[Federal Register Volume 75, Number 225 (Tuesday, November 23, 2010)]
[Proposed Rules]
[Pages 71373-71375]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-29450]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0494; Directorate Identifier 2010-NE-20-AD]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines 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: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for 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. This proposed AD would require initial and
repetitive 360[deg] borescope inspections of high-pressure turbine
(HPT) stage 1 blade outer air seal segments for evidence of certain
distress conditions. This proposed AD would also require incorporation
of improved durability stage 1 blade outer air seal segments at the
next exposure to the HPT module subassembly, as terminating action to
the repetitive inspections. This proposed AD results from three reports
received of HPT case burn-through events, numerous shop reports of loss
of stage 1 blade outer air seal segments, and HPT case bulging. We are
proposing this AD to prevent HPT case burn-through, uncontrolled under-
cowl engine fire, and damage to the airplane.
DATES: We must receive any comments on this proposed AD by January 24,
2011.
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.
[[Page 71374]]
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.
FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7189; 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-2010-0494; Directorate
Identifier 2010-NE-20-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
Since August 2006 we have received three reports of IAE V2500
series engines experiencing HPT case burn-through events. There have
also been numerous shop reports of loss of stage 1 blade outer air seal
segments, and reports of HPT case bulging. Investigation revealed the
cause to be due to HPT stage 1 blade outer air seal distress. Distress
initially starts with surface erosion and cracking of the blade outer
air seal segments. Continued engine operation then leads to burn-
through, radial bowing of the segments into the gas path, contact with
the HPT stage 1 blades, and loss of the segments from the HPT case.
This condition, if not corrected, could then result in HPT case burn-
through, uncontrolled under-cowl engine fire, and damage to the
airplane.
Relevant Service Information
We have reviewed and approved the technical contents of IAE Service
Bulletin (SB) No. V2500-ENG-72-0580, Revision 2, dated August 12, 2010,
that describes procedures for initial and repetitive 360[deg] borescope
inspections of stage 1 blade outer air seal segments for evidence of
distress. We have also reviewed and approved IAE SB No. V2500-ENG-72-
0483, Revision 3, dated January 7, 2009, and IAE SB No. V2500-ENG-72-
0542, Revision 1, dated January 7, 2009, which incorporate improved
durability stage 1 blade outer air seal segments.
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
initial and repetitive 360[deg] borescope inspections of HPT stage 1
blade outer air seal segments for evidence of distress. This proposed
AD would also require incorporation of improved design stage 1 blade
outer air seal segments at the next exposure to the HPT module
subassembly. The proposed AD would require you to use the service
information described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would affect 34 V2500 A1 series
and 510 V2500 A5/D5 series engines installed on airplanes of U.S.
registry. We also estimate that it would take about 3 work-hours per
engine to perform one proposed inspection, about 3 work-hours per
engine to install the improved durability stage 1 blade outer air seal
segments, and that the average labor rate is $85 per work-hour.
Required parts would cost about $150,882 (V2500 A1 series) and $155,195
(V2500 A5/D5 series), per engine. Based on these figures, we estimate
the total cost of the proposed AD to U.S. operators to be $84,556,878.
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, Incorporation by
reference, Safety.
[[Page 71375]]
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-2010-0494; Directorate
Identifier 2010-NE-20-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 24,
2011.
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. These engines are
installed on, but not limited to, Airbus A319, A320, A321, and
McDonnell Douglas MD-90 airplanes.
Unsafe Condition
(d) This AD results from three reports received of high-pressure
turbine (HPT) case burn-through events. There have also been
numerous shop reports of loss of stage 1 blade outer air seal
segments, and HPT case bulging. We are issuing this AD to prevent
HPT case burn-through, uncontrolled under-cowl engine fire, and
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.
(f) For engines that have incorporated IAE Service Bulletin (SB)
No. V2500-ENG-72-0483, Revision 3 or earlier, or IAE SB No. V2500-
ENG-72-0542, Revision 1 or earlier, no further action is required.
