Airworthiness Directives; Cessna Aircraft Company Model 525A Airplanes, 34354-34357 [2010-13139]
Download as PDF
<![CDATA[
34354
Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations
TABLE 6—MATERIAL INCORPORATED BY REFERENCE
AFM/POM name
AFM effective pages list
MU–2B–25 Airplane Flight Manual K Model, Document Number MR–
0156–1, MU–2B–25; MU–2B–25 Pilot’s Operating Manual, Document
Number MR–0157–1, revised July 15, 2004.
MU–2B–26 Airplane Flight Manual M Model, Document Number MR–
0160–1; MU–2B–26 Pilot’s Operating Manual, Document Number
MR–0161–1, revised July 15, 2004.
MU–2B–26A Airplane Flight Manual P Model, Document Number MR–
0194–1; MU–2B–26A Pilot’s Operating Manual, Document Number
MR–0195–1, revised July 15, 2004.
MU–2B–36A Airplane Flight Manual N Model, Document Number MR–
0196–1; MU–2B–36A Pilot’s Operating Manual, Document Number
MR–0197–1, revised July 15, 2004.
MU–2B–40 Airplane Flight Manual SOLITAIRE Model, Document Number MR–0271–1; MU–2B–40 Pilot’s Operating Manual, Document
Number MR–0335–1, revised July 15, 2004.
MU–2B–60 Airplane Flight Manual MARQUISE Model, Document Number MR–0273–1; MU–2B–60 Pilot’s Operating Manual, Document
Number MR–0338–1, revised July 15, 2004.
MU–2B Airplane Flight Manual, YET 67026A; MU–2B Pilot’s Operating
Manual, Document Number YET 67025A, revised September 10,
1997.
MU–2B–10 Airplane Flight Manual, YET 86400; MU–2B–10 Pilot’s Operating Manual, Document Number YET 87236, revised September
10, 1997.
MU–2B–15 Airplane Flight Manual, YET 68038A; MU–2B–15 Pilot’s
Operating Manual, Document Number YET 87237, revised September 10, 1997.
MU–2B–20 Airplane Flight Manual, YET 68034A; MU–2B–20 Pilot’s
Operating Manual, Document Number YET 68134A, revised February 20, 1998.
MU–2B–25 Airplane Flight Manual, YET 71367A; MU–2B–25 Pilot’s
Operating Manual, Document Number YET 72067A, revised September 10, 1997.
MU–2B–26 Airplane Flight Manual, YET 74129A; MU–2B–26 Pilot’s
Operating Manual, Document Number YET 74130A, revised September 10, 1997.
MU–2B–30 Airplane Flight Manual, YET 69013A; MU–2B–30 Pilot’s
Operating Manual, Document Number YET 69224A, revised September 10, 1997.
MU–2B–35 Airplane Flight Manual, YET 70186A; MU–2B–10 Pilot’s
Operating Manual, Document Number YET 70187A, revised September 10, 1997.
MU–2B–36 Airplane Flight Manual, YET 74122A; MU–2B–36 Pilot’s
Operating Manual, Document Number YET 74123A, revised September 10, 1997.
all revised pages up to and including revision 11, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 11, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 15, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 15, dated March
2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 14, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 14, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
all revised pages up to and including revision 13, dated November
2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in
AFM.
Issued in Kansas City, Missouri on May 4,
2010.
Wes Ryan,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2010–11034 Filed 6–16–10; 8:45 am]
[Docket No. FAA–2010–0327; Directorate
Identifier 2010–CE–012–AD; Amendment
39–16321; AD 2010–12–01]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
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
VerDate Mar<15>2010
14:49 Jun 16, 2010
Jkt 220001
PO 00000
Frm 00036
Fmt 4700
Sfmt 4700
10,
the
10,
the
10,
the
10,
the
10,
the
10,
the
29,
the
29,
the
29,
the
29,
the
29,
the
29,
the
29,
the
29,
the
29,
the
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
E:\FR\FM\17JNR1.SGM
17JNR1
Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations
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: https://
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 https://
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
34355
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):
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
1 work-hour × $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:
Labor cost
Parts cost for
two fasteners
Total cost per
airplane
2 work-hours × $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 paddle)
Total cost per
airplane
3 work-hours × $85 per hour = $255 ..............................................................................................................
