76610 Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE—Continued

EMBRAER service bulletin Page No. Change/revision level Date 

145LEG–31–0001 ................................ 1–12 ..................................................... Original ................................................ August 19, 2002.

This incorporation by reference was 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), PO Box 343—CEP 12.225, Sao 

Jose dos Campos—SP, Brazil. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; 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/

code_of_federal_regulations/

ibr_locations.html.

Note 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2003–03–

01, dated April 3, 2003.

Effective Date 

(g) This amendment becomes effective on 

January 26, 2005.

Issued in Renton, Washington, on 

December 6, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–27509 Filed 12–21–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NE–67–AD; Amendment 

39–13914; AD 2004–26–02] 

RIN 2120–AA64

Airworthiness Directives; GE Aircraft 

Engines (GE) CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, CF34–3B, and 

CF34–3B1 Series Turbofan Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF34–3A, CF34–3A2, CF34–1A, CF34–

3A1, CF34–3B, and CF34–3B1 series 

turbofan engines. This AD requires 

removal from service of certain high 

pressure compressor (HPC) forward 

spools, at the first piece-part level 

exposure after 6,000 cycles since new 

(CSN); but not later than 20,000 CSN for 

CF34–3B engines, and not later than 

22,000 CSN for CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, and CF34–3B1 

engines. This AD results from an 

updated low-cycle fatigue (LCF) 

analysis performed on certain HPC 

forward spools. We are issuing this AD 

to prevent LCF cracks and failure of the 

HPC forward spool, which could result 

in an uncontained engine failure and 

damage to the airplane.

DATES: This AD becomes effective 

January 26, 2005.

ADDRESSES: You may examine the AD 

docket at the FAA, New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Robert Grant, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7757; fax 

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF34–3A, CF34–3A2, 

CF34–1A, CF34–3A1, CF34–3B, and 

CF34–3B1 series turbofan engines. We 

published the proposed AD in the 

Federal Register on May 18, 2004 (69 

FR 28093). That action proposed to 

require removal from service of certain 

HPC forward spools, at the first piecepart level exposure after 6,000 CSN, but 

not later than 20,000 CSN for CF34–3B 

engines and not later than 22,000 CSN 

for CF34–3A, CF34–3A2, CF34–1A, 

CF34–3A1, and CF34–3B1 engines. That 

action results from GE updating the LCF 

analysis for these HPC forward spools. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the one comment received. 

Request for Definition Clarification of 

Serviceable HPC Forward Spool 

One commenter requests that we 

clarify the definition of a serviceable 

HPC forward spool. The commenter 

states that a clarification would ensure 

that operators are not led to believe that 

HPC forward spools installed in their 

engines are not serviceable based on the 

AD’s definition of a serviceable HPC 

forward spool. 

We partially agree. As written in the 

proposal, the compliance requires 

replacing certain HPC forward spools 

with a serviceable HPC forward spool at 

next piece-part level exposure, and then 

defines what a serviceable HPC forward 

spool is and what it is not. We agree that 

this definition could cause confusion. 

We do not agree that a clarification to 

the existing definition is the best 

approach to ensure that the AD is 

understandable. For clarification, we 

have rewritten the compliance in the 

final rule to require operators to remove 

certain specific spools from service. We 

have also added a paragraph in the final 

rule to clarify that after the effective 

date of this AD, do not install any HPC 

forward spool, P/N 6078T56P03. We 

have also clarified the requirement that 

after the effective date of this AD, do not 

install any HPC forward spool, P/N 

6078T56P04, with more than 0 CSN. We 

have also deleted from the final rule the 

definition which described serviceable 

spools. 

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 

There are about 2,681 GE CF34–3A, 

CF34–3A2, CF34–1A, CF34–3B and 

CF34–3B1 series turbofan engines of the 

affected design in the worldwide fleet. 

We estimate that 1,826 engines installed 

on airplanes of U.S. registry would be 

affected by this AD. We also estimate 

that 59% of the replacements will not be 

done at piece-part exposure, and will 

require approximately 650 work hours 

per engine to perform the actions, and 

that the average labor rate is $65 per 

work hour. Required parts will cost 

about $16,000 per engine (a prorated 

cost of the unused spool life to the 

original life). Based on these figures, we 

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

operators to be $74,420,000. 

