Federal Register, Volume 75 Issue 60 (Tuesday, March 30, 2010)

[Federal Register Volume 75, Number 60 (Tuesday, March 30, 2010)]
[Proposed Rules]
[Pages 15629-15632]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-7024]

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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]
RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company Model 525A
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2009-24-
13, which applies to certain Cessna Aircraft Company (Cessna) Model
525A airplanes. AD 2009-24-13 currently requires you to repetitively
inspect the thrust attenuator paddle assemblies for loose and damaged
fasteners and for cracks. AD 2009-24-13 also requires you to replace
loose or damaged fasteners and replace cracked thrust attenuator
paddles found during any inspection. Since we issued AD 2009-24-13,
Cessna has developed new design thrust attenuator paddles and universal
head rivets as terminating action for the repetitive inspections.
Consequently, this proposed AD would retain the requirements of AD
2009-24-13 until replacement of both thrust attenuator paddles and the
eight countersunk fasteners with new design thrust attenuator paddles
and universal head rivets. We are proposing this AD to detect and
correct loose and damaged fasteners and cracks in the thrust attenuator
paddles, which could result in in-flight departure of the thrust
attenuator paddles. This failure could lead to rudder and elevator
damage and result in loss of control.

DATES: We must receive comments on this proposed AD by May 14, 2010.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS
67277; telephone: (316) 517-6000; fax: (316) 517-8500; Internet: http://www.cessna.com.

FOR FURTHER INFORMATION CONTACT: TN Baktha, Aerospace Engineer, ACE-
118W, Wichita Aircraft Certification Office (ACO), 1801 Airport Road,
Room 100, Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316)
946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket

[[Page 15630]]

number, ``FAA-2010-0327; Directorate Identifier 2010-CE-012-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this proposed AD.

Discussion

Reports of fatigue cracks found in thrust attenuator paddles on
Cessna Model 525A airplanes caused us to issue AD 2009-24-13, Amendment
39-16105 (74 FR 62479, November 30, 2009). AD 2009-24-13 currently
requires the following on Cessna Model 525A airplanes:
Inspect repetitively the thrust attenuator paddle
assemblies for loose and damaged fasteners and for cracks; and
replace loose or damaged fasteners and replace cracked
thrust attenuator paddles found during any inspection.
Four incidents of thrust attenuator paddles departing from
airplanes have been reported. In two cases, the thrust attenuator
paddles hit the rudder and caused structural damage to the rudder.
The thrust attenuator paddles are attached to the aft fuselage. The
attachment fasteners fatigue and break.
It is also possible that a failed thrust attenuator paddle could
depart the airplane and hit and damage the elevator.
We considered AD 2009-24-13 an interim action while Cessna
developed a design improvement to change the attachment fasteners from
the currently used counter sunk rivets to universal head rivets. Since
we issued AD 2009-24-13, Cessna has developed new design thrust
attenuator paddles and universal head rivets to replace the old design
thrust attenuator paddle assemblies and the counter sunk fasteners.
This condition, if not corrected, could result in in-flight
departure of the thrust attenuator paddles. This failure could lead to
rudder and elevator damage and result in loss of control.

Relevant Service Information

We have reviewed:
Cessna Citation Alert Service Letter ASL525A-78-01,
Revision 1, dated October 27, 2009;
Cessna Citation Service Bulletin SB525A-78-02, dated
November 13, 2009, and
Cessna Citation Service Bulletin SB525A-78-02, Revision 1,
dated February 5, 2010.
Cessna Citation Alert Service Letter ASL525A-78-01 describes
procedures for inspecting and modifying the thrust attenuator paddle
assemblies.
Cessna Citation Service Bulletin SB525A-78-02 describes procedures
for replacing the thrust attenuator paddles and attachment hardware.

FAA's Determination and Requirements of the Proposed AD

We are proposing this AD because we evaluated all information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This proposed AD
would supersede AD 2009-24-13 with a new AD that would retain the
requirements of AD 2009-24-13 until you replace both thrust attenuator
paddles and the eight countersunk fasteners with new design thrust
attenuator paddles and universal head rivets. This proposed AD would
require you to use the service information described previously to
perform these actions.

Costs of Compliance

We estimate that this proposed AD would affect 136 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection
(retained from AD 2009-24-13):

----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85.......... Not Applicable................ $85 $11,560
----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary installation
(retained from AD 2009-24-13) of missing/damaged fasteners that would
be required based on the results of the proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

------------------------------------------------------------------------
Parts cost for Total cost per
Labor cost two fasteners airplane
------------------------------------------------------------------------
2 work-hours x $85 per hour = $170 $99.90 $269.90
------------------------------------------------------------------------

We estimate the following costs to do any necessary replacement
(retained from AD 2009-24-13) of a cracked thrust attenuator paddle
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that may need
this replacement:

------------------------------------------------------------------------
Parts cost (per Total cost per
Labor cost paddle) airplane
------------------------------------------------------------------------
3 work-hours x $85 per hour = $255 $1,200 $1,455
------------------------------------------------------------------------

We estimate the following costs to do the proposed replacement of
both thrust attenuator paddles and the eight countersunk fasteners with
new design thrust attenuator paddles and universal head rivets:

[[Page 15631]]

----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
5 work-hours x $85 per hour = $425..................... $3,464 $3,889 $528,904
----------------------------------------------------------------------------------------------------------------

As determined by the manufacturer, eligible airplanes may qualify
for warranty coverage of parts and labor.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket that contains the proposed AD, the
regulatory evaluation, any comments received, and other information on
the Internet at http://www.regulations.gov; or in person at the Docket
Management Facility between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Office (telephone (800) 647-5527)
is located at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Airworthiness Directive
(AD) 2009-24-13, Amendment 39-16105 (74 FR 62479, November 30, 2009),
and adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2010-0327; Directorate
Identifier 2010-CE-012-AD.

