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, 71373-71375 [2010-29450]
Download as PDF
<![CDATA[
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
(i) For TAE 125–01 engines, Operation &
Maintenance Manual OM–01–02, Issue 3,
Revision 13.
(ii) For TAE 125–02–99 and TAE 125–02–
114 engines, Operation & Maintenance
Manual OM–02–02, Issue 1, Revision 10.
List of Subjects in 14 CFR Part 39
Prohibition of FADEC Software Earlier
Versions
Air transportation, Aircraft, Aviation
safety, Safety.
(f) Once FADEC software version 2.91 is
installed, do not install any earlier version of
FADEC software.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Thielert Aircraft Engines GmbH: Docket No.
FAA–2010–0820; Directorate Identifier
2010–NE–31–AD.
Comments Due Date
(a) We must receive comments by January
7, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Thielert Aircraft
Engines GmbH models TAE 125–01, TAE
125–02–99, and TAE 125–02–114
reciprocating engines installed in, but not
limited to, Cessna 172 and (Reims-built) F172
series (European Aviation Safety Agency
(EASA) STC No. EASA.A.S.01527); Piper
PA–28 series (EASA STC No. EASA.A.S.
01632); APEX (Robin) DR 400 series (EASA
STC No. A.S.01380); and Diamond Aircraft
Industries Models DA 40, DA 42, and DA
42M NG airplanes.
erowe on DSK5CLS3C1PROD with PROPOSALS-1
Reason
(d) This AD results from mandatory
continuing airworthiness information (MCAI)
issued by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. We are
issuing this AD to prevent engine in-flight
shutdown or power loss, possibly resulting in
reduced control of the airplane.
FAA AD Differences
(g) EASA AD 2010–0137 permits
installation of earlier FADEC software
versions, once version 2.91 is installed. This
AD does not.
(h) EASA AD 2010–0137 requires
compliance within 110 flight hours after the
effective date of the AD or during next
maintenance, whichever occurs first, but no
later than 6 months after the effective date of
the AD. This AD requires compliance within
110 flight hours after the effective date of the
AD or during next maintenance, whichever
occurs first.
Alternative Methods of Compliance
(AMOCS)
(i) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(j) Refer to AD 2010–0137, dated June 30,
2010, for related information. Contact
Thielert Aircraft Engines GmbH,
Platanenstrasse 14 D–09350, Lichtenstein,
Germany, telephone: +49–37204–696–0; fax:
+49–37204–696–2912; e-mail:
info@centurion-engines.com, for a copy of
the service information referenced in this
AD.
(k) Contact Alan Strom, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: alan.strom@faa.gov; telephone
(781) 238–7143; fax (781) 238–7199, for more
information about this AD.
Issued in Burlington, Massachusetts, on
November 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2010–29449 Filed 11–22–10; 8:45 am]
BILLING CODE 4910–13–P
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) Within 110 flight hours after the
effective date of the AD or during next
maintenance, whichever occurs first, install
full-authority digital electronic control
(FADEC) software version 2.91.
(2) Guidance on FADEC software
installation can be found in the following:
VerDate Mar<15>2010
14:36 Nov 22, 2010
Jkt 223001
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
71373
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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° 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 burnthrough, uncontrolled under-cowl
engine fire, and damage to the airplane.
DATES: We must receive any comments
on this proposed AD by January 24,
2011.
SUMMARY:
Use one of the following
addresses to comment on this proposed
AD.
• Federal eRulemaking Portal: Go to
https://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.
ADDRESSES:
E:\FR\FM\23NOP1.SGM
23NOP1
71374
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules
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: carlos.fernandes@faa.gov;
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 https://
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).
erowe on DSK5CLS3C1PROD with PROPOSALS-1
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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.
VerDate Mar<15>2010
14:36 Nov 22, 2010
Jkt 223001
Discussion
Since August 2006 we have received
three reports of IAE V2500 series
engines experiencing HPT case burnthrough 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 burnthrough, 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 undercowl 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° 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° 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
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
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.
E:\FR\FM\23NOP1.SGM
23NOP1
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules
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:
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.
PART 39—AIRWORTHINESS
DIRECTIVES
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 undercowl engine fire, and damage to the airplane.
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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–
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° 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:
71375
(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
Stage 1 blade
outer air seal
segments hourssince-new or
since-last-repair
(greater than)
Engine model
A1 ...............................................................................................................................
A5 ...............................................................................................................................
D5 ..............................................................................................................................
(h) Exhaust Gas Temperature Margin is
defined as the expected margin during a sealevel takeoff on a 30-degree Celsius Outside
Air Temperature Day.
erowe on DSK5CLS3C1PROD with PROPOSALS-1
Terminating Action
(i) As terminating action to the repetitive
360° 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–
VerDate Mar<15>2010
14:36 Nov 22, 2010
Jkt 223001
Stage 1 blade
outer air seal
segments cyclessince-new or
since-last-repair
(greater than)
Exhaust gas
temperature
margin degrees
celsius (less than)
3,800
3,500
3,500
45
45
45
6,000
6,000
5,000
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.
(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]
BILLING CODE 4910–13–P
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: mark.riley@faa.gov; telephone
PO 00000
Frm 00008
Fmt 4702
Sfmt 9990
E:\FR\FM\23NOP1.SGM
23NOP1
]]>Agencies
[Federal Register Volume 75, Number 225 (Tuesday, November 23, 2010)]
[Proposed Rules]
[Pages 71373-71375]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-29450]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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:
carlos.fernandes@faa.gov; 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 https://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 https://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
----------------------------------------------------------------------------------------------------------------
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)
----------------------------------------------------------------------------------------------------------------
A1..................................................... 6,000 3,800 45
A5..................................................... 6,000 3,500 45
D5..................................................... 5,000 3,500 45
----------------------------------------------------------------------------------------------------------------
(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:
mark.riley@faa.gov; 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]
BILLING CODE 4910-13-P
