Airworthiness Directives; General Electric Company CF6-45 and CF6-50 Series Turbofan Engines, 6323-6326 [2011-2387]
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Federal Register / Vol. 76, No. 24 / Friday, February 4, 2011 / Rules and Regulations
4700 River Road, Unit 43, Riverdale,
MD 20737–1231; (301) 734–6954.
DEPARTMENT OF TRANSPORTATION
On
December 27, 2010, we published in the
Federal Register (75 FR 81090–81096,
Docket No. APHIS–2009–0083) an
interim rule that amended the
brucellosis regulations to reduce the
amount of testing required to maintain
Class Free status for States that have
been Class Free for 5 or more years and
that also have no Brucella abortus in
wildlife. The interim rule also removed
the provision for automatic
reclassification of any Class Free State
or area to a lower status if two or more
herds are found to have brucellosis
within a 2-year period or if a single
brucellosis-affected herd is not
depopulated within 60 days. Further,
the interim rule reduced the age at
which cattle are included in herd blood
tests. The interim rule also added a
requirement that any Class Free State or
area with Brucella abortus in wildlife
must develop and implement a
brucellosis management plan approved
by the Administrator in order to
maintain Class Free status. Finally, the
interim rule provided an alternative
testing protocol for maintaining the
certified brucellosis-free status of dairy
herds, which will give producers more
flexibility for the herd certification
process.
Comments on the interim rule were
currently required to be received on or
before February 25, 2011. We are
extending the comment period on
Docket No. APHIS–2009–0083 for an
additional 14 days. This action will
allow interested persons additional time
to prepare and submit comments.
SUPPLEMENTARY INFORMATION:
Authority: 7 U.S.C. 8301–8317; 7 CFR
2.22, 2.80, and 371.4.
Done in Washington, DC, this 31st day of
January 2011.
Gregory L. Parham,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 2011–2507 Filed 2–3–11; 8:45 am]
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BILLING CODE 3410–34–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0068; Directorate
Identifier 2010–NE–05–AD; Amendment 39–
16580; AD 2011–02–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CF6–45 and CF6–50
Series Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
General Electric Company (GE) CF6–45
and CF6–50 series turbofan engines
with certain low-pressure turbine (LPT)
rotor stage 3 disks installed. That AD
currently requires initial and repetitive
borescope inspections of the highpressure turbine (HPT) rotor stage 1 and
stage 2 blades for wear and damage,
including excessive airfoil material loss.
That AD also requires fluorescentpenetrant inspection (FPI) of the LPT
rotor stage 3 disk under certain
conditions and removal of the disk from
service before further flight if found
cracked. That AD also requires
repetitive exhaust gas temperature
(EGT) system checks (inspections). This
AD requires HPT rotor stage 1 and stage
2 blade inspections and EGT system
inspections. This AD also requires FPI
of the LPT rotor stage 3 disk under
certain conditions, removal of the disk
from service before further flight if
found cracked, and an ultrasonic
inspection (UI) of the LPT rotor stage 3
disk forward spacer arm. This AD also
requires initial and repetitive engine
core vibration surveys and reporting to
the FAA any crack findings, disks that
fail the UI, and engines that fail the
engine core vibration survey.
This AD was prompted by reports
received of additional causes of HPT
rotor imbalance not addressed in AD
2010–12–10, and two additional LPT
rotor stage 3 disk events. We are issuing
this AD to prevent critical life-limited
rotating engine part failure, which could
result in an uncontained engine failure
and damage to the airplane.
DATES: This AD is effective February 22,
2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of February 22, 2011.
We must receive any comments on
this AD by March 21, 2011.
SUMMARY:
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6323
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
ADDRESSES:
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 street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Tomasz Rakowski, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7735; fax: 781–238–
7199; e-mail: tomasz.rakowski@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 4, 2010, we issued AD 2010–
12–10, Amendment 39–16331 (75 FR
32649, June 9, 2010), for CF6–45 and
CF6–50 series turbofan engines with
certain LPT rotor stage 3 disks installed.
That AD requires initial and repetitive
borescope inspections of the HPT rotor
stage 1 and stage 2 blades for wear and
damage, including excessive airfoil
material loss. That AD also requires FPI
of the LPT rotor stage 3 disk under
certain conditions, removal of the disk
from service before further flight if
found cracked, and repetitive EGT
system checks (inspections). That AD
resulted from reports received of two
additional LPT rotor stage 3 disk events
since the original AD 2010–06–15,
Amendment 39–16240 (75 FR 12661,
March 17, 2010) was issued. We issued
those ADs to prevent critical life-limited
rotating engine part failure, which could
result in an uncontained engine failure
and damage to the airplane.