Comments Due Date

(a) We must receive comments on this airworthiness directive
(AD) action by May 14, 2010.

Affected ADs

(b) This AD supersedes AD 2009-24-13, Amendment 39-16105.

Applicability

Subject

(d) Air Transport Association of America (ATA) Code 72: Engine.

Unsafe Condition

(e) This AD results from reports of fatigue cracks found in
thrust attenuator paddles on Cessna Model 525A airplanes. We are
issuing this AD to detect and correct loose and damaged fasteners
and cracks in the thrust attenuator paddles, which could result in
in-flight departure of the thrust attenuator paddles. This failure
could lead to rudder and elevator damage and result in loss of
control.

Compliance

(f) To address this problem, you must do the following, unless
already done:

------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Visually inspect the Within the next 60 Follow Cessna
left and right thrust days after December Citation Alert
attenuator paddle 15, 2009 (the Service Letter
assemblies to determine if effective date of ASL525A-78-01,
there are any missing, AD 2009-24-13) or Revision 1, dated
loose, or damaged fasteners within the next 30 October 27, 2009.
and to determine if there hours time-in-
are any cracks in the service (TIS) after
paddle. December 15, 2009
(the effective date
of AD 2009-24-13),
whichever occurs
first. Repetitively
inspect thereafter
at intervals not to
exceed 150 hours
TIS.
(2) If you do not find any Before further Follow Cessna
cracks in the thrust flight after the Citation Alert
attenuator paddles during inspection required Service Letter
any inspection required in in paragraph (f)(1) ASL525A-78-01,
paragraph (f)(1) of this of this AD. Revision 1, dated
AD, install any missing Continue with the October 27, 2009.
fasteners, and replace any repetitive
loose or damaged fasteners. inspections
specified in
paragraph (f)(1) of
this AD.
(3) If cracks are found Before further Follow Cessna
during any inspection flight after the Citation Alert
required in paragraph inspection required Service Letter
(f)(1) of this AD, do a in paragraph (f)(1) ASL525A-78-01,
surface eddy current of this AD in which Revision 1, dated
inspection of the thrust cracks are found. October 27, 2009.
attenuator paddles and the
fastener hole(s) to
determine the length of the
cracks(s).

[[Page 15632]]

(4) If the cracks identified (i) If the Follow Cessna
in paragraph (f)(3) of this conditions of Citation Alert
AD meet or exceed the paragraph 3.A.(1) Service Letter
limits specified in of Cessna Citation ASL525A-78-01,
paragraph 3 of Cessna Alert Service Revision 1, dated
Citation Alert Service Letter October 27, 2009.
Letter ASL525A-78-01, ASL525A[dash]78-01,
Revision 1, dated October Revision 1, dated
27, 2009, replace the October 27, 2009,
thrust attenuator paddle are met, replace
and attachment hardware, as before further
applicable. flight after the
inspection required
in paragraph (f)(3)
of this AD. After
the replacement,
continue with the
repetitive
inspections
specified in
paragraph (f)(1) of
this AD.
(ii) If the
conditions of
paragraph 3.A.(2)
of Cessna Citation
Alert Service
Letter
ASL525A[dash]78-01,
Revision 1, dated
October 27, 2009,
are met, replace
within the next 150
hours TIS after the
inspection required
in paragraph (f)(3)
of this AD. After
the replacement,
continue with the
repetitive
inspections
specified in
paragraph (f)(1) of
this AD.
(5) Replace both thrust Within the next 300 Follow Cessna
attenuator paddles. hours TIS after the Citation Service
effective date of Bulletin SB525A-78-
this AD or within 1 02, Revision 1,
year after the dated February 5,
effective date of 2010.
this AD, whichever
occurs first.
------------------------------------------------------------------------

(g) The replacement required in paragraph (f)(5) of this AD
terminates the repetitive inspection requirement of this AD. This
replacement may be done at anytime, but must be done no later than
300 hours TIS or within 1 one after the effective date of this AD,
whichever occurs first.
(h) If, before the effective date of this AD, you have done all
the actions in the original issue of Cessna Citation Service
Bulletin SB525A-78-02, dated November 13, 2009, then no further
action is required by this AD. This is considered ``unless already
done'' credit for this AD action.

Alternative Methods of Compliance (AMOCs)

(i) The Manager, Wichita Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: TN Baktha, Aerospace Engineer, ACE-118W, Wichita Aircraft
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-4107. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(j) AMOCs approved for AD 2009-24-13 are approved for this AD.

Related Information

(k) To get copies of the service information referenced in this
AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706,
Wichita, KS 67277; telephone: (316) 517-6000; fax: (316) 517-8500;
Internet: http://www.cessna.com. To view the AD docket, go to U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at http://www.regulations.gov.

Issued in Kansas City, Missouri, on March 23, 2010.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-7024 Filed 3-29-10; 8:45 am]
BILLING CODE 4910-13-P