77378 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

plates for a split caused by exfoliation 

corrosion, in accordance with the 

Accomplishment Instructions of BAE 

SYSTEMS (Operations) Limited Service 

Bulletin J41–52–064, dated September 15, 

2009. Repeat the ultrasonic inspection, 

thereafter, at intervals not to exceed 48 

months. 

(h) If a split caused by exfoliation corrosion 

of an area of 78mm2 (0.12 in.2) or greater is 

found during any ultrasonic inspection 

required by paragraph (g) of this AD: Before 

further flight, replace any affected guide 

plates with a serviceable guide plate, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin J41–52–064, dated 

September 15, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0179, 

dated August 30, 2010; and BAE Systems 

(Operations) Limited Service Bulletin J41– 

52–064, dated September 15, 2009; for 

related information. 

Material Incorporated by Reference 

(k) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(1) BAE Systems (Operations) Limited 

Service Bulletin J41–52–064, dated 

September 15, 2009, approved for IBR 

January 17, 2012. 

(2) For BAE Systems (Operations) Limited 

service information identified in this AD, 

contact Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

November 23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31314 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0710; Directorate 

Identifier 2010–NE–26–AD; Amendment 

39–16892; AD 2011–26–02] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 1 Series Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD was 

prompted by Turbomeca restoring all or 

part of the life limits of the affected 

discs, and European Aviation Safety 

Agency’s (EASA) issuance of AD 2010– 

0101R2, dated March 24, 2011, to do the 

same. Turbomeca has introduced a 

reinforced eddy-current inspection (ECI) 

which, combined with a revised 

analysis, allows the life limit of the 

affected discs to be extended. We are 

issuing this revision to prevent failure of 

the gas generator (GG) second stage 

turbine disc which could result in the 

release of high energy debris and 

damage to the helicopter. 

DATES: This AD is effective January 17, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca, 40220 Tarnos, France; 

phone: 33 05 59 74 40 00; fax: 33 05 59 

74 45 15; email: noriadallas@turbomeca.com. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7125. 

Examining the AD Docket 

You may examine the AD docket 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 AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: (800) 647–5527) 

is Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, 12 

New England Executive Park, 

Burlington, MA; phone: (781) 238–7779; 

fax: (781) 238–7199; email: 

frederick.zink@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2010–19–06, 

amendment 39–16434 (75 FR 57371, 

September 21, 2010). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

July 19, 2011 (76 FR 42610). That NPRM 

proposed to require removing GG 

second stage turbine discs, P/N 0 292 25 

040 0, that do not have the ‘‘CFR’’ 

marking, from service before exceeding 

4,000 cycles-in-service (CIS) since-new. 

That NPRM also proposed to require 

removing GG second stage turbine discs, 

P/N 0 292 25 040 0, that have the ‘‘CFR’’ 

marking, from service before exceeding 

6,500 CIS since-new. 

That NPRM was prompted by 

Turbomeca restoring all or part of the 

life limits of the affected discs, per 


jlentini on DSK4TPTVN1PROD with RULES
Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 77379 

EASA’s issuance of AD 2010–0101R2, 

dated March 24, 2011, to do the same. 

Turbomeca’s reinforced ECI provides a 

lower (improved) detection threshold 

for metallurgical non-conformities. This 

reinforced ECI, combined with a revised 

analysis, allows the life limit of the 

post-TU347 GG second stage turbine 

discs identified as ‘‘CFR’’ to be extended 

to 6,500 CIS since-new. Further, as a 

result of this testing and analysis, the 

non-CFR 2nd stage turbine discs preTU347 inspection disc life has been 

extended to 4,000 CIS since-new. This 

new AD still prevents disc failure but 

also extends the life limits of the 

affected discs. We are issuing this 

revision to prevent failure of the GG 

second stage turbine disc which could 

result in the release of high energy 

debris and damage to the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 42610, July 19, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor 

clarifications. We have determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

42610, July 19, 2011) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 42610, 

July 19, 2011). 

Costs of Compliance 

We estimate that this AD will affect 

203 Turbomeca Arriel 1 series 

turboshaft engines on helicopters of U.S. 

registry. We estimate that no additional 

labor costs will be incurred to return 

part of the life limit of the discs that do 

not have the ‘‘CFR’’ marking to the 

original published life limit. Based on 

these figures, we estimate the total cost 

of this AD to U.S. operators to be $0. 

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 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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2010–19–06, Amendment 39–16434 (75 

FR 57371, September 21, 2010), and 

adding the following new AD: 

2011–26–02 Turbomeca: Amendment 39– 

16892; Docket No. FAA–2010–0710; 

Directorate Identifier 2010–NE–26–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 17, 2012. 

(b) Affected ADs 

This AD revises AD 2010–19–06, 

Amendment 39–16434. 

(c) Applicability 

This AD applies to Turbomeca Arriel 1A, 

1A1, 1B, 1C, 1C1, 1C2, 1D, 1D1, and 1S1 

turboshaft engines that have incorporated 

Modification TU347. 