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Federal Register / Vol. 76, No. 24 / Friday, February 4, 2011 / Rules and Regulations
Actions Since AD was Issued
Since we issued AD 2010–12–10,
investigations have revealed additional
causes for HPT rotor imbalance not
addressed in that AD, and two
additional LPT rotor stage 3 disk events
have occurred.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
AD Requirements
This AD requires:
• HPT rotor stage 1 and stage 2 blade
inspections and EGT system
inspections; and
• FPI of the LPT rotor stage 3 disk
under certain conditions and removal of
the disk from service before further
flight if found cracked; and
• A UI of the LPT rotor stage 3 disk
forward spacer arm; and
• Initial and repetitive engine core
vibration surveys; and
• Reporting to the FAA any crack
findings, disks that fail the UI, and
engines that fail the engine core
vibration survey.
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FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because we require near immediate
corrective action to address the unsafe
condition. Therefore, we find that notice
and opportunity for prior public
comment are impracticable, and that
good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2010–0068 and directorate
identifier 2010–NE–05–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
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environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because 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 we receive
about this AD.
Costs of Compliance
We estimate that this AD will affect
387 CF6–45 and CF6–50 series turbofan
engines installed on airplanes of U.S.
registry. We also estimate that it will
take, about 8 hours to perform the HPT
blade inspection, 6 hours to perform a
vibration survey, 4 hours to perform an
ultrasonic inspection, 2 hours to
perform an EGT resistance check, and
1 hour to perform an EGT thermocouple
inspection for each engine. The average
labor rate is $85 per work-hour. We
anticipate no required parts cost. Based
on these figures, we estimate the total
cost of the AD to U.S. operators to be
$690,795.
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.
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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 part 39 of the Federal
Aviation Regulations (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
removing airworthiness directive (AD)
2010–12–10, Amendment 39–16331 (75
FR 32649, June 9, 2010) and adding the
following new AD:
■
2011–02–07 General Electric Company:
Amendment 39–16580; Docket No.
FAA–2010–0068; Directorate Identifier
2010–NE–05–AD.
Effective Date
(a) This AD is effective February 22, 2011.
Affected ADs
(b) This AD supersedes AD 2010–12–10,
Amendment 39–16331.
Applicability
(c) This AD applies to the following
engines with any of the low-pressure turbine
(LPT) rotor stage 3 disk part numbers listed
in Table 1 of this AD installed in:
(1) General Electric Company (GE) CF6–
45A, CF6–45A2, CF6–50A, CF6–50C, CF6–
50CA, CF6–50C1, CF6–50C2, CF6–50C2B,
CF6–50C2D, CF6–50E, CF6–50E1, and CF6–
50E2 turbofan engines, including engines
marked on the engine data plate as CF6–
50C2–F and CF6–50C2–R.
(2) These engines are installed on, but not
limited to, Airbus A300 series, Boeing 747
series, McDonnell Douglas DC–10 series, and
DC–10–30F (KDC–10) airplanes.
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Federal Register / Vol. 76, No. 24 / Friday, February 4, 2011 / Rules and Regulations
6325
TABLE 1—APPLICABLE LPT ROTOR STAGE 3 DISK PART NUMBERS
9061M23P06
9061M23P10
9061M23P12
1479M75P02
1479M75P07
1479M75P14
9061M23P07
1473M90P01
9061M23P14
1479M75P03
1479M75P08
N/A
Unsafe Condition
(d) This AD results from reports received
of additional causes of high-pressure turbine
(HPT) rotor imbalance not addressed in AD
2010–12–10, and two additional LPT rotor
stage 3 disk events. We are issuing this AD
to prevent critical life-limited rotating engine
part failure, which could result in an
uncontained engine failure and damage to
the airplane.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
9061M23P08
1473M90P02
9061M23P15
1479M75P04
1479M75P09
N/A
9061M23P09
1473M90P03
9061M23P16
1479M75P05
1479M75P11
N/A
Borescope Inspections of HPT Rotor Stage 1
and Stage 2 Blades
(f) For the borescope inspections required
by paragraphs (f)(1), (f)(2), and (f)(3) of this
AD, inspect the blades from the forward and
aft directions. Inspect all areas of the blade
airfoil: Your inspection must include blade
leading and trailing edges, and their convex
and concave airfoil surfaces. Inspect for signs
of impact, cracking, burning, damage, or
distress.
