Airworthiness Directives; Cessna Aircraft Company Model 525A Airplanes, 62479-62481 [E9-28234]

Download as PDF Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1096; Directorate Identifier 2009–CE–056–AD; Amendment 39–16105; AD 2009–24–13] RIN 2120–AA64 Airworthiness Directives; Cessna Aircraft Company Model 525A Airplanes WReier-Aviles on DSKGBLS3C1PROD with RULES AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 525A airplanes. This AD requires you to repetitively inspect the thrust attenuator paddle assemblies for loose and damaged fasteners and for cracks. This AD also requires you to replace loose or damaged fasteners and replace cracked thrust attenuator paddles found during any inspection. This AD results from reports of fatigue cracks found in thrust attenuator paddles. 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 December 15, 2009. On December 15, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive any comments on this AD by January 14, 2010. ADDRESSES: Use one of the following addresses to comment on this 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. To get the service information identified in this AD, contact Cessna Aircraft Company, Product Support, VerDate Nov<24>2008 14:56 Nov 27, 2009 Jkt 220001 P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–6000; fax: (316) 517–8500; Internet: http:// www.cessna.com. To view the comments to this AD, go to http://www.regulations.gov. The docket number is FAA–2009–1096; Directorate Identifier 2009–CE–056–AD. FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4155; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Discussion We received reports of fatigue cracks found in thrust attenuator paddles on Cessna Model 525A airplanes. 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. 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 reviewed Cessna Citation Alert Service Letter ASL525A–78–01, Revision 1, dated October 27, 2009. The service information describes procedures for inspecting and modifying the thrust attenuator paddle assemblies. FAA’s Determination and Requirements of This AD We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires repetitively inspecting the thrust attenuator paddle assemblies for loose and damaged fasteners and for cracks. This AD also requires replacing loose or damaged fasteners and replacing cracked thrust attenuator paddles. This is considered interim action. Cessna is working on a design improvement to change the attachment fasteners from the currently used counter sunk rivets to universal head rivets. The FAA will consider taking additional rulemaking action to supersede this AD and terminate the PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 62479 above repetitive inspections when Cessna completes the design change, and the FAA approves it as addressing the unsafe condition. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the thrust attenuator paddles attached to the aft fuselage and the attachment fasteners are subject to fatigue. Fatigue in these parts 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. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ‘‘FAA– 2009–1096; Directorate Identifier 2009– CE–056–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 AD. 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 E:\FR\FM\30NOR1.SGM 30NOR1 62480 Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations 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 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 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 AD and placed it in the AD docket. Examining the AD Docket § 39.13 You may examine the AD docket that contains the 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 2009–24–13 Cessna Aircraft Company: Amendment 39–16105; Docket No. FAA–2009–1096; Directorate Identifier 2009–CE–056–AD. Effective Date (a) This AD becomes effective on December 15, 2009. Affected ADs (b) None. 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 78: Engine Exhaust. Unsafe Condition (e) This AD results from reports of fatigue cracks found in thrust attenuator paddles. We are issuing this AD to detect and correct 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 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 of this AD) or within the next 30 hours time-in-service (TIS) after December 15, 2009 (the effective date of this AD), 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. WReier-Aviles on DSKGBLS3C1PROD with RULES (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 Nov<24>2008 14:56 Nov 27, 2009 Jkt 220001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Follow Cessna Citation Alert Service Letter ASL525A–78–01, Revision 1, dated October 27, 2009. E:\FR\FM\30NOR1.SGM 30NOR1 Federal Register / Vol. 74, No. 228 / Monday, November 30, 2009 / Rules and Regulations 62481 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. Follow Cessna Citation Alert Service Letter ASL525A–78–01, Revision 1, dated October 27, 2009. Alternative Methods of Compliance (AMOCs) (g) 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, 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. WReier-Aviles on DSKGBLS3C1PROD with RULES Material Incorporated by Reference (h) You must use Cessna Citation Alert Service Letter ASL525A–78–01, Revision 1, dated October 27, 2009, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517–6000; fax: (316) 517–8500; Internet: http://www.cessna.com. (3) 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. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/ federal_register/ code_of_federal_regulations/ ibr_locations.html. VerDate Nov<24>2008 14:56 Nov 27, 2009 Jkt 220001 Issued in Kansas City, Missouri, on November 19, 2009. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28234 Filed 11–27–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0328; Directorate Identifier 2008–NE–44–AD; Amendment 39– 16103; AD 2009–24–11] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF34–1A, CF34–3A, and CF34–3B Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF34–1A, CF34–3A, and CF34–3B series turbofan engines. This AD requires removing from service certain part number (P/N) and serial number (SN) fan blades within compliance times specified in this AD, inspecting the fan blade abradable rub strip on certain engines for wear, inspecting the fan blades on certain engines for cracks, inspecting the aft actuator head hose fitting for correct position, and, if necessary, repositioning the hose fitting. This AD results from a report of an under-cowl fire and a failed fan blade. We are issuing this AD to prevent failure of certain P/N and SN fan blades and aft actuator head hoses, which PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 could result in an under-cowl fire and subsequent damage to the airplane. DATES: This AD becomes effective January 4, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 4, 2010. ADDRESSES: You can get the service information identified in this AD from General Electric Company, GE– Aviation, Room 285, 1 Newmann Way, Cincinnati, OH 45215, telephone (513) 552-–3272; fax (513) 552–3329; e-mail: geae.aoc@ge.com. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: john.frost@faa.gov; telephone (781) 238–7756; fax (781) 238–7199. The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF34–1A, CF34–3A, and CF34–3B series turbofan engines. We published the proposed AD in the Federal Register on April 8, 2009 (74 FR 15896). That action proposed to require removing from service certain P/N and SN fan blades within compliance times specified in the proposed AD, inspecting the fan blade abradable rub strip on certain engines for wear, inspecting the fan blades on certain engines for cracks, inspecting the aft actuator head hose fitting for correct position, and, if necessary, repositioning the hose fitting. SUPPLEMENTARY INFORMATION: E:\FR\FM\30NOR1.SGM 30NOR1

