Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64289 

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), 

(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. 

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 airworthiness 

directive (AD): 

General Electric Company: Docket No. FAA– 

2011–0599; Directorate Identifier 2011– 

NE–19–AD. 

(a) Comments Due Date 

We must receive comments by December 2, 

2011. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF34–10E series turbofan 

engines, serial number (S/N) 994116, and 

S/Ns 994118 through 994186 inclusive. 

(d) Unsafe Condition 

This AD was prompted by a report of 

heavy wear found on the seating surface of 

the center vent duct (CVD) (commonly 

referred to as center vent tube) support ring 

and on the inside diameter of the fan drive 

shaft at the mating location. The wear is 

caused by relative motion between the CVD 

support assembly (consisting of self-locking 

nut, part number (P/N) 2226M57G03, 

threaded sleeve, P/N 2226M55P03, and 

support ring, P/N 2226M56P01) and the fan 

drive shaft, during engine operation. We are 

issuing this AD to prevent fan drive shaft 

failure, leading to uncontained engine failure 

and damage to the airplane. 

(e) Compliance 

Comply with this AD before accumulating 

11,500 total cycles-in-service on the engine, 

unless already done. 

(f) Inspection and Removal From Service of 

CVD Support Assembly; and Determination 

of Fan Drive Shaft Serviceability 

Visually inspect the seating surface of the 

CVD support ring for wear. 

(1) If there is sign of wear on the CVD 

support ring, remove the CVD support 

assembly and the fan drive shaft from service 

before further flight. 

(2) If there is no sign of wear on the CVD 

support ring, remove the CVD support 

assembly from service and borescope inspect 

the inside diameter of the fan drive shaft at 

the CVD support ring contact area, for wear. 

(3) If there is sign of wear on the fan drive 

shaft, remove the fan drive shaft from service 

before further flight. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

return to service any CVD support assembly 

(consisting of self-locking nut, P/N 

2226M57G03, threaded sleeve, P/N 

2226M55P03, and support ring, P/N 

2226M56P01) removed from service as 

specified in this AD. 

(h) Definition 

For the purposes of this AD, the phrase 

‘‘any sign of wear’’ is defined as any visual 

indication of removal of parent material from 

the CVD seating surface or the fan drive shaft. 

(i) Alternative Methods of Compliance 

(AMOCs) 

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. 

(j) Related Information 

(1) For more information about this AD, 

contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7756; fax: 781–238– 

7199; e-mail: john.frost@faa.gov. 

(2) Refer to GE Service Bulletin No. CF34– 

10E S/B 72–0188, for related information. 

Contact GE–Aviation, M/D Rm. 285, One 

Neumann Way, Cincinnati, OH 45215, 

phone: 513–552–3272; e-mail: 

geae.aoc@ge.com, for a copy of this service 

information. 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. 

Issued in Burlington, Massachusetts, on 

October 6, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26824 Filed 10–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0956; Directorate 

Identifier 2011–NE–23–AD] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) TAE 

125–02–99 and TAE 125–02–114 

Reciprocating 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: 

In-flight engine shutdown incidents have 

been reported on aeroplanes equipped with 

TAE 125 engines. Preliminary investigations 

showed that it was mainly the result of the 

sensitivity of friction disk Part Number (P/N) 

05–7211–K010201 against possible 

misalignment of gearbox and core engine 

during assembly. 

This condition, if not corrected, could 

result in further cases of engine in-flight 

shutdown and consequent loss of control of 

the aeroplane. 

To address this unsafe condition, Thielert 

Aircraft Engines GmbH has developed a new 

friction disk. 

We are proposing this AD to prevent 

in-flight engine shutdown, which could 

result in loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by December 2, 2011. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


srobinson on DSK4SPTVN1PROD with PROPOSALS
64290 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 

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 (phone: 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, 

MA; phone: 781–238–7143; fax: 781– 

238–7199; e-mail: alan.strom@faa.gov. 

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–2011–0956; Directorate Identifier 

2011–NE–23–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 AD 2011– 

0087–E, dated May 12, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

In-flight engine shutdown incidents have 

been reported on aeroplanes equipped with 

TAE 125 engines. 

Preliminary investigations showed that it 

was mainly the result of the sensitivity of 

friction disk Part Number (P/N) 05–7211– 

K010201 against possible misalignment of 

gearbox and core engine during assembly. 

This condition, if not corrected, could 

result in further cases of engine in-flight 

shutdown and consequent loss of control of 

the aeroplane. 

To address this unsafe condition, Thielert 

Aircraft Engines GmbH has developed a new 

friction disk. 

We are proposing this AD to require 

replacement of affected friction disks, 

which would resolve the unsafe 

condition described above. You may 

obtain further information by examining 

the MCAI in the AD docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Germany, and 

is approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the European 

Community, EASA 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 on all TAE 125–02–99 

and TAE 125–02–114 reciprocating 

engines, replacing the friction disk, P/N 

05–7211–K010201. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 206 TAE 125–02–99 and 

TAE 125–02–114 reciprocating engines 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per engine to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $1,500 

per engine. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $361,530. Our cost 

estimate is exclusive of possible 

warranty coverage. 

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 airworthiness 

directive (AD): 

Thielert Aircraft Engines GmbH: Docket No. 

FAA–2011–0956; Directorate Identifier 

2011–NE–23–AD. 

(a) Comments Due Date 

We must receive comments by December 2, 

2011. 

(b) Affected ADs 

None. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64291 

(c) Applicability 

This AD applies to all Thielert Aircraft 

Engines GmbH TAE 125–02–99 and TAE– 

125–02–114 reciprocating engines with 

friction disk, part number (P/N) 05–7211– 

K010201, installed. 