(1) Perform an initial borescope inspection
of the HPT rotor stage 1 and stage 2 blades,
9224M75P01
1473M90P04
1479M75P01
1479M75P06
1479M75P13
N/A
within 10 cycles after the effective date of
this AD.
(2) Thereafter, repeat the borescope
inspection of the HPT rotor stage 1 and stage
2 blades within every 75 cycles-since-lastinspection (CSLI).
(3) Borescope-inspect the HPT rotor stage
1 and stage 2 blades within the cycle limits
after the engine has experienced any of the
events specified in Table 2 of this AD.
(4) Remove any engine from service before
further flight if the engine fails any of the
borescope inspections required by this AD.
TABLE 2—CONDITIONAL BORESCOPE INSPECTION CRITERIA
If the engine has experienced:
Then Borescope-Inspect:
(i) An exhaust gas temperature (EGT) above redline ....................................................................................................
(ii) A shift in the smoothed EGT trending data that exceeds 18 °F (10 °C), but is less than or equal to 36 °F (20
°C).
(iii) A shift in the smoothed EGT trending data that exceeds 36 °F (20 °C) .................................................................
(iv) Two consecutive raw EGT trend data points that exceed 18 °F (10 °C) above the smoothed average, but is
less than or equal to 36 °F (20 °C).
(v) Two consecutive raw EGT trend data points that exceed 36 °F (20 °C) above the smoothed average ................
Within 10 cycles.
Within 10 cycles.
Actions Required for Engines With Damaged
HPT Rotor Blades
(g) For those engines that fail any
borescope inspection requirements of this
AD, before returning the engine to service,
fluorescent-penetrant inspect the inner
diameter surface forward cone body (forward
spacer arm) of the LPT rotor stage 3 disk. If
a crack is found or if a circumferential band
of fluorescence appears, remove the disk
from service.
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EGT Thermocouple Probe Inspections
(h) Inspect the EGT thermocouple probe for
damage within 50 cycles after the effective
date of this AD or before accumulating 750
CSLI, whichever occurs later.
(i) Thereafter, re-inspect the EGT
thermocouple probe for damage within every
750 CSLI.
(j) If any EGT thermocouple probe shows
wear through the thermocouple guide sleeve,
remove and replace the EGT thermocouple
probe before further flight, and ensure the
turbine mid-frame liner does not contact the
EGT thermocouple probe.
EGT System Resistance Check Inspections
(k) Perform an EGT system resistance
check within 50 cycles from the effective
date of this AD or before accumulating 750
cycles-since-the-last-resistance check on the
EGT system, whichever occurs later.
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(l) Thereafter, repeat the EGT system
resistance check within every 750 cyclessince-the-last-resistance check.
(m) Remove and replace, or repair any EGT
system component that fails the resistance
system check before further flight.
Ultrasonic Inspection (UI) of the LPT Rotor
Stage 3 Disk Forward Spacer Arm
(n) Within 75 cycles after the effective date
of this AD, perform a UI of the forward cone
body (forward spacer arm) of the LPT rotor
stage 3 disk. Use paragraphs E. through K. of
Appendix A of GE Service Bulletin (SB) No.
CF6–50–SB 72–1312, Revision 1, dated
October 18, 2010, to do the UI.
Engine Core Vibration Survey
(o) Within 75 cycles after the effective date
of this AD, perform an initial engine core
vibration survey.
(1) Use approximately a one-minute
acceleration and a one-minute deceleration of
the engine between ground idle and 84% N2
(about 8,250 rpm) to perform the engine core
vibration survey.
(2) Use a spectral/trim balance analyzer or
equivalent, to determine the N2 rotor
vibration.
(p) Thereafter, within every 350 cyclessince-the-last-engine core vibration survey,
perform the engine core vibration survey as
required in paragraphs (o)(1) through (o)(2) of
this AD.
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Before further flight.
Within 10 cycles.
Before further flight.
(q) If the vibration level is above 5 mils
Double Amplitude then before further flight,
remove the engine from service.
(r) For those engines that fail any engine
core vibration survey requirements of this
AD, before returning the engine to service,
fluorescent-penetrant inspect the inner
diameter surface forward cone body (forward
spacer arm) of the LPT rotor stage 3 disk. If
a crack is found or if a circumferential band
of fluorescence appears, remove the disk
from service.
