Document ID: FAA-2009-0294-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; International Aero Engines AG (IAE) V2500-A1, V2527E-A5, V2530-A5, and V2528-D5 Turbofan Engines
Posted Date: 2009-06-29T04:00Z

[Federal Register: June 29, 2009 (Volume 74, Number 123)]
[Proposed Rules]               
[Page 30981-30983]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29jn09-17]                         

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0294; Directorate Identifier 2009-NE-08-AD]
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: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for International Aero Engines AG (IAE) V2500-A1, V2527E-A5, V2530-A5, 
and V2528-D5 turbofan engines. This proposed AD would require reducing 
the published life limit of certain high-pressure compressor (HPC) 
stage 9-12 disc assemblies. This proposed AD would also remove from 
service those HPC stage 9-12 disc assemblies using a drawdown schedule. 
This proposed AD results from IAE updating the low-cycle-fatigue (LCF) 
life analysis for certain HPC stage 9-12 disc assemblies. We are 
proposing this AD to prevent an uncontained failure of the HPC stage 9-
12 disc assembly, resulting in an in-flight engine shutdown and 
possible damage to the airplane.

DATES: We must receive any comments on this proposed AD by August 28, 
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.

FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
mark.riley@faa.gov; telephone (781) 238-7758; fax (781) 238-7199.
    Contact International Aero Engines AG, 400 Main Street, East 
Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510, for 
a copy of the service information identified in this proposed AD.

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-2009-0294; Directorate 
Identifier 2009-NE-08-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

    IAE Engineering updated their life analysis for certain HPC stage 
9-12 disc assemblies installed in V2500-A1, V2527E-A5, V2530-A5, and 
V2528-D5 turbofan engines. Stress analysis calculations have shown that 
missing ceramic liner material affects thermal gradients at the weld 
joining discs stage 11 and 12. This results in an increase in the 
stress in the weld, which affects the life of the component. This 
condition, if not corrected, could result in uncontained engine failure 
resulting in an in-flight engine shutdown and possible damage to the 
airplane.

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:
     Reducing the published life limit of HPC stage 9-12 disc 
assemblies, P/N 2A3200, 2A3300, 2A3400, 2A3500, 6A4131, and 6A7545, 
installed in V2500-A1 engines, from 15,000 cycles-since-new (CSN) to 
14,600 CSN; and
     Reducing the published life limit of HPC stage 9-12 disc 
assemblies, P/N 6A4156 and 6A7547, installed in V2527E-A5 and V2530-A5 
engines, from 12,000 CSN to 11,800 CSN; and
     Reducing the published life limit of HPC stage 9-12 disc 
assemblies, P/N 6A4156 and 6A7547, installed in V2528-D5 engines, from 
13,200 CSN to 11,800 CSN.
    This proposed AD would also remove from service those HPC stage 9-
12 disc assemblies using a drawdown schedule.

Costs of Compliance

    We estimate that this proposed AD would affect 18 engines installed 
on airplanes of U.S. registry. We also estimate that it would take 
about 200 work-hours per engine to perform the proposed actions, and 
that the average

[[Page 30982]]

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 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 AG: Docket No. FAA-2009-0294; Directorate 
Identifier 2009-NE-08-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 28, 
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 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 in-flight 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 cycles-since-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.

[[Page 30983]]

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 Mark Riley, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; 
telephone (781) 238-7758; fax (781) 238-7199, for more information 
about this AD.

    Issued in Burlington, Massachusetts, on June 22, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-15250 Filed 6-26-09; 8:45 am]

BILLING CODE 4910-13-P