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.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

54895 

Vol. 74, No. 205 

Monday, October 26, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0294; Directorate 

Identifier 2009–NE–08–AD; Amendment 

39–16057; AD 2009–22–06] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG (IAE) V2500–A1, 

V2527E–A5, V2530–A5, and V2528–D5 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

International Aero Engines AG (IAE) 

V2500–A1, V2527E–A5, V2530–A5, and 

V2528–D5 turbofan engines. This AD 

requires reducing the published life 

limit of certain high-pressure 

compressor (HPC) stage 9–12 disc 

assemblies. This AD also removes from 

service those HPC stage 9–12 disc 

assemblies using a drawdown schedule. 

This AD results from IAE updating the 

low-cycle-fatigue (LCF) life analysis for 

certain HPC stage 9–12 disc assemblies. 

We are issuing this AD to prevent an 

uncontained failure of the HPC stage 

9–12 disc assembly, resulting in an inflight engine shutdown and possible 

damage to the airplane. 

DATES: This AD becomes effective 

November 30, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

International Aero Engines AG, 400 

Main Street, East Hartford, CT 06108; 

telephone: (860) 565–5515; fax: (860) 

565–5510. 

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: 

Kevin Dickert, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: kevin.dickert@faa.gov; telephone 

(781) 238–7117; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to IAE V2500–A1, V2527E–A5, 

V2530–A5, and V2528–D5 turbofan 

engines. We published the proposed AD 

in the Federal Register on June 29, 2009 

(74 FR 30981). That action proposed to 

require reducing the published life limit 

of certain HPC stage 9–12 disc 

assemblies. That action also proposed to 

remove from service those HPC stage 

9–12 disc assemblies using a drawdown 

schedule. 

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 

18 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 200 work-hours per engine to 

perform the actions, and that the 

average labor rate is $80 per work-hour. 

The prorated cost due to a life reduction 

for a HPC stage 9–12 disc assembly 

installed in a V2500–A1 engine, is about 

$5,600 per engine, and for one installed 

in a V2527E–A5, V2530–A5, or V2528– 

D5 engine, is about $29,700 per engine. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$485,200. 

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. 


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54896 Federal Register / Vol. 74, No. 205 / Monday, October 26, 2009 / Rules and Regulations 

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: 

2009–22–06 International Aero Engines 

AG: Amendment 39–16057. Docket No. 

FAA–2009–0294; Directorate Identifier 

2009–NE–08–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 30, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to International Aero 

Engines AG (IAE) V2500–A1, V2527E–A5, 

V2530–A5, and V2528–D5 turbofan engines. 

These engines are installed on, but not 

limited to, Airbus A320 and A321 series, and 

McDonnell Douglas Corporation MD–90 

airplanes. 

Unsafe Condition 

(d) This AD results from IAE updating the 

low-cycle-fatigue (LCF) life analysis for 

certain high-pressure compressor (HPC) stage 

9–12 disc assemblies. We are issuing this AD 

to prevent an uncontained failure of the HPC 

stage 9–12 disc assembly, resulting in an inflight engine shutdown and possible 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. 

V2500–A1 Turbofan Engines 

(f) For V2500–A1 turbofan engines with 

HPC stage 9–12 disc assemblies, P/N 2A3200, 

2A3300, 2A3400, 2A3500, 6A4131, and 

6A7545, installed, remove from service as 

follows: 

(1) For HPC stage 9–12 disc assemblies that 

have accumulated fewer than 12,000 cyclessince-new (CSN) on the effective date of this 

AD, remove from service before the disc 

assembly accumulates 14,600 CSN. 

(2) For HPC stage 9–12 disc assemblies that 

have accumulated 12,000 or more CSN but 

fewer than 14,600 CSN on the effective date 

of this AD: 

(i) If the next engine shop visit will occur 

before accumulating 14,600 CSN, then 

remove from service before accumulating 

14,600 CSN. 

(ii) If the next engine shop visit will occur 

upon accumulating 14,600 or more CSN, then 

remove from service at the next engine shop 

visit but not to exceed 15,000 CSN. 

