[Federal Register Volume 74, Number 156 (Friday, August 14, 2009)]
[Proposed Rules]
[Pages 41096-41099]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-19498]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27747; Directorate Identifier 2007-CE-030-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company 150 and 152 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to revise Airworthiness Directive (AD) 2009-10-09, 
which applies to certain Cessna Aircraft Company (Cessna) 150 and 152 
series airplanes. AD 2009-10-09 requires either installing a placard 
prohibiting spins and other acrobatic maneuvers in the airplane or 
replacing the rudder stop, the rudder stop bumper, and the attachment 
hardware with a new rudder stop modification kit and replacing the 
safety wire with jamnuts. Since we issued AD 2009-10-09, we became 
aware of a need to clarify certain model and serial number 
designations, remove the duplicate requirement of replacing the safety 
wire with jamnuts, and clarify the conditional acceptability of using 
Modification Kit part number (P/N) SK152-25 as a terminating action to 
this proposed AD. Consequently, this proposed AD would retain the 
actions currently required in AD 2009-10-09, correct model designation 
for certain serial numbers, remove the duplicate requirement of 
replacing safety wire with jamnuts, and clarify the conditional 
acceptability of using Modification Kit P/N SK152-25 as a terminating 
action to this proposed AD. We are proposing this AD to prevent the 
rudder from traveling past the normal travel limit. Operation in this 
non-certificated control position is unacceptable and could cause 
undesirable consequences, such as contact between the rudder and the 
elevator.

DATES: We must receive comments on this proposed AD by September 28, 
2009.

[[Page 41097]]


ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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) 517-7271; Internet: http://www.cessna.com.

FOR FURTHER INFORMATION CONTACT: Ann Johnson, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4105; fax: (316) 946-4107; 
e-mail: ann.johnson@faa.gov.

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-
2007-27747; Directorate Identifier 2007-CE-030-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://www.regulations.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

    Investigations of two spin accidents involving Cessna Model 152 
airplanes revealed the rudder was found in the over-travel position 
with the stop plate hooked over the stop bolt heads. After examining 
the accident airplanes and other Cessna Models 150 and 152 airplanes, 
accident investigators determined that, under certain conditions, it is 
possible to jam the rudder past its normal travel limit. The jam occurs 
when the stop plate is forced aft of the stop bolt head. The forward 
edge of the stop plate can then become lodged under the head of the 
stop bolt causing the rudder to jam in this over-travel position. 
Recovery from a spin may not be possible with the rudder jammed beyond 
the normal rudder travel stop limits. This condition caused us to issue 
AD 2009-10-09, Amendment 39-15904 (74 FR 22429, May 13, 2009) on 
certain Cessna 150 and 152 series airplanes. AD 2009-10-09 currently 
requires the following:
     Installing a placard prohibiting spins and other acrobatic 
maneuvers in the airplane; or
     Replacing the rudder stop, the rudder stop bumper, and the 
attachment hardware with a new rudder stop modification kit; and
     Replacing the safety wire with jamnuts.
    Since we issued AD 2009-10-09, we became aware of a need to clarify 
certain model and serial number designations and to remove the 
duplicate requirement to replace safety wire with jamnuts since this 
procedure is already included in the modification kit instructions. We 
also became aware of a need to clarify the conditional acceptability of 
using Modification Kit P/N S152-25 as a terminating action to this 
proposed AD.
    This condition, if not corrected, could cause contact between the 
rudder and the elevator and result in loss of control.

Relevant Service Information

    The service information referenced in AD 2009-10-09 is still 
applicable for this proposed AD.

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 revise AD 2009-10-09 with a new AD that would retain the actions 
currently required in AD 2009-10-09, correct model designation for 
certain serial numbers, remove the duplicate requirement to replace the 
safety wire with jamnuts, and clarify the conditional acceptability of 
using the P/N SK152-25 kit as a terminating action to this proposed AD. 
This proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    We estimate that this AD affects 17,090 airplanes in the U.S. 
registry.
    We estimate the following costs to do the proposed insertion of the 
operational limitation:

----------------------------------------------------------------------------------------------------------------
                                                                             Total cost  per     Total cost on
                 Labor cost                            Parts cost                airplane        U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 per hour = $80...........  Not applicable...............               $80         $1,367,200
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed modification:

----------------------------------------------------------------------------------------------------------------
                                                                              Total cost per     Total cost on
                       Labor cost                            Parts cost          airplane        U.S. operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $80 per hour = $320.....................               $90               $410         $7,006,900
----------------------------------------------------------------------------------------------------------------

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

[[Page 41098]]

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.

