30018 Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 

hour. Required parts would cost about 

$12,943 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$20,836,800. 

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 AD: 

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. Would 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. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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: 

Rolls-Royce Corporation (formerly Allison 

Engine Company): Docket No. FAA– 

2009–0246; Directorate Identifier 2009– 

NE–04–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

August 24, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (RRC) AE 3007A1/1, AE 

3007A1/3, AE 3007A1, AE 3007A1E, AE 

3007A1P, AE 3007A3, AE 3007C, and AE 

3007C1 turbofan engines with a fan spinner 

part number (P/N) 23070964 or P/N 

23078783, installed. These engines are 

installed on, but not limited to, Embraer 

EMB–135, EMB–145, and Cessna Citation X 

airplanes. 

Unsafe Condition 

(d) This AD results from a report of a fan 

spinner releasing from an AE 3007A turbofan 

engine during flight. We are issuing this AD 

to prevent the fan spinner from releasing, 

which could result in injury, damage to the 

engine, and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Replacement of the Fan Spinner 

(f) For RRC AE 3007A1/1, AE 3007A1/3, 

AE 3007A1, AE 3007A1E, AE 3007A1P, and 

AE 3007A3 turbofan engines, remove fan 

spinner P/N 23070964 or P/N 23078783 at 

the next shop visit, but no later than 1,500 

additional cycles-in-service (CIS) after the 

effective date of this AD. 

(g) For RRC AE 3007C and AE 3007C1 

turbofan engines, remove fan spinner P/N 

23070964 or P/N 23078783 at the next shop 

visit, but no later than 1,500 additional CIS 

after the effective date of this AD. 

Fan Spinner Installation Prohibition 

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

not install any fan spinner P/N 23070964 or 

P/N 23078783 on any Rolls Royce 

Corporation engine. 

Definition 

(i) For the purpose of this AD, a shop visit 

is induction of the engine into the engine 

maintenance shop for any cause. 

Alternative Methods of Compliance 

(j) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(k) Contact Michael Downs, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 East Devon Avenue, Des Plaines, IL 

60018; e-mail: michael.downs@faa.gov; 

telephone: (847) 294–7870; fax: (847) 294– 

7834, for more information about this AD. 

(l) Rolls-Royce Corporation Service 

Bulletin (SB) No. AE 3007A–72–361, dated 

June 26, 2008, and SB No. AE 3007C–72–285, 

dated June 26, 2008, pertain to the subject of 

this AD. Contact Rolls-Royce Corporation, 

P.O. Box 420, Indianapolis, IN 46206; 

telephone (317) 230–3774; fax (317) 230– 

8084; e-mail: indy.pubs.services@rollsroyce.com, for a copy of this service 

information. 

Issued in Burlington, Massachusetts, on 

June 17, 2009. 

Carlos Pestana, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14812 Filed 6–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24171; Directorate 

Identifier 2006–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–50C Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to revise 

an existing airworthiness directive (AD) 

for General Electric Company (GE) CF6– 

50C series turbofan engines. That AD 

currently requires reworking certain 

forward fan stator cases and installing a 

fan module secondary containment 

shield. This proposed AD would require 

the same actions but would eliminate a 

certain service bulletin from the 

compliance method. This proposed AD 

results from a review that shows that 

only one of the service bulletins 

referenced in the original AD is 

applicable as a compliance method. We 

are proposing this AD revision to 

prevent uncontained fan blade failures, 

which can result in separation of 

Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 30019 

airplane hydraulic lines, damage to 

critical airplane systems, and possible 

loss of airplane control. 

DATES: We must receive any comments 

on this proposed AD by August 24, 

2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• 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. 

FOR FURTHER INFORMATION CONTACT: 

James Rosa, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: james.rosa@faa.gov; telephone 

(781) 238–7152; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2006–24171; Directorate Identifier 

2006–NE–08–AD’’ in the subject line 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 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). 

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. 

Discussion 

On May 22, 2007, we issued AD 

2007–11–18, Amendment 39–15075 (72 

FR 30249, May 31, 2007). That AD 

requires reworking certain forward fan 

stator cases and installing a fan module 

secondary containment shield. That AD 

resulted from reports of uncontained fan 

blade failures. That condition, if not 

corrected, could result in separation of 

airplane hydraulic lines, damage to 

critical airplane systems, and possible 

loss of airplane control due to 

uncontained fan blade failures. 

