Airworthiness Directives; General Electric Company (GE) GE90-110B1 and GE90-115B Turbofan Engines, 82103-82105 [2011-32832]
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Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Rules and Regulations
associated with the information in the NRC’s
EA for the AP1000 design, Appendix 1B of
Revision 15 of the generic DCD, the NRC’s
final EA for Amendment 1 to the AP1000
design, and Appendix 1B of Revision 19 of
the generic DCD, for plants referencing this
appendix whose site parameters are within
those specified in the severe accident
mitigation design alternatives evaluation.
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E. The NRC will specify at an appropriate
time the procedures to be used by an
interested person who wishes to review
portions of the design certification or
references containing safeguards information
or sensitive unclassified non-safeguards
information (including proprietary
information, such as trade secrets or financial
information obtained from a person that are
privileged or confidential (10 CFR 2.390 and
10 CFR part 9)), for the purpose of
participating in the hearing required by 10
CFR 52.85, the hearing provided under 10
CFR 52.103, or in any other proceeding
relating to this appendix in which interested
persons have a right to request an
adjudicatory hearing.
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VIII. Processes for Changes and Departures
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B. * * *
5. * * *
b. A proposed departure from Tier 2, other
than one affecting resolution of a severe
accident issue identified in the plant-specific
DCD or one affecting information required by
10 CFR52.47(a)(28) to address 10 CFR 50.150,
requires a license amendment if it would:
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d. If an applicant or licensee proposes to
depart from the information required by 10
CFR 52.47(a)(28) to be included in the FSAR
for the standard design certification, then the
applicant or licensee shall consider the effect
of the changed feature or capability on the
original assessment required by 10 CFR
50.150(a). The applicant or licensee must
also document how the modified design
features and functional capabilities continue
to meet the assessment requirements in 10
CFR 50.150(a)(1) in accordance with Section
X of this appendix.
tkelley on DSK3SPTVN1PROD with RULES
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b. A licensee who references this appendix
may not depart from the following Tier 2*
matters without prior NRC approval. A
request for a departure will be treated as a
request for a license amendment under 10
CFR 50.90.
(1) Maximum fuel rod average burn-up.
(2) Fuel principal design requirements.
(3) Fuel criteria evaluation process.
(4) Fire areas.
(5) Reactor coolant pump type.
(6) Small-break loss-of-coolant accident
(LOCA) analysis methodology.
(7) Screen design criteria.
(8) Heat sink data for containment pressure
analysis.
c. A licensee who references this appendix
may not, before the plant first achieves full
power following the finding required by 10
CFR 52.103(g), depart from the following Tier
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2* matters except under paragraph B.6.b of
this section. After the plant first achieves full
power, the following Tier 2* matters revert
to Tier 2 status and are subject to the
departure provisions in paragraph B.5 of this
section.
(1) Nuclear Island structural dimensions.
(2) American Society of Mechanical
Engineers Boiler & Pressure Vessel Code
(ASME Code) piping design and welding
restrictions, and ASME Code Cases.
(3) Design Summary of Critical Sections.
(4) American Concrete Institute (ACI) 318,
ACI 349, American National Standards
Institute/American Institute of Steel
Construction (ANSI/AISC)–690, and
American Iron and Steel Institute (AISI),
‘‘Specification for the Design of Cold Formed
Steel Structural Members, Part 1 and 2,’’
1996 Edition and 2000 Supplement.
(5) Definition of critical locations and
thicknesses.
(6) Seismic qualification methods and
standards.
(7) Nuclear design of fuel and reactivity
control system, except burn-up limit.
(8) Motor-operated and power-operated
valves.
(9) Instrumentation and control system
design processes, methods, and standards.
(10) Passive residual heat removal (PRHR)
natural circulation test (first plant only).
(11) Automatic depressurization system
(ADS) and core make-up tank (CMT)
verification tests (first three plants only).
(12) Polar crane parked orientation.
(13) Piping design acceptance criteria.
(14) Containment vessel design parameters,
including ASME Code, Section III,
Subsection NE.
(15) Human factors engineering.
(16) Steel composite structural module
details.
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X. Records and Reporting
A. * * *
1. The applicant for this appendix shall
maintain a copy of the generic DCD that
includes all generic changes it makes to Tier
1 and Tier 2, and the generic TS and other
operational requirements. The applicant shall
maintain sensitive unclassified nonsafeguards information (including
proprietary information) and safeguards
information referenced in the generic DCD
for the period that this appendix may be
referenced, as specified in Section VII of this
appendix.
