[Federal Register Volume 67, Number 11 (Wednesday, January 16, 2002)]
[Proposed Rules]
[Pages 2146-2148]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1057]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-54-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
407 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 407 helicopters. 
This proposal would require visually inspecting the forward hanger 
bearing bracket (bracket). This proposal is prompted by reports of 
cracks in the bracket. The actions specified by this proposed AD are 
intended to detect a crack in the bracket, to prevent loss of tail 
rotor drive or tail rotor control and subsequent loss of control of the 
helicopter.

DATES: Comments must be received on or before March 18, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-54-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 under the 
caption ADDRESSES. 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, 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 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. 2001-SW-54-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. 2001-SW-54-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

[[Page 2147]]

Discussion

    Transport Canada, the airworthiness authority for Canada, notified 
the FAA that an unsafe condition may exist on BHTC Model 407 
helicopters. Transport Canada advises of reports of cracks in certain 
brackets.
    BHTC has issued Alert Service Bulletin No. 407-01-39, Revision A, 
dated May 30, 2001 (ASB). That ASB specifies initial and repetitive 
inspections for a crack in bracket, part number (P/N) 407-040-321-101 
and -103, for helicopters, serial number 53000 through 53442 with 
flywheel, P/N 407-040-316-101, installed. Transport Canada classified 
this ASB as mandatory and issued AD No. CF-2001-32, dated August 13, 
2001, 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 agreement. Pursuant to the 
applicable bilateral 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.
    This unsafe condition is likely to exist or develop on other 
helicopter models of the same type design registered in the United 
States. Therefore, the proposed AD would require initial and repetitive 
visual inspections for a crack in certain brackets and if a crack is 
found, removing the bracket before further flight.
    The FAA estimates that 442 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1/4 work 
hour per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $6630 assuming no crack is detected in a bracket.
    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. 2001-SW-54-AD.
    Applicability: Model 407 helicopters, serial number 53000 
through 53442, with flywheel, part number (P/N) 407-040-316-101, 
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 (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 as indicated, unless accomplished 
previously.
    To detect a crack in the forward bearing hanger bracket 
(bracket) and to prevent loss of tail rotor drive or tail rotor 
control and subsequent loss of control of the helicopter, accomplish 
the following:
    (a) Within 25 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 25 hours TIS, visually inspect each bracket, 
P/N 407-040-321-101 or -103, for a crack in the shaded area shown in 
Figure 1 of this AD. Remove any cracked bracket from service.

    Note 2: Dismantling of the bearing hanger and the support is not 
required to accomplish the requirements of this AD.


[[Page 2148]]


[GRAPHIC] [TIFF OMITTED] TP16JA02.001


    Note 3: Bell Helicopter Textron Canada Alert Service Bulletin 
No. 407-01-39, Revision A, dated May 30, 2001, pertains to the 
subject of this AD.

    (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 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 No. CF-2001-32, dated August 13, 2001.


    Issued in Fort Worth, Texas, on January 4, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-1057 Filed 1-15-02; 8:45 am]
BILLING CODE 4910-13-P