Airworthiness Directives; Kaman Aerospace Corporation Model K-1200 Helicopters

[Federal Register Volume 69, Number 129 (Wednesday, July 7, 2004)]
[Rules and Regulations]
[Pages 40764-40765]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15127]



[[Page 40764]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-46-AD; Amendment 39-13708; AD 2004-13-26]
RIN 2120-AA64


Airworthiness Directives; Kaman Aerospace Corporation Model K-
1200 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Kaman Aerospace Corporation (Kaman) Model K-1200 helicopters. This 
action requires certain initial and repetitive visual inspections of 
the main rotor blade (blade) grips for a crack. If a crack is found, 
this AD requires replacing the blade grip before further flight. This 
amendment is prompted by an accident involving the loss of all blades 
because of a crack in a blade grip on the upper surface around the 
bolthole. The actions specified in this AD are intended to prevent 
failure of a blade grip, loss of a blade, and subsequent loss of 
control of the helicopter.

DATES: Effective July 22, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 22, 2004.
    Comments for inclusion in the Rules Docket must be received on or 
before September 7, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2003-SW-46-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].
    You may obtain the service information referenced in this AD from 
Kaman Aerospace Corporation, P.O. Box 2, Old Windsor Rd., Bloomfield, 
CT 06002-0002, telephone (888) 626-KMAX (5629), fax (880) 243-7047. You 
may examine this information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas; or at the National Archives and Records Administration (NARA). 
For information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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: This amendment adopts a new AD for the Kaman 
Model K1200 helicopters. This action requires certain initial and 
repetitive inspections of the blade grips. This amendment is prompted 
by an accident involving the loss of all blades because of a blade grip 
crack on the upper surface around the bolthole of one blade.
    The FAA has reviewed Kaman Service Bulletin No. 109 dated October 
31, 2003, which describes visually inspecting blade grips for a crack 
before the next flight and before the first flight of each day.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to prevent failure of a blade grip leading to loss of a blade and 
subsequent loss of control of the helicopter. This AD requires, before 
further flight, removing the paint and primer from each blade grip; and 
using a light and 10x power or higher magnifying glass, visually 
inspecting each blade grip at the top (bolt) and bottom (nut) locations 
for a crack around the bolthole. Also, this AD requires, before the 
first flight of each day, removing corrosion preventative compound from 
each blade grip, and using a light and 10x power or higher magnifying 
glass, visually inspecting each blade grip at the top (bolt) and bottom 
(nut) locations for a crack around the bolthole. After each inspection, 
if a crack is not detected, applying corrosion protection compound over 
the exposed area is required. If a crack is found, this AD requires 
replacing the blade grip before further flight. Accomplish the actions 
in accordance with the service bulletin described previously.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
before further flight, and before the first flight of each day, 
visually inspecting each blade grip for a crack and replacing any 
cracked blade grip are required, and this AD must be issued 
immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that this AD will affect 23 helicopters. The 
initial inspection of the blade grip will take approximately 2 work 
hours, and the daily inspection will take approximately \1/2\ work hour 
to do at an average labor rate of $65 per work hour. Based on these 
figures, we estimate the total cost impact of the AD on U.S. operators 
will be $197,340 for the first year ($2,990 for the initial inspection 
plus $194,350 for the repetitive inspections ($747.50 each day and 
assuming each helicopter is flown 260 days per year)).

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available in the Rules Docket for examination by interested persons. A 
report that summarizes each FAA-public contact concerned with the 
substance of this AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2003-SW-46-AD.'' The postcard will be date 
stamped and returned to the commenter.

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    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 adding a new airworthiness directive to 
read as follows:

2004-13-26 Kaman Aerospace Corporation: Amendment 39-13708. Docket 
No. 2003-SW-46-AD.

    Applicability: Model K-1200 helicopters, certificated in any 
category.
    Compliance: Required as indicated.
    To prevent failure of a blade grip, blade contact with the 
opposite rotor mast, blade failure, and loss of control of the 
helicopter, accomplish the following:
    (a) Before further flight, unless accomplished previously, 
remove the paint topcoat and primer from each blade grip; and using 
a light and 10x power or higher magnifying glass, visually inspect 
each blade grip in accordance with the Accomplishment Instructions, 
paragraph 1. and 2.a., of Kaman Aerospace Corporation Service 
Bulletin No. 109, dated October 31, 2003 (SB).

    Note: Do not damage or remove the sealant around the blade grip 
bolt heads and nuts.

    (1) If a crack is detected, remove the grip and replace it with 
an airworthy grip.
    (2) If no crack is detected, cover the exposed area with 
corrosion preventative compound.
    (b) Before the first flight of each day, remove corrosion 
preventative compound from each blade grip using acetone. Using a 
light and 10x power or higher magnifying glass, visually inspect 
each blade grip for a crack in the area depicted in Figure 1 of the 
SB.
    (1) If a crack is detected, remove the grip and replace it with 
an airworthy grip.
    (2) If no crack is detected, cover the exposed area with 
corrosive preventative compound.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Safety Management Group, Rotorcraft Directorate, FAA, 
for information about previously approved alternative methods of 
compliance.
    (d) Special flight permits will not be issued.
    (e) The inspections shall be done in accordance with Kaman 
Aerospace Corporation Service Bulletin No. 109, dated October 31, 
2003. This incorporation by reference was approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Kaman Aerospace Corporation, 
P.O. Box 2, Old Windsor Rd., Bloomfield, CT 06002-0002, telephone 
(888) 626-KMAX (5629), fax (880) 243-7047. Copies may be inspected 
at the FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth, Texas; or at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    (f) This amendment becomes effective on July 22, 2004.

    Issued in Fort Worth, Texas, on June 24, 2004.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-15127 Filed 7-6-04; 8:45 am]
BILLING CODE 4910-13-P

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