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
64292 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 

docket contains this proposed 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: 

Tomasz Rakowski, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7735; fax: 781–238– 

7199; e-mail: tomasz.rakowski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0982; Directorate Identifier 2011– 

NE–09–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 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 proposed AD. 

Discussion 

We received a report that a supplier 

shipped a batch of nonconforming No. 

3 bearing packings, part number (P/N) 

1292M70P04, with undersized cooling 

holes. The No. 3 bearing packing design 

did not feature permanent part markings 

and parts could be confused when being 

installed. After GE changed the design 

to introduce part marking on all newmade parts and added secondary 

inspections to the CF6–80C2 engine 

manual section 72–23–00 Fan Frame 

Assembly, customers reported several 

nonconforming No. 3 bearing packings, 

various P/Ns, found installed on engines 

in-service outside of the known 

population of engines affected by the 

quality escape. The nonconformance of 

No. 3 bearing packings will result in 

incorrect HPC and LPT rotor bore 

cooling and, if not corrected, could 

result in a reduced parts life of the lifelimited HPC rotor stage 10-through-stage 

14 spool, the HPC rotor stage 11- 

through-stage 14 spool, the LPT rotor 

stage 3 disk, and the LPT rotor stage 4 

disk. Because the problem exists beyond 

the known population of engines 

affected by the quality escape and the 

consequences represent an unsafe 

condition in all affected engines in 

service, it is necessary to inspect the No. 

3 bearing packing configuration of the 

entire fleet. This condition, if not 

corrected, could result in failure of the 

HPC rotor or the LPT rotor or both, 

which could cause uncontained engine 

failure and damage to the airplane. 

Relevant Service Information 

We reviewed GE Service Bulletin (SB) 

CF6–80C2 S/B 72–1405, dated June 30, 

2011. The SB describes procedures for 

inspecting and removing the 

nonconforming No. 3 bearing packing, 

and determining the effect of 

nonconforming packing on the HPC and 

LPT rotor bore cooling. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require: 

• A one-time inspection of the No. 3 

bearing packing at the next engine shop 

visit, but not later than 5,500 cycles-inservice (CIS) since the last engine shop 

visit where the fan was removed from 

the core. 

• Removing the No. 3 bearing packing 

if it is found to be nonconforming 

within the above specified times. 

• Removing certain rotating parts if 

they have operated more than 5,500 CIS 

with the wrong packing configuration. 

Differences Between the Proposed AD 

and the Service Information 

This proposed AD includes CF6 

engine models CF6–80C2B1F1, CF6– 

80C2B1F2, CF6–80C2B3F, and CF6– 

C2B7F1 in the Applicability paragraph 

(c). The GE service information does not 

include these engine models. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 688 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 1 

work-hour per engine to perform the 

inspection and 1 work-hour to replace 

the No. 3 bearing packing, if found 

nonconforming. The average labor rate 

is $85 per work-hour. Required parts 

would cost about $488 per engine to 

replace an anticipated quantity of 21 

No. 3 bearing packings. Based on these 

figures, we estimate the total cost of this 

proposed AD to U.S. operators to be 

$70,513. GE has informed us that they 

may cover these costs under warranty. 

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), 

(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: 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64293 

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 (GE): Docket No. 

FAA–2011–0982; Directorate Identifier 

2011–NE–09–AD. 

(a) Comments Due Date 

We must receive comments by December 2, 

2011. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD is applicable to 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. 

(d) Unsafe Condition 

This AD was prompted by a report of a 

supplier shipping a batch of nonconforming 

No. 3 bearing packings that had an incorrect 

size of cooling holes and by several 

subsequent reports of nonconforming No. 3 

bearing packings being installed on engines 

in service. The nonconformance of No. 3 

bearing packings will result in incorrect highpressure compressor (HPC) rotor and lowpressure turbine (LPT) rotor bore cooling 

and, if not corrected, could result in a 

reduced parts life of the life-limited rotating 

parts. We are issuing 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. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) One-Time Inspection of the No. 3 Bearing 

Packing and Disposition of Affected Rotating 

Parts 

(1) Perform a one-time inspection of the 

No. 3 bearing packing at the next engine shop 

visit, but not later than 5,500 cycles-inservice (CIS) since the last engine shop visit, 

where the fan was removed from the core. 

Use paragraphs 3.A.(1) through 3.A.(1).(a) of 

the Accomplishment Instructions of GE 

Service Bulletin (SB) No. CF6–80C2 S/B 72– 

1405, dated June 30, 2011. 

(2) If the packing part number (P/N) is 

determined not eligible for installation on the 

engine, then before further flight: 

(i) Remove the nonconforming packing 

from service; and 

(ii) Remove the following rotating parts 

from service, if they were operated for 5,500 

CIS or more with a packing determined to be 

other than a ‘‘CORRECT FLOW’’ packing 

using paragraph 3.A.(1).(b) of the 

Accomplishment Instructions of SB No. CF6– 

80C2 S/B 72–1405, dated June 30, 2011: 

(A) HPC rotor stage 10-through-14 spool, 

any P/N, 

(B) HPC rotor stage 11-through-14 spool, 

any P/N, 

(C) LPT rotor stage 3 disk, P/N 

9373M53P05, and 

(D) LPT rotor stage 4 disk, P/N 

9373M54P03. 

(g) Definition 

For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop after the effective date of this AD, 

where the separation of a major engine flange 

occurs; except the following maintenance 

actions, or any combination, are not 

considered engine shop visits: 

(1) Introduction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance or 

variable stator vane bushing replacement. 

(2) Introduction of an engine into a shop 

solely for replacement of the turbine rear 

frame. 

(3) Introduction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7735; fax: 781–238– 

7199; e-mail: tomasz.rakowski@faa.gov. 

(2) For service information identified in 

this AD, contact GE-Aviation M/D Rm. 285, 

One Neumann Way, Cincinnati, OH 45215, 

phone 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, 

01803. 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. 2011–26825 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–2011–0946; Directorate 

Identifier 2011–NE–02–AD] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S. A. Model CFM56–5B 

Series 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 the 

products listed above. This proposed 

AD would require removing from 

service certain serial number (S/N) fan 

blades, part number (P/N) 338–002– 

114–0. This proposed AD was prompted 

by a normal quality sampling at CFM 

that isolated a production batch of fan 

blades with nonconforming geometry of 

mid-span shroud tips of the fan blades. 

This defect would cause the upper 

panel of the fan blade to be liberated 

following foreign object damage (FOD) 

or bird strike, and likely result in an 

inflight shutdown (IFSD). We are 

proposing this AD to prevent an IFSD of 

one or more engines following FOD or 

a bird strike. 

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. 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 CFM 

International, Inc., Aviation Operations 

Center, 1 Neumann Way, M/D Room 

285, Cincinnati, OH 45125; 

International Phone: 1–513–552–3272; 

USA Phone: 877–432–3272; 

International Fax: 1–513–552–3329; 

USA Fax: 877–432–3329; e-mail: 

geae.aoc@ge.com; or CFM International 

SA, Customer Support Center, 

International Phone: 33 1 64 14 88 66; 

Fax: 33 1 64 79 85 55; e-mail: 

snecma.csc@snecma.fr. 


srobinson on DSK4SPTVN1PROD with PROPOSALS