Agencies

[Federal Register Volume 74, Number 228 (Monday, November 30, 2009)]
[Rules and Regulations]
[Pages 62479-62481]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28234]



[[Page 62479]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1096; Directorate Identifier 2009-CE-056-AD; 
Amendment 39-16105; AD 2009-24-13]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Model 525A 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Cessna Aircraft Company (Cessna) Model 525A airplanes. This AD requires 
you to repetitively inspect the thrust attenuator paddle assemblies for 
loose and damaged fasteners and for cracks. This AD also requires you 
to replace loose or damaged fasteners and replace cracked thrust 
attenuator paddles found during any inspection. This AD results from 
reports of fatigue cracks found in thrust attenuator paddles. 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 December 15, 2009.
    On December 15, 2009, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.
    We must receive any comments on this AD by January 14, 2010.

ADDRESSES: Use one of the following addresses to comment on this 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.
    To get the service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 
67277; telephone: (316) 517-6000; fax: (316) 517-8500; Internet: http://www.cessna.com.
    To view the comments to this AD, go to http://www.regulations.gov. 
The docket number is FAA-2009-1096; Directorate Identifier 2009-CE-056-
AD.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We received reports of fatigue cracks found in thrust attenuator 
paddles on Cessna Model 525A airplanes.
    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.
    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 reviewed Cessna Citation Alert Service Letter ASL525A-78-01, 
Revision 1, dated October 27, 2009. The service information describes 
procedures for inspecting and modifying the thrust attenuator paddle 
assemblies.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This AD requires 
repetitively inspecting the thrust attenuator paddle assemblies for 
loose and damaged fasteners and for cracks. This AD also requires 
replacing loose or damaged fasteners and replacing cracked thrust 
attenuator paddles.
    This is considered interim action. Cessna is working on a design 
improvement to change the attachment fasteners from the currently used 
counter sunk rivets to universal head rivets. The FAA will consider 
taking additional rulemaking action to supersede this AD and terminate 
the above repetitive inspections when Cessna completes the design 
change, and the FAA approves it as addressing the unsafe condition.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because the 
thrust attenuator paddles attached to the aft fuselage and the 
attachment fasteners are subject to fatigue. Fatigue in these parts 
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.
    Therefore, we determined that notice and opportunity for public 
comment before issuing this AD are impracticable and that good cause 
exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and an opportunity for 
public comment. We invite you to send any written relevant data, views, 
or arguments regarding this AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number ``FAA-2009-1096; 
Directorate Identifier 2009-CE-056-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the 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 AD.

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

[[Page 62480]]

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 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 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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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 adding the following new airworthiness 
directive (AD):

2009-24-13 Cessna Aircraft Company: Amendment 39-16105; Docket No. 
FAA-2009-1096; Directorate Identifier 2009-CE-056-AD.

Effective Date

    (a) This AD becomes effective on December 15, 2009.

Affected ADs

    (b) None.

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 78: Engine 
Exhaust.

Unsafe Condition

    (e) This AD results from reports of fatigue cracks found in 
thrust attenuator paddles. We are issuing this AD to detect and 
correct 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,        this AD) or within    Revision 1, dated
 loose, or damaged fasteners   the next 30 hours     October 27, 2009.
 and to determine if there     time-in-service
 are any cracks in the         (TIS) after
 paddle.                       December 15, 2009
                               (the effective date
                               of this AD),
                               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 62481]]

 
(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.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (g) 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, 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.

Material Incorporated by Reference

    (h) You must use Cessna Citation Alert Service Letter ASL525A-
78-01, Revision 1, dated October 27, 2009, 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 this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 
67277; telephone: (316) 517-6000; fax: (316) 517-8500; Internet: 
http://www.cessna.com.
    (3) 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.
    (4) You may also review copies of the service information 
incorporated by reference for this AD at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/ federal_register/ code_of_federal_regulations/ 
ibr_locations.html.

    Issued in Kansas City, Missouri, on November 19, 2009.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-28234 Filed 11-27-09; 8:45 am]
BILLING CODE 4910-13-P