[Federal Register Volume 74, Number 82 (Thursday, April 30, 2009)]
[Proposed Rules]
[Pages 19904-19905]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-9965]


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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).

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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.
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> 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.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> 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: <a href="/cdn-cgi/l/email-protection#acc7c9dac5c2f3c8c5cfc7c9ded8eccacdcd82cbc3da"><span class="__cf_email__" data-cfemail="a6cdc3d0cfc8f9c2cfc5cdc3d4d2e6c0c7c788c1c9d0">[email protected]</span></a>; 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.

[[Page 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  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: <a href="/cdn-cgi/l/email-protection#731816051a1d2c171a1018160107331512125d141c05"><span class="__cf_email__" data-cfemail="ddb6b8abb4b382b9b4beb6b8afa99dbbbcbcf3bab2ab">[email protected]</span></a>; 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


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