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4.a. The applicant for the AP1000 design
shall maintain a copy of the AIA performed
to comply with the requirements of 10 CFR
50.150(a) for the term of the certification
(including any period of renewal).
b. An applicant or licensee who references
this appendix shall maintain a copy of the
AIA performed to comply with the
requirements of 10 CFR 50.150(a) throughout
the pendency of the application and for the
term of the license (including any period of
renewal).
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Dated at Rockville, Maryland, this 22nd
day of December 2011.
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82103
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. 2011–33266 Filed 12–29–11; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0278; Directorate
Identifier 2010–NE–10–AD; Amendment 39–
16901; AD 2011–26–11]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) GE90–110B1
and GE90–115B Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above, with certain part
number (P/N) high-pressure compressor
(HPC) stages 2–5 spools installed. This
AD was prompted by an aborted takeoff
caused by liberation of small pieces
from the HPC stages 1–2 seal teeth and
two shop findings of cracks in the seal
teeth. This AD requires eddy current
inspection (ECI) or spot fluorescent
penetrant inspection (FPI) of the stages
1–2 seal teeth of the HPC stages 2–5
spool for cracks. This AD only allows
installation of either HPC stator stage 1
interstage seals that are pregrooved or
previously worn seals with acceptable
wear marks to prevent heavy rubs. We
are issuing this AD to detect cracks in
the HPC stages 1–2 seal teeth due to
heavy rubs that could result in failure of
the seal of the HPC stages 2–5 spool,
uncontained engine failure, and damage
to the airplane.
DATES: This AD is effective February 3,
2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of February 3, 2012.
ADDRESSES: For service information
identified in this proposed AD, contact
General Electric, GE–Aviation, Room
285, 1 Neumann Way, Cincinnati, Ohio
45215; email: geae.aoc@ge.com; phone:
(513) 552–3272; fax: (513) 552–3329.
You may review copies of the
referenced service information at the
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
Burlington, MA. For information on the
availability of this material at the FAA,
call (781) 238–7125.
SUMMARY:
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Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Rules and Regulations
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility 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 address for the
Docket Office (phone: (800) 647–5527)
is Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: (781) 238–7747; fax: (781) 238–
7199; email: jason.yang@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM published in the Federal
Register on May 26, 2011 (76 FR 30573).
That NPRM proposed to require ECI or
spot FPI of the stages 1–2 seal teeth of
the HPC stages 2–5 spool for cracks and
to prohibit installation of HPC stator
stage 1 interstage seals that are not
pregrooved to prevent heavy rubs.
great certainty. Cracks propagating into
the seal will result in a more substantial
failure of the HPC stages 1–2 seal.
Historical experience has shown that
catastrophic failure of critical rotating
engine parts can result in an
uncontained engine failure that can
damage the airplane. We did not change
the AD based on this comment.
Request Change to Service Bulletin
Reference
Two commenters, Boeing and GE,
requested that we change the ‘‘Previous
Credit’’ section by replacing ‘‘SB GE90–
100 S/B 72–0320, Revision 01, dated
May 11, 2010 or earlier revision’’ with
‘‘SB GE90–100 S/B 72–0320, Revision
02, dated October 1, 2010, or earlier
version.’’ The commenters indicated
that the NPRM (76 FR 30573, May 26,
2011) mandates accomplishment of GE
Service Bulletin (SB) GE90–100
S/B 72–0320, Revision 02, dated
October 1, 2010, and therefore it would
be consistent to provide credit for
accomplishment of GE SB GE90–100
S/B 72–0320, Revision 02, dated
October 1, 2010, or an earlier revision.
We agree. We changed the reference
in the service bulletin to Revision 02 in
the Previous Credit paragraph.
Remove Reference to ‘‘Uncontained
Engine Failure and Damage to the
Airplane’’
Request To Allow Reinstallation of
Previously Worn Seals
Three commenters, FedEx, Japan
Airlines and All Nippon Airways,
requested that the FAA allow the
installation of previously worn seals.
Use of these seals is allowed by GE SB
GE90–100 S/B 72–0360.
We agree. We replaced the Installation
Prohibition paragraph in the AD with a
new paragraph called ‘‘Installation of
HPC Stator Stage 1 Interstage Seals’’ to
allow for the installation of previously
worn seals. Refer to GE SB GE90–100
S/B 72–360, Revision 04, dated
November 7, 2011, for seals eligible for
installation.
