[Federal Register Volume 65, Number 41 (Wednesday, March 1, 2000)]
[Proposed Rules]
[Pages 11006-11009]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-4798]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-43-AD]


Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) 
Model 222, 222B, 222U, and 230 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) applicable to BHTC Model 222, 222B, 222U, and 230 
helicopters. This proposal would require inspecting each flapping 
bearing to yoke attachment bolt (bolt) and replacing each bolt that 
shows thread damage, shank wear, or corrosion

[[Page 11007]]

pitting with an airworthy bolt. This proposal is prompted by the 
discovery of a fractured bolt during a post-flight inspection. The 
actions specified by the proposed AD are intended to prevent a fracture 
of a bolt, failure of the bearing and yoke interface, and subsequent 
loss of control of the helicopter.

DATES: Comments must be received on or before May 1, 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-43-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas. Comments may be inspected at this location between 
9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, 
Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax (514) 433-0272. 
This information may be examined at the FAA, Office of the Regional 
Counsel, Southwest Region, Room 663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aerospace Engineer, FAA, 
Rotorcraft Directorate, Rotorcraft Standards Staff, 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-43-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-43-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 222, 222B, 
222U, and 230 helicopters. Transport Canada advises that an inspection 
revealed a fractured bolt due to stress corrosion. Stress-corrosion 
from a combination of mechanical wear, fatigue, and environmental 
exposure caused the bolt to fail.
    BHTC has issued Alert Service Bulletins (ASB's) 230-98-15, 222-98-
83, and 222U-98-54, all dated October 12, 1998, which specify 
inspecting the bolts and replacing each bolt that shows thread damage, 
shank wear, or corrosion pitting with an airworthy bolt. Transport 
Canada classified these ASB's as mandatory and issued AD's CF-99-12 and 
CF-99-13, both dated April 21, 1999, to ensure the continued 
airworthiness of these helicopters in Canada.
    These helicopter models are manufactured in Canada and are 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 Transport Canada, reviewed all available information, and 
determined that AD action is necessary for products of these type 
designs 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 222, 222B, 222U, and 230 
helicopters of the same type designs registered in the United States, 
the proposed AD would require inspecting the bolts and replacing each 
bolt that shows thread damage, shank wear, or corrosion with an 
airworthy bolt.
    The FAA estimates that 101 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 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 $20 per bolt. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be $20,200.
    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-43-AD.

    Applicability: Model 222 helicopters, serial number (S/N) 47006 
through 47089; Model 222B helicopters, S/N 47131 through 47156;

[[Page 11008]]

Model 222U helicopters, S/N 47501 through 47574; and Model 230 
helicopters, S/N 23001 through 23038 inclusive, 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 (b) 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, unless 
accomplished previously.
    To prevent the fracture of a flapping bearing to yoke attachment 
bolt (bolt), failure of the bearing and yoke interface, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Remove one bolt at a time and inspect each bolt located as 
shown in Figure 1.

    Note 2:
    For main rotor hubs installed on rotorcraft, the bolts may be 
removed, inspected, and installed one at a time.


    Note 3:
    Bell Helicopter Textron Canada Alert Service Bulletins 230-98-
15, 222-98-83, and 222U-98-54, all dated October 12, 1998, pertain 
to the subject of this AD.

    (1) Clean each bolt with a cloth dampened with methyl ethyl 
ketone, RHO SOLV756, Desoto 110, or equivalent.
    (2) Visually inspect each bolt and discard those that have 
thread damage, shank wear, or corrosion.
    (3) Apply corrosion preventative compound MIL-C-16173 GR2, or 
equivalent, to the shank of the bolt only.
    (4) Install, torque, and lockwire each bolt.
    (5) Coat each bolt head and nut with corrosion preventative 
compound MIL-C-16173 GR1 or equivalent.
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    (b) 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 4:
    Information concerning the existence of approved alternative 
methods of compliance with this AD, if any, may be obtained from the 
Regulations Group.

    (c) 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.

    Note 5:
    The subject of this AD is addressed in Transport Canada (Canada) 
AD's CF-99-12 and CF-99-13, both dated April 21, 1999.


    Issued in Fort Worth, Texas, on February 22, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-4798 Filed 2-29-00; 8:45 am]
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