This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

15627 

Vol. 75, No. 60 

Tuesday, March 30, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0219; Directorate 

Identifier 2010–NE–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Astazou XIV B and XIV H Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Investigation of an 

uncommanded in-flight shutdown 

(IFSD) revealed that a third stage turbine 

wheel rupture was not contained by the 

turbine casings. The released portion 

consisted of a turbine blade together 

with the rim piece immediately below 

the blade. The rim piece was bounded 

by two adjacent axial slots and a fatigue 

crack that had developed between the 

holes in which the slots terminate. The 

slots and holes, which are closed by 

riveted plugs, were introduced by 

modification AB 173 in order to 

improve the vibration characteristics of 

the turbine wheel. Modification AB 208 

brings an improvement to modification 

AB 173 by changing only the riveting 

detail. SN 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve 

their surface condition. A 

manufacturing process modification has 

been introduced to improve the surface 

condition of these holes in third stage 

turbine wheels. Wheels subject to the 

improved manufacturing process have 

S/Ns outside the range specified in 

Table 1. Although there is only one 

known event, and 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. 

We are proposing this AD to prevent 

uncontained failures of the third stage 

turbine wheel, which could result in 

damage to the helicopter. 

DATES: We must receive comments on 

this proposed AD by April 29, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Contact Turbomeca, 40220 Tarnos, 

France; telephone (33) 05 59 74 40 00, 

fax (33) 05 59 74 45 15, for the service 

information identified in this proposed 

AD. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0219; Directorate Identifier 

2010–NE–14–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0004, 

dated January 5, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Investigation of an uncommanded IFSD 

revealed that a third stage turbine wheel 

rupture was not contained by the turbine 

casings. The released portion consisted of a 

turbine blade together with the rim piece 

immediately below the blade. The rim piece 

was bounded by two adjacent axial slots and 

a fatigue crack that had developed between 

the holes in which the slots terminate. The 

slots and holes, which are closed by riveted 

plugs, were introduced by modification AB 

173 in order to improve the vibration 

characteristics of the turbine wheel. 

Modification AB 208 brings an improvement 

to modification AB 173 by changing only the 

riveting detail. SB 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve their 

surface condition. A manufacturing process 

modification has been introduced to improve 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

15628 Federal Register / Vol. 75, No. 60 / Tuesday, March 30, 2010 / Proposed Rules 

the surface condition of these holes in third 

stage turbine wheels. Wheels subject to the 

improved manufacturing process have S/Ns 

outside the range specified in Table 1. 

Although there is only one known event, and 

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. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Turbomeca has issued Mandatory 

Service Bulletin No. 283 72 0804, 

Version C, dated October 23, 2009. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, they have 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

proposing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require performing 

dye penetrant inspections for cracks on 

the rear face of certain third stage 

turbine wheels with fewer than 1,200 

cycles-since-last-overhaul or repair, or 

since-new if the engine has never been 

overhauled, on the effective date of the 

AD, and removal of the third stage 

turbine wheel before further flight if 

found cracked. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about three Astazou engines 

installed on products of U.S. registry. 

We also estimate that it would take 

about 5 work-hours per engine to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

We anticipate no parts to be required. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $1,275. 

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 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 this 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. 

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 adding 

the following new AD: 

Turbomeca: Docket No. FAA–2010–0219; 

Directorate Identifier 2010–NE–14–AD. 

Comments Due Date 

(a) We must receive comments by April 29, 

2010. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca Astazou 

XIV B and XIV H turboshaft engines with the 

following part number (P/N) third stage 

turbine wheels that incorporate modification 

AB 173 (Turbomeca Service Bulletin (SB) No. 

283 72 0091) or modification AB 208 

(Turbomeca SB No. 283 72 0117), but that do 

not incorporate Turbomeca SB No. 283 72 

805: 

(1) Third stage turbine wheels P/N 

0265257000, all serial numbers (S/Ns); 

(2) Third stage turbine wheels P/N 

0265257020, all S/Ns; 

(3) Third stage turbine wheels P/N 

0265257060, all S/Ns; 

(4) Third stage turbine wheels P/N 

0265257050, of the S/Ns listed in Appendix 

1 of Turbomeca Mandatory Service Bulletin 

No. 283 72 0804, Version C, dated October 

23, 2009. 

(5) These engines are installed on, but not 

limited to, single-engine Aerospatiale 

AS319B ‘‘Alouette III’’ and AS342J ‘‘Gazelle’’ 

helicopters. 

Reason 

(d) European Aviation Safety Agency 

(EASA) AD No. 2010–0004, dated January 5, 

2010, states: 

Investigation of an uncommanded in-flight 

shutdown (IFSD) revealed that a third stage 

turbine wheel rupture was not contained by 

the turbine casings. The released portion 

consisted of a turbine blade together with the 

rim piece immediately below the blade. The 

rim piece was bounded by two adjacent axial 

slots and a fatigue crack that had developed 

between the holes in which the slots 

terminate. The slots and holes, which are 

closed by riveted plugs, were introduced by 

modification AB 173 in order to improve the 

vibration characteristics of the turbine wheel. 

Modification AB 208 brings an improvement 

to modification AB 173 by changing only the 

riveting detail. SN 283 72 0805 provides 

instructions for re-boring the holes at 

overhaul or repair in order to improve their 

surface condition. A manufacturing process 

modification has been introduced to improve 

the surface condition of these holes in third 

stage turbine wheels. Wheels subject to the 

improved manufacturing process have S/Ns 

outside the range specified in Table 1. 

Although there is only one known event, and 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

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