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://www.regulations.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, Incorporation by 
reference, 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 removing Airworthiness Directive 
(AD) 2009-10-09, Amendment 39-15904 (74 FR 22429, May 13, 2009), and 
adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2007-27747; Directorate 
Identifier 2007-CE-030-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by September 28, 2009.

Affected ADs

    (b) This AD revises AD 2009-10-09, Amendment 39-15904.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                     Models                             Serial Nos.
------------------------------------------------------------------------
(1) 150F........................................  15061533 through
                                                   15064532.
(2) 150G........................................  15064533 through
                                                   15064969 and 15064971
                                                   through 15067198.
(3) 150H........................................  15067199 through
                                                   15069308 and 649.
(4) 150J........................................  15069309 through
                                                   15071128.
(5) 150K........................................  15071129 through
                                                   15072003.
(6) 150L........................................  15072004 through
                                                   15075781.
(7) 150M........................................  15075782 through
                                                   15079405.
(8) A150K.......................................  A1500001 through
                                                   A1500226.
(9) A150L.......................................  A1500227 through
                                                   A1500432 and A1500434
                                                   through A1500523.
(10) A150M......................................  A1500524 through
                                                   A1500734 and
                                                   15064970.
(11) F150F......................................  F150-0001 through F150-
                                                   0067.
(12) F150G......................................  F150-0068 through F150-
                                                   0219.
(13) F150H......................................  F150-0220 through F150-
                                                   0389.
(14) F150J......................................  F150-0390 through F150-
                                                   0529.
(15) F150K......................................  F15000530 through
                                                   F15000658.
(16) F150L......................................  F15000659 through
                                                   F15001143.
(17) F150M......................................  F15001144 through
                                                   F15001428.
(18) FA150K.....................................  FA1500001 through
                                                   FA1500081.
(19) FA150L.....................................  FA1500082 through
                                                   FA1500120.
(20) FA150L or FRA150L..........................  FA1500121 through
                                                   FA1500261 that are
                                                   equipped with FKA150-
                                                   2311 and FKA150-2316,
                                                   or FRA1500121 through
                                                   FRA1500261.
(21) FA150M or FRA150M..........................  FA1500262 through
                                                   FA1500336 that are
                                                   equipped with FKA150-
                                                   2311 and FKA150-2316,
                                                   or FRA1500262 through
                                                   FRA1500336.
(22) 152........................................  15279406 through
                                                   15286033.
(23) A152.......................................  A1520735 through
                                                   A1521049, A1500433,
                                                   and 681.
(24) F152.......................................  F15201429 through
                                                   F15201980.
(25) FA152......................................  FA1520337 through
                                                   FA1520425.
------------------------------------------------------------------------


    Note: This AD revision clarifies the applicability of AD 2009-
10-09, eliminates a duplicate requirement for replacement of safety 
wire with jamnuts, and clarifies the intent of the conditional 
acceptability of using Modification Kit P/N SK152-25 as a 
terminating requirement to the AD. No further action is required for 
those already in compliance with AD 2009-10-09.

Unsafe Condition

    (d) Aircraft in full conformity with type design can exceed the 
travel limits set by the rudder stops. We are issuing this AD to 
prevent the rudder from traveling past the normal travel limit. 
Operation in this non-certificated control position is unacceptable 
and could cause undesirable consequences, such as contact between 
the rudder and the elevator.

Compliance

    (e) To address this problem, you must do either the actions in 
option 1 or option 2 of this AD, unless already done:

[[Page 41099]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Option 1: For all         Within the next 100   A person authorized
 airplanes that do not have    hours time-in-        to perform
 modification kits part        service (TIS) after   maintenance as
 number (P/N) SK152-25A or P/  June 17, 2009 (the    specified in 14 CFR
 N SK152-24A installed, do     effective date        section 43.3 of the
 the following:                retained from AD      Federal Aviation
(i) Insert the following       2009-10-09), or       Administration
 text into the Limitations     within the next 12    Regulations (14 CFR
 section of the FAA-approved   months after June     43.3) is required
 airplane flight manual        17, 2009 (the         to make the AFM and
 (AFM), and pilots operating   effective date        POH changes,
 handbook (POH):               retained from AD      fabricate the
 ``INTENTIONAL SPINS AND       2009-10-09),          placard required in
 OTHER ACROBATIC/AEROBATIC     whichever occurs      paragraph (e)(1)(i)
 MANEUVERS PROHIBITED PER AD   first.                of this AD, and
 2009-10-09. NOTE: THIS AD                           make an entry into
 DOES NOT PROHIBIT                                   the aircraft
 PERFORMING INTENTIONAL                              logbook showing
 STALLS''.                                           compliance with the
                                                     portion of the AD
                                                     per compliance with
                                                     14 CFR 43.9.
    (ii) Fabricate a placard
     (using at least \1/8\-
     inch letters) with the
     following words and
     install the placard on
     the instrument panel
     within the pilot's
     clear view:
     ``INTENTIONAL SPINS AND
     OTHER ACROBATIC/
     AEROBATIC MANEUVERS
     PROHIBITED PER AD 2009-
     10-09.''
    (iii) The AFM and POH
     limitations in
     paragraph (e)(1)(i) of
     the AD and the placard
     in paragraph (e)(1)(ii)
     of this AD may be
     removed after either
     paragraph (e)(2)(i) or
     paragraph (e)(2)(ii) of
     this AD is done.
(2) Option 2: Install a       Within the next 100   Follow Cessna
 rudder stop modification      hours TIS after       Aircraft Company
 kit:                          June 17, 2009 (the    Service Bulletin
(i) For airplanes with a       effective date        SEB01-1, dated
 forged bulkhead, replace      retained from AD      January 22, 2001;
 the rudder stops, rudder      2009-10-09), or       and, as applicable,
 stop bumpers, and             within the next 12    either Cessna
 attachment hardware with      months after June     Aircraft Company
 the new rudder stop           17, 2009 (the         Service Kit SK152-
 modification kit P/N SK152-   effective date        25A, Revision A,
 25A, which includes           retained from AD      dated February 9,
 replacing the safety wire     2009-10-09),          2001, or Cessna
 with jamnuts.                 whichever occurs      Aircraft Company
                               first.                Service Kit SK152-
                                                     24A, Revision A,
                                                     dated March 9,
                                                     2001.
    (ii) For airplanes with
     a sheet metal bulkhead,
     replace the rudder
     stops, rudder stop
     bumpers, and attachment
     hardware with the new
     rudder stop
     modification kit P/N
     SK152-24A, which
     includes replacing the
     safety wire with
     jamnuts.
------------------------------------------------------------------------

    (f) Kit P/Ns SK152-24 and SK152-25, which are listed in SEB01-1, 
were superseded by kit P/Ns SK152-24A and SK152-25A. Cessna has not 
revised the service bulletin to reflect the new P/Ns. The kits P/Ns 
SK152-24 and SK152-25 will automatically be filled with P/Ns SK152-
24A and SK152-25A, respectively.
    (1) The P/N SK152-24 kit does not address the unsafe condition 
because the nutplate in the kit can not be used due to rivet spacing 
on the aft bulkhead. In addition, a note was added to kit P/N SK152-
24A stating ``some airplanes in this serial range may have a forged 
bulkhead installed after leaving the factory. Service Kit SK152-25A 
or later revision must be used to modify these airplanes.'' 
Therefore, kit P/N SK152-24 is not allowed for installation for this 
AD.
    (2) The P/N SK152-25 kit did not address the unsafe condition 
because a washer that was too small, P/N NAS1149FN832P, was included 
in the kit. This error was corrected in the P/N SK152-25A kit. If a 
P/N SK152-25 kit is installed using the correct washer P/N 
NAS1149F0332P (and this information is recorded in the maintenance 
log), credit will be given for installing P/N SK152-25A kit because 
this was the only difference between the kits.
    (3) If you previously installed a kit P/N SK152-24 or a kit P/N 
SK152-25 with washer P/N NAS1149FN832P, and you choose the Option 2 
kit installation to comply with this AD, then kit P/N SK152-24A or 
either kit P/N SK152-25 with washer P/N NAS1149F0332P or kit P/N 
SK152-25A, as applicable, must be installed.
    (4) If a P/N SK152-25 kit was installed prior to this AD and the 
washer P/N used in the installation is unknown (not recorded in the 
maintenance log), and you wish to use Option 2 to comply with this 
AD, the washer installed in place of P/N NAS1149F0332P must be 
replaced with a washer P/N NAS1149F0332P, and this work must be 
recorded in the maintenance log.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, FAA, ATTN: Ann Johnson, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Wichita, Kansas 67209; telephone: (316) 946-4105; fax: (316) 
946-4107; e-mail: ann.johnson@faa.gov, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. Before using any approved AMOC on any airplane to which the 
AMOC applies, notify your appropriate principal inspector (PI) in 
the FAA Flight Standards District Office (FSDO), or lacking a PI, 
your local FSDO.
    (h) AMOCs approved for AD 2009-10-09 are approved for this AD.

Related Information

    (i) 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) 517-7271; 
Internet: http://www.cessna.com. To view the AD docket, go to U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC 20590, or on the Internet at http://www.regulations.gov.

    Issued in Kansas City, Missouri, on August 7, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-19498 Filed 8-13-09; 8:45 am]
BILLING CODE 4910-13-P