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Labor cost
$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:
Labor cost
Parts cost
Total cost per
airplane
Total cost on
U.S. operators
5 work-hours × $85 per hour = $425 ..........................................................................................
$3,464
$3,889
$528,904
VerDate Mar<15>2010
14:49 Jun 16, 2010
Jkt 220001
PO 00000
Frm 00037
Fmt 4700
Sfmt 4700
E:\FR\FM\17JNR1.SGM
17JNR1
34356
Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations
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.
§ 39.13
[Amended]
2. The FAA amends § 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.
List of Subjects in 14 CFR Part 39
Applicability
(c) This AD applies to Model 525A
airplanes, serial numbers 0001 through 0244,
that are certificated in any category.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Subject
(d) Air Transport Association of America
(ATA) Code 72: Engine.
Adoption of the Amendment
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 inflight departure of the thrust attenuator
paddles. This failure could lead to rudder
and elevator damage and result in loss of
control.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
Compliance
(f) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Visually inspect the left and right thrust attenuator paddle assemblies to determine if
there are any missing, loose, or damaged
fasteners and to determine if there are any
cracks in the paddle.
Within the next 60 days after December 15,
2009 (the effective date retained from AD
2009–24–13) or within the next 30 hours
time-in-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.
Before further flight after the inspection required in paragraph (f)(1) of this AD. Continue with the repetitive inspections specified in paragraph (f)(1) of this AD.
Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
Before further flight after the inspection required in paragraph (f)(1) of this AD in
which cracks are found.
Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
(2) If you do not find any cracks in the thrust attenuator paddles during any inspection required in paragraph (f)(1) of this AD, install
any missing fasteners, and replace any loose
or damaged fasteners.
(3) If cracks are found during any inspection required in paragraph (f)(1) of this AD, do a
surface eddy current inspection of the thrust
attenuator paddles and the fastener hole(s)
to determine the length of the cracks(s).
VerDate Mar<15>2010
14:49 Jun 16, 2010
Jkt 220001
PO 00000
Frm 00038
Fmt 4700
Sfmt 4700
Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
E:\FR\FM\17JNR1.SGM
17JNR1
Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations
34357
Actions
Compliance
Procedures
(4) If the cracks identified in paragraph (f)(3) of
this AD meet or exceed the limits specified in
paragraph 3 of Cessna Citation Alert Service
Letter ASL525A–78–01, Revision 1, dated
October 27, 2009, replace the thrust attenuator paddle and attachment hardware, as applicable.
(i) If the conditions of paragraph 3.A.(1) of
Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009, are met, replace before further 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–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.
Within the next 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.
Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
(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: https://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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
(5) Replace both thrust attenuator paddles .......
(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.
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
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.
VerDate Mar<15>2010
14:49 Jun 16, 2010
Jkt 220001
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
PO 00000
Follow Cessna Citation Service Bulletin
SB525A–78–02, Revision 1, dated February
5, 2010.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0170; Directorate
Identifier 2009–NM–127–AD; Amendment
39–16328; AD 2010–12–07]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135ER,
–135KE, –135KL, and –135LR
Airplanes; and EMBRAER Model
EMB–145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Reassessment of the damage tolerance
analysis resulted in threshold reduction for
some Structure Significant Items (SSI) of the
Maintenance Review Board Report (MRBR)
Airworthiness Limitations Items (ALI).
Failure to inspect these structural
components, according to the new threshold,
could prevent a timely detection of fatigue
cracking. These cracks, if not properly
Frm 00039
Fmt 4700
Sfmt 4700
E:\FR\FM\17JNR1.SGM
17JNR1
]]>Agencies
[Federal Register Volume 75, Number 116 (Thursday, June 17, 2010)]
[Rules and Regulations]
[Pages 34354-34357]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-13139]
-----------------------------------------------------------------------
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: https://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
https://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:
https://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: https://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
