[Federal Register Volume 68, Number 76 (Monday, April 21, 2003)]
[Rules and Regulations]
[Pages 19341-19342]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9576]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-50-AD; Amendment 39-13123; AD 2001-13-03 R1]
RIN 2120-AA64


Airworthiness Directives; Kaman Aerospace Corporation Model K-
1200 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD) for Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters 
that currently requires reducing the life limit of the rotor shaft and 
teeter pin assembly and establishing a life limit for the flap clevis. 
This amendment retains those requirements but removes a flap clevis 
part number from the applicability and, as a result of a comment, 
changes the application of the life limit from the flap clevis to the 
flap clevis assembly. This amendment is prompted by the determination 
after an analysis of testing results that a certain flap clevis 
assembly should have an unlimited life. The actions specified by this 
revision are intended to remove the life limit for a specified flap 
clevis assembly. The actions specified by this AD are intended to 
prevent fatigue failure of the rotor shaft, teeter pin assembly, and 
flap clevis assembly, and subsequent loss of control of the helicopter.

DATES: Effective May 27, 2003.

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: A proposal to amend 14 CFR part 39 by 
revising AD 2001-13-03, Amendment 39-12283 (66 FR 34102, June 27, 
2001), for 1 Kaman Model K-1200 helicopters, was published in the 
Federal Register on May 13, 2002 (67 FR 31992). The action proposed 
retaining the existing life limit for each rotor shaft, teeter pin 
assembly, and flap clevis, except flap clevis, part number (P/N) 
K911049-021. That action was prompted by the determination after an 
analysis of testing results that flap clevis, P/N K911049-021, should 
have an unlimited life.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received. The one commenter, the manufacturer, states that 
the flap clevis assembly part numbers should be identified instead of 
the flap clevis part numbers to be consistent with actual current 
maintenance practices. The FAA agrees because we have approved a 
revision to the Airworthiness Limitations of the Kaman Model K-1200 
helicopter maintenance manual that imposes the life limit on the flap 
clevis assembly part numbers not the flap clevis part numbers. The 
proposed change will make this AD consistent with the Airworthiness 
Limitations section. Additionally, two part numbers for the flap clevis 
were incorrectly stated in paragraph (b) of the proposed AD; however, 
this change to flap clevis assembly parts number also corrects that 
error.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require adopting the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates that this AD will affect nine helicopters of U.S. 
registry. No additional costs will be incurred to accomplish the 
proposed actions because it would relieve a previously-imposed AD life 
limit for flap clevis, P/N K911049-021.
    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory

[[Page 19342]]

Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
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), Amendment 39-13123, to read as follows:

2001-13-03 R1 Kaman Aerospace Corporation: Amendment 39-13123. 
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 2 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 assembly, P/N K911049-001, -003, or -005, 
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 each flap clevis assembly, P/N K911049-001, -003, and -005 
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.
    (e) This amendment becomes effective on May 27, 2003.

    Issued in Fort Worth, Texas, on April 9, 2003.
Michele M. Owsley,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-9576 Filed 4-18-03; 8:45 am]
BILLING CODE 4910-13-P