[Federal Register Volume 66, Number 43 (Monday, March 5, 2001)]
[Proposed Rules]
[Pages 13269-13271]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-5170]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-50-AD]
RIN 2120-AA64


Airworthiness Directives; Kaman Aerospace Corporation Model K-
1200 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) for Kaman Aerospace Corporation (Kaman) Model K-1200 
helicopters. The AD would require reducing the life limit of the rotor 
shaft and teeter pin assembly, and establishing a life limit for the 
flap clevis. This proposal is prompted by the discovery of cracks in 
parts that were returned to the manufacturer. The actions specified by 
the proposed AD are intended to prevent failure of the rotor shaft, 
teeter pin assembly, or flap clevis due to fatigue cracks, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before May 4, 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-50-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#5d64703c2e2a703c393e3230303833292e1d3b3c3c733a322b"><span class="__cf_email__" data-cfemail="635a4e0210144e0207000c0e0e060d1710230502024d040c15">[email protected]</span></a>. 
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: Richard Noll, Aviation Safety 
Engineer, Boston Aircraft Certification Office, 12 New England 
Executive Park, Burlington, MA 01803, telephone (781) 238-7160, fax 
(781) 238-7199.

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

[[Page 13270]]

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 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. 2000-SW-50-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-50-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    This document proposes the adoption of a new airworthiness 
directive (AD) for Kaman Model K-1200 helicopters. The AD would 
require:
    <bullet> Reducing the life limit for the rotor shaft from 10,000 
hours time-in-service (TIS) to 3,750 TIS;
    <bullet> Reducing the life limit of the teeter pin assembly from 
10,000 hours TIS to 550 hours TIS; and
    <bullet> Establishing a life limit of the flap clevis of 640 hours 
TIS.
    This proposal is prompted by the discovery of cracks in parts that 
were returned to the manufacturer. The actions specified by the 
proposed AD are intended to prevent failure of the rotor shaft, teeter 
pin assembly, or flap clevis due to fatigue cracks, and subsequent loss 
of control of the helicopter.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Kaman Model K-1200 helicopters of the same 
type design, the proposed AD would require:
    <bullet> Reducing the life limit of the rotor shaft, part number 
(P/N) K974112-001, -003, -005, -007, -009, or -101, from 10,000 hours 
TIS to 3,750 hours TIS;
    <bullet> Reducing the life limit of the teeter pin assembly, P/N 
K910005-007 or -009, from 10,000 hours to 550 hours TIS; and
    <bullet> Establishing a life limit of the flap clevis, P/N K911049-
011, -017, -019, or -021, of 640 hours TIS.
    The FAA estimates that 9 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take 0.25 hour per 
helicopter to accomplish the proposed changes to the Limitations 
section of the applicable maintenance manual, 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 $135, 
plus an increase in hourly operating costs of approximately $13 for 
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 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:

Kaman Aerospace Corporation: Docket No. 2000-SW-50-AD.

    Applicability: Model K-1200 helicopters, 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 25 hours time-in-service, unless 
accomplished previously.
    To prevent failure of the rotor shaft, teeter pin assembly, or 
flap clevis due to fatigue cracks, and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Remove any rotor shaft, part number 
(P/N) K974112-001, -003, -005, -007, -009, or -101, that has 3,750 
or more hours time-in-service (TIS) and replace it with an airworthy 
rotor shaft. Remove any teeter pin assembly, P/N K910005-007 or -
009, that has 550 or more hours TIS and replace it with an airworthy 
teeter pin assembly. Remove any flap clevis, P/N K911049-011, -017, 
-019, or -021, that has 640 or more hours TIS and replace it with an 
airworthy flap clevis.
    (b) This AD revises the Limitations section of the maintenance 
manual by reducing the life limit of the rotor shaft, P/N K974112-
001, 003, -005, -007, -009, and -001, to 3,740 hours TIS; reducing 
the life limit of the teeter pin assembly, P/N K910005-007 and -009, 
to 550 hours TIS; and establishing a life limit for the flap clevis, 
P/N K911049-011, -017, -019, and -021, of 640 hours TIS.
    (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, Boston Aircraft Certification 
Office, FAA. Operators shall submit their requests through an FAA 
Principal Maintenance Inspector, who may concur or comment and then 
send it to the Manager, Boston Aircraft Certification Office.

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

    (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.


[[Page 13271]]


    Issued in Fort Worth, Texas, on February 21, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-5170 Filed 3-2-01; 8:45 am]
BILLING CODE 4910-13-P


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