
[Federal Register: June 17, 2010 (Volume 75, Number 116)]
[Rules and Regulations]               
[Page 34354-34357]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17jn10-9]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0327; Directorate Identifier 2010-CE-012-AD; 
Amendment 39-16321; AD 2010-12-01]
RIN 2120-AA64

 
Airworthiness Directives; Cessna Aircraft Company Model 525A 
Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) to 
supersede 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 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

[[Page 34355]]

rivets. 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.

DATES: This AD becomes effective on July 22, 2010.
    On July 22, 2010, the Director of the Federal Register approved the 
incorporation by reference of Cessna Citation Service Bulletin SB525A-
78-02, Revision 1, dated February 5, 2010, listed in this AD.
    As of December 15, 2009 (74 FR 62479, November 30, 2009), the 
Director of the Federal Register approved the incorporation by 
reference of Cessna Citation Alert Service Letter ASL525A-78-01, 
Revision 1, dated October 27, 2009, listed in this AD.

ADDRESSES: For service information identified 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. The docket number is FAA-2010-0327; 
Directorate Identifier 2010-CE-012-AD.

FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, 
Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 
100, Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-
4107.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 23, 2010, we issued a proposal to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) to include an AD that 
would apply to certain Cessna Model 525A airplanes. This proposal was 
published in the Federal Register as a notice of proposed rulemaking 
(NPRM) on March 30, 2010 (75 FR 15629). The NPRM proposed to supersede 
AD 2009-24-13 with a new AD that 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.

Comments

    We provided the public the opportunity to participate in developing 
this AD. We received no comments on the proposal or on the 
determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. We have determined that these 
minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    We estimate that this AD affects 136 airplanes in the U.S. 
registry.
    We estimate the following costs to do the 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 will be 
required based on the results of the 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 will be required based on the results of the 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 replacement of both 
thrust attenuator paddles and the eight countersunk fasteners with new 
design thrust attenuator paddles and universal head rivets:

----------------------------------------------------------------------------------------------------------------
                                                                                 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
----------------------------------------------------------------------------------------------------------------


[[Page 34356]]

    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 AD.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    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 summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2010-0327; Directorate Identifier 2010-CE-012-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
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:

2010-12-01 Cessna Aircraft Company: Amendment 39-16321; Docket No. 
FAA-2010-0327; Directorate Identifier 2010-CE-012-AD.

Effective Date

    (a) This AD becomes effective on July 22, 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        ASL525A-78-01,
 there are any missing,        retained from AD      Revision 1, dated
 loose, or damaged fasteners   2009-24-13) or        October 27, 2009.
 and to determine if there     within the next 30
 are any cracks in the         hours time-in-
 paddle.                       service (TIS) after
                               December 15, 2009
                               (the effective date
                               retained from AD
                               2009-24-13),
                               whichever occurs
                               first. Repetitively
                               thereafter inspect
                               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 34357]]


(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 ASL525A-78-    October 27, 2009.
 Letter ASL525A-78-01,         01, Revision 1,
 Revision 1, dated October     dated October 27,
 27, 2009, replace the         2009, are met,
 thrust attenuator paddle      replace before
 and attachment hardware, as   further flight
 applicable.                   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-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       Citation Service
                               July 22, 2010 (the    Bulletin SB525A-78-
                               effective date of     02, Revision 1,
                               this AD), or within   dated February 5,
                               1 year after July     2010.
                               22, 2010 (the
                               effective date of
                               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 after July 22, 2010 (the effective date of this AD), 
or within 1 year after July 22, 2010 (the effective date of this 
AD), whichever occurs first.
    (h) If, before July 22, 2010 (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: T.N. Baktha, Aerospace Engineer, Wichita 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.

Material Incorporated by Reference

    (l) You must use Cessna Citation Alert Service Letter ASL525A-
78-01, Revision 1, dated October 27, 2009, and Cessna Citation 
Service Bulletin SB525A-78-02, Revision 1, dated February 5, 2010, 
to do the actions required by this AD, unless the AD specifies 
otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Cessna Citation Service Bulletin 
SB525A-78-02, Revision 1, dated February 5, 2010, under 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) On December 15, 2009 (74 FR 62479, November 30, 2009), the 
Director of the Federal Register approved the incorporation by 
reference of Cessna Citation Alert Service Letter ASL525A-78-01, 
Revision 1, dated October 27, 2009.
    (3) For service information identified 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.
    (4) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (5) You may also review copies of the service information 
incorporated by reference for this AD at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Kansas City, Missouri, on May 26, 2010.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-13139 Filed 6-16-10; 8:45 am]
BILLING CODE 4910-13-P