(3) For HPC stage 9–12 disc assemblies that 

have accumulated 14,600 or more CSN on the 

effective date of this AD, remove from service 

at the next engine shop visit but not to 

exceed 15,000 CSN. 

V2527E–A5 and V2530–A5 Turbofan 

Engines 

(g) For V2527E–A5 and V2530–A5 turbofan 

engines with HPC stage 9–12 disc assemblies, 

P/N 6A4156 and 6A7547 installed, remove 

from service as follows: 

(1) For HPC stage 9–12 disc assemblies that 

have accumulated fewer than 9,000 CSN on 

the effective date of this AD, remove from 

service before the disc assembly accumulates 

11,800 CSN. 

(2) For HPC stage 9–12 disc assemblies that 

have accumulated 9,000 or more CSN but 

fewer than 11,800 CSN on the effective date 

of this AD: 

(i) If the next engine shop visit will occur 

before accumulating 11,800 CSN, then 

remove from service before accumulating 

11,800 CSN. 

(ii) If the next engine shop visit will occur 

upon accumulating 11,800 or more CSN, then 

remove from service at the next engine shop 

visit but not to exceed 12,000 CSN. 

(3) For HPC stage 9–12 disc assemblies that 

have accumulated 11,800 or more CSN on the 

effective date of this AD, remove from service 

at the next engine shop visit but not to 

exceed 12,000 CSN. 

V2528–D5 Turbofan Engines 

(h) For V2528–D5 turbofan engines with 

HPC stage 9–12 disc assemblies, P/N 6A4156 

and 6A7547 installed, remove from service as 

follows: 

(1) For HPC stage 9–12 disc assemblies that 

have accumulated fewer than 9,000 CSN on 

the effective date of this AD, remove from 

service before the disc assembly accumulates 

11,800 CSN. 

(2) For HPC stage 9–12 disc assemblies that 

have accumulated 9,000 or more CSN but 

fewer than 11,800 CSN on the effective date 

of this AD: 

(i) If the next engine shop visit will occur 

before accumulating 11,800 CSN, then 

remove from service before accumulating 

11,800 CSN. 

(ii) If the next engine shop visit will occur 

upon accumulating 11,800 or more CSN, then 

remove from service at the next engine shop 

visit but not to exceed 13,200 CSN. 

(3) For HPC stage 9–12 disc assemblies that 

have accumulated 11,800 or more CSN on the 

effective date of this AD, remove from service 

at the next engine shop visit but not to 

exceed 13,200 CSN. 

Definition 

(i) For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance does not constitute an engine 

shop visit. 

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) IAE Alert Service Bulletin No. V2500– 

ENG–72–A0554, Revision 1, dated June 27, 

2008, also pertains to the subject of this AD. 

Contact International Aero Engines AG, 400 

Main Street, East Hartford, CT 06108; 

telephone: (860) 565–5515; fax: (860) 565– 

5510, for a copy of this service information. 

(l) Contact Kevin Dickert, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: Kevin.dickert@faa.gov; 

telephone (781) 238–7117; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(m) None. 

Issued in Burlington, Massachusetts, on 

October 16, 2009. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–25644 Filed 10–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0128; Airspace 

Docket No. 08–ASW–15] 

RIN 2120–AA66 

Amendment of Federal Airways V–163 

and V–358 in the Lampasas, TX, Area 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends the legal 

descriptions of two Federal airways that 

have ‘‘Lampasas, TX, very high 

frequency omnidirectional range/ 

tactical air navigation (VORTAC)’’ 

included as part of their route structure. 

Currently, the Lampasas VORTAC and 

the Lampasas Airport share the same 

location name and identifier (LZZ). To 

eliminate confusion and potential flight 

safety issues, the ‘‘Lampasas VORTAC’’ 

(LZZ) will be renamed the ‘‘Gooch 

Springs VORTAC’’ (AGJ). All airways 

with Lampasas [VORTAC] included in 

their legal descriptions will be 

amended, concurrent with the effective 

date of this final rule, to reflect the 

name change. 


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