15896 Federal Register / Vol. 74, No. 66 / Wednesday, April 8, 2009 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0328; Directorate 

Identifier 2008–NE–44–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF34–1A, 

CF34–3A, and CF34–3B 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 GE 

CF34–1A, CF34–3A, and CF34–3B 

series turbofan engines. This proposed 

AD would require: Removing from 

service certain part number (P/N) and 

serial number (SN) fan blades within 

compliance times specified in this 

proposed AD, inspecting the fan blade 

abradable rub strip on certain engines 

for wear, inspecting the fan blades on 

certain engines for cracks, and 

inspecting the aft actuator head hose 

fitting for correct position, and if 

necessary repositioning. This proposed 

AD results from a report of an undercowl fire, and a failed fan blade. We are 

proposing this AD to prevent failure of 

certain P/N and SN fan blades and aft 

actuator head hoses, which could result 

in an under-cowl fire and subsequent 

damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by June 8, 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. 

You can get the service information 

identified in this proposed AD from 

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 FURTHER INFORMATION CONTACT: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: kenneth.steeves@faa.gov; 

telephone (781) 238–7765; 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– 

2009–0328; Directorate Identifier 2008– 

NE–44–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 

We have received reports of certain P/ 

N and SN fan blades failing on CF34 

series engines. The first failure also 

included an under-cowl fire that caused 

extensive damage to the engine. 

Although we haven’t been able to 

determine the exact cause of the undercowl fire because of the thermal 

damage, the investigation revealed two 

problems; a fan blade failed at the 

platform tang and the aft actuator head 

hose failed. The investigation also 

revealed that the accessory gearbox had 

separated from the engine, possibly 

contributing to the actuator hose failure. 

We traced the failed fan blades to a 

specific supplier and their billet 

material. The investigation found that 

the billet alloy material met 

specifications and the supplier’s 

approved processes were different from 

other suppliers’ approved processes. 

The differences allowed a larger area of 

aligned alpha colonies to form in the 

tang region of the fan blade. If the alpha 

colonies align, they can cause cracks in 

the blade tang. Although the material 

was within specification, and the 

processes and billet size conformed to 

the engineering drawings for the blades, 

GE determined that the material, 

process, and billet size combined to 

allow the alpha colonies to align. The 

investigation also found that although 

the aft actuator hose is designed to 

include enough slack to prevent its 

failure if the gearbox separates from the 

engine, the incorrect orientation of the 

aft actuator head hose fitting at the main 

fuel control removed that slack. The 

incorrect position of the fitting might 

have caused the hose to fail and 

contribute to fire. 

This condition, if not corrected, could 

result in failure of certain P/N and SN 

fan blades and aft actuator head hoses, 

which could result in an under-cowl fire 

and subsequent damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of the following GE 

Aircraft Engines Service Bulletins (SBs): 

• CF34–AL S/B 73–0046, Revision 02, 

dated August 27, 2008, and CF34–BJ S/ 

B 73–0062, Revision 02, dated August 

27, 2008, that provide instructions for 

inspecting the orientation of the aft 

actuator hose assembly and the main 

fuel control. 

• CF34–AL S/B 72–0245, Revision 01, 

dated July 3, 2008, CF34–BJ S/B 72– 

0229, Revision 01, dated July 30, 2008, 

and CF34–BJ S/B 72–0230, Revision 01, 

dated July 30, 2008, that provide 

instructions for replacing certain 

existing blades, P/Ns 6018T30P14 and 

4923T56G08, that have a SN listed in 

Appendix A of those SBs. 

• CF34–AL S/B 72–0250, Revision 01, 

dated November 26, 2008, and CF34–BJ 

S/B 72–0231, Revision 02, dated 

November 26, 2008, that provide 

instructions for inspecting the fan case 

abradable rub strip and fan blade tangs. 


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Federal Register / Vol. 74, No. 66 / Wednesday, April 8, 2009 / Proposed Rules 15897 

Differences Between the Proposed AD 

and the Manufacturer’s Service 

Information 

• Service Bulletin CF34–AL S/B 73– 

0046, Revision 02, dated August 27, 

2008 recommends performing the 

inspection at the next ‘‘A’’ check, but no 

later than 750 hours time-in-service 

(TIS). This proposed AD would require 

performing the inspection within 750 

hours TIS after the effective date of the 

proposed AD. 

• Service Bulletin CF34–BJ S/B 73– 

0062, Revision 02, dated August 27, 

2008, recommends performing the 

inspection of the CF34–3A1 engines at 

the next scheduled 300 hour check, but 

no later than 600 hours. This proposed 

AD would require performing the 

inspection within 300 hours TIS after 

the effective date of the proposed AD. 

