[Federal Register Volume 72, Number 72 (Monday, April 16, 2007)]
[Proposed Rules]
[Pages 18925-18927]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-7180]


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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 Models 150 and 
152 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 150 and 152 airplanes. 
This proposed AD would require replacing the rudder stop, rudder stop 
bumper, and attachment hardware with a new rudder stop modification 
kit. This proposed AD also requires replacing the safety wire with 
jamnuts. This proposed AD results from two accidents where the rudder 
was found in the over-travel position with the stop plate hooked over 
the stop bolt heads. We are proposing this AD to prevent the rudder 
from traveling past the normal travel limit and becoming jammed in the 
over-travel position. This condition could result in loss of control.

DATES: We must receive comments on this proposed AD by June 15, 2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    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, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4123; fax: (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-
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://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

    This AD results from two spin accidents involving Cessna Model 152 
airplanes where the rudder was found in the over-travel position with 
the stop plate hooked over the stop bolt heads.
    In the first accident, which occurred in Canada, a flight 
instructor and student pilot were unable to recover after performing a 
spin maneuver. When the airplane was inspected, the rudder was found 
jammed.
    In the second accident the rudder bumper was found to be installed 
incorrectly, which resulted in a rudder jam during an attempted spin 
recovery.
    Upon recovery of the airplanes after the accidents, both accident 
airplanes had their rudder stop plates hooked over the stop bolts. 
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, if not corrected, could result in loss of control.

[[Page 18926]]

Relevant Service Information

    We have reviewed the following Cessna Aircraft Company service 
information, dated January 22, 2001:
    <bullet> Service Bulletin SEB01-1;
    <bullet> Service Kit SK152-25; and
    <bullet> Service Kit SK152-24.
    The service information describes procedures for replacing the 
rudder stop, rudder stop bumper, and attachment hardware with a new 
rudder stop modification kit. The service information also describes 
the procedure for replacing the safety wire with jamnuts.

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 replacing the rudder stop, rudder stop bumper, and 
attachment hardware with a new rudder stop modification kit. This 
proposed AD also requires replacing the safety wire with jamnuts.

Costs of Compliance

    We estimate that this proposed AD would affect 18,670 airplanes in 
the U.S. registry.
    We estimate the following costs to do the proposed modification:

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                                                                                 Total cost per   Total cost on
                          Labor cost                              Parts cost        airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
4 work-hours x $80 per hour = $320...........................             $60             $380       $7,094,600
----------------------------------------------------------------------------------------------------------------

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.

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-2007-27747; Directorate 
Identifier 2007-CE-030-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 15, 2007.

Affected ADs

    (b) None.

Applicability

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

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             Models                                               Serial numbers
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(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) A-150L....................  A-1501001 through A-1501039.
(12) A-A150L...................  A-A1500001 through A-A1500009.

[[Page 18927]]

 
(13) F150F.....................  F150-0001 through F150-0067.
(14) F150G.....................  F150-0068 through F150-0219.
(15) F150H.....................  F150-0220 through F150-0389.
(16) F150J.....................  F150-0390 through F150-0529.
(17) F150K.....................  F15000530 through F15000658.
(18) F150L.....................  F15000659 through F15001143.
(19) F150M.....................  F15001144 through F15001428.
(20) FA150K....................  FA1500001 through FA1500081.
(21) FA150L....................  FA1500082 through FA1500261.
(22) FA150M....................  FA1500262 through FA1500336.
(23) 152.......................  15279406 through 15286033.
(24) A152......................  A1520735 through A1521049, A1500433, and 681.
(25) F152......................  F15201429 through F15201980.
(26) FA152.....................  FA1520337 through FA1520425.
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Unsafe Condition

    (d) This AD results from two accidents where the rudder was 
found in the over-travel position with the stop plate hooked over 
the stop bolt heads. We are issuing this AD to prevent the rudder 
from traveling past the normal travel limit and becoming jammed in 
the over-travel position. This condition could result in loss of 
control.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

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           Action                  Compliance            Procedures
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(1) For airplanes with a      Within the next 100   Follow Cessna
 forged bulkhead: Replace      hours time-in-        Aircraft Company
 the rudder stop, rudder       service (TIS) or 12   Service Bulletin
 stop bumper, and attachment   months after the      SEB01-1, and Cessna
 hardware with the new         effective date of     Aircraft Company
 rudder stop modification      this AD, whichever    Service Kit SK152-
 kit SK152-25; and replace     occurs first.         25, both dated
 safety wire with jamnuts.                           January 22, 2001.
(2) For airplanes with a      Within the next 100   Follow Cessna
 sheet metal bulkhead:         hours TIS or 12       Aircraft Company
 Replace the rudder stop,      months after the      Service Bulletin
 rudder stop bumper, and       effective date of     SEB01-1, and Cessna
 attachment hardware with      this AD, whichever    Aircraft Company
 the new rudder stop           occurs first.         Service Kit SK152-
 modification kit SK152-24;                          24, both dated
 and replace safety wire                             January 22, 2001.
 with jamnuts.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, FAA, ATTN: Gary Park, Aerospace Engineer, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4123; fax: (316) 946-4107, 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.

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 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-2007-27747; 
Directorate Identifier 2007-CE-030-AD.

    Issued in Kansas City, Missouri, on April 10, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-7180 Filed 4-13-07; 8:45 am]
BILLING CODE 4910-13-P