[Federal Register Volume 71, Number 153 (Wednesday, August 9, 2006)]
[Proposed Rules]
[Pages 45454-45457]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-12946]


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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:

--------------------------------------------------------------------------------------------------------------------------------------------------------
           Labor cost                 Parts cost for both seats       Total cost per airplane for both seats         Total cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed fabrication and 
installation of a steel lock rod/bar:

----------------------------------------------------------------------------------------------------------------
                                                            Total cost per
           Labor cost            Parts cost for both seats   airplane for       Total cost on U.S. operators
                                                              both seats
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed installation 
inspection on airplanes that have Modification Kit MK172-25-10A 
installed:

------------------------------------------------------------------------
                                                          Total cost per
             Labor cost              Parts cost for both   airplane for
                                            seats           both seats
------------------------------------------------------------------------
1 work-hour x $80 an hour = $80 for  Not applicable.....             $80
 both crew seats.
------------------------------------------------------------------------

    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.
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

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:

----------------------------------------------------------------------------------------------------------------
               Action                              Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    (2) Airplanes that have Modification Kit MK172-25-10A installed:

----------------------------------------------------------------------------------------------------------------
               Action                              Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------


    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