• Service Bulletin CF34–BJ S/B 73– 

0062, Revision 02, dated August 27, 

2008, recommends performing the 

inspection of the CF34–3B engines at 

the next scheduled 400 hour check but 

no later than 800 hours TIS. This 

proposed AD would require performing 

the inspection within 400 hours TIS 

after the effective date of the proposed 

AD. 

• Service Bulletin CF34–AL S/B 72– 

0250, Revision 01, dated November 26, 

2008, recommends inspection of the fan 

blades if there is a continuous 360 

degree rub indication. This proposed 

AD would require the inspection of the 

fan blades if there is a continuous 360 

degree rub indication. The service 

bulletin also contains an alternate 

compliance method using GE’s remote 

diagnostics trend monitoring program. 

This proposed AD does not include that 

alternate method. 

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. We are proposing this AD, 

which would require: 

• Removing from service certain P/N 

and SN blades within compliance times 

specified in this proposed AD. 

• Inspecting the fan blade abradable 

rub strip on certain engines for wear. 

• Inspecting the fan blades on certain 

engines for cracks. 

• Inspecting the aft actuator head 

hose fitting for correct position, and if 

necessary, repositioning. 

The proposed AD would require you 

to use the service information described 

previously to perform these actions. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 1,966 engines installed on 

airplanes of U.S. registry. We estimate 

that the fan blade inspection and 

replacement requirement would affect 

300 of these engines, and the actuator 

head hose inspection would affect 1,662 

engines. We also estimate that it would 

take 0.5 work-hour per engine to inspect 

the fan blade abradable rub strip, 6 

work-hours per engine to visually 

inspect the fan blades, 11 work-hours 

per engine to perform an eddy current 

inspection of the fan blades, and 0.25 

work-hour per engine to inspect the 

actuator head hose fitting, and that the 

average labor rate is $80 per work-hour. 

Required parts would cost $51,106,600. 

Based on these figures, we estimate the 

total cost of the proposed AD to U.S. 

operators to be $51,184,000. 

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. 

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: 

General Electric Company: Docket No. FAA– 

2009–0328; Directorate Identifier 2008– 

NE–44–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by June 8, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF34–1A, CF34–3A, CF34– 

3A1, CF34–3A2, CF34–3B, and CF34–3B1 

turbofan engines. These engines are installed 

on, but not limited to, Bombardier Canadair 

Models CL–600–2A12, CL–600–2B16, and 

CL–600–2B19 airplanes. 

Unsafe Condition 

(d) This AD results from a report of an 

under-cowl fire, and a failed fan blade. We 

are issuing this AD to prevent failure of 

certain part number (P/N) and serial number 

(SN) fan blades and aft actuator head hoses, 

which could result in an under-cowl fire and 

subsequent 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. 

CF34–3A1 and CF34–3B1 Engines 

(f) For CF34–3A1 engines with fan drive 

shaft, P/N 6036T78P02, and airworthiness 

limitation section life limit of 22,000 CSN, 

and CF34–3B1 engines with fan blades, P/Ns 

6018T30P14 or 4923T56G08, that have a fan 


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15898 Federal Register / Vol. 74, No. 66 / Wednesday, April 8, 2009 / Proposed Rules 

blade SN listed in Appendix A of GE Aircraft 

Engines (GEAE) Service Bulletin (SB) CF34– 

AL S/B 72–0245, Revision 01, dated July 3, 

2008, do the following: 

(1) Remove fan blades from service within 

4,000 cycles-in-service (CIS) after the 

effective date of this AD or by December 31, 

2010, whichever occurs first. 

Initial Visual Inspection of the Fan Blade 

Abradable Rub Strip for Wear 

(2) For fan blades with 1,200 or more 

cycles-since-new (CSN) on the effective date 

of this AD, within 20 CIS after the effective 

date of this AD, perform an initial visual 

inspection of the fan blade abradable rub 

strip for wear. Use paragraphs 3.A.(1) 

through 3.A.(2) of the Accomplishment 

Instructions of GEAE SB CF34–AL S/B 72– 

0250, Revision 01, dated November 26, 2008, 

to perform the inspection. 

(3) For fan blades with fewer than 1,200 

CSN on the effective date of this AD, within 

1,220 CSN, perform an initial visual 

inspection of the fan blade abradable rub 

strip for wear. Use paragraphs 3.A.(1) 

through 3.A.(2) of the Accomplishment 

Instructions of GEAE SB CF34–AL S/B 72– 

0250, Revision 01, dated November 26, 2008, 

to perform the inspection. 

