[Federal Register: January 9, 2007 (Volume 72, Number 5)]
[Proposed Rules]
[Page 918-920]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09ja07-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26696; Directorate Identifier 2006-SW-19-AD]
RIN 2120-AA64
Airworthiness Directives; Robinson Helicopter Company Model R44
and R44 II 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 robinson Helicopter Company (Robinson) Model R44 and R44 II
helicopters that have a certain seat belt buckle (buckle) assembly
installed. The AD would require removing the buckle assembly and the
buckle assembly spacer, and replacing them with airworthy parts. This
proposal is prompted by an accident in which a seat belt failed, and
also by reports of cracking in the buckle assembly stainless support
strap (support strap). The actions specified by the proposed AD are
intended to prevent cracking in the support strap and failure of a seat
belt.
DATES: Comments must be received on or before March 12, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to http://www.regulations.gov
follow the instructions for sending your comments
electronically;
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590;
Fax: 202-493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You may get the service information identified in this proposed AD
from Robinson Helicopter Company, 2901 Airport Drive, Torrance,
California 90505, telephone (310) 539-0508, fax (310) 539-5198.
You may examine the comments to this proposed AD in the AD docket
on the Internet at http://dms.dot.gov.
[[Page 919]]
FOR FURTHER INFORMATION CONTACT: Venessa Stiger, Aviation Safety
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5337, fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2006-
26696, Directorate Identifier 2006-SW-19-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed rulemaking. Using the search
function of our docket Web site, you can find and read the comments to
any of our dockets, including the name of the individual who sent or
signed the comment. You may review the DOT's complete Privacy Act
Statement in the Federal Register published on April 11, 2000 (65 FR
19477-78) or you may visit http://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation Nassif Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
This document proposes adopting a new AD for Robinson model R44
helicopters, through serial number (S/N) 1576, and Model R44 II
helicopters, through S/N 11107, that have a C628-4, revision M or
prior, buckle assembly installed. The AD would require, within 100
hours time-in-service, removing the buckle assembly and the A130-52
buckle assembly spacer, and replacing them with a C628-4, revision N
buckle assembly and a new A130-52 buckle assembly spacer. The A130-52
buckle assembly spacers have been redesigned to be slightly longer than
the previous A130-52 buckle assembly spacers, to reduce friction in the
joint. This proposal is prompted by an investigation in which a seat
belt failed during an accident, and also by reports of cracking in the
buckle assembly support strap. Excessive bending of the buckles can
damage their stainless support straps. The actions specified by the
proposed AD are intended to prevent cracking in the support strap and
failure of a seat belt.
We have reviewed Robinson Service SB-56, dated March 29, 2006,
which describes procedures for inspecting the buckle assemblies for
cracks and replacing the buckle assemblies. This proposed AD would not
require inspecting the buckle assemblies for cracks.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, the proposed AD would
require removing any C628-4, revision M or prior, buckle assembly and
any A130-52 buckle assembly spacer, and replacing them with a C628-4,
revision N buckle assembly and a new A130-52 buckle assembly spacer.
Replacing the buckle assembly and buckle assembly spacer with a C628-4,
Revision N buckle assembly and a new A130-52 buckle assembly spacer
would be the terminating action for the requirements of this proposed
AD. The replacement would be required to be accomplished by following
specified portions of the service bulletin described previously.
We estimate that this proposed AD would affect 900 helicopters of
U.S. registry, and replacing a buckle assembly would take approximately
0.2 work hour per buckle to accomplish at an average labor rate of $80
per work hour. Required parts would cost approximately $105 for each
C628-4, revision N buckle assembly, and $8.25 for each A130-52 buckle
assembly spacer. Based on these figures, the total cost impact of the
proposed AD on U.S. operators would be $517 for each helicopter, or
$465,300 for the entire fleet, assuming that four buckle assemblies and
buckle assembly spacers are replaced in each helicopter.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft economic
evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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.
[[Page 920]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Robinson Helicopter Company: Docket No. FAA-2006-26696; Directorate
Identifier 2006-SW-19-AD.
Applicability: Model R44 helicopters, through serial number (S/
N) 1576, and Model R44 II helicopters, through S/N 11107, with a
seat belt buckle assembly (buckle assembly) part number C628-4,
revision M or prior, installed, certificated in any category.
Compliance: Required within 100 hours time-in-service, unless
accomplished previously.
To prevent cracking in the buckle assembly stainless support
strap and failure of a seat belt, accomplish the following:
(a) Remove the buckle assembly and any A130-52 buckle assembly
spacer, and replace them with a C628-4, revision N buckle assembly
and a new A130-52 buckle assembly spacer, in accordance with the
Compliance Procedure, paragraph 3, in Robinson Helicopter Company
Service Bulletin SB-56, dated March 29, 2006. The new A130-52 buckle
assembly spacers have been redesigned to be slightly longer than the
previous A130-52 buckle assembly spacers, to reduce friction in the
joint.
Note: Inspecting the buckle assembly for cracks is not required
by this AD.
(b) Replacing the buckle assembly and buckle assembly spacer
with a C628-4, Revision N buckle assembly and a new A130-52 buckle
assembly spacer is a terminating action for the requirements of this
AD.
(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 Manager, Los Angeles Aircraft Certification Office, FAA,
ATTN: Venessa Stiger, Aviation Safety Engineer, 3960 Paramount
Blvd., Lakewood, California 90712-4137, telephone (562) 627-5337,
fax (562) 627-5210, for information about previously approved
alternative methods of compliance.
Issued in Fort Worth, Texas, on December 18, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 07-26 Filed 1-8-07; 8:45 am]
BILLING CODE 4910-13-M