Two commenters, Boeing Company
(Boeing) and GE, wanted us to remove
the reference to ‘‘uncontained engine
failure, and damage to the airplane’’
from the Summary and Unsafe
Condition paragraphs. GE claimed that
all instances to date of material
liberation have been contained. The
commenters further stated that it has
been demonstrated that once the crack
reaches the aft tooth, it turns
circumferentially, which minimizes the
amount of material liberated.
We disagree. While all of the fractures
to date have resulted in small pieces
that are contained by the engine case,
the direction that the crack will
propagate cannot be determined with
Request Change in Installation
Prohibition Section
FedEx requested that wording in the
‘‘Installation Prohibition’’ section that
states ‘‘do not install any HPC forward
case unless it has an HPC stator stage 1
interstage seals, P/N 351–109–503–0’’ be
changed to ‘‘allow the installation of
previously worn seals and/or potential
future (post-SB 72–0358) interstage seal
configurations.’’ FedEx indicated that
the current wording unnecessarily
prohibits the installation of any
forthcoming design improvements to the
interstage seals that GE might develop.
We partially agree. We agree with use
of a previously worn interstage seal
because a worn interstage seal could
Comments
tkelley on DSK3SPTVN1PROD with RULES
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal and the FAA’s
response to each comment.
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prevent the HPC stages 2–5 spool from
cracking. We disagree with use of the
phrase ‘‘potential future (post-SB 72–
0358) interstage seal configurations’’
because the AD compliance section can
only mandate the use of currently
approved designs. We added a new
paragraph called ‘‘Installation of HPC
Stator Stage 1 Interstage Seals,’’ which
allows for the installation of previously
worn seals.
Remove Reference to Pregrooved Seals
GE stated that the AD requires the
HPC module be reassembled with
pregrooved seals. GE indicated that this
requirement to use pregrooved seals is
beyond the inspection requirements in
GE90–100 S/B 72–0320. GE said that the
inclusion of pregrooved seal references
would cause disagreement with the
‘‘Relevant Service Information’’ and
‘‘Previous Credit’’ paragraphs which
refer only to the inspection requirement
in GE90–100 S/B 72–0320.
We disagree. This AD is issued to
mitigate a safety issue caused by failure
of the HPC stages 2–5 spool stages 1–2
seal. Reassembling the HPC module
with a pregrooved seal would prevent
the heavy rubs that result in HPC stages
2–5 spool stages 1–2 seal failure. We did
not change the AD based on this
comment.
Request Correction to Address
GE requested that its address in the
Addresses paragraph be revised to
correct a missing space.
We agree. We corrected the GE
address in the Addresses paragraph of
the AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
30573, May 26, 2011) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 30573,
May 26, 2011).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD affects 19
GE90–110B1 and GE90–115B engines
installed on airplanes of U.S. registry.
We also estimate that it will take about
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Federal Register / Vol. 76, No. 251 / Friday, December 30, 2011 / Rules and Regulations
2 work-hours per engine to perform the
proposed actions, and that the average
labor rate is $85 per work-hour.
Required parts will cost about $9,857
per engine. Based on these figures, we
estimate the total cost of this AD to U.S.
operators to be $190,513.
Authority for This Rulemaking
Regulatory Findings
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),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
tkelley on DSK3SPTVN1PROD with RULES
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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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):
■
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.
Adoption of the Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
2011–26–11 General Electric Company:
Amendment 39–16901; Docket No.
FAA–2011–0278; Directorate Identifier
2010–NE–10–AD.
(a) Effective Date
This AD is effective February 3, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company (GE) GE90–110B1 and GE90–115B
turbofan engines with high-pressure
compressor (HPC) stages 2–5 spool, part
number (P/Ns) 351–103–106–0, 351–103–
107–0, 351–103–108–0, 351–103–109–0,
351–103–141–0, 351–103–142–0, 351–103–
143–0, or 351–103–144–0, installed.
(d) Unsafe Condition
This AD was prompted by an aborted
takeoff caused by liberation of small pieces
from HPC stages 1–2 seal teeth and two shop
findings of cracks in the seal teeth. We are
issuing this AD to detect cracks in the HPC
stages 1–2 seal teeth due to heavy rubs that
could result in failure of the seal of the HPC
stages 2–5 spool, uncontained engine failure,
and damage to the airplane.
(e) Compliance
Comply with this AD when the HPC
forward case half is removed from the engine
after the effective date of this AD, unless the
actions have already been done.
(f) Inspection
Perform an eddy current inspection (ECI)
or a fluorescent penetrant inspection (FPI) of
the HPC stages 1–2 seal teeth using
paragraphs 3.B. or 3.C. of GE Service Bulletin
(SB) GE90–100 S/B 72–0320, Revision 02,
dated October 1, 2010.
(g) Remove Cracked Spools
Remove from service HPC stages 2–5 spool
with cracked stages 1–2 seal teeth before
further flight.
(h) Previous Credit
An ECI or FPI inspection performed before
the effective date of this AD using GE SB
GE90–100 S/B 72–0320, Revision 02, dated
October 1, 2010, or earlier revision, satisfies
the inspection requirement of this AD.
(i) Installation of HPC Stator Stage 1
Interstage Seals
(1) After the effective date of this AD, do
not install or reinstall any HPC forward case
unless it is equipped with either:
(i) HPC stator stage 1 interstage seals, P/N
351–109–503–0;
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82105
(ii) HPC stator stage 1 interstage seals, P/
N 351–109–502–0, with the grooves on seals
that meet the dimensional requirements
defined in paragraph 3.D.(1) of GE SB GE90–
100 S/B 72–360, Revision 04, dated
November 7, 2011.
(iii) A mixture of the HPC stator stage 1
interstage seals listed in paragraphs (i)(1)(i)
and (i)(1)(ii) of this AD.
(j) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make
your request.
(k) Related Information
(1) Contact Jason Yang, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: (781) 238–7747; fax: (781)
238–7199; email: jason.yang@faa.gov, for
more information about this AD.
(2) GE Service Bulletins GE90–100 S/B 72–
0320, Revision 02, dated October 1, 2010,
and GE90–100 S/B 72–0360, Revision 04,
November 7, 2011, pertain to the subject of
this AD. Contact General Electric, GE–
Aviation, Room 285, 1 Neumann Way,
Cincinnati, Ohio 45215; email:
geae.aoc@ge.com; phone: (513) 552–3272;
fax: (513) 552–3329; for a copy of this service
information.
(l) Material Incorporated by Reference
(1) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51 of the
following service information:
(i) General Electric Company (GE) Service
Bulletin (SB) GE90–100 S/B 72–0320,
Revision 02, October 1, 2010; and
(ii) GE SB GE90–100 S/B 72–0360,
Revision 04, dated November, 7, 2011.
(2) For service information identified in
this AD, contact General Electric, GE–
Aviation, Room 285, 1 Neumann Way,
Cincinnati, Ohio 45215; email:
geae.aoc@ge.com; phone: (513) 552–3272;
fax: (513) 552–3329.
(3) You may review copies of the
referenced service information at the FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call (781) 238–7125.
(4) You may also review copies of the
service information incorporated by reference
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
December 15, 2011.
Thomas A. Boudreau,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2011–32832 Filed 12–29–11; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 76, Number 251 (Friday, December 30, 2011)]
[Rules and Regulations]
[Pages 82103-82105]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-32832]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0278; Directorate Identifier 2010-NE-10-AD;
Amendment 39-16901; AD 2011-26-11]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) GE90-
110B1 and GE90-115B Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above, with certain part number (P/N) high-pressure
compressor (HPC) stages 2-5 spools installed. This AD was prompted by
an aborted takeoff caused by liberation of small pieces from the HPC
stages 1-2 seal teeth and two shop findings of cracks in the seal
teeth. This AD requires eddy current inspection (ECI) or spot
fluorescent penetrant inspection (FPI) of the stages 1-2 seal teeth of
the HPC stages 2-5 spool for cracks. This AD only allows installation
of either HPC stator stage 1 interstage seals that are pregrooved or
previously worn seals with acceptable wear marks to prevent heavy rubs.
We are issuing this AD to detect cracks in the HPC stages 1-2 seal
teeth due to heavy rubs that could result in failure of the seal of the
HPC stages 2-5 spool, uncontained engine failure, and damage to the
airplane.
DATES: This AD is effective February 3, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 3,
2012.
ADDRESSES: For service information identified in this proposed AD,
contact General Electric, GE-Aviation, Room 285, 1 Neumann Way,
Cincinnati, Ohio 45215; email: geae.aoc@ge.com; phone: (513) 552-3272;
fax: (513) 552-3329. You may review copies of the referenced service
information at the FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call (781) 238-7125.