(4) If you find a continuous 360 degree rub 

indication, before further flight, visually 

inspect the fan blades using paragraphs 

3.A.(2)(a) through 3.A.(2)(b) of the 

Accomplishment Instructions of GEAE SB 

CF34–AL S/B 72–0250, Revision 01, dated 

November 26, 2008, to perform the 

inspection. 

(5) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Repetitive Visual Inspection of the Fan 

Blade Abradable Rub Strip for Wear 

(6) Within 75 cycles-since-last inspection 

(CSLI) or 100 hours-since-last-inspection 

(HSLI), whichever occurs later, perform a 

visual inspection of the fan blade abradable 

rub strip for wear. Use paragraphs 3.A.(1) 

through 3.A.(2) of the Accomplishment 

Instructions of GEAE SB CF34–AL S/B 72– 

0250, Revision 01, dated November 26, 2008, 

to perform the inspection. 

(i) If you find a continuous 360 degree rub 

indication, before further flight, visually 

inspect the fan blades using paragraphs 

3.A.(2)(a) through 3.A.(2)(b) of the 

Accomplishment Instructions of GEAE SB 

CF34–AL S/B 72–0250, Revision 01, dated 

November 26, 2008, to perform the 

inspection. 

(ii) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Inspection of the Aft Actuator Head Hose 

Fitting on CF34–3A1 and CF34–3B1 Engines 

(7) Within 750 hours time in service (TIS) 

after the effective date of this AD, visually 

inspect and, if necessary, reposition the aft 

actuator head hose fitting. Use paragraph 3.A 

of the Accomplishment Instructions of GEAE 

SB CF34–AL S/B 73–0046, Revision 02, 

dated August 27, 2008, to perform the 

inspection. 

CF34–1A, CF34–3A, CF34–3A2, CF34–3B, 

and CF34–3A1 Engines 

(g) For CF34–3A1 engines with fan drive 

shaft, P/N 6036T78P02, and airworthiness 

limitation section life limit of 15,000 CSN, 

and CF34–1A, CF34–3A, CF34–3A2, and 

CF34–3B engines with fan blades, P/N 

6018T30P14 or P/N 4923T56G08, that have a 

fan blade SN listed in Appendix A of GEAE 

SB CF34–BJ S/B 72–0229, Revision 01, dated 

July 30, 2008, do the following: 

(1) Remove fan blades, P/N 6018T30P14, 

from service within 2,400 CSN. 

(2) Remove fan blades, P/N 4923T56G08, 

from service within 1,200 CIS since the 

bushing repair of the fan blade hole. 

Initial Eddy Current Inspection of the Fan 

Blades 

(3) For fan blades, P/N 6018T30P14, with 

more than 850 CSN, but fewer than 1,200 

CSN on the effective date of this AD, within 

350 CIS after the effective date of this AD, 

perform an initial eddy current inspection 

(ECI) of the fan blades for cracks. Use 

paragraphs 3.A. or 3.B. of the 

Accomplishment Instructions of GEAE SB 

CF34–BJ S/B 72–0229, Revision 01, dated 

July 30, 2008, to perform the inspection. 

(4) For fan blades, P/N 6018T30P14, with 

850 or fewer CSN on the effective date of this 

AD, within 1,200 CSN, perform an initial ECI 

of the fan blades for cracks. Use paragraphs 

3.A. or 3.B. of the Accomplishment 

Instructions of GEAE SB CF34–BJ S/B 72– 

0229, Revision 01, dated July 30, 2008, to 

perform the inspection. 

(5) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Repetitive ECI of the Fan Blades 

(6) For fan blades, P/N 6018T30P14, 

installed, within 600 CSLI, perform an ECI of 

the fan blades for cracks. Use paragraphs 3.A. 

or 3.B. of the Accomplishment Instructions of 

GEAE SB CF34–BJ S/B 72–0229, Revision 01, 

dated July 30, 2008, to perform the 

inspection. 

(7) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Initial Visual Inspection of the Fan Blade 

Abradable Rub Strip for Wear 

(8) For engines with fan blades, P/N 

6018T30P14, installed that have a fan blade 

SN listed in Appendix A of GEAE SB CF34– 

BJ S/B 72–0229, Revision 01, dated July 30, 

2008, with 1,200 or more CSN on the 

effective date of this AD, that haven’t had an 

ECI of the fan blades for cracks, do the 

following: 

(i) Perform an initial inspection of the fan 

blade abradable rub strip for wear within 20 

CIS after the effective date of this AD. Use 

paragraph 3.A.(1) of the Accomplishment 

Instructions of GEAE SB CF34–BJ S/B 72– 

0231, Revision 02, dated November 26, 2008, 

to perform the inspection. 

