[Federal Register Volume 75, Number 116 (Thursday, June 17, 2010)]
[Rules and Regulations]
[Pages 34354-34357]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-13139]
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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.
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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
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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:
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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
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[[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:
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Actions Compliance Procedures
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(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]
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