[Federal Register: August 9, 2006 (Volume 71, Number 153)]
[Proposed Rules]
[Page 45454-45457]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09au06-37]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25261; Directorate Identifier 2006-CE-38-AD]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 172R,
172S, 182S, 182T, T182T, 206H, and T206H Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T,
T182T, 206H, and T206H airplanes. This proposed AD would require you to
install Modification Kit MN172-25-10B or a steel lock rod/bar on both
crew seat back cylinder lock assemblies. If a steel lock rod/bar has
already been installed on the crew seat back cylinder lock assembly, no
further action is required. If Modification Kit MK172-25-10A has
previously been installed, this proposed AD would require you to do an
installation inspection and correct any discrepancies found. This
proposed AD results from reports of the crew seat back cylinder lock
assembly failing at the aft end and other cylinder lock assemblies
found cracked. We are proposing this AD to prevent the crew seat
cylinder lock assembly from bending, cracking, or failing. This failure
could cause uncontrolled movement of the seat back, resulting in
possible backward collapse during flight. Backward collapse of either
crew seat back could result in an abrupt pitch-up if the affected crew
member continues to hold on to the control yoke during this failure and
could cause difficulty in exiting the airplane from an aft passenger
seat after landing.
DATES: We must receive comments on this proposed AD by October 10,
2006.
ADDRESSES: Use one of the following addresses to comment 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
and 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 20590-0001.
Fax: (202) 493-2251.
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.
For service information identified in this proposed AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517-5800; fax: (316) 942-9006.
FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209; telephone: (316) 946-4123; facsimile:
(316) 946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-25261; Directorate Identifier 2006-CE-38-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 we
receive concerning this proposed AD.
Discussion
We have received reports of the crew seat back cylinder lock
bending at the aft end and failing. We have also received reports of
cracks found in the cylinder lock assembly.
This condition, if not corrected, could result in failure of the
crew seat back cylinder lock assembly. This failure could cause
uncontrolled movement of the seat back, resulting in possible backward
collapse during flight. Backward collapse of either crew seat back
could result in an abrupt pitch-up
[[Page 45455]]
if the affected crew member continues to hold on to the control yoke
during this failure and could cause difficulty in exiting the airplane
from an aft passenger seat after landing.
Relevant Service Information
We have reviewed Cessna Single Engine Service Bulletin SB04-25-01,
Revision 3, dated July 24, 2006.
This service bulletin describes procedures for installing
Modification Kit MK172-25-10B on both crew seat back cylinder lock
assemblies to replace the cylinder lock with a new model cylinder lock.
This service bulletin also described procedures for doing an
installation inspection on airplanes that have Modification Kit MK172-
25-10A installed following Cessna Single Engine Service Bulletin SB04-
25-01, Revision 2, dated June 5, 2006.
We have also reviewed Cessna Single Engine Service Bulletin SB04-
25-02 Revision 1, dated October 17, 2005, and Revision 2, dated June 5,
2006.
These service bulletins describe procedures for installing a steel
lock rod/bar on the crew seat to replace the crew seat back cylinder
lock assembly.
FAA's Determination and Requirements of the Proposed AD
We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would require you to install a modification kit on both crew seat back
cylinder lock assemblies, which replaces the cylinder lock with a new
model cylinder lock, or install a steel lock rod/bar on both crew seat
back cylinder lock assemblies.
Costs of Compliance
We estimate that this proposed AD would affect 4,039 airplanes in
the U.S. registry. We provide below total fleet costs for both the
proposed modification and the proposed steel lock rod/bar installation;
however, only one of these proposed actions would be required.
We estimate the following costs to do the proposed installation of
the modification kit:
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Labor cost Parts cost for both seats Total cost per airplane for both seats Total cost on U.S. operators
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3.5 work-hours x $80 an hour = $590 for each modification kit. $280 + $590 = $870. $870 x 4,039 = $3,513,930.
$280 for each modification kit. One modification kit required
for each airplane. Total parts
cost for both seats would be
$590.
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We estimate the following costs to do the proposed fabrication and
installation of a steel lock rod/bar:
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Total cost per
Labor cost Parts cost for both seats airplane for Total cost on U.S. operators
both seats
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1.5 work-hours x $80 an hour = Not applicable........... $240 $240 x 4,039 = $969,360
$120 for each crew seat. Total
labor cost for both seats
would be $240.