(s) If the engine has experienced any
vibration reported by maintenance or flight
crew that is suspected to be caused by the
HPT rotor (N2), perform the engine core
vibration survey as required in paragraphs
(o)(1) through (o)(2) of this AD within 10
cycles after the report.
(t) You can find further guidance about
performing the engine core vibration survey
in GE SB No. CF6–50–SB 72–1313, Revision
1, dated October 18, 2010.
Reporting Requirements
(u) Report to the FAA within 10 days after
any of the following:
(1) Any crack findings; and
(2) Any disks that failed a UI performed as
specified in paragraph (n) of this AD; and
(3) Any engines that failed an engine core
vibration survey as specified in paragraphs
(o) and (p) of this AD.
(4) Submit these findings to FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-
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Federal Register / Vol. 76, No. 24 / Friday, February 4, 2011 / Rules and Regulations
mail: tomasz.rakowski@faa.gov; phone: 781–
238–7735; fax: 781–238–7199.
Paperwork Reduction Act Burden Statement
(5) A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave., SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
Definitions
(v) For the purposes of this AD, an EGT
above redline is a confirmed overtemperature indication that is not a result of
EGT system error.
(w) For the purposes of this AD, a shift in
the smoothed EGT trending data is a shift in
a rolling average of EGT that can be
confirmed by a corresponding shift in the
trending of fuel flow or fan speed/core speed
(N1/N2) relationship. You can find further
guidance about evaluating EGT trend data in
GE Company Service Rep Tip 373
‘‘Guidelines For Parameter Trend
Monitoring.’’
(bb) 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
(cc) Contact Tomasz Rakowski, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; phone: 781–238–7735; fax: 781–238–
7199; e-mail: tomasz.rakowski@faa.gov, for
more information about this AD.
Material Incorporated by Reference
(dd) You must use GE Service Bulletin No.
CF6–50–SB 72–1312, Revision 1, dated
October 18, 2010, to do the ultrasonic
inspections required by this AD.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) Contact General Electric Company, GE–
Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215, telephone (513) 552–
3272; fax (513) 552–3329; e-mail:
geae.aoc@ge.com for a copy of this service
information.
(3) You may review copies at the FAA,
New England Region, 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 that is 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.
jdjones on DSK8KYBLC1PROD with RULES
Previous Credit
(x) A borescope inspection performed
before the effective date of this AD using AD
2010–06–15, Amendment 39–16240 (75 FR
12661, March 17, 2010) or AD 2010–12–10,
Amendment 39–16331 (75 FR 32649, June 9,
2010) within the last 75 cycles, satisfies the
initial borescope inspection requirement in
paragraph (f)(1) of this AD.
(y) A UI performed before the effective date
of this AD using GE SB No. CF6–50–SB 72–
1312, dated August 9, 2010 or GE SB No.
CF6–50–SB 72–1312 Revision 1, dated
October 18, 2010, satisfies the inspection
requirement in paragraph (n) of this AD.
(z) An engine core vibration survey
performed before the effective date of this AD
using GE SB No. CF6–50–SB 72–1313, dated
August 9, 2010 or GE SB No. CF6–50–SB 72–
1313 Revision 1, dated October 18, 2010,
within the last 350 cycles, satisfies the initial
survey requirement in paragraph (o) of this
AD.
Issued in Burlington, Massachusetts, on
January 14, 2011.
Peter A. White,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
Alternative Methods of Compliance
(AMOCs)
(aa) AMOCs previously approved for AD
2010–06–15, Amendment 39–16240 (75 FR
12661, March 17, 2010) are not approved for
this AD. However, AMOCs previously
approved for AD 2010–12–10, Amendment
39–16331 (75 FR 32649, June 9, 2010) are
approved for this AD.
ACTION:
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[FR Doc. 2011–2387 Filed 2–3–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Parts 510 and 516
[Docket No. FDA–2011–N–0003]
New Animal Drugs; Masitinib
AGENCY:
Food and Drug Administration,
HHS.
Final rule.
The Food and Drug
Administration (FDA) is amending the
animal drug regulations to reflect
conditional approval of an application
for a new animal drug intended for a
minor use filed by AB Science. The
application for conditional approval
SUMMARY:
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provides for the veterinary prescription
use of masitinib mesylate tablets in
dogs.