(ii) If you find a continuous 360 degree rub 

indication, before further flight, perform a 

visual inspection of the fan blades for cracks. 

Use paragraphs 3.A(2)(a) or 3.A(2)(b) of the 

Accomplishment Instructions of GEAE SB 

CF34–BJ S/B 72–0231, Revision 02, dated 

November 26, 2008, to perform the 

inspection. 

(iii) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Repetitive Inspection of the Fan Blade 

Abradable Rub Strip for Wear 

(9) For engines with fan blades, P/N 

6018T30P14, installed, if you have performed 

an ECI of the fan blade, you don’t need to 

inspect the fan blade abradable rub strip for 

wear. 

(10) For engines with fan blades, P/N 

6018T30P14, installed, within 75 CSLI or 100 

HSLI, whichever occurs later, do the 

following: 

(i) Perform a visual inspection of the fan 

blade abradable rub strip for wear. Use 

paragraph 3.A.(1) of the Accomplishment 

Instructions of GEAE SB CF34–BJ S/B 72– 

0231, Revision 02, dated November 26, 2008, 

to perform the inspection. 

(ii) If you find a continuous 360 degree rub 

indication, before further flight, visually 

inspect the fan blades using paragraphs 

3.A.(2)(a) through 3.A.(2)(b) of the 

Accomplishment Instructions of GEAE SB 

CF34–BJ S/B 72–0231, Revision 02, dated 

November 26, 2008. 

(iii) If you find a crack in the retaining pin 

holes of the fan blade, remove the blade from 

service. 

Inspection of the Aft Actuator Head Hose 

Fitting on CF34–3A1 and CF34–3B Engines 

(11) For CF34–3A1 engines, within 300 

hours TIS after the effective date of this AD, 

visually inspect and, if necessary, reposition 

the aft actuator head hose fitting. Use 

paragraph 3.A of the Accomplishment 

Instructions of GEAE SB CF34–BJ S/B 73– 

0062, Revision 02, dated August 27, 2008, to 

perform the inspection. 

(12) For CF34–3B engines, within 400 

hours TIS after the effective date of this AD, 

visually inspect and if necessary, reposition 

the aft actuator head hose fitting. Use 

paragraph 3.A of the Accomplishment 

Instructions of GEAE SB CF34–BJ S/B 73– 

0062, Revision 02, dated August 27, 2008, to 

perform the inspection. 

Credit for Previous Actions 

(h) Inspections previously performed using 

the following GEAE SBs meet the 

requirements specified in the indicated 

paragraphs: 

(1) CF34–AL S/B 72–0250, dated August 

15, 2008, meet the requirements specified in 

paragraphs (f)(2) through (f)(4) of this AD. 

(2) CF34–AL S/B 73–0046, Revision 01, 

dated July 1, 2008, or earlier issue, meet the 

requirements specified in paragraph (f)(7) of 

this AD. 

(3) CF34–BJ S/B 72–0229, dated April 10, 

2008, meet the requirements specified in 

paragraphs (g)(3) and (g)(4) of this AD. 

(4) CF34–BJ S/B 72–0231, Revision 01, 

dated October 1, 2008, or earlier issue, meet 

the requirements specified in paragraphs 

(g)(10)(i) and (g)(10)(ii) of this AD. 

(5) CF34–BJ S/B 73–0062, Revision 01, 

dated July 1, 2008, or earlier issue, meet the 

requirements specified in paragraphs (g)(11) 

and (g)(12) of this AD. 


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Federal Register / Vol. 74, No. 66 / Wednesday, April 8, 2009 / Proposed Rules 15899 

Installation Prohibitions 

(i) After the effective date of this AD: 

(1) Do not install any fan blade into any 

CF34–3A1 engine with fan drive shaft, P/N 

6036T78P02, with an airworthiness 

limitation section life limit of 22,000 CSN if 

that fan blade: 

(i) Was installed in a CF34–3A1 engine 

with fan drive shaft, P/N 6036T78P02, with 

an airworthiness limitation section life limit 

of 15,000 CSN; and 

(ii) Is listed in Appendix A of GEAE SB 

CF34–BJ S/B 72–0229, Revision 01, dated 

July 30, 2008; or 

(iii) Is listed in Appendix A of GEAE SB 

CF34–BJ S/B 72–0230, Revision 01, dated 

July 30, 2008. 

