[Federal Register Volume 65, Number 86 (Wednesday, May 3, 2000)]
[Proposed Rules]
[Pages 25694-25695]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-11063]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-84-AD]


Airworthiness Directives; Bell Helicopter Textron Canada Model 
430 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to Bell Helicopter Textron Canada 
(BHTC) Model 430 helicopters. This proposal would require replacing arm 
clamp screws (screws) in the yaw, roll, pitch, and collective syncro 
resolvers, and installing a guard bracket on the yaw, roll, pitch, and 
collective syncro resolvers. This proposal is prompted by an operator's 
report that a yaw control channel jammed during freedom-of-control 
checks following maintenance. The actions specified by the proposed AD 
are intended to prevent a jammed flight control and subsequent loss of 
control of the helicopter.

DATES: Comments must be received on or before July 3, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-84-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 
9:00 a.m. and 3:00 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice 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, both before and after the closing 
date for comments, 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 comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-SW-84-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-84-AD, 2601

[[Page 25695]]

Meacham Blvd., Room 663, Fort Worth, Texas 76137.

Discussion

    Transport Canada, which is the airworthiness authority for Canada, 
recently notified the FAA that an unsafe condition may exist on certain 
BHTC Model 430 helicopters. Transport Canada advises that a yaw control 
channel malfunctioned during a check for freedom-of-controls following 
maintenance because a screw that clamps the control arm to the yaw 
synchro resolver shaft was loose. This allowed the control arm to 
separate from the shaft and jam against an airframe stringer. To secure 
the installation of the four resolver control arms, the screws must be 
removed and replaced with airworthy screws and guard brackets must be 
installed.
    BHTC has issued Bell Helicopter Textron Alert Service Bulletin No. 
430-99-11, dated May 7, 1999, which introduces a higher torque alloy 
steel screw to replace the screws for the yaw, roll, pitch, and 
collective syncro resolvers. This service bulletin also specifies 
installing a guard bracket on the yaw, roll, pitch, and collective 
syncro resolvers to prevent the control arm from separating in case of 
a loss of torque of the clamping screw. Transport Canada classified 
this service bulletin as mandatory and issued AD No. CF-99-26, dated 
September 28, 1999, in order to assure 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 
section 21.29 of the Federal Aviation Regulations (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 the 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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTC Model 430 helicopters of the same type 
design registered in the United States, the proposed AD would require 
replacing screws in the yaw, roll, pitch, and collective syncro 
resolvers, and installing a guard bracket on the yaw, roll, pitch, and 
collective syncro resolvers. The actions would be required to be 
accomplished in accordance with the service bulletins described 
previously.
    The FAA estimates that 33 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 6.0 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $548. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $29,964.
    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. 99-SW-84-AD.
    Applicability: Model 430, serial numbers 49001 through 49018, 
49020 through 49043, and 49045 through 49051, 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 (c) 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 within 150 hours time-in-service after the 
effective date of this AD, unless accomplished previously.
    To prevent a jammed flight control and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Remove the arm clamp screws (screws) in the yaw, roll, 
pitch, and collective syncro resolvers and replace them with 
airworthy screws in accordance with the Accomplishment Instructions 
in Alert Service Bulletin 430-99-11, dated May 7, 1999 (ASB).
    (b) Install a guard bracket on the yaw, roll, pitch, and 
collective syncro resolvers in accordance with the Accomplishment 
Instructions in the ASB.
    (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, 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (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.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD No. CF-99-26, dated September 28, 1999.


    Issued in Fort Worth, Texas, on April 20, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-11063 Filed 5-2-00; 8:45 am]
BILLING CODE 4910-13-U