DATES: This rule is effective February 4,
2011.
FOR FURTHER INFORMATION CONTACT: Lisa
M. Troutman, Center for Veterinary
Medicine (HFV–116), Food and Drug
Administration, 7500 Standish Pl.,
Rockville, MD 20855, 240–276–8322,
e-mail: lisa.troutman@fda.hhs.gov.
SUPPLEMENTARY INFORMATION: AB
Science, 3 Avenue George V, 75008
Paris, France, filed an application for
conditional approval (141–308) that
provides for veterinary prescription use
of KINAVET–CA1 (masitinib mesylate)
Tablets for the treatment of recurrent
(post-surgery) or nonresectable Grade II
or III cutaneous mast cell tumors in dogs
that have not previously received
radiotherapy and/or chemotherapy
except corticosteroids. In accordance
with the Federal Food, Drug, and
Cosmetic Act (the FD&C Act), as
amended by the Minor Use and Minor
Species Animal Health Act of 2004
(MUMS Act), this drug is conditionally
approved as of December 15, 2010, and
the regulations in part 516 (21 CFR part
516) are amended by adding new
§ 516.1318.
In addition, AB Science has not been
previously listed in the animal drug
regulations as a sponsor of an approved
application. Accordingly, 21 CFR
510.600(c) is being amended to add
entries for this firm.
In accordance with the freedom of
information provisions of 21 CFR part
20 and 21 CFR 514.11(e)(2)(ii), a
summary of safety and effectiveness
data and information submitted to
support conditional approval of this
application may be seen in the Division
of Dockets Management (HFA–305),
Food and Drug Administration, 5630
Fishers Lane, rm. 1061, Rockville, MD
20852, between 9 a.m. and 4 p.m.,
Monday through Friday.
The Agency has determined under 21
CFR 25.33 that this action is of a type
that does not individually or
cumulatively have a significant effect on
the human environment. Therefore,
neither an environmental assessment
nor an environmental impact statement
is required.
KINAVET–CA1 (masitinib mesylate)
Tablets for the intended uses
conditionally approved by FDA under
application number 141–308 qualifies
for 7 years of exclusive marketing rights
beginning on the date of conditional
approval. This new animal drug
qualifies for exclusive marketing rights
under section 573(c) of the FD&C Act
(21 U.S.C. 360ccc–2(c)) because it has
E:\FR\FM\04FER1.SGM
04FER1
]]>Agencies
[Federal Register Volume 76, Number 24 (Friday, February 4, 2011)]
[Rules and Regulations]
[Pages 6323-6326]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2387]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0068; Directorate Identifier 2010-NE-05-AD;
Amendment 39-16580; AD 2011-02-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-45 and
CF6-50 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for General Electric Company (GE) CF6-45 and CF6-50 series turbofan
engines with certain low-pressure turbine (LPT) rotor stage 3 disks
installed. That AD currently requires initial and repetitive borescope
inspections of the high-pressure turbine (HPT) rotor stage 1 and stage
2 blades for wear and damage, including excessive airfoil material
loss. That AD also requires fluorescent-penetrant inspection (FPI) of
the LPT rotor stage 3 disk under certain conditions and removal of the
disk from service before further flight if found cracked. That AD also
requires repetitive exhaust gas temperature (EGT) system checks
(inspections). This AD requires HPT rotor stage 1 and stage 2 blade
inspections and EGT system inspections. This AD also requires FPI of
the LPT rotor stage 3 disk under certain conditions, removal of the
disk from service before further flight if found cracked, and an
ultrasonic inspection (UI) of the LPT rotor stage 3 disk forward spacer
arm. This AD also requires initial and repetitive engine core vibration
surveys and reporting to the FAA any crack findings, disks that fail
the UI, and engines that fail the engine core vibration survey.
This AD was prompted by reports received of additional causes of
HPT rotor imbalance not addressed in AD 2010-12-10, and two additional
LPT rotor stage 3 disk events. We are issuing this AD to prevent
critical life-limited rotating engine part failure, which could result
in an uncontained engine failure and damage to the airplane.
DATES: This AD is effective February 22, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 22,
2011.
