Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations 32775 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25896; Directorate 

Identifier 2006–NE–33–AD; Amendment 39–

15093; AD 2007–12–15] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF34–10E 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

GE CF34–10E series turbofan engines. 

That AD currently requires removing 

the fuel inlet strainer from main fuel 

pump (MFP) part number (P/N) 

2043M12P03, installing a certain 

replacement flange as an interim repair, 

remarking the MFP to P/N 2043M12P04, 

and performing initial and repetitive 

visual inspections of the main fuel filter. 

This AD requires removing MFPs, P/Ns 

2043M12P03, 2043M12P04, 837600–3, 

and 837600–4, from service and 

installing an improved MFP with a 

different P/N. This AD results from GE 

determining that the cause of MFP fuel 

strainer failure is a design problem with 

the strainer. We are issuing this AD to 

prevent engine in-flight shutdown due 

to MFP malfunctions. 

DATES: This AD becomes effective July 

19, 2007. 

ADDRESSES: You can get the service 

information identified in this 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. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room W12–140 on the ground floor of 

the West Building, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone: (781) 238–7765, fax: 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2006–20–06, 

Amendment 39–14775 (71 FR 57403, 

September 29, 2006), with a proposed 

AD. The proposed AD applies to GE 

CF34–10E2A1, –10E5, –10E5A1, –10E6, 

–10E6A1, and –10E7 turbofan engines, 

with MFP P/Ns 2043M12P03, P/N 

2043M12P04, 837600–3, and 837600–4, 

installed. We published the proposed 

AD in the Federal Register on 

September 29, 2006 (71 FR 57403). That 

action proposed to require removing 

MFPs, P/N 2043M12P03, 2043M12P04, 

83600–3, and 83600–4 from service and 

installing an improved MFP, not later 

than July 31, 2007. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

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

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Address the Use of Parts Manufacturer 

Approval (PMA) Parts 

One commenter, Mr. Jack Buster of 

the Modification and Repair Parts 

Association (MARPA), states that the 

PMA part may often share the identical 

design data with the original part while 

carrying a completely different part 

number; therefore, it is possible the AD 

will not address certain defective PMA 

parts installed on the aircraft, allowing 

the unsafe condition to continue. 

The same commenter also states that 

it is possible that a ‘‘new and improved’’

PMA version of the defective original 

part may already exist in the 

marketplace. Therefore, specifying one 

approved part in preference to a 

different, but also approved part, will 

impart a commercial advantage to one 

manufacturer over the other. 

We agree. We changed the final rule 

to add the PMA P/Ns 837600–3 and 

837600–4 to the Applicability and 

replacement requirements of the final 

rule. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

50 CF34–10E series turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it will take about 

3 work-hours per engine to perform the 

required actions, and that the average 

labor rate is $80 per work-hour. 

Required parts will cost about $4,226 

per engine to upgrade the MFP to a 

different P/N to make it serviceable. 

Based on these figures, we estimate the 

total upgrade cost of this AD to U.S. 

operators to be $223,300. 

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 

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 


pwalker on PROD1PC71 with RULES
32776 Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 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 39–14775 (71 FR 

57403, September 29, 2006) and by 

adding a new airworthiness directive, 

Amendment 39–15093, to read as 

follows: 

2007–12–15 General Electric Company: 

Amendment 39–15093. Docket No. 

FAA–2005–25896; Directorate Identifier 

2006–NE–33–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 19, 2007. 

Affected ADs 

(b) This AD supersedes AD 2006–20–06, 

Amendment 39–14755. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF34–10E2A1, –10E5, 

–10E5A1, –10E6, –10E6A1, and –10E7 

turbofan engines, with main fuel pump 

(MFP) part number (P/N) 2043M12P03, P/N 

2043M12P04, P/N 837600–3, and P/N 

837600–4 installed. These engines are 

installed on, but not limited to, Embraer ERJ 

190–100–STD, ERJ 190–100–LR, and ERJ 

190–100–IGW airplanes. 

Unsafe Condition 

(d) This AD results from GE determining 

that the cause of MFP fuel strainer failure is 

a design problem with the strainer. We are 

issuing this AD to prevent engine in-flight 

shutdown due to MFP malfunctions. 

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. 

MFP Removal and Installation 

(f) Not later than July 31, 2007, remove 

MFPs, P/Ns 2043M12P03, 2043M12P04, 

837600–3, and 837600–4 from service and 

install a serviceable MFP. 

Definition 

(g) For the purpose of this AD, a 

serviceable MFP is one that does not have 

P/N 2043M12P03, 2043M12P04, 837600–3 or 

837600–4. 

Recommended Actions 

(h) We recommend that operators avoid 

performing the actions in this AD on both 

engines installed on the same airplane at the 

same time, if at all possible. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, FAA, 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) GE Service Bulletin No. CF34–10E S/B 

73–0013, dated December 15, 2006, pertains 

to the subject of this AD. 

(k) Contact Kenneth Steeves, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7765, fax (781) 

238–7199, for more information about this 

AD. 

Issued in Burlington, Massachusetts, on 

June 1, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 07–2843 Filed 6–13–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27849; Directorate 

Identifier 2006–NM–249–AD; Amendment 

39–15094; AD 2007–12–16] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 2000EX and Falcon 

900EX Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an airworthiness authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as some stringer 

reinforcements (F900DX) and some 

rivets (F900DX/F2000EX) missing from 

the skin panels on each side of the 

fuselage between frames 9 and 10 on 

certain Falcon 900DX and Falcon 

2000EX EASy aircraft; this situation 

affects the structural integrity of the 

fuselage. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective July 

19, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 19, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

allow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 12, 2007 (72 FR 

18415). That NPRM proposed to require 

inspecting skin panels on each side of 

the fuselage between frames 9 and 10, 

including holes and structure, where 

missing rivets are found, adding missing 

rivets and stringer caps, as applicable, 

and contacting the manufacturer if the 

holes are out-of-round beyond tolerance, 

or if cracks are found, as applicable. The 

MCAI states that following the 

incorporation of a design change to the 

Karman fairing, it has been determined 

that some stringer reinforcements 


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