(d) Reason 

This 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: 

In-flight engine shutdown incidents have 

been reported on aeroplanes equipped with 

TAE 125 engines. Preliminary investigations 

showed that it was mainly the result of the 

sensitivity of friction disk Part Number (P/N) 

05–7211–K010201 against possible 

misalignment of gearbox and core engine 

during assembly. 

This condition, if not corrected, could 

result in further cases of engine in-flight 

shutdown and consequent loss of control of 

the aeroplane. 

To address this unsafe condition, Thielert 

Aircraft Engines GmbH has developed a new 

friction disk. 

We are issuing this AD to prevent in-flight 

engine shutdown, which could result in loss 

of control of the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) TAE 125–02–99 Engines, P/Ns 05–7200– 

K000201; 05–7200–K000701; 05–7200– 

K000101; 05–7200–K000901; 05–7200– 

K001101; and 05–7200–K001301; and TAE 

125–02–114 Engines, P/Ns 05–7200–K000501; 

05–7200–K000801; and 05–7200–K001401 

For TAE 125–02–99 engines, P/Ns 05– 

7200–K000201; 05–7200–K000701; 05–7200– 

K000101; 05–7200–K000901; 05–7200– 

K001101; and 05–7200–K001301; and TAE 

125–02–114 engines, P/Ns 05–7200– 

K000501; 05–7200–K000801; and 05–7200– 

K001401, remove friction disk, P/N 05–7211– 

K010201, within 100 flight hours (FH) timesince-new (TSN) on the clutch or within 10 

FH time-in-service (TIS) after the effective 

date of this AD, whichever is later. 

(2) TAE 125–02–99 Engines, P/Ns 05–7200– 

K000301 

For TAE 125–02–99 engines, P/N 05–7200– 

K000301, installed on multiengine aircraft, 

remove friction disk, P/N 05–7211–K010201, 

on one engine within 100 FH TSN on the 

clutch or within 10 FH TIS after the effective 

date of this AD, whichever is later. Remove 

friction disk, P/N 05–7211–K010201, from 

the other engine within 300 FH TSN on the 

clutch or within 10 FH TIS after the effective 

date of this AD, whichever is later. 

(f) Installation Prohibition 

After the effective date of this AD: 

(1) Do not install any friction disk, P/N 05– 

7211–K010201, into any engine. 

(2) Do not install any TAE 125–02–99 

engine, P/N 05–7200–K000201, 05–7200– 

K000301, or 05–7200–K000701, or TAE 125– 

02–114 engine, P/N 05–7200–K00801 or 05– 

7200–K00501, that has a friction disk, P/N 

05–7211–K010201 installed, onto any 

airplane. 

(g) Operating Prohibition 

Do not operate any multi-engine aircraft 

after 300 FH TSN on the clutch or 10 FH TIS 

after the effective date of this AD, whichever 

is later, which has installed a friction disk, 

P/N 05–7211–K010201. 

(h) FAA AD Differences 

The MCAI mandates the replacement 

friction disk P/N. This AD does not. 

(i) Alternative Methods of Compliance 

(AMOCs) 

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. 

(j) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0087–E, dated May 12, 2011, 

and Thielert Service Bulletin No. TM TAE 

125–1013 P1, for related information. Contact 

Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, telephone: +49–37204–696–0; fax: 

+49–37204–696–55; e-mail: info@centurionengines.com, for a copy of this service 

information. 

(2) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

12 New England Executive Park, Burlington, 

MA; phone: 781–238–7143; fax: 781–238– 

7199; e-mail: alan.strom@faa.gov, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

October 4, 2011. 

Peter A. White, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26827 Filed 10–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0982; Directorate 

Identifier 2011–NE–09–AD 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all GE 

CF6–80C2A1, CF6–80C2A2, CF6– 

80C2A3, CF6–80C2A5, CF6–80C2A5F, 

CF6–80C2A8, CF6–80C2B1, CF6– 

80C2B1F, CF6–80C2B1F1, CF6– 

80C2B1F2, CF6–80C2B2, CF6–80C2B2F, 

CF6–80C2B3F, CF6–80C2B4, CF6– 

80C2B4F, CF6–80C2B5F, CF6–80C2B6, 

CF6–80C2B6F, CF6–80C2B6FA, CF6– 

80C2B7F, CF6–80C2B8F, CF6– 

80C2D1F, CF6–80C2K1F, and CF6– 

80C2L1F turbofan engines, including 

engines marked on the engine data plate 

as CF6–80C2B7F1. This proposed AD 

was prompted by a report of a supplier 

shipping a batch of nonconforming No. 

3 bearing packings that had incorrect 

cooling holes, and by subsequent 

reports of nonconforming No. 3 bearing 

packings being installed on engines in 

service. This proposed AD would 

require a one-time inspection of the No. 

3 bearing packing for an incorrect 

cooling hole size and, if it is found 

nonconforming, removing the packing 

and removing certain engine rotating 

life-limited parts, if they were operated 

with the wrong packing for a specified 

number of cycles. We are proposing this 

AD to prevent an uncontained failure of 

the high-pressure compressor (HPC) 

rotor or the low-pressure turbine (LPT) 

rotor or both, which could cause 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 2, 2011. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact GE-Aviation 

M/D Rm. 285, One Neumann Way, 

Cincinnati, OH 45215, telephone 513– 

552–3272; e-mail: geae.aoc@ge.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 


srobinson on DSK4SPTVN1PROD with PROPOSALS