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[Federal Register: March 30, 2010 (Volume 75, Number 60)]
[Proposed Rules]               
[Page 15629-15632]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30mr10-21]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0327; Directorate Identifier 2010-CE-012-AD]
RIN 2120-AA64

 
Airworthiness Directives; Cessna Aircraft Company Model 525A 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2009-24-
13, which applies to certain Cessna Aircraft Company (Cessna) Model 
525A airplanes. AD 2009-24-13 currently requires you to repetitively 
inspect the thrust attenuator paddle assemblies for loose and damaged 
fasteners and for cracks. AD 2009-24-13 also requires you to replace 
loose or damaged fasteners and replace cracked thrust attenuator 
paddles found during any inspection. Since we issued AD 2009-24-13, 
Cessna has developed new design thrust attenuator paddles and universal 
head rivets as terminating action for the repetitive inspections. 
Consequently, this proposed AD would retain the requirements of AD 
2009-24-13 until replacement of both thrust attenuator paddles and the 
eight countersunk fasteners with new design thrust attenuator paddles 
and universal head rivets. We are proposing this AD to detect and 
correct loose and damaged fasteners and cracks in the thrust attenuator 
paddles, which could result in in-flight departure of the thrust 
attenuator paddles. This failure could lead to rudder and elevator 
damage and result in loss of control.

DATES: We must receive comments on this proposed AD by May 14, 2010.

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) 517-6000; fax: (316) 517-8500; Internet: http://www.cessna.com.

FOR FURTHER INFORMATION CONTACT: TN Baktha, Aerospace Engineer, ACE-
118W, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, 
Room 100, Wichita, Kansas 67209; telephone: (316) 946-4155; 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

[[Page 15630]]

number, ``FAA-2010-0327; Directorate Identifier 2010-CE-012-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

    Reports of fatigue cracks found in thrust attenuator paddles on 
Cessna Model 525A airplanes caused us to issue AD 2009-24-13, Amendment 
39-16105 (74 FR 62479, November 30, 2009). AD 2009-24-13 currently 
requires the following on Cessna Model 525A airplanes:
     Inspect repetitively the thrust attenuator paddle 
assemblies for loose and damaged fasteners and for cracks; and
     replace loose or damaged fasteners and replace cracked 
thrust attenuator paddles found during any inspection.
    Four incidents of thrust attenuator paddles departing from 
airplanes have been reported. In two cases, the thrust attenuator 
paddles hit the rudder and caused structural damage to the rudder.
    The thrust attenuator paddles are attached to the aft fuselage. The 
attachment fasteners fatigue and break.
    It is also possible that a failed thrust attenuator paddle could 
depart the airplane and hit and damage the elevator.
    We considered AD 2009-24-13 an interim action while Cessna 
developed a design improvement to change the attachment fasteners from 
the currently used counter sunk rivets to universal head rivets. Since 
we issued AD 2009-24-13, Cessna has developed new design thrust 
attenuator paddles and universal head rivets to replace the old design 
thrust attenuator paddle assemblies and the counter sunk fasteners.
    This condition, if not corrected, could result in in-flight 
departure of the thrust attenuator paddles. This failure could lead to 
rudder and elevator damage and result in loss of control.

Relevant Service Information

    We have reviewed:
     Cessna Citation Alert Service Letter ASL525A-78-01, 
Revision 1, dated October 27, 2009;
     Cessna Citation Service Bulletin SB525A-78-02, dated 
November 13, 2009, and
     Cessna Citation Service Bulletin SB525A-78-02, Revision 1, 
dated February 5, 2010.
    Cessna Citation Alert Service Letter ASL525A-78-01 describes 
procedures for inspecting and modifying the thrust attenuator paddle 
assemblies.
    Cessna Citation Service Bulletin SB525A-78-02 describes procedures 
for replacing the thrust attenuator paddles and attachment hardware.

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 supersede AD 2009-24-13 with a new AD that would retain the 
requirements of AD 2009-24-13 until you replace both thrust attenuator 
paddles and the eight countersunk fasteners with new design thrust 
attenuator paddles and universal head rivets. This proposed AD would 
require you to use the service information described previously to 
perform these actions.

Costs of Compliance

    We estimate that this proposed AD would affect 136 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed inspection 
(retained from AD 2009-24-13):

----------------------------------------------------------------------------------------------------------------
                                                                              Total cost per     Total cost on
                Labor cost                            Parts cost                 airplane        U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85..........  Not Applicable................               $85            $11,560
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do any necessary installation 
(retained from AD 2009-24-13) of missing/damaged fasteners that would 
be required based on the results of the proposed inspection. We have no 
way of determining the number of airplanes that may need this 
replacement:

------------------------------------------------------------------------
                                      Parts cost for     Total cost per
            Labor cost                two fasteners         airplane
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170            $99.90            $269.90
------------------------------------------------------------------------

     We estimate the following costs to do any necessary replacement 
(retained from AD 2009-24-13) of a cracked thrust attenuator paddle 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that may need 
this replacement:

------------------------------------------------------------------------
                                     Parts cost (per     Total cost per
            Labor cost                   paddle)            airplane
------------------------------------------------------------------------
3 work-hours x $85 per hour = $255            $1,200             $1,455
------------------------------------------------------------------------

     We estimate the following costs to do the proposed replacement of 
both thrust attenuator paddles and the eight countersunk fasteners with 
new design thrust attenuator paddles and universal head rivets:

[[Page 15631]]



----------------------------------------------------------------------------------------------------------------
                                                                              Total cost per     Total cost on
                       Labor cost                            Parts cost          airplane        U.S. operators
----------------------------------------------------------------------------------------------------------------
5 work-hours x $85 per hour = $425.....................            $3,464             $3,889           $528,904
----------------------------------------------------------------------------------------------------------------

     As determined by the manufacturer, eligible airplanes may qualify 
for warranty coverage of parts and labor.

