Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules 15629 

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-sincelast-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). 

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 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

15630 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 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): 

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 

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 

attenuator paddles and the eight 

countersunk fasteners with new design 

thrust attenuator paddles and universal 

head rivets: 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

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. 

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. 

§ 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 

(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 

(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 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.

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.

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. 

(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).

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 PROPOSALS

15632 Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules 

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.

Follow Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009. 

(ii) If the conditions of paragraph 3.A.(2) of 

Cessna Citation Alert Service Letter 

ASL525A-78–01, Revision 1, dated October 

27, 2009, are met, replace within the next 

150 hours TIS after the inspection required 

in paragraph (f)(3) of this AD. After the replacement, continue with the repetitive inspections specified in paragraph (f)(1) of 

this AD.

(5) Replace both thrust attenuator paddles ....... Within the next 300 hours TIS after the effective date of this AD or within 1 year after 

the effective date of this AD, whichever occurs first.

Follow Cessna Citation Service Bulletin 

SB525A–78–02, Revision 1, dated February 

5, 2010. 

(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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2009–1050; Airspace 

Docket No. 09–ASW–3] 

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, 

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 http://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 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS