This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

1017 

Vol. 75, No. 5 

Friday, January 8, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0328; Directorate 

Identifier 2008–NE–44–AD; Amendment 39– 

16161; AD 2010–01–04] 

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: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

GE CF34–1A, CF34–3A, and CF34–3B 

series turbofan engines. That AD 

currently requires removing from 

service certain part number (P/N) and 

serial number (S/N) fan blades within 

compliance times specified in the 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 hose fitting. This ad supersedure 

requires the same actions but corrects 

the effectivity for certain fan blades 

requiring corrective actions and changes 

the effective date of the current AD. 

This AD supersedure results from the 

FAA discovering that the existing AD 

has an incorrect effectivity for certain 

fan blades requiring corrective actions, 

and from a report of an under-cowl fire 

and a failed fan blade. We are issuing 

this AD to prevent failure of certain 

P/N and S/N fan blades and aft actuator 

head hoses, which could result in an 

under-cowl fire and subsequent damage 

to the airplane. 

DATES: This AD becomes effective 

January 25, 2010. The Director of the 

Federal Register previously approved 

the incorporation by reference of certain 

publications listed in the regulations as 

of January 4, 2010. 

We must receive any comments on 

this AD by March 9, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this 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, 

GE–Aviation, Room 285, 1 Neumann 

Way, Cincinnati, OH 45215, telephone 

(513) 552–3272; fax (513) 552–3329; 

e-mail: geae.aoc@ge.com for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: John 

Frost, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

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

(781) 238–7756; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

amends 14 CFR part 39 by superseding 

AD 2009–24–11, Amendment 39–16103 

(74 FR 62481, November 30, 2009). That 

AD requires removing from service 

certain P/N and S/N fan blades within 

compliance times specified in the 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 hose fitting. That AD was the result 

of a report of an under-cowl fire and a 

failed fan blade. That condition, if not 

corrected, could result in an under-cowl 

fire and subsequent damage to the 

airplane. 

Actions Since AD 2009–24–11 Was 

Issued 

Since AD 2009–24–11 was issued, we 

discovered that when we recodified the 

compliance section as part of our 

response to a comment received on the 

proposed AD, we inadvertently left out 

of the AD certain fan blade effectivity 

information from paragraphs (f) and (g) 

and (j). Paragraphs (f) and (g) are 

missing information on fan blades, P/Ns 

6018T30P14 or 4923T56G08, that have 

any fan blade S/Ns listed in Appendix 

A of General Electric Aircraft Engines 

(GEAE) Service Bulletin (SB) No. CF34– 

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

30, 2008. Also, paragraph (j) is missing 

information on fan blades, P/N 

6018T30P14 or P/N 4923T56G08, that 

have any fan blade S/Ns listed in 

Appendix A of GEAE SB No. CF34–BJ 

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

2008. This AD supersedure adds the 

missing information to the compliance 

section and changes the effective date of 

the original AD to the same effective 

date as this AD, to prevent possible 

grounding of airplanes. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of the following GE 

Aircraft Engines 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 S/N 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. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other GE CF34–1A, CF34–3A, and 

CF34–3B series turbofan engines of the 

same type design. We are issuing this 

AD supersedure to prevent failure of 

certain P/N and S/N fan blades and aft 

actuator head hoses, which could result 

in an under-cowl fire and subsequent 

damage to the airplane. This AD 


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1018 Federal Register / Vol. 75, No. 5 / Friday, January 8, 2010 / Rules and Regulations 

requires removing from service certain 

P/N and S/N fan blades within 

compliance times specified in the 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 hose fitting. You must use the 

service information described 

previously to perform the actions 

required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2008–0328; 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 rule that might suggest a 

need to modify it. 

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 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 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. 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this 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. 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. 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. 

Adoption of the Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (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 39–16103 (74 FR 

62481, November 30, 2009), and by 

adding a new airworthiness directive, 

Amendment 39–16161, to read as 

follows: 

2010–01–04 General Electric Company: 

Amendment 39–16161. Docket No. 

FAA–2008–0328; Directorate Identifier 

2008–NE–44–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 25, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–24–11, 

Amendment 39–16103. 

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 the FAA 

discovering that the existing AD has an 

incorrect effectivity for certain fan blades 

requiring corrective actions, and 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 (S/N) 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 that meet all of 

the following criteria, perform the actions 

specified in paragraph (i) of this AD: 

(1) Fan drive shaft, P/N 6036T78P02, 

installed; and 

(2) Airworthiness limitation section fan 

drive shaft life limit of 22,000 cycles-sincenew (CSN); and 

(3) Installed fan blades, P/Ns 6018T30P14 

or 4923T56G08, that have any fan blade 

S/Ns listed in Appendix A of General Electric 

Aircraft Engines (GEAE) SB No. CF34–AL S/ 

B 72–0245, Revision 01, dated July 30, 2008. 

(g) For CF34–3A1 engines that meet all of 

the following criteria, perform the actions 

specified in paragraph (i) of this AD: 


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Federal Register / Vol. 75, No. 5 / Friday, January 8, 2010 / Rules and Regulations 1019 

(1) Fan drive shaft, P/N 6036T78P02, 

installed; and 

(2) Airworthiness limitation section fan 

drive shaft life limit of 15,000 CSN; and 

(3) In compliance with GEAE SB No. 

CF34–AL S/B 72–0147, dated May 21, 2003, 

Revision 01, dated October 17, 2003, 

Revision 02, dated August 5, 2004, or 

Revision 3, dated August 28, 2003; and 

(4) Installed fan blades, P/Ns 6018T30P14 

or 4923T56G08, that have any fan blade 

S/Ns listed in Appendix A of GEAE SB No. 

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

July 30, 2008. 

(h) For CF34–3B1 engines that meet all of 

the following criteria, perform the actions 

specified in paragraph (i) of this AD: 

(1) Installed fan blades, P/Ns 6018T30P14 

or 4923T56G08; and 

(2) With any fan blade S/Ns listed in 

Appendix A of GEAE SB No. CF34–AL S/B 

72–0245, Revision 01, dated July 30, 2008. 

(i) Do the following for the engines meeting 

the criteria in paragraph (f), (g), or (h) of this 

AD, as applicable: 

(1) Remove listed 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 CSN 

on the effective date of this AD, perform an 

initial visual inspection of the fan blade 

abradable rub strip for wear within 20 CIS 

after the effective date of this AD. Use 

paragraphs 3.A.(1) through 3.A.(2) of the 

Accomplishment Instructions of GEAE SB 

No. 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, perform 

an initial visual inspection of the fan blade 

abradable rub strip for wear within 1,220 

CSN. Use paragraphs 3.A.(1) through 3.A.(2) 

of the Accomplishment Instructions of GEAE 

SB No. 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 

No. CF34–AL S/B 72–0250, Revision 01, 

dated November 26, 2008. 

(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 No. 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 

No. CF34–AL S/B 72–0250, Revision 01, 

dated November 26, 2008. 

(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 No. 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 

(j) For CF34–3A1 engines that meet all of 

the following criteria, perform the actions 

specified in paragraph (l) of this AD: 

(1) Fan drive shaft, P/N 6036T78P02, 

installed; and 

(2) Airworthiness limitation section fan 

drive shaft life limit of 15,000 CSN that are 

not in compliance with GEAE SB No. CF34– 

AL S/B 72–0147, dated May 21, 2003, 

Revision 01, dated October 17, 2003, 

Revision 02, dated August 5, 2004, or 

Revision 03, dated August 28, 2003; and 

(3) With fan blades, P/Ns 6018T30P14 or 

4923T56G08, that have any fan blade S/Ns 

listed in Appendix A of GEAE SB No. CF34– 

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

2008. 

(k) For CF34–1A, CF34–3A, CF34–3A2, 

and CF34–3B engines that meet all of the 

following criteria, perform the actions 

specified in paragraph (l) of this AD: 

(1) Installed fan blades, P/N 6018T30P14 or 

P/N 4923T56G08; and 

(2) Installed fan blade S/Ns listed in 

Appendix A of GEAE SB No. CF34–BJ S/B 

72–0229, Revision 01, dated July 30, 2008: 

(l) Do the following for the engines meeting 

the criteria in paragraph (j) or (k) of this AD 

as applicable: 

(1) Remove listed fan blades, P/N 

6018T30P14, from service within 2,400 CSN. 

(2) Remove listed 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, perform an initial eddy 

current inspection (ECI) of the fan blades for 

cracks within 350 CIS after the effective date 

of this AD. Use paragraphs 3.A. or 3.B. of the 

Accomplishment Instructions of GEAE SB 

No. 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, perform an initial ECI of the fan blades 

for cracks within 1,200 CSN. Use paragraphs 

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

Instructions of GEAE SB No. 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, 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 

No. 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 any fan 

blade S/Ns listed in Appendix A of GEAE SB 

No. 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, and 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 No. 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 

No. 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 No. 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 

No. 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 No. CF34–BJ S/B 


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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 No. CF34–BJ S/B 

73–0062, Revision 02, dated August 27, 2008, 

to perform the inspection. 

Credit for Previous Actions 

(m) 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 (i)(2) through (i)(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 (i)(7) of 

this AD. 

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

2008, meet the requirements specified in 

paragraphs (l)(3) and (l)(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 

(l)(10)(i) and (l)(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 (l)(11) 

and (l)(12) of this AD. 

Installation Prohibitions 

(n) 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 fan drive shaft 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 fan drive 

shaft life limit of 15,000 CSN; and 

(ii) Is listed in Appendix A of GEAE SB No. 

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

July 30, 2008; or 

(iii) Is listed in Appendix A of GEAE SB 

No. 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 fan drive shaft 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 fan drive 

shaft life limit of 22,000 CSN; and 

(ii) Is listed in Appendix A of GEAE SB No. 

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

July 3, 2008. 

Alternative Methods of Compliance 

(o) 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 

(p) Contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: john.frost@faa.gov; telephone (781) 

238–7756; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(q) You must use the GE Aircraft Engines 

service information specified in the following 

Table 1 to do the actions required by this AD. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin No. Page Revision Date 

CF34–AL S/B 73–0046.

Total Pages: 8 All .................................................. 02 August 27, 2008. 

CF34–BJ S/B 73–0062.

Total Pages: 8 All .................................................. 02 August 27, 2008. 

CF34–BJ S/B 72–0229.

Total Pages: 158 All .................................................. 01 July 30, 2008. 

CF34–BJ S/B 72–0230.

Total Pages: 153 All .................................................. 01 July 30, 2008. 

CF34–BJ S/B 72–0231.

Total Pages: 8 All .................................................. 02 November 26, 2008. 

CF34–AL S/B 72–0245.

Total Pages: 153 All .................................................. 01 July 3, 2008. 

CF34–AL S/B 72–0250.

Total Pages: 9 All .................................................. 01 November 26, 2008. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of this service information under 5 

U.S.C. 552(a) and 1 CFR part 51, as of January 

4, 2010. 

(2) For service information identified in 

this AD, contact General Electric Company, 

GE–Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, telephone (513) 552– 

3272; fax (513) 552–3329; e-mail: 

geae.aoc@ge.com. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

December 29, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31274 Filed 1–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 738 

[Docket No. 0907241162–91276–01] 

RIN 0694–AE62 

Amendments to the Export 

Administration Regulations (EAR) 

Based Upon the Accession of Albania 

and Croatia to Formal Membership in 

the North Atlantic Treaty Organization 

(NATO) 

Correction 

In rule document E9–30484 beginning 

on page 68142 in the issue of 

Wednesday, December 23, 2009, make 

the following correction: 


pwalker on DSK8KYBLC1PROD with RULES