact of 
this AD on U.S. operators is estimated to be $176,800, assuming a blade 
must be replaced on each affected helicopter.
    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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-11732 (65 FR 
31256, May 17, 2000), and by adding a new airworthiness directive (AD), 
Amendment 39-12452, to read as follows:

2000-10-08 R1  Eurocopter France: Amendment 39-12452. Docket No. 99-
SW-34-AD. Revises AD 2000-10-08, 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 (e) 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 before 
the first flight of each day, visually check each blade (see Figure 
1) for a crack, blister, or wrinkling. An owner/operator (pilot), 
holding at least a private pilot certificate, may perform the visual 
check and must enter compliance into the aircraft maintenance 
records in accordance with 14 CFR sections 43.11 and 
91.417(a)(2)(v)).
    (b) If a crack, blister, or wrinkling is found as a result of 
the visual check, accomplish the following before further flight 
(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.
    (i) For blades, P/N 365A33-2131--all dash numbers, 365A12-0010--
all dash numbers, and 365A12-0020-00, and -01, if bonding separation 
or a crack is found, replace the blade with an airworthy blade 
before further flight.
    (ii) For blades, P/N 365A12-0020-02, and -03, if bonding 
separation exceeds 900 mm<SUP>2</SUP> in a 30  x  30 mm square or if 
there is a crack, 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.
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    (c) Within 10 hours TIS, conduct a tapping test inspection on 
each blade. If there is bonding separation that exceeds the criteria 
in paragraph b(1) of this AD, 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.

    (1) 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.
    (2) 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. For Zone A, if bonding separation exceeds the criteria specified 
in paragraph (b)(1)(ii) of

[[Page 50310]]

this AD or if a crack is found, replace the blade with an airworthy 
blade before further flight. For Zone B, if a crack, wrinkling, or a 
blister is found, replace the blade with an airworthy blade before 
further flight.
    (d) 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.
    (e) 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.

    (f) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (g) This amendment becomes effective on November 7, 2001.

    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 September 25, 2001.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-24624 Filed 10-2-01; 8:45 am]
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