[Federal Register Volume 66, Number 122 (Monday, June 25, 2001)]
[Proposed Rules]
[Pages 33649-33651]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-15797]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-37-AD]


Airworthiness Directives; Bell Helicopter Textron Canada Model 
206L-4 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Bell Helicopter Textron Canada (BHTC) Model 206L-4 
helicopters. This proposal would require installing a high altitude 
tail rotor static stop yield indicator (indicator) to allow operators 
to detect excessive bending loads sustained by the tail rotor yoke. A 
preflight check of the indicator would also be required. This proposal 
is prompted by a determination that a tail rotor yoke with a high 
altitude rotor system is susceptible to a static and dynamic overload. 
Static overload could occur after the tail rotor yoke sustains an 
excessive bending load due to a strike from a ground vehicle. Dynamic 
overload could occur as a result of a hard landing. The actions 
specified by the proposed AD are intended to prevent failure of the 
tail rotor yoke in flight and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before August 24, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-37-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: Marc Belhumeur, Aviation Safety 
Engineer, FAA, Rotorcraft Certification Office, Rotorcraft Directorate, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5177, fax (817) 222-
5783.

[[Page 33650]]


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 proposal will be filed in 
the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this action must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-37-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. 2000-SW-37-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on BHTC Model 206L-4 
helicopters. Transport Canada advises that the tail rotor yoke is 
susceptible to static and dynamic overloads. The use of a previously 
overloaded yoke creates a safety hazard since the airworthiness of the 
overloaded yoke has been seriously compromised. There are a number of 
events that can lead to overloading the yoke. Installing an indicator 
will allow for timely detection of the overload condition.
    BHTC has issued Alert Service Bulletin No. 206L-96-104, Revision B, 
dated July 24, 1998 (ASB), which specifies immediate review of all 
installed and spare tail rotor yoke assembly, part number (P/N) 406-
012-102-107, historical records for any static or dynamic incident. The 
ASB gives instructions to install a new indicator, P/N 206-011-752-101, 
to detect excessive bending loads sustained by the tail rotor yoke. The 
ASB also provides helicopter mooring and pre-flight check information. 
Transport Canada classified this ASB as mandatory and issued AD No. CF-
98-11, dated June 16, 1998, to ensure the continued airworthiness of 
these helicopters in Canada.
    This helicopter model is manufactured in Canada and is 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, Transport Canada 
has kept the FAA informed of the situation described above. The FAA has 
examined the findings of Transport Canada, 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.
    We have identified an unsafe condition that is likely to exist or 
develop on other BHTC Model 206L-4 helicopters of the same type design 
registered in the United States. The proposed AD would require 
installing an indicator, P/N 206-011-752-101, within 100 hours time-in-
service. The actions would be required to be accomplished in accordance 
with the ASB described previously. A preflight visual check for damage 
to the indicator is also required.
    An owner/operator (pilot) may perform the visual check required by 
this AD and must enter compliance with paragraph (b) of this AD in 
accordance with 14 CFR 43.11 and 91.417(a)(2)(v)). This AD allows a 
pilot to perform this check because it involves only a visual check for 
damage to the indicator and can be performed equally well by a pilot or 
a mechanic.
    The FAA estimates that 16 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 0.5 work 
hour per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $1753. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $28,528.
    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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

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 adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron Canada: Docket No. 2000-SW-37-AD.

    Applicability: Model 206L-4 helicopters, with High Altitude Tail 
Rotor Kit, part number (P/N) 206-704-722-101 (BHT-206-SI-2054), 
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 (d) 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.


[[Page 33651]]


    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the tail rotor yoke in flight and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 100 hours time-in-service, install a high altitude 
tail rotor static stop yield indicator (indicator), P/N 206-011-752-
101, in accordance with the Accomplishment Instructions, Part II, 
Bell Helicopter Textron Alert Service Bulletin No. 206L-96-104, 
Revision B, dated July 24, 1998.
    (b) Before each engine start, check the indicator for damage in 
accordance with Figure 1 of this AD. If damage is found, before 
further flight, replace the damaged indicator with an airworthy 
indicator, and replace the tail rotor yoke, P/N 406-012-102-107, 
with an airworthy tail rotor yoke.

[GRAPHIC] [TIFF OMITTED] TP25JN01.000

    (c) An owner/operator (pilot) holding at least a private pilot 
certificate may perform the visual check required by paragraph (b) 
of this AD, and must record compliance in the helicopter maintenance 
records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v)).
    (d) 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 Certification Office, 
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 Certification 
Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (e) 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 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-98-11, dated June 16, 1998.


    Issued in Fort Worth, Texas, on June 15, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-15797 Filed 6-22-01; 8:45 am]
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