Airworthiness Directives; Cessna Aircraft Company Model 525A Airplanes, 15629-15632 [2010-7024]
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Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
although it resulted only in an
uncommanded IFSD, with no damage to the
aircraft, the possibility exists that additional
events may occur, potentially involving
damage to the aircraft.
To address the unsafe condition, EASA
issued AD 2009–0136, mandating inspection
of certain third stage turbine wheels and
removal of any damaged wheel. The wheels
to be inspected were those whose cycles
since new (CSN) would exceed 2,000 by
February 1, 2011. Following additional
research by Turbomeca on crack initiation
and growth, this AD mandates inspections
based on new criteria and removal of any
damaged wheel.
We are issuing this AD to prevent
uncontained failures of the third stage
turbine wheel, which could result in damage
to the helicopter.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) For any affected third stage turbine
wheel that on the effective date of this AD
has accumulated fewer than 500 cycles-sincelast-overhaul or repair, or since-new if the
engine has never been overhauled or
repaired:
(i) Within 300 additional cycles, perform a
dye penetrant inspection on the rear face of
the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be
Incorporated, of Turbomeca Mandatory
Service Bulletin (MSB) No. 283 72 0804,
Version C, dated October 23, 2009, to do the
inspection.
(iii) Perform a second dye penetrant
inspection when the engine has accumulated
between 450 and 550 cycles from the first
inspection.
(2) For any affected third stage turbine
wheel that on the effective date of this AD,
has accumulated 500 or more but fewer than
700 cycles-since-last-overhaul or repair, or
since-new if the engine has never been
overhauled or repaired:
(i) Within 200 additional cycles, perform a
dye penetrant inspection on the rear face of
the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be
Incorporated, of Turbomeca Mandatory
Service Bulletin (MSB) No. 283 72 0804,
Version C, dated October 23, 2009, to do the
inspection.
(3) For any affected third stage turbine
wheel that on the effective date of this AD,
has accumulated 700 or more but fewer than
1,200 cycles-since-last-overhaul or repair, or
since-new if the engine has never been
overhauled or repaired:
(i) Within 150 additional cycles, perform a
dye penetrant inspection on the rear face of
the third stage turbine wheel.
(ii) Use Section 2, Instructions to Be
Incorporated, of Turbomeca Mandatory
Service Bulletin (MSB) No. 283 72 0804,
Version C, dated October 23, 2009, to do the
inspection.
(4) If any crack indication is found, then
before further flight, remove the third stage
turbine wheel from service.
(5) For any affected third stage turbine
wheel that on the effective date of this AD
has accumulated 1,200 or more cycles-since-
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15:13 Mar 29, 2010
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last-overhaul or repair, or since-new if the
engine has never been overhauled or
repaired, no action is required.
FAA AD Differences
(f) This AD differs from the Mandatory
Continuing Airworthiness Information
(MCAI) and or service information as follows:
(1) EASA AD 2010–0004, dated January 5,
2010, requires removing the engine from
service before further flight if a third stage
turbine wheel is found cracked.
(2) This AD requires removing the third
stage turbine wheel from service before
further flight if a third stage turbine wheel is
found cracked.
Alternative Methods of Compliance
(g) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(h) Refer to MCAI EASA AD 2010–0004,
dated January 5, 2010, and Turbomeca
Mandatory Service Bulletin No. 283 72 0804,
Version C, dated October 23, 2009, for related
information. Contact Turbomeca, 40220
Tarnos, France; telephone (33) 05 59 74 40
00, fax (33) 05 59 74 45 15, for a copy of this
service information.
(i) Contact Kevin Dickert, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov;
telephone (781) 238–7117, fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
March 23, 2010.
Robert Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–7055 Filed 3–29–10; 8:45 am]
BILLING CODE 4910–13–P
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).
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
SUMMARY:
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15629
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
https://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: https://
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
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Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules
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 https://
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):
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 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:
Labor cost
Parts cost for
two fasteners
Total cost per
airplane
2 work-hours × $85 per hour = $170 ..............................................................................................................
$99.90
$269.90
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
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:
Labor cost
Parts cost (per
paddle)
Total cost per
airplane
3 work-hours × $85 per hour = $255 ..............................................................................................................
$1,200
$1,455
We estimate the following costs to do
the proposed replacement of both thrust
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15:13 Mar 29, 2010
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attenuator paddles and the eight
countersunk fasteners with new design
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thrust attenuator paddles and universal
head rivets:
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Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules
15631
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
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.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 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:
Cessna Aircraft Company: Docket No. FAA–
2010–0327; Directorate Identifier 2010–
CE–012–AD.
Comments Due Date
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 https://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
(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 inflight departure of the thrust attenuator
paddles. This failure could lead to rudder
and elevator damage and result in loss of
control.
Compliance
1. The authority citation for part 39
continues to read as follows:
(f) To address this problem, you must do
the following, unless already done:
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.
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
Actions
Within the next 60 days after December 15,
2009 (the effective date of AD 2009–24–13)
or within the next 30 hours time-in-service
(TIS) after 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.
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.
(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).
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15:13 Mar 29, 2010
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Follow Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated October 27, 2009.
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Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules
Actions
Compliance
(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.
(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 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)
WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS
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: 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.
15:13 Mar 29, 2010
Jkt 220001
(i) If the conditions of paragraph 3.A.(1) of Follow Cessna Citation Alert Service Letter
Cessna Citation Alert Service Letter
ASL525A–78–01, Revision 1, dated OctoASL525A-78–01, Revision 1, dated October
ber 27, 2009.
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 the effec- Follow Cessna Citation Service Bulletin
tive date of this AD or within 1 year after
SB525A–78–02, Revision 1, dated February
the effective date of this AD, whichever oc5, 2010.
curs first.
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 73
[Docket No. FAA–2009–1050; Airspace
Docket No. 09–ASW–3]
(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.
VerDate Nov<24>2008
Procedures
RIN 2120–AA66
Proposed Amendment to and
Establishment of Restricted Areas and
Other Special Use Airspace;
Razorback Range Airspace Complex,
AR
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: This action proposes to
restructure the restricted areas and other
special use airspace (SUA) located in
the vicinity of Fort Chaffee, AR. The Air
National Guard (ANG) requested these
modifications to the Razorback Range
Airspace Complex, by establishing two
new restricted areas, renaming an
existing restricted area, and amending
the boundaries section of the legal
description of the Hog High North
military operation area (MOA) that is
contained in the airspace complex.
Unlike restricted areas which are
designated under Title 14 Code of
Federal Regulations (14 CFR) part 73,
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Fmt 4702
Sfmt 4702
MOAs are not rulemaking airspace
actions. However, since the proposed R–
2402B infringes on the Hog High North
MOA, the FAA is including a discussion
of the Hog High North MOA change in
this NPRM. The ANG requested these
airspace changes to permit more
realistic aircrew training in modern
tactics to be conducted in the Razorback
Range Airspace Complex and to enable
more efficient use of the National
Airspace System (NAS).
DATES: Comments must be received on
or before May 14, 2010.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, 1200 New Jersey Avenue, SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001; telephone:
(202) 366–9826. You must identify FAA
Docket No. FAA–2009–1050 and
Airspace Docket No. 09–ASW–3 at the
beginning of your comments. You may
also submit comments through the
Internet at https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Colby Abbott, Airspace and Rules
Group, Office of System Operations
Airspace and AIM, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
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]]>Agencies
[Federal Register Volume 75, Number 60 (Tuesday, March 30, 2010)]
[Proposed Rules]
[Pages 15629-15632]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7024]
-----------------------------------------------------------------------
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 https://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: https://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 https://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 https://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: 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.
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