(2) Do not install any fan blade into any 

CF34–3A1 engine with fan drive shaft, P/N 

6036T78P02, with an airworthiness 

limitation section life limit of 15,000 CSN if 

that fan blade: 

(i) Was installed in any CF34–3A1 engine 

with fan drive shaft, P/N 6036T78P02, with 

an airworthiness limitation section life limit 

of 22,000 CSN and, 

(ii) Is listed in Appendix A of GEAE SB 

CF34–AL S/B 72–0245, Revision 01, dated 

July 3, 2008. 

Alternative Methods of Compliance 

(j) 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 

(k) Contact Kenneth Steeves, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kenneth.steeves@faa.gov; 

telephone (781) 238–7765; fax (781) 238– 

7199, for more information about this AD. 

(l) GE Aircraft Engines SBs CF34–AL S/B 

73–0046, Revision 02, dated August 27, 2008; 

CF34–AL S/B 72–0245, Revision 01, dated 

July 3, 2008; CF34–AL S/B 72–0250, dated 

August 15, 2008; CF34–BJ S/B 73–0062, 

Revision 02, dated August 27, 2008; CF34– 

BJ S/B 72–0229, Revision 01, dated July 30, 

2008; CF34–BJ S/B 72–0230, Revision 01, 

dated July 30, 2008; and CF34–BJ S/B 72– 

0231, Revision 01, dated October 1, 2008; 

pertain to the subject of this AD. 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 this service information. 

Issued in Burlington, Massachusetts, on 

April 4, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8070 Filed 4–6–09; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket No. USCG–2009–0189] 

RIN 1625–AA00 

Safety Zone; Norfolk Tides Post-Game 

Fireworks Display, Elizabeth River, 

Norfolk, VA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Coast Guard proposes a 

temporary safety zone on the Elizabeth 

River in the vicinity of Harbor Park, 

Norfolk, VA in support of the post-game 

fireworks displays over the Elizabeth 

River. This action will protect the 

maritime public on the Elizabeth River 

from the hazards associated with 

fireworks displays. 

DATES: Comments and related material 

must be received by the Coast Guard on 

or before April 29, 2009. 

ADDRESSES: Documents indicated in this 

preamble as being available in the 

docket are part of docket USCG–2009– 

0189 and are available online by going 

to http://www.regulations.gov, selecting 

the Advanced Docket Search option on 

the right side of the screen, inserting 

USCG–2009–0189 in the Docket ID box, 

pressing Enter, and then clicking on the 

item in the Docket ID column. They are 

also available for inspection or copying 

two locations: the 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, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this temporary 

rule, call or e-mail LT Tiffany Duffy, 

Coast Guard; telephone 757–668–5580, 

e-mail Tiffany.A.Duffy@uscg.mil. If you 

have questions on viewing 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–2009–0189), 

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 you successfully transmit the 

comment. If you fax, hand deliver, or 

mail your comment, it will be 

considered as having been received by 

the Coast Guard when it is received at 

the Docket Management Facility. We 

recommend that you include your name 

and a mailing address, an e-mail 

address, or a telephone number in the 

body of your document so that we can 

contact you if we have questions 

regarding your submission. 

To submit your comment online, go to 

http://www.regulations.gov, select the 

Advanced Docket Search option on the 

right side of the screen, insert ‘‘USCG– 

2009–0189’’ in the Docket ID box, press 

Enter, and then click on the balloon 

shape in the Actions column. If you 

submit your comments by mail or hand 

delivery, submit them in an unbound 

format, no larger than 8c by 11 inches, 

suitable for copying and electronic 

filing. If you submit comments by mail 

and would like to know that they 

reached the Facility, please enclose a 

stamped, self-addressed postcard or 

envelope. We will consider all 

comments and material received during 

the comment period and may change 

the rule based on your comments. 

Viewing Comments and Documents 

To view comments, as well as 

documents mentioned in this preamble 

as being available in the docket, go to 

http://www.regulations.gov, select the 

Advanced Docket Search option on the 

right side of the screen, insert USCG– 

2009–0189 in the Docket ID box, press 

Enter, and then click on the item in the 

Docket ID column. You may also visit 

the Docket Management Facility in 

Room W12–140 on the ground floor of 

the Department of Transportation West 

Building, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. We have an 

agreement with the Department of 

Transportation to use the Docket 

Management Facility. 


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