Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 16755 

Costs of Compliance 

We estimate that this AD will affect 3 

out of 316 CF6–80A series turbofan 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 1 work-hour per engine to 

perform the actions if the engine is 

already removed and disassembled to 

piece-part exposure of the disk, and will 

take about 115 work-hours per engine 

for an unplanned engine shop visit. The 

average labor rate is $80 per work-hour. 

Required parts would cost about 

$300,000 per engine. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $927,600. 

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 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 adding 

the following new airworthiness 

directive: 

2009–08–06 General Electric Company: 

Amendment 39–15879. Docket No. 

FAA–2008–0827; Directorate Identifier 

2008–NE–26–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 18, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–80A series turbofan 

engines with any of the following stage 

1 high-pressure turbine (HPT) rotor disk 

part numbers (P/Ns), installed: 

(1) 1380M69G01; 1380M69G02; 

1380M69G04; 1380M69G05; or 

1380M69G06; or 

(2) 9234M67G12; 9234M67G13; 

9234M67G14; 9234M67G15; or 

9234M67G16; or 

(3) 9362M58G04; or 

(4) 9367M45G01; 9367M45G03; 

9367M45G05; 9367M45G06; 

9367M45G07; or 9367M45G08. 

(d) These CF6–80A series turbofan 

engines are installed on, but not limited 

to, Airbus A310–200 series and Boeing 

767–200 and –300 series airplanes. 

Unsafe Condition 

(e) This AD results from the FAA 

learning that those disks are susceptible 

to cracks developing at the aft chamfer 

of the blade dovetail slots. We are 

issuing this AD to prevent cracks 

developing at the aft chamfer of the 

blade dovetail slots that could propagate 

to a failure of the disk and cause an 

uncontained engine failure and damage 

to the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed 

within 30 days after the effective date of 

this AD, unless the actions have already 

been done. 

(g) Remove from service HPT stage 1 

rotor disks identified by P/N in 

paragraph (c) of this AD. 

Prohibition of HPT Stage 1 Rotor Disks 

(h) After the effective date of this AD, 

do not install any of the HPT stage 1 

rotor disks, listed by P/N in paragraph 

(c) of this AD into any engine. 

Alternative Methods of Compliance 

(i) 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 

(j) Contact Robert Green, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; e-mail: 

robert.green@faa.gov; telephone: (781) 

238–7754, fax: (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(k) None. 

Issued in Burlington, Massachusetts, on 

April 6, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8263 Filed 4–10–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1207; Directorate 

Identifier 2007–NE–47–AD; Amendment 39– 

15880; AD 2009–08–07] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. ALF502L–2 and 

ALF502L–2C Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Honeywell International Inc. ALF502L– 

2 and ALF502L–2C turbofan engines 

with certain high-pressure compressor 

(HPC) first stage discs installed. This AD 

requires performing a dimensional 

inspection to determine if excessive disc 

balance material was removed and a 

magnetic particle inspection if the disc 

16756 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 

passes the dimensional inspection. This 

AD results from reports of discs found 

with excessive material removed from 

the balancing locations of the disc. We 

are issuing this AD to prevent the discs 

from fracturing before reaching the 

currently published life limit. A disc 

fracture could result in an uncontained 

failure of the disc and damage to the 

airplane. 

DATES: This AD becomes effective May 

18, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

Honeywell International Inc. 111 S. 34th 

Street, Phoenix, AZ 85034–2802, U.S.A.; 

telephone (800) 601–3099, Web site 

http://portal.honeywell.com/wps/portal/ 

aero. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: 

robert.baitoo@faa.gov; telephone (562) 

627–5245; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to Honeywell International Inc. 

ALF502L–2 and ALF502L–2C turbofan 

engines with certain HPC first stage 

discs installed. We published the 

proposed AD in the Federal Register on 

November 28, 2008 (73 FR 72370). That 

action proposed to require performing a 

dimensional inspection to determine if 

excessive disc balance material was 

removed and a magnetic particle 

inspection if the disc passes the 

dimensional inspection. 

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 provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

148 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 3 work-hours per engine 

to perform the actions, and that the 

average labor rate is $80 per work-hour. 

Required parts will cost about $21,000 

per engine. Based on these figures, we 

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

operators to be $3,143,520. 

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 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 adding 

the following new airworthiness 

directive: 

2009–08–07 Honeywell International Inc. 

(Formerly AlliedSignal and Lycoming): 

Amendment 39–15880. Docket No. 

FAA–2008–1207; Directorate Identifier 

2007–NE–47–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 18, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell 

International Inc. ALF502L–2 and ALF502L– 

2C turbofan engines with high pressure 

compressor (HPC) first stage discs, part 

numbers (P/Ns) 2–101–331–03, 2–101–331– 

04, and 2–101–331–10, installed. These 

engines are installed on, but not limited to, 

Bombardier CL–600–1A11 airplanes. 

Unsafe Condition 

(d) This AD results from reports of discs 

found with excessive material removed from 

the balancing locations of the disc. We are 

issuing this AD to prevent the discs from 

fracturing before reaching the currently 

published life limit. A disc fracture could 

result in an uncontained failure of the disc 

and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

next shop visit, but not later than 2,500 

cycles-in-service after the effective date of 

this AD, unless the actions have already been 

done. 

Visual Inspection 

(f) For discs with 5,000 or more cyclessince-new on the effective date of this AD, 

perform a dimensional inspection of the HPC 

first stage disc to determine if excessive disc 

Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 16757 

balance material was removed. See the 

following Figure 1 for limits. 

BILLING CODE 4910–13–P 


ER13AP09.012</GPH>
16758 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 

(g) Replace the disc if excessive disc 

balance material was removed. See limits in 

Figure 1 of this AD. 

(h) If the removed balance material 

condition is acceptable, perform a magnetic 

particle inspection of the disc rim and slots 

for cracks using a 3 to 7 power magnification 

glass. The Engine Overhaul Manual, 72–34– 

11, Inspection/Check, contains information 

on the magnetic particle inspection 

procedure. Contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802, U.S.A.; telephone (800) 601–3099, Web 

site http://portal.honeywell.com/wps/portal/ 

aero, for a copy of this service information. 

(i) Replace the disc if you find any cracks. 

Alternative Methods of Compliance 

(j) The Manager, Los Angeles Aircraft 

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) Honeywell Alert Service Bulletin ALF/ 

LF A72–1102, dated April 24, 2007, contains 

information that pertains to the subject of 

this AD. Contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802, U.S.A.; telephone (800) 601–3099, Web 

site http://portal.honeywell.com/wps/portal/ 

aero, for a copy of this service information. 

(l) Contact Robert Baitoo, Aerospace 

Engineer, Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: robert.baitoo@faa.gov; 

telephone (562) 627–5245; fax (562) 627– 

5210, for more information about this AD. 

Material Incorporated by Reference 

(m) None. 

Issued in Burlington, Massachusetts, on 

April 6, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–8264 Filed 4–10–09; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 30653; Amdt. No. 479] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


ER13AP09.013</GPH>