19904 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Transport Canada Civil 

Aviation Airworthiness Directive CF–2008– 

34, dated December 2, 2008; and Bombardier 

Service Bulletin 670BA–49–012, Revision A, 

dated August 28, 2008; for related 

information. 

Issued in Renton, Washington, on April 22, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–9866 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29060; Directorate 

Identifier 2007–NE–34–AD] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines (IAE) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

IAE V2500–A1, V2527E–A5, V2527M– 

A5, V2528–D5, V2530–A5, and V2533– 

A5 turbofan engines. This proposed AD 

would require a onetime inspection of 

certain vortex reducers for cracks, and 

replacing the reducer and high-pressure 

(HP) compressor stage 3–8 drum if the 

reducer is cracked. This proposed AD 

results from reports of fractured vortex 

reducers found at shop visits. We are 

proposing this AD to inspect for cracks 

in the vortex reducer. Cracks in the 

vortex reducer could cause an 

uncontained failure of the HP 

compressor stage 3–8 drum, which 

could result in damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by June 29, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

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 International Aero Engines, 

400 Main St., East Hartford, CT 06108; 

telephone (860) 565–5515, fax (860) 

565–0600 for a copy of the service 

information identified in this AD. 

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: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2007–29060; Directorate Identifier 

2007–NE–34–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

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 proposed 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 proposed 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. 

Discussion 

International Aero Engines has 

informed us that they received reports 

of two fractured vortex reducers found 

at engine shop visits. Those findings 

prompted IAE to perform stress analyses 

and lifing work on both the vortex 

reducer and the HP compressor stage 3– 

8 drum. That work showed that a 

cracked vortex reducer leads to an 

increase in stress levels at the bolt holes 

of the HP compressor stage 3–8 drum. 

For certain stage 3–8 drums, the stress 

increase at the stage 8 bolt holes could 

lead to a reduced drum life depending 

on the drum life when the vortex 

reducer was cracked and the thrust 

rating of the engine. Stage 3–8 drums, 

part numbers (P/Ns) 6A5467, 6A6473, 

and 6A7401, could fail from the 

increased loading caused by a cracked 

vortex reducer. This condition, if not 

corrected, could cause an uncontained 

failure of the HP compressor stage 3–8 

drum, which could result in damage to 

the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of IAE Service 

Bulletin (SB) V2500–ENG–72–0510, 

Revision 1, dated October 8, 2007, that 

describes procedures for inspecting the 

vortex reducer for cracks. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require a onetime 

fluorescent penetrant inspection of 

certain vortex reducers for cracks. 

Costs of Compliance 

We estimate that this proposed AD 

would affect no engines installed on 

airplanes of U.S. registry. Based on this, 

we estimate there is no cost to U.S. 

operators for the proposed AD. 

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. 

Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Proposed Rules 19905 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed 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. Would 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 regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. 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. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 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: 

International Aero Engines: Docket No. 

FAA–2007–29060; Directorate Identifier 

2007–NE–34–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by June 

29, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to International Aero 

Engines (IAE) V2500–A1, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, and 

V2533–A5 turbofan engines with high 

pressure (HP) compressor stage 3–8 drums, 

part numbers (P/Ns) 6A5467, 6A6473, and 

6A7401, installed. These engines are 

installed on, but not limited to, Airbus A319, 

A320, and A321 series airplanes and Boeing 

MD–90 airplanes. 

Unsafe Condition 

(d) This AD results from reports of 

fractured vortex reducers found at shop 

visits. We are issuing this AD to inspect for 

cracks in the vortex reducer. Cracks in the 

vortex reducer could cause an uncontained 

failure of the HP compressor stage 3–8 drum, 

which could result in 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. 

Onetime Fluorescent Penetrant Inspection 

(f) Fluorescent penetrant inspect the vortex 

reducer for cracks when the HPC stage 3–8 

drum has between 3,000 and 13,500 cycles 

since new (CSN) if all of the following 

conditions also apply: 

(1) The HPC stage 3–8 drum has ever 

operated in an engine at the V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5 thrust 

ratings, 

(2) The vortex reducer had cycles 

accumulated on it when mated with the HPC 

stage 3–8 drum, and 

(3) The HPC stage 3–8 drum had fewer 

than 3,000 CSN when mated to the vortex 

reducer. 

(g) If the vortex reducer is cracked, remove 

both the vortex reducer and the HPC stage 3– 

8 drum from service. 

(h) After the effective date of this AD, do 

not return to service any HPC stage 3–8 drum 

that was removed as specified in paragraph 

(g) of this AD. 

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 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. 

Issued in Burlington, Massachusetts, on 

April 27, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–9965 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0398; Directorate 

Identifier 2008–NM–193–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

There have been a number of incidents 

where wing-to-fuselage or MLG [main 

landing gear] door fairing panels have 

detached from the aircraft during flight. 

Subsequent inspection revealed the loss of 

the fairing panels to be due to failure of 

certain steel grommets * * *. A detaching 

panel could strike the aircraft during flight, 

causing damage. In addition, a detaching 

panel could become attached to the structure 

or control surfaces, resulting in reduced 

control of the aircraft. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 1, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE.,