[[Page 82104]]
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
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 address for the
Docket Office (phone: (800) 647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: (781) 238-7747;
fax: (781) 238-7199; email: jason.yang@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM published in the Federal Register on May 26, 2011 (76 FR
30573). That NPRM proposed to require ECI or spot FPI of the stages 1-2
seal teeth of the HPC stages 2-5 spool for cracks and to prohibit
installation of HPC stator stage 1 interstage seals that are not
pregrooved to prevent heavy rubs.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Remove Reference to ``Uncontained Engine Failure and Damage to the
Airplane''
Two commenters, Boeing Company (Boeing) and GE, wanted us to remove
the reference to ``uncontained engine failure, and damage to the
airplane'' from the Summary and Unsafe Condition paragraphs. GE claimed
that all instances to date of material liberation have been contained.
The commenters further stated that it has been demonstrated that once
the crack reaches the aft tooth, it turns circumferentially, which
minimizes the amount of material liberated.
We disagree. While all of the fractures to date have resulted in
small pieces that are contained by the engine case, the direction that
the crack will propagate cannot be determined with great certainty.
Cracks propagating into the seal will result in a more substantial
failure of the HPC stages 1-2 seal. Historical experience has shown
that catastrophic failure of critical rotating engine parts can result
in an uncontained engine failure that can damage the airplane. We did
not change the AD based on this comment.
Request Change to Service Bulletin Reference
Two commenters, Boeing and GE, requested that we change the
``Previous Credit'' section by replacing ``SB GE90-100 S/B 72-0320,
Revision 01, dated May 11, 2010 or earlier revision'' with ``SB GE90-
100 S/B 72-0320, Revision 02, dated October 1, 2010, or earlier
version.'' The commenters indicated that the NPRM (76 FR 30573, May 26,
2011) mandates accomplishment of GE Service Bulletin (SB) GE90-100 S/B
72-0320, Revision 02, dated October 1, 2010, and therefore it would be
consistent to provide credit for accomplishment of GE SB GE90-100 S/B
72-0320, Revision 02, dated October 1, 2010, or an earlier revision.
We agree. We changed the reference in the service bulletin to
Revision 02 in the Previous Credit paragraph.
Request To Allow Reinstallation of Previously Worn Seals
Three commenters, FedEx, Japan Airlines and All Nippon Airways,
requested that the FAA allow the installation of previously worn seals.
Use of these seals is allowed by GE SB GE90-100 S/B 72-0360.
We agree. We replaced the Installation Prohibition paragraph in the
AD with a new paragraph called ``Installation of HPC Stator Stage 1
Interstage Seals'' to allow for the installation of previously worn
seals. Refer to GE SB GE90-100 S/B 72-360, Revision 04, dated November
7, 2011, for seals eligible for installation.
Request Change in Installation Prohibition Section
FedEx requested that wording in the ``Installation Prohibition''
section that states ``do not install any HPC forward case unless it has
an HPC stator stage 1 interstage seals, P/N 351-109-503-0'' be changed
to ``allow the installation of previously worn seals and/or potential
future (post-SB 72-0358) interstage seal configurations.'' FedEx
indicated that the current wording unnecessarily prohibits the
installation of any forthcoming design improvements to the interstage
seals that GE might develop.
We partially agree. We agree with use of a previously worn
interstage seal because a worn interstage seal could prevent the HPC
stages 2-5 spool from cracking. We disagree with use of the phrase
``potential future (post-SB 72-0358) interstage seal configurations''
because the AD compliance section can only mandate the use of currently
approved designs. We added a new paragraph called ``Installation of HPC
Stator Stage 1 Interstage Seals,'' which allows for the installation of
previously worn seals.
Remove Reference to Pregrooved Seals
GE stated that the AD requires the HPC module be reassembled with
pregrooved seals. GE indicated that this requirement to use pregrooved
seals is beyond the inspection requirements in GE90-100 S/B 72-0320. GE
said that the inclusion of pregrooved seal references would cause
disagreement with the ``Relevant Service Information'' and ``Previous
Credit'' paragraphs which refer only to the inspection requirement in
GE90-100 S/B 72-0320.
We disagree. This AD is issued to mitigate a safety issue caused by
failure of the HPC stages 2-5 spool stages 1-2 seal. Reassembling the
HPC module with a pregrooved seal would prevent the heavy rubs that
result in HPC stages 2-5 spool stages 1-2 seal failure. We did not
change the AD based on this comment.
Request Correction to Address
GE requested that its address in the Addresses paragraph be revised
to correct a missing space.
We agree. We corrected the GE address in the Addresses paragraph of
the AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
[Agr]re consistent with the intent that was proposed in
the NPRM (76 FR 30573, May 26, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 30573, May 26, 2011).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 19 GE90-110B1 and GE90-115B
engines installed on airplanes of U.S. registry. We also estimate that
it will take about
[[Page 82105]]
2 work-hours per engine to perform the proposed actions, and that the
average labor rate is $85 per work-hour. Required parts will cost about
$9,857 per engine. Based on these figures, we estimate the total cost
of this AD to U.S. operators to be $190,513.
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
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA 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 (AD):
2011-26-11 General Electric Company: Amendment 39-16901; Docket No.
FAA-2011-0278; Directorate Identifier 2010-NE-10-AD.
(a) Effective Date
This AD is effective February 3, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) GE90-110B1 and
GE90-115B turbofan engines with high-pressure compressor (HPC)
stages 2-5 spool, part number (P/Ns) 351-103-106-0, 351-103-107-0,
351-103-108-0, 351-103-109-0, 351-103-141-0, 351-103-142-0, 351-103-
143-0, or 351-103-144-0, installed.
(d) Unsafe Condition
This AD was prompted by an aborted takeoff caused by liberation
of small pieces from HPC stages 1-2 seal teeth and two shop findings
of cracks in the seal teeth. We are issuing this AD to detect cracks
in the HPC stages 1-2 seal teeth due to heavy rubs that could result
in failure of the seal of the HPC stages 2-5 spool, uncontained
engine failure, and damage to the airplane.
(e) Compliance
Comply with this AD when the HPC forward case half is removed
from the engine after the effective date of this AD, unless the
actions have already been done.
(f) Inspection
Perform an eddy current inspection (ECI) or a fluorescent
penetrant inspection (FPI) of the HPC stages 1-2 seal teeth using
paragraphs 3.B. or 3.C. of GE Service Bulletin (SB) GE90-100 S/B 72-
0320, Revision 02, dated October 1, 2010.
(g) Remove Cracked Spools
Remove from service HPC stages 2-5 spool with cracked stages 1-2
seal teeth before further flight.
(h) Previous Credit
An ECI or FPI inspection performed before the effective date of
this AD using GE SB GE90-100 S/B 72-0320, Revision 02, dated October
1, 2010, or earlier revision, satisfies the inspection requirement
of this AD.
(i) Installation of HPC Stator Stage 1 Interstage Seals
(1) After the effective date of this AD, do not install or
reinstall any HPC forward case unless it is equipped with either:
(i) HPC stator stage 1 interstage seals, P/N 351-109-503-0;
(ii) HPC stator stage 1 interstage seals, P/N 351-109-502-0,
with the grooves on seals that meet the dimensional requirements
defined in paragraph 3.D.(1) of GE SB GE90-100 S/B 72-360, Revision
04, dated November 7, 2011.
(iii) A mixture of the HPC stator stage 1 interstage seals
listed in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(j) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(k) Related Information
(1) Contact Jason Yang, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; phone: (781) 238-7747; fax:
(781) 238-7199; email: jason.yang@faa.gov, for more information
about this AD.
(2) GE Service Bulletins GE90-100 S/B 72-0320, Revision 02,
dated October 1, 2010, and GE90-100 S/B 72-0360, Revision 04,
November 7, 2011, pertain to the subject of this AD. Contact General
Electric, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, Ohio
45215; email: geae.aoc@ge.com; phone: (513) 552-3272; fax: (513)
552-3329; for a copy of this service information.
(l) Material Incorporated by Reference
(1) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the incorporation by
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the
following service information:
(i) General Electric Company (GE) Service Bulletin (SB) GE90-100
S/B 72-0320, Revision 02, October 1, 2010; and
(ii) GE SB GE90-100 S/B 72-0360, Revision 04, dated November, 7,
2011.
(2) For service information identified in this AD, contact
General Electric, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati,
Ohio 45215; email: geae.aoc@ge.com; phone: (513) 552-3272; fax:
(513) 552-3329.
(3) You may review copies of the referenced service information
at the FAA, Engine & Propeller Directorate, 12 New England Executive
Park, Burlington, MA. For information on the availability of this
material at the FAA, call (781) 238-7125.
(4) You may also review copies of the service information
incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on December 15, 2011.
Thomas A. Boudreau,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-32832 Filed 12-29-11; 8:45 am]
BILLING CODE 4910-13-P