(d) Unsafe Condition 

This AD was prompted by Turbomeca 

restoring all or part of the life limits of the 

affected discs. We are issuing this AD to 

prevent failure of the gas generator (GG) 

second stage turbine disc which could result 

in the release of high energy debris and 

damage to the helicopter. 

(e) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) Remove from service the GG second 

stage turbine discs, part number (P/N) 0 292 

25 040 0, that do not have the ‘‘CFR’’ marking 

before exceeding 4,000 cycles-in-service (CIS) 

since-new. 

(3) Remove from service gas generator 

second stage turbine discs, P/N 0 292 25 040 

0, that have the ‘‘CFR’’ marking before 

exceeding 6,500 CIS since-new. 

(f) Gas Generator Second Stage Turbine 

Installation Prohibition 

(1) After the effective date of this AD, do 

not install into any engine gas generator 

second stage turbine discs, P/N 0 292 25 040 

0, that do not have the ‘‘CFR’’ marking and 

have 4,000 or more CIS since-new. 

(2) After the effective date of this AD, do 

not install into any engine gas generator 

second stage turbine discs, P/N 0 292 25 040 

0, that have the ‘‘CFR’’ marking and have 

6,500 or more CIS since-new. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

(1) Refer to Turbomeca Alert Mandatory 

Service Bulletin No. A292 72 0831, Version 

C, for related information. Contact 

Turbomeca, 40220 Tarnos, France; phone: 33 

05 59 74 40 00; fax: 33 05 59 74 45 15; or 

email: noria-dallas@turbomeca.com for a 

copy of this service information. 

(2) You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call (781) 238–7125. 

(3) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7779; fax: (781) 

238–7199; email: frederick.zink@faa.gov. 

(i) Material Incorporated by Reference 

None. 


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77380 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

Issued in Burlington, MA, on December 5, 

2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31797 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1298; Directorate 

Identifier 2011–NE–39–AD; Amendment 39– 

16888; AD 2011–25–12] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney Canada PT6A–15AG, –27, –28, 

–34, –34AG, –34B, and –36 series 

turboprop engines. This AD requires the 

removal of certain affected part 

manufacturer approval (PMA) 

replacement Timken Alcor Aerospace 

Technologies, Inc. (TAATI) first stage 

reduction sun gears and/or the 

interacting planetary gear sets from the 

propeller reduction gearbox assembly. 

This AD was prompted by a failure 

report of a certain TAATI PMA sun gear, 

installed since December 22, 2008. We 

are issuing this AD to prevent failure of 

the sun gear, which will result in an 

engine in-flight shut down, possible 

uncontained engine failure, aircraft 

damage, and serious injuries. 

DATES: This AD is effective December 

28, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 28, 2011. 

We must receive any comments on 

this AD by January 27, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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 AD, contact Timken Alcor 

Aerospace Technologies, Inc., 3110 N. 

Oakland, Mesa, Arizona 85215; phone: 

(480) 632–1039; Web site: http:// 

www.timken.com/mro. You may review 

copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7125. 

Examining the AD Docket 

You may examine the AD docket 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 AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (phone: (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Paul 

Craig, Aerospace Engineer, Los Angeles 

Aircraft Certification Office, FAA, 3960 

Paramount Blvd., Suite 100, Lakewood, 

CA 90712; phone: (562) 627–5252; fax: 

(562) 627–5210; email: 

paul.craig@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 12, 2011, we issued AD 

2011–20–51, Amendment 39–16843 (76 

FR 64001, October 17, 2011), for Pratt & 

Whitney Canada PT6A–15AG, –27, –28, 

–34, –34AG, –34B, and –36 series 

turboprop engines having a TAATI PMA 

replacement first stage reduction sun 

gear, part number (P/N) E3024765, 

installed. 

Actions Since AD 2011–20–51 (76 FR 

64001, October 17, 2011) Was Issued 

Since we issued AD 2011–20–51, we 

received a report of another failure of a 

sun gear not listed in that AD. Analysis 

has revealed that additional PMA 

replacement TAATI gears, installed 

since December 22, 2008, have the same 

failure potential as the gears affected by 

that AD. The additional gears are 

identified as follows: 

• Replacement first stage reduction 

sun gears, P/N E3024765, serial 

numbers (S/Ns) PC5–051 through PC5– 

089, and S/Ns SG36–051 through SG36– 

120, including the associated planetary 

gears in propeller reduction gearbox 

assembly. 

• Replacement planetary gear sets, 

P/N E3101455–02, S/Ns EE–051 through 

EE–197, S/Ns EE–4051 through EE– 

4094, and S/N EE–4113, including the 

associated sun gear in the propeller 

reduction gearbox assembly. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined that the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

AD Requirements 

This AD requires the removal of 

affected sun gears and planetary gear 

sets described previously. 

FAA’s Justification and 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 of the short compliance 

time required in this AD to remove any 

affected parts from service. Therefore, 

we find that notice and opportunity for 

prior public comment are impracticable 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2011–1298 and directorate 

identifier 2011–NE–39–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because 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 

about this AD. 


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