[Federal Register Volume 67, Number 92 (Monday, May 13, 2002)]
[Proposed Rules]
[Pages 31992-31993]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-11807]


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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 revising an existing airworthiness 
directive (AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 
helicopters. That AD currently requires reducing the life limit of the 
rotor shaft and teeter pin assembly and establishing a life limit for 
the flap clevis. This action would retain those requirements but would 
remove a flap clevis part number from the applicability. This proposal 
is prompted by the determination after an analysis of testing results 
that a certain flap clevis should have an unlimited life. The actions 
specified by the proposed AD are intended to remove the life limit for 
a specified flap clevis and to revise the maintenance manual by 
removing the life limit for that flap clevis. Also, the actions 
specified by the proposed AD are intended to prevent fatigue failure of 
the rotor shaft, the teeter pin assembly, and the flap clevis and 
subsequent loss of control of the helicopter.

DATES: Comments must be received by July 12, 2002.

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: [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: Richard Noll, Aviation Safety 
Engineer, Boston Aircraft Certification Office, 12 New England 
Executive Park, Burlington, MA 01803, telephone (781) 238-7160, fax 
(781) 238-7170.

SUPPLEMENTARY INFORMATION:

[[Page 31993]]

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 action 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.

Discussion

    On June 12, 2001, the FAA issued AD 2001-13-03, Amendment 39-12283 
(66 FR 34102, June 27, 2001), to require reducing the life limit of the 
rotor shaft and the teeter pin assembly and establishing a life limit 
for the flap clevis. That action was prompted by the discovery of 
cracks in parts returned to the manufacturer. That condition, if not 
corrected, could result in failure of a part and subsequent loss of 
control of the helicopter.
    Since the issuance of that AD, further testing indicates that a 
specified time-in-service (TIS) life limit is unwarranted for flap 
clevis, part number (P/N) K911049-021.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, the FAA proposes 
revising AD 2001-13-03 to retain the existing life limits for each 
rotor shaft, teeter pin assembly, and flap clevis, except flap clevis, 
P/N K911049-021. Accordingly, this NPRM would also propose to revise 
the Limitations section of the maintenance manual to remove the life 
limit of 640 hours TIS for flap clevis, part number K911049-021.
    The FAA estimates that 9 helicopters of U.S. registry would be 
affected by this proposed AD. No additional costs would be incurred to 
accomplish the proposed actions because it would relieve an AD 
requirement.
    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 removing Amendment 39-12283 (66 FR 
34102, June 27, 2001), and by adding a new airworthiness directive 
(AD), to read as follows:

Kaman Aerospace Corporation: Docket No. 2000-SW-50-AD. Revises AD 
2001-13-03, Amendment 39-12283, 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 as indicated, 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) Before further flight, 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 
part. Remove any teeter pin assembly, P/N K910005-007 or -009, that 
has 550 or more hours TIS and replace it with an airworthy part. 
Remove any flap clevis, P/N K911049-011, -017, or -019, that has 640 
or more hours TIS, and replace it with an airworthy part.
    (b) This AD revises the Limitations section of the maintenance 
manual by removing the life limit of 640 hours TIS established for 
the flap clevis, P/N K911049-021. The life limit for each rotor 
shaft, P/N K974112-001, -003, -005, -007, -009, and -101 remains at 
3,750 hours TIS; the life limit for each teeter pin assembly, P/N 
K910005-007 and -009, remains at 550 hours TIS; and the life limit 
for the flap clevis, P/N K911049-011, -107, and -109 remains at 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 will not be issued.

    Issued in Fort Worth, Texas, on April 29, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-11807 Filed 5-10-02; 8:45 am]
BILLING CODE 4910-13-P