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We estimate the following costs to do the proposed installation
inspection on airplanes that have Modification Kit MK172-25-10A
installed:
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Total cost per
Labor cost Parts cost for both airplane for
seats both seats
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1 work-hour x $80 an hour = $80 for Not applicable..... $80
both crew seats.
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We have no method of determining the number of airplanes that may
have the previously installed Modification Kit MK172-25-10A.
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.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. 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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
[[Page 45456]]
Examining the AD Docket
You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at http://dms.dot.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5227)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
Cessna Aircraft Company: Docket No. FAA-2006-25261; Directorate
Identifier 2006-CE-38-AD.
Comments Due Date
(a) We must receive comments on this airworthiness directive
(AD) action by October 10, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial Nos.
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172R........................ 17280001 through 17281262.
172S........................ 172S8001 through 172S9994.
182S........................ 18280001 through 18280944.
182T........................ 18280945 through 18281701.
T182T....................... T18208001 through T18208453.
206H........................ 20608001 through 20608250.
T206H....................... T20608001 through T20608570.
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Unsafe Condition
(d) This AD results from reports of the crew seat back cylinder
lock assembly failing at the aft end area and other cylinder lock
assemblies found cracked. We are issuing this AD to prevent the crew
seat cylinder lock assembly from bending, cracking, or failing. This
failure could cause uncontrolled movement of the seat back,
resulting in possible backward collapse during flight. Backward
collapse of either crew seat back could result in an abrupt pitch-up
if the affected crew member continues to hold on to the control yoke
during this failure and could cause difficulty in exiting the
airplane from an aft passenger seat after landing.
Compliance
(e) To address this problem, you must do the following, unless
already done:
(1) Airplanes that do not have Modification Kit MK172-25-10A
installed:
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Action Compliance Procedures
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For each crew seat (pilot and For airplanes that have over 1,000 Follow Cessna Single Engine Service
copilot), install Modification Kit hours time-in-service (TIS) on the Bulletin SB04-25-01, Revision 3,
MK172-25-10B or fabricate and effective date of this AD, do the dated July 24, 2006, for installing
install a steel lock rod/bar. action within the next 4 months Modification Kit MK172-25-10B.
after the effective date of this AD. Follow Cessna Single Engine Service
For airplanes that have from 501 to Bulletin SB04-25-02 Revision 1,
1,000 hours TIS on the effective dated October 17, 2005, or Revision
date of this AD, do the action 2, dated June 5, 2006, for
within the next 8 months after the fabricating and installing a steel
effective date of this AD. lock rod/bar.
For airplanes that have from 0 to
500 hours TIS on the effective date
of this AD, do the action within
the next 12 months after the
effective date of this AD.
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(2) Airplanes that have Modification Kit MK172-25-10A installed:
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Action Compliance Procedures
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(i) For each crew seat (pilot and Within the next 30 days after the Follow Cessna Single Engine Service
copilot), do an installation effective date of this AD. Bulletin SB04-25-01, Revision 3,
inspection. dated July 24, 2006.
(ii) If you do not find any Before further flight after the Follow Cessna Single Engine Service
discrepancies during the inspection inspection required in paragraph Bulletin SB04-25-01, Revision 3,
required in paragraph (e)(2)(i) of (e)(2)(i) of this AD. dated July 24, 2006.
this AD, make a log book entry
showing compliance with this AD and
no further action is required.
(iii) If you find discrepancies Before further flight after the Follow Cessna Single Engine Service
during the inspection required in inspection required in paragraph Bulletin SB04-25-01, Revision 3,
paragraph (e)(2)(i) of this AD, (e)(2)(i) of this AD. dated July 24, 2006.
make all necessary corrective
actions.
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Note: Although not required by this AD, you may replace the
steel lock rod/bar with Modification Kit MK172-25-10B.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Wichita Aircraft Certification Office, FAA,
ATTN: Gary Park, Aerospace Engineer, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4123;
facsimile: (316) 946-4107, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Related Information
(g) To get copies of the service information referenced in this
AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706,
Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 942-9006.
To view the AD docket, go to the Docket Management
[[Page 45457]]
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC, or on the
Internet at http://dms.dot.gov. The docket number is Docket No. FAA-
2006-25261; Directorate Identifier 2006-CE-38-AD.
Issued in Kansas City, Missouri, on August 3, 2006.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-12946 Filed 8-8-06; 8:45 am]
BILLING CODE 4910-13-P