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://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) 647-5527) 
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) 2009-24-13, Amendment 39-16105 (74 FR 62479, November 30, 2009), 
and adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2010-0327; Directorate 
Identifier 2010-CE-012-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by May 14, 2010.

Affected ADs

    (b) This AD supersedes AD 2009-24-13, Amendment 39-16105.

Applicability

    (c) This AD applies to Model 525A airplanes, serial numbers 0001 
through 0244, that are certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 72: Engine.

Unsafe Condition

    (e) This AD results from reports of fatigue cracks found in 
thrust attenuator paddles on Cessna Model 525A airplanes. We are 
issuing this AD to detect and correct loose and damaged fasteners 
and cracks in the thrust attenuator paddles, which could result in 
in-flight departure of the thrust attenuator paddles. This failure 
could lead to rudder and elevator damage and result in loss of 
control.

Compliance

    (f) To address this problem, you must do the following, unless 
already done:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Visually inspect the      Within the next 60    Follow Cessna
 left and right thrust         days after December   Citation Alert
 attenuator paddle             15, 2009 (the         Service Letter
 assemblies to determine if    effective date of     ASL525A-78-01,
 there are any missing,        AD 2009-24-13) or     Revision 1, dated
 loose, or damaged fasteners   within the next 30    October 27, 2009.
 and to determine if there     hours time-in-
 are any cracks in the         service (TIS) after
 paddle.                       December 15, 2009
                               (the effective date
                               of AD 2009-24-13),
                               whichever occurs
                               first. Repetitively
                               inspect thereafter
                               at intervals not to
                               exceed 150 hours
                               TIS.
(2) If you do not find any    Before further        Follow Cessna
 cracks in the thrust          flight after the      Citation Alert
 attenuator paddles during     inspection required   Service Letter
 any inspection required in    in paragraph (f)(1)   ASL525A-78-01,
 paragraph (f)(1) of this      of this AD.           Revision 1, dated
 AD, install any missing       Continue with the     October 27, 2009.
 fasteners, and replace any    repetitive
 loose or damaged fasteners.   inspections
                               specified in
                               paragraph (f)(1) of
                               this AD.
(3) If cracks are found       Before further        Follow Cessna
 during any inspection         flight after the      Citation Alert
 required in paragraph         inspection required   Service Letter
 (f)(1) of this AD, do a       in paragraph (f)(1)   ASL525A-78-01,
 surface eddy current          of this AD in which   Revision 1, dated
 inspection of the thrust      cracks are found.     October 27, 2009.
 attenuator paddles and the
 fastener hole(s) to
 determine the length of the
 cracks(s).

[[Page 15632]]


(4) If the cracks identified  (i) If the            Follow Cessna
 in paragraph (f)(3) of this   conditions of         Citation Alert
 AD meet or exceed the         paragraph 3.A.(1)     Service Letter
 limits specified in           of Cessna Citation    ASL525A-78-01,
 paragraph 3 of Cessna         Alert Service         Revision 1, dated
 Citation Alert Service        Letter                October 27, 2009.
 Letter ASL525A-78-01,         ASL525A[dash]78-01,
 Revision 1, dated October     Revision 1, dated
 27, 2009, replace the         October 27, 2009,
 thrust attenuator paddle      are met, replace
 and attachment hardware, as   before further
 applicable.                   flight after the
                               inspection required
                               in paragraph (f)(3)
                               of this AD. After
                               the replacement,
                               continue with the
                               repetitive
                               inspections
                               specified in
                               paragraph (f)(1) of
                               this AD.
                              (ii) If the
                               conditions of
                               paragraph 3.A.(2)
                               of Cessna Citation
                               Alert Service
                               Letter
                               ASL525A[dash]78-01,
                               Revision 1, dated
                               October 27, 2009,
                               are met, replace
                               within the next 150
                               hours TIS after the
                               inspection required
                               in paragraph (f)(3)
                               of this AD. After
                               the replacement,
                               continue with the
                               repetitive
                               inspections
                               specified in
                               paragraph (f)(1) of
                               this AD.
(5) Replace both thrust       Within the next 300   Follow Cessna
 attenuator paddles.           hours TIS after the   Citation Service
                               effective date of     Bulletin SB525A-78-
                               this AD or within 1   02, Revision 1,
                               year after the        dated February 5,
                               effective date of     2010.
                               this AD, whichever
                               occurs first.
------------------------------------------------------------------------

    (g) The replacement required in paragraph (f)(5) of this AD 
terminates the repetitive inspection requirement of this AD. This 
replacement may be done at anytime, but must be done no later than 
300 hours TIS or within 1 one after the effective date of this AD, 
whichever occurs first.
    (h) If, before the effective date of this AD, you have done all 
the actions in the original issue of Cessna Citation Service 
Bulletin SB525A-78-02, dated November 13, 2009, then no further 
action is required by this AD. This is considered ``unless already 
done'' credit for this AD action.

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: TN Baktha, Aerospace Engineer, ACE-118W, Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, 
Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-4107. 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.
    (j) AMOCs approved for AD 2009-24-13 are approved for this AD.

Related Information

    (k) 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) 517-6000; fax: (316) 517-8500; 
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 March 23, 2010.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-7024 Filed 3-29-10; 8:45 am]
BILLING CODE 4910-13-P
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