27282 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules 

inspections of the buttress threads in the 

propeller hub ports for cracks. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 2 propellers installed on 

one airplane of U.S. registry. We also 

estimate that it would take about 1 

work-hour per propeller to comply with 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $20,000 per 

propeller. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $40,170. 

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: 

Dowty Propellers (formerly Dowty 

Aerospace; Dowty Rotol Limited; and 

Dowty Rotol): Docket No. FAA–2011– 

0033; Directorate Identifier 2011–NE– 

01–AD. 

Comments Due Date 

(a) We must receive comments by June 27, 

2011. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Dowty Propellers 

type R212/4–30–4/22 propeller assemblies 

with hub and driving center assembly part 

number (P/N) 601022105, 601022211, 

601022294, 601021426, 601021858, or 

601021859 installed, and type R251/4–30–4/ 

49 propeller assemblies with hub and driving 

center assembly P/N 660207202 or P/N 

660207203 installed. 

Reason 

(d) 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. We are 

issuing this AD to prevent propeller hub 

failure due to cracks in the hub, which could 

result in damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following: 

(1) Within 500 flight hours after the 

effective date of this AD, and thereafter at 

intervals not exceeding 500 flight hours, 

inspect the buttress threads in the propeller 

hub and driving center assembly, for cracks. 

(2) Use paragraphs 2.A.(1) through 

2.A.(4)(a) of Accomplishment Instructions of 

Dowty Propellers Alert Service Bulletin No. 

61–1043, Revision 6, dated January 5, 2011, 

and NDT Technique NDT 175U (Appendix A 

of Dowty Propellers Alert Service Bulletin 

No. 61–1043, Revision 6, dated January 5, 

2011), to do the inspection. 

(3) If a crack is found, remove the propeller 

assembly from service before further flight. 

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

not install this propeller on any airplane 

unless the propeller hub and driving center 

has passed the inspections required by this 

AD. 

FAA AD Differences 

(f) This AD differs from the service 

information as follows: 

(1) Although the service bulletin tells you 

to return the affected parts to the 

manufacturer, this AD does not require that 

action. 

(2) Although the service bulletin tells you 

to submit information to the manufacturer, 

this AD does not require that action. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Boston Aircraft 

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 European Aviation 

Safety Agency AD 2011–0012, dated January 

20, 2011, and Dowty Propellers Alert Service 

Bulletin No. 61–1043, Revision 6, dated 

January 5, 2011, for related information. 

Contact Dowty Propellers, 114 Powers Court, 

Sterling, VA 20166, telephone (703) 421– 

4434; fax (703) 450–0087, for a copy of this 

service information. 

(i) Contact Michael Schwetz, Aerospace 

Engineer, Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA 01803; e-mail: michael.schwetz@faa.gov; 

telephone (781) 238–7761; fax (781) 238– 

7170, for more information about this AD. 

Issued in Burlington, Massachusetts, on 

April 28, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–11480 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0187; Directorate 

Identifier 2011–NE–07–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34–10E2A1; 

CF34–10E5, CF34–10E5A1; CF34– 

10E6; CF34–10E6A1; CF34–10E7; and 

CF34–10E7–B 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 with certain part 

number (P/N) fan rotor spinners 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules 27283 

installed. This proposed AD would 

require removing from service certain 

fan rotor blade retainers, and removing 

from service the fan rotor spinner 

support that was installed with those 

fan rotor blade retainers. This proposed 

AD was prompted by a fan rotor spinner 

support found cracked at the attachment 

lugs. We are proposing this AD to 

prevent high-cycle fatigue cracking of 

the fan rotor spinner support attachment 

lugs, leading to separation of the fan 

rotor spinner assembly, uncontained 

failure of the engine, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 27, 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 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 

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: 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. 

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– 

2011–0187; Directorate Identifier 2011– 

NE–07–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 

Investigation of a General Electric 

Company (GE) CF34–10E turbofan 

engine experiencing high fan frame 

vibrations led to removal of the fan rotor 

spinner. Eight of the twelve attachment 

lugs on the fan rotor spinner support 

were found cracked. The cause of the 

vibration was determined to be a nonsynchronous vibration induced by a 

spinner redesign that removed an 

interference between the fan blade 

retainers and the spinner. This 

condition, if not corrected, could result 

in high-cycle fatigue cracking of the fan 

rotor spinner support attachment lugs, 

leading to separation of the fan rotor 

spinner assembly, uncontained failure 

of the engine, and damage to the 

airplane. 

Relevant Service Information 

We reviewed GE Service Bulletin (SB) 

No. CF34–10E–S/B 72–0186, dated 

January 31, 2011. The SB describes 

procedures for replacement of the fan 

rotor blade retainers with redesigned 

retainers that reintroduce the 

interference between the fan blade 

retainers and the spinner. The SB also 

describes procedures for replacement of 

the fan rotor spinner support, with a 

new support of the same P/N. 