Actions Since AD 2007–11–18 Was 

Issued 

Since AD 2007–11–18 was issued, we 

determined that we don’t need GE 

Service Bulletin No. CF6–50 S/B 72– 

0986, Revision 2, dated March 21, 2007, 

applicable to DC–10 series aircraft, in 

order to satisfy our corrective action 

requirements. Accordingly, this 

proposed AD deletes this SB as a 

required corrective action. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. For this reason, we are 

proposing this AD revision, which 

would require reworking certain 

forward fan stator cases and installing a 

fan module secondary containment 

shield on Airbus A300 series airplanes, 

and would eliminate GE Service 

Bulletin No. CF6–50 S/B 72–0986, 

Revision 2, dated March 21, 2007. The 

proposed AD would require that you do 

the rework and installations using GE 

Service Bulletin No. CF6–50 S/B 72– 

0985, Revision 2, dated March 21, 2007 

only. 

Costs of Compliance 

We estimate that this AD would affect 

40 CF6–50C series turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 2.5 work hours per engine to 

perform the actions, and that the 

average labor rate is $80 per work hour. 

Required parts would cost about $9,451 

per engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $386,040. 

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 AD: 

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. Would 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. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

30020 Federal Register / Vol. 74, No. 120 / Wednesday, June 24, 2009 / Proposed Rules 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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 Amendment 39–15075 (72 FR 

30249, May 31, 2007), and by adding a 

new airworthiness directive, to read as 

follows: 

General Electric Company: Docket No. FAA– 

2006–24171; Directorate Identifier 2006– 

NE–08–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

August 24, 2009. 

Affected ADs 

(b) This AD revises AD 2007–11–18, 

Amendment 39–15075. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–50C, CF6–50C1, CF6– 

50C2, and CF6–50C2R turbofan engines, with 

a forward fan stator case, part number (P/N) 

9064M53G04, G05, G06, G07, G08, G09, G10, 

G12, or G13, or P/N 9173M37G01, G02, G03, 

G04, G05, or G06 installed. These engines are 

installed on, but not limited to, Airbus A300, 

McDonnell Douglas DC–10 series, and DC– 

10–30F (KC–10A, KDC–10) airplanes. 

Unsafe Condition 

(d) This AD revision results from a review 

that shows that only one of the service 

bulletins referenced in the original AD is 

applicable as a compliance method. We are 

issuing this AD to prevent uncontained fan 

blade failures, which can result in separation 

of airplane hydraulic lines, damage to critical 

airplane systems, and possible loss of 

airplane control. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) At the next engine shop visit after the 

effective date of this AD, but no later than 

June 30, 2010, rework the forward fan stator 

case and install the fan module secondary 

containment shield. 

(1) For engines on Airbus 300 series 

airplanes, use paragraph 3, Accomplishment 

Instructions, of GE Service Bulletin (SB) No. 

CF6–50 S/B 72–0985, Revision 2, dated 

March 21, 2007, to do the rework and 

installation. 

(2) Deleted. 

(g) The rework and installation specified in 

paragraph (f)(1) of this AD can also be done 

on-wing. 

Previous Credit 

(h) Previous credit is allowed for fan stator 

cases reworked and containment shields 

installed using GE SB No. CF6–50 S/B 72– 

0985, dated December 2, 1991 or Revision 1, 

dated September 15, 1998 before the effective 

date of this AD. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) European Aviation Safety Agency 

airworthiness directive 2004–0007, dated 

December 15, 2004, also addresses the 

subject of this AD. 

(k) Contact James Rosa, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.rosa@faa.gov; telephone 

(781) 238–7152; fax (781) 238–7199, for more 

information about this AD. 

(l) Contact General Electric Company via 

Lockheed Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax (513) 

672–8422, for a copy of the service 

information referenced in this AD. 

Issued in Burlington, Massachusetts, on 

June 17, 2009. 

Carlos Pestana, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–14815 Filed 6–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0143; Directorate 

Identifier 2009–NE–05–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company GE90–110B1, GE90– 

113B, and GE90–115B Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

General Electric Company (GE) GE90– 

110B1, GE90–113B, and GE90–115B 

series turbofan engines with stage 6 lowpressure turbine (LPT) blades, part 

number (P/N) 1765M37P03 or P/N 

1765M37P04, installed. This proposed 

AD would require initial and repetitive 

inspections for shroud interlock wear of 

the stage 6 LPT blades. This proposed 

AD would also require replacing those 

blades with stage 6 LPT blades eligible 

for installation at the next engine shop 

visit as terminating action to the 

repetitive blade inspections. This 

proposed AD results from eight reports 

of GE90–115B stage 6 LPT single-blade 

separation events. We are proposing this 

AD to prevent failure of stage 6 LPT 

blades, which could result in 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive any comments 

on this proposed AD by August 24, 

2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• 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 General Electric Company via 

GE—Aviation, Attn: Distributions, 111 

Merchant St., Room 230, Cincinnati, 

Ohio 45246; telephone (513) 552–3272; 

fax (513) 552–3329, for a copy of the 

service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: barbara.caufield@faa.gov; 

telephone (781) 238–7146; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2009–0143; Directorate Identifier 2009– 

NE–05–AD’’ in the subject line 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