AD 2010-06-18

[Federal Register Volume 75, Number 52 (Thursday, March 18, 2010)]
[Rules and Regulations]
[Pages 12971-12972]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-5860]


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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; 
Amendment 39-16243; AD 2010-06-18]
RIN 2120-AA64


Airworthiness Directives; 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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for IAE 
V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, 
V2528-D5, V2530-A5, and V2533-A5 turbofan engines. This AD requires a 
onetime fluorescent penetrant inspection of certain vortex reducers for 
cracks. 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 high-pressure (HP) compressor stage 3-8 drum 
and subsequent damage to the airplane.

DATES: This AD becomes effective April 22, 2010.

ADDRESSES: 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 
<a href="/cdn-cgi/l/email-protection#d1b5b8b2bab4a3a591b7b0b0ffb6bea7"><span class="__cf_email__" data-cfemail="c0a4a9a3aba5b2b480a6a1a1eea7afb6">[email&#160;protected]</span></a>; 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, V2522-A5, 
V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, 
and V2533-A5 turbofan engines. We published the proposed AD in the 
Federal Register on April 30, 2009 (74 FR 19904), and a supplemental 
proposed AD on December 23, 2009 (74 FR 68192). That action proposed to 
require a onetime inspection of certain vortex reducers for cracks, and 
replacing the reducer and HP compressor stage 3-8 drum if the reducer 
is cracked.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 developing 
this AD. We responded to the comments received on the NPRM, in the 
supplemental NPRM. We received no comments on the supplemental NPRM 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 six IAE turbofan engines 
installed on airplanes of U.S. registry. We also estimate that it will 
take about one work-hour per engine to perform the 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 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 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

0
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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2010-06-18 International Aero Engines: Amendment 39-16243. Docket 
No. FAA-2007-29060; Directorate Identifier 2007-NE-34-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
22, 2010.

[[Page 12972]]

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.

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, 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, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: kevin 
<a href="/cdn-cgi/l/email-protection#90f4f9f3fbf5e2e4d0f6f1f1bef7ffe6"><span class="__cf_email__" data-cfemail="117578727a746365517770703f767e67">[email&#160;protected]</span></a>; telephone (781) 238-7117; fax (781) 238-7199, for 
more information about this AD.

Material Incorporated by Reference

    (k) None.


    Issued in Burlington, Massachusetts, on March 11, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-5860 Filed 3-17-10; 8:45 am]
BILLING CODE 4910-13-P