Federal Register / Vol. 69, No. 245 / Wednesday, December 22, 2004 / Rules and Regulations 76611

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 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 2003–NE–67–

AD’’ in your request.

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 adding 

the following new airworthiness 

directive (AD):

2004–26–02 GE Aircraft Engines (GE):

Amendment 39–13914. Docket No. 

2003–NE–67–AD. 

Effective Date 

(a) This AD becomes effective January 26, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to GE CF34–3A, CF34–

3A2, CF34–1A, CF34–3A1, CF34–3B, and 

CF34–3B1 series turbofan engines with high 

pressure compressor (HPC) forward spool, 

part number (P/N) 6078T56P03 or 

6078T56P04, installed. These engines are 

installed on, but not limited to, Bombardier 

series Business Jet Model CL–600–2A12 (CL–

601), Bombardier series Business Jet Model 

CL–600–2B16 (CL–601–3A, CL–601–3R, and 

CL–604), and Bombardier series Regional Jet 

Model CL–600–2B19 (Regional Jet Series 100 

and 440) airplanes. 

Unsafe Condition 

(d) This AD results from an updated lowcycle fatigue (LCF) analysis performed on 

HPC forward spools, P/Ns 6078T56P03 and 

6078T56P04, by GE. We are issuing this AD 

to prevent LCF cracks and failure of the HPC 

forward spool, which could result in an 

uncontained engine failure and damage to 

the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

HPC Spool Replacement 

(f) For CF34–3B engines, remove from 

service HPC forward spools, P/Ns 

6078T56P03 and 6078T56P04 at the first 

piece-part exposure after 6,000 cycles-sincenew (CSN), but no later than 20,000 CSN. 

(g) For CF34–3A, CF34–3A2, CF34–1A, 

CF34–3A1, and CF34–3B1 engines, remove 

from service HPC forward spools, P/Ns 

6078T56P03 and 6078T56P04 at the first 

piece-part exposure after 6,000 CSN, but no 

later than 22,000 CSN. 

(h) After the effective date of this AD: 

(1) Do not install any HPC forward spool, 

P/N 6078T56P03. 

(2) Do not install any HPC forward spool, 

P/N 6078T56P04, with more than 0 CSN. 

Definition 

(i) For the purpose of this AD, the 

definition of piece-part exposure for the HPC 

forward spool is when the spool is 

completely disassembled. 

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. 

Material Incorporated by Reference 

(k) None. 

Related Information 

(l) None.

Issued in Burlington, Massachusetts, on 

December 15, 2004. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–27948 Filed 12–21–04; 8:45 am] 

BILLING CODE 4910–13–P

FEDERAL TRADE COMMISSION

16 CFR Part 1

Federal Civil Penalties Inflation 

Adjustment Act

AGENCY: Federal Trade Commission 

(FTC).

ACTION: Final rule amendments.

SUMMARY: The FTC is making 

adjustments to certain civil penalty 

amounts within its jurisdiction, as 

required by law. These adjustments 

reflect inflation since the penalty 

amounts were last adjusted.

EFFECTIVE DATE: January 21, 2005.

FOR FURTHER INFORMATION CONTACT: Alex 

Tang, Attorney, Office of General 

Counsel, FTC, 600 Pennsylvania 

Avenue, NW., Washington, DC 20580, 

(202) 326–2447, atang@ftc.gov.

SUPPLEMENTARY INFORMATION: As 

required at least once every four years 

by the Federal Civil Penalties Inflation 

Adjustment Act of 1990, 28 U.S.C. 2461 

note, as amended by the Debt Collection 

Improvement Act of 1996, Pub. L. 104–

134, § 31001, 110 Stat. 1321–373, the 

FTC is making certain regulatory 

adjustments to civil penalty amounts 

within its jurisdiction. The civil penalty 

amounts adjusted by the FTC are set 

forth in Commission Rule 1.98, 16 CFR 

1.98. The FTC published the original 

adjustments in 1996. See 61 FR 54548 

(Oct. 21, 1996), 55840 (Oct. 29, 1996). 

No adjustments were warranted under 

the law in 2000. See 65 FR 69665 (Nov. 

20, 2000). 

Adjustments are based on the increase 

in the Consumer Price Index (CPI) 

between June of the year in which the 

prior adjustment was made and June of 

the year preceding the year in which the 

adjustment is being made. Thus, for the 

relevant period between June 1996 and