[Federal Register Volume 66, Number 112 (Monday, June 11, 2001)]
[Proposed Rules]
[Pages 31189-31192]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-14536]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-34-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking.

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SUMMARY: This document proposes revising 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 action would 
contain the same requirements but would allow the pilot to perform the 
daily visual check and would contain a damage allowance for certain 
blades. This proposal is prompted by FAA determination that the pilot 
can check for a cracked, blistered, or wrinkled blade and that some 
debonding of the blade is acceptable. The actions specified by the 
proposed 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.

DATES: Comments must be received by August 10. 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-34-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. You may also send comments electronically to 
the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available in the Rules Docket for 
examination by interested persons. A report summarizing each FAA-public 
contact concerned with the substance of this document will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 99-SW-34-AD.'' The postcard will be date 
stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-34-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    On May 9, 2000, the FAA issued AD 2000-10-08, Amendment No. 39-
11732 (65 FR 31256) to require 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 a 
blade if necessary. That action was prompted by an inflight incident in 
which the tail rotor blades were significantly damaged due to bonding 
separation. That condition, if

[[Page 31190]]

not corrected, could result in loss of tail rotor control and 
subsequent loss of control of the helicopter.
    Since the issuance of that AD, the FAA has reevaluated the 
requirements due to reports from operators that the AD has placed an 
unnecessary burden on them and that a pilot should be allowed to 
perform the check. ECF has issued Service Bulletins 05.09 and 05.00.17, 
both dated December 18, 1998; and based on these service bulletins, the 
Direction Generale De L'Aviation Civile (DGAC) (France) has issued AD's 
88-152-010(A)R5 and 88-153-023(A)R5, both dated December 30, 1998. The 
FAA has reviewed these documents and determined that the pilot may 
perform the check and that some debonding is acceptable.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral airworthiness agreement. 
Pursuant to this bilateral airworthiness agreement, the DGAC has kept 
the FAA informed of the situation described above. The FAA has examined 
the findings of the DGAC, reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.
    An owner/operator (pilot) may perform the visual check required by 
this AD and enter compliance with the visual check provisions in 
paragraph (a) of this AD in accordance with 14 CFR 43.11 and 
91.417(a)(2)(v). This AD allows a pilot to perform the check because it 
involves only a visual check of the tail rotor blades for a crack, 
wrinkling, or a blister and can be performed equally well by a pilot or 
a mechanic.
    Since we have identified an unsafe condition that is likely to 
exist or develop on other ECF Model SA-365N1, AS-365N2, and SA-366G1 
helicopters of the same type design, the proposed AD would contain the 
same requirements as the existing AD. However, the proposed AD would 
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. The 
proposed AD would also allow some debonding in blades, part number 
365A12-0020-02 and 365A12-0020-03.
    The FAA estimates that 136 helicopters of U.S. registry would be 
affected by this proposed AD. If a tapping inspection is required, it 
would take approximately 1 work hour per helicopter to conduct, and 
that 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 the AD on U.S. operators is estimated to be 
$176,800, assuming a blade must be replaced on each affected 
helicopter.
    The regulations proposed herein would 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 proposed rule would not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
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) if 
promulgated, would 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 copy of the draft regulatory 
evaluation has been prepared for this action 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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) and by adding a new airworthiness directive to read as follows:

Eurocopter France: 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 mm2 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 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.

    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 31, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-14536 Filed 6-8-01; 8:45 am]
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