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 

removing from service fan rotor blade 

retainers, P/N 2050M56P02, and 

removing from service the fan rotor 

spinner support that was installed with 

those fan rotor blade retainers. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 164 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 2 

work-hours per engine to perform the 

actions required by this proposed AD, 

and that the average labor rate is $85 per 

work-hour. If all removed parts get 

replaced, required parts would cost 

about $10,458 per engine. Based on 

these figures, we estimate the total cost 

of the proposed AD to U.S. operators to 

be $1,742,992. 

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 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
27284 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Proposed Rules 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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– 

2011–0187; Directorate Identifier 2011– 

NE–07–AD. 

Comments Due Date 

(a) We must receive comments by June 27, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF34–10E2A1; CF34–10E5, 

CF34–10E5A1; CF34–10E6; CF34–10E6A1; 

CF34–10E7; and CF34–10E7–B turbofan 

engines, with a fan rotor spinner part number 

(P/N) 2050M34G03; 2050M34G04; 

2050M34G05; 2050M34G06; 2437M60G01; or 

2437M60G02, installed. 

Unsafe Condition 

(d) This AD was prompted by a fan rotor 

spinner support found cracked at the 

attachment lugs. We are issuing this AD to 

prevent high-cycle fatigue cracking of the fan 

rotor spinner support attachment lugs, 

leading to separation of the fan rotor spinner 

assembly, uncontained failure of the engine, 

and damage to the airplane. 

Compliance 

(e) Comply with this AD within 1,800 

hours-in-service after the effective date of 

this AD, unless already done. 

Removal of Fan Rotor Blade Retainers 

(f) Remove from service the 24 fan rotor 

blade retainers, P/N 2050M56P02. 

Removal of Fan Rotor Spinner Support 

(g) Remove from service the fan rotor 

spinner support that operated with the fan 

rotor blade retainers removed in paragraph (f) 

of this AD. 

Installation Prohibition 

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

not install any fan rotor blade retainer, P/N 

2050M56P02, into any engine. Do not 

attempt to repair, make serviceable, or reinstall, this part. 

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

not install any fan rotor spinner support 

removed in paragraph (g) of this AD, into any 

engine. Do not attempt to repair, make 

serviceable, or re-install, this part. 

Alternative Methods of Compliance 

(AMOCs) 

(j) 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 

(k) 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. 

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

10E–S/B 72–0186, dated January 31, 2011, for 

related information. Contact GE-Aviation, 

M/D Rm. 285, One Neumann Way, 

Cincinnati, OH 45215, telephone 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 

April 28, 2011. 

Peter A. White, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–11481 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 100 

[Docket No. USCG–2011–0211] 

RIN 1625–AA08 

Special Local Regulation; Partnership 

in Education, Dragon Boat Race; 

Maumee River, Toledo, OH 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes 

establishing a permanent Special Local 

Regulation on the Maumee River, 

Toledo, Ohio. This regulation is 

intended to restrict vessels from 

portions of the Maumee River during 

the Dragon Boat Races which take place 

during the third or fourth weekend in 

July each year. This special local 

regulated area is necessary to protect 

race participants from other vessel 

traffic. 

DATES: Comments and related material 

must be received by the Coast Guard on 

or before June 10, 2011. 

ADDRESSES: You may submit comments 

identified by docket number USCG– 

2011–0211 using any one of the 

following methods: 

(1) Federal eRulemaking Portal: 

http://www.regulations.gov. 

(2) Fax: 202–493–2251. 

(3) Mail: Docket Management Facility 

(M–30), U.S. Department of 

Transportation, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590– 

0001. 

(4) Hand delivery: Same as mail 

address above, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The telephone number 

is 202–366–9329. 

To avoid duplication, please use only 

one of these four methods. See the 

‘‘Public Participation and Request for 

Comments’’ portion of the 

SUPPLEMENTARY INFORMATION section 

below for instructions on submitting 

comments. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this proposed 

rule, call or e-mail BM1 Tracy Girard, 

Response Department, MSU Toledo, 

Coast Guard; telephone (419) 418–6036, 

e-mail Tracy.M.Girard@uscg.mil. If you 

have questions on viewing or submitting 

material to the docket, call Renee V. 

Wright, Program Manager, Docket 

Operations, telephone 202–366–9826. 

SUPPLEMENTARY INFORMATION: 

Public Participation and Request for 

Comments 

We encourage you to participate in 

this rulemaking by submitting 

comments and related materials. All 

comments received will be posted 

without change to http:// 

www.regulations.gov and will include 

any personal information you have 

provided. 

Submitting Comments 

If you submit a comment, please 

include the docket number for this 

rulemaking (USCG–2011–0211), 

indicate the specific section of this 

document to which each comment 

applies, and provide a reason for each 

suggestion or recommendation. You 

may submit your comments and 

material online (via http:// 

www.regulations.gov) or by fax, mail, or 

hand delivery, but please use only one 

of these means. If you submit a 

comment online via 

www.regulations.gov, it will be 

considered received by the Coast Guard 

when the comment is successfully 


emcdonald on DSK2BSOYB1PROD with PROPOSALS