[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: [email protected].
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:
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Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
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1 work-hour x $80 per hour = $80........... Not applicable............... $80 $1,367,200
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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
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4 work-hours x $80 per hour = $320..................... $90 $410 $7,006,900
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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:
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Models Serial Nos.
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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) 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.
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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]]
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Actions Compliance Procedures
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(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.
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(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: [email protected], 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