Borescope Inspections
(g) Perform 360[deg] borescope inspections of the HPT stage 1
blade outer air seal segments for evidence of the distress
conditions listed in Appendix D of IAE SB No. V2500-ENG-72-0580,
Revision 2, dated August 12, 2010.
(1) For V2525-D5 and V2528-D5 turbofan engines:
(i) Inspect within 1,000 operating hours after the engine meets
all criteria as defined in Table 1 of this AD, or within 600
operating hours after the effective date of this AD, whichever is
greater.
(ii) Thereafter, re-inspect within every 1,000 operating hours
or as defined in Appendix D of IAE SB No. V2500-ENG-72-0580,
Revision 2, dated August 12, 2010, whichever is less.
(iii) Use Accomplishment Instructions paragraphs 3.B.(1) through
3.B.(3), and Appendices A through D of IAE SB No. V2500-ENG-72-0580,
Revision 2, dated August 12, 2010, to do these inspections.
(2) For V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5,
V2527M-A5, V2530-A5, and V2533-A5 turbofan engines:
(i) Inspect within 1,200 operating hours after the engine meets
all criteria as defined in Table 1 of this AD, or within 600
operating hours after the effective date of this AD, whichever is
greater.
(ii) Thereafter, re-inspect within every 1,200 operating hours
or as defined in Appendix D of IAE SB No. V2500-ENG-72-0580,
Revision 2, dated August 12, 2010, whichever is less.
(iii) Use Accomplishment Instructions paragraphs 3.A.(1) through
3.A.(3), and Appendices A through D of IAE SB No. V2500-ENG-72-0580,
Revision 2, dated August 12, 2010, to do these inspections.
Table 1--Stage 1 Blade Outer Air Seal Segment Inspection Compliance Criteria
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Stage 1 blade Stage 1 blade
outer air seal outer air seal Exhaust gas
segments hours- segments cycles- temperature
Engine model since-new or since-new or margin degrees
since-last-repair since-last-repair celsius (less
(greater than) (greater than) than)
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A1..................................................... 6,000 3,800 45
A5..................................................... 6,000 3,500 45
D5..................................................... 5,000 3,500 45
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(h) Exhaust Gas Temperature Margin is defined as the expected
margin during a sea-level takeoff on a 30-degree Celsius Outside Air
Temperature Day.
Terminating Action
(i) As terminating action to the repetitive 360[deg] borescope
inspections required in paragraphs (g)(1)(ii) and (g)(2)(ii) above,
install improved durability stage 1 blade outer air seal segments at
the next HPT module subassembly exposure.
(1) For V2500-A1 turbofan engines, use paragraphs 1.B.,
Concurrent Requirements, and paragraphs 3.(1) through 3.(2)(b) of
the Accomplishment Instructions of IAE SB No. V2500-ENG-72-0542,
Revision 1, dated January 7, 2009, to do the installation.
(2) For V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5,
V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines, use
paragraphs 1.B., Concurrent Requirements, and paragraphs 3.(1)
through 3.(2)(b) of the Accomplishment Instructions of IAE SB No.
V2500-ENG-72-0483, Revision 3, dated January 7, 2009, to do the
installation.
(3) Both IAE SBs No. V2500-ENG-72-0542, Revision 1, and SB No.
V2500-ENG-72-0483, Revision 3, require modification of the stage 1
HPT support assembly before installing the new blade outer air seal
segments. You must complete the modification using those SBs, as
applicable to the appropriate engine model, to properly perform the
mandatory terminating action of this AD.
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) Contact Carlos Fernandes, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7189; fax (781) 238-7199,
for more information about this AD.
(l) 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 referenced in this AD.
Issued in Burlington, Massachusetts, on November 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-29450 Filed 11-22-10; 8:45 am]
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