We must receive any comments on this AD by March 21, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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 street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7735;
fax: 781-238-7199; e-mail: tomasz.rakowski@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On June 4, 2010, we issued AD 2010-12-10, Amendment 39-16331 (75 FR
32649, June 9, 2010), for CF6-45 and CF6-50 series turbofan engines
with certain LPT rotor stage 3 disks installed. That AD requires
initial and repetitive borescope inspections of the HPT rotor stage 1
and stage 2 blades for wear and damage, including excessive airfoil
material loss. That AD also requires FPI of the LPT rotor stage 3 disk
under certain conditions, removal of the disk from service before
further flight if found cracked, and repetitive EGT system checks
(inspections). That AD resulted from reports received of two additional
LPT rotor stage 3 disk events since the original AD 2010-06-15,
Amendment 39-16240 (75 FR 12661, March 17, 2010) was issued. We issued
those ADs to prevent critical life-limited rotating engine part
failure, which could result in an uncontained engine failure and damage
to the airplane.
[[Page 6324]]
Actions Since AD was Issued
Since we issued AD 2010-12-10, investigations have revealed
additional causes for HPT rotor imbalance not addressed in that AD, and
two additional LPT rotor stage 3 disk events have occurred.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires:
HPT rotor stage 1 and stage 2 blade inspections and EGT
system inspections; and
FPI of the LPT rotor stage 3 disk under certain conditions
and removal of the disk from service before further flight if found
cracked; and
A UI of the LPT rotor stage 3 disk forward spacer arm; and
Initial and repetitive engine core vibration surveys; and
Reporting to the FAA any crack findings, disks that fail
the UI, and engines that fail the engine core vibration survey.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because we
require near immediate corrective action to address the unsafe
condition. Therefore, we find that notice and opportunity for prior
public comment are impracticable, and that good cause exists for making
this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2010-0068 and directorate identifier 2010-NE-05-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because 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 we
receive about this AD.
Costs of Compliance
We estimate that this AD will affect 387 CF6-45 and CF6-50 series
turbofan engines installed on airplanes of U.S. registry. We also
estimate that it will take, about 8 hours to perform the HPT blade
inspection, 6 hours to perform a vibration survey, 4 hours to perform
an ultrasonic inspection, 2 hours to perform an EGT resistance check,
and 1 hour to perform an EGT thermocouple inspection for each engine.
The average labor rate is $85 per work-hour. We anticipate no required
parts cost. Based on these figures, we estimate the total cost of the
AD to U.S. operators to be $690,795.
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 part 39 of the Federal Aviation
Regulations (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 removing airworthiness directive (AD)
2010-12-10, Amendment 39-16331 (75 FR 32649, June 9, 2010) and adding
the following new AD:
2011-02-07 General Electric Company: Amendment 39-16580; Docket No.
FAA-2010-0068; Directorate Identifier 2010-NE-05-AD.
Effective Date
(a) This AD is effective February 22, 2011.
Affected ADs
(b) This AD supersedes AD 2010-12-10, Amendment 39-16331.
Applicability
(c) This AD applies to the following engines with any of the
low-pressure turbine (LPT) rotor stage 3 disk part numbers listed in
Table 1 of this AD installed in:
(1) General Electric Company (GE) CF6-45A, CF6-45A2, CF6-50A,
CF6-50C, CF6-50CA, CF6-50C1, CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-
50E, CF6-50E1, and CF6-50E2 turbofan engines, including engines
marked on the engine data plate as CF6-50C2-F and CF6-50C2-R.
(2) These engines are installed on, but not limited to, Airbus
A300 series, Boeing 747 series, McDonnell Douglas DC-10 series, and
DC-10-30F (KDC-10) airplanes.
[[Page 6325]]
Table 1--Applicable LPT Rotor Stage 3 Disk Part Numbers
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
9061M23P06 9061M23P07 9061M23P08 9061M23P09 9224M75P01
9061M23P10 1473M90P01 1473M90P02 1473M90P03 1473M90P04
9061M23P12 9061M23P14 9061M23P15 9061M23P16 1479M75P01
1479M75P02 1479M75P03 1479M75P04 1479M75P05 1479M75P06
1479M75P07 1479M75P08 1479M75P09 1479M75P11 1479M75P13
1479M75P14 N/A N/A N/A N/A
--------------------------------------------------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports received of additional causes
of high-pressure turbine (HPT) rotor imbalance not addressed in AD
2010-12-10, and two additional LPT rotor stage 3 disk events. We are
issuing this AD to prevent critical life-limited rotating engine
part failure, which could result in an uncontained engine failure
and damage to the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Borescope Inspections of HPT Rotor Stage 1 and Stage 2 Blades
(f) For the borescope inspections required by paragraