Document ID: FAA-2007-29060-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: International Aero Engines
Posted Date: 2009-12-23T05:00Z

[Federal Register: December 23, 2009 (Volume 74, Number 245)]
[Proposed Rules]               
[Page 68192-68194]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23de09-19]                         

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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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[[Page 68192]]

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), Department of 
Transportation (DOT).

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: This supplemental NPRM revises an earlier proposed 
airworthiness directive (AD) applicable to IAE V2500-A1, V2527E-A5, 
V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. That 
proposed AD would have required a one-time 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. That proposed AD 
resulted from reports of fractured vortex reducers found at shop 
visits. This supplemental NPRM revises the proposed AD to add four 
engine models and four additional part numbers of HP compressor stage 
3-8 drums to the applicability requirement. This proposed AD results 
from the manufacturer's latest service information containing engine 
models and drum assembly P/Ns that were not specified in the proposed 
AD. We are proposing this AD to inspect for cracks in the vortex 
reducer. Cracks in the vortex reducer could result in an uncontained 
failure of the HP compressor stage 3-8 drum and subsequent damage to 
the airplane.

DATES: We must receive any comments on this proposed AD by February 22, 
2010.

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.
    You can get the service information identified in this proposed AD 
from International Aero Engines, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-5515, fax (860) 565-0600.

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. 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

    On April 27, 2009, we issued a proposal to amend part 39 of the 
Code of Federal Regulations (14 CFR part 39) to add an AD applicable to 
IAE V2500-A1, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 
turbofan engines. The proposed AD published as an NPRM in the Federal 
Register on April 30, 2009 (74 FR 19904). That NPRM proposed to require 
a one-time fluorescent penetrant inspection of certain vortex reducers 
for cracks. This condition, if not corrected, could result in an 
uncontained failure of the HP compressor stage 3-8 drum and subsequent 
damage to the airplane.
    Since we issued that NPRM, IAE has informed us that IAE Alert 
Service Bulletin (ASB) V2500-ENG-72-A0510, Revision 2, dated December 
19, 2007, contains additional engine models and HP compressor Stage 3 
to 8 drum P/Ns that must be inspected. Because we expanded the 
population of affected engines by adding the V2522-A5, V2524-A5, V2525-
D5, and V2527-A5 engine models and HP compressor stage 3 to 8 drums, P/
Ns 6A4900, 6A7383, 6A7384, and 6A7385, this supplemental NPRM reopens 
the comment period to include the additional engine models and drum P/
Ns.

Comments

    We provided the public the opportunity to participate in the 
development of this proposed AD. We have considered the comments 
received.

[[Page 68193]]

Request To Add Additional Part Numbers and Engine Models

    One commenter, IAE, asks us to add to the applicability of the 
proposed AD, additional part numbers (P/Ns) for the HP compressor stage 
3 to 8 drum, and additional IAE engine models that were not included in 
the NPRM.
    The commenter states that we need to make the AD applicable to the 
additional P/Ns and engine models to ensure that the proposed AD covers 
all affected parts.
    We agree. We have added P/Ns 6A4900, 6A7383, 6A7384, and 6A7385; 
and IAE engine models V2522-A5, V2524-A5, V2525-D5, V2527-A5 turbofan 
engines to the applicability.

Request To Revise Costs of Compliance Section

    One commenter, Air Transport Association, asks us to revise the 
Costs of Compliance section to include six engines operated by Delta 
Airlines.
    We agree. We have changed the Costs of Compliance section to 
include the six engines operated by Delta, and provided an estimated 
total cost to the fleet.

Relevant Service Information

    We have reviewed and approved the technical contents of IAE ASB 
V2500-ENG-72-0510, Revision 2, dated December 19, 2007, that describes 
procedures for inspecting the vortex reducer for cracks.

FAA's Determination and Requirements of the Proposed AD

    We 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 will require a one-
time fluorescent penetrant inspection of certain vortex reducers for 
cracks.

Costs of Compliance

    We estimate that this proposed AD would affect six IAE turbofan 
engines installed on airplanes of U.S. registry. We also estimate that 
it would take about 1 work-hour per engine to perform the proposed 
actions, and that the average labor rate is $80 per work-hour. No parts 
are required. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $480.

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 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 
regulation:
    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. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 February 22, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to International Aero Engines (IAE) V2500-
A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, 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) 6A4900, 6A5467, 
6A6473, 6A7383, 6A7384, 6A7385, 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 result in 
an uncontained failure of the HP compressor stage 3-8 drum and 
subsequent 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.

One-Time 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, or V2533-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,

[[Page 68194]]

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.

Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-30508 Filed 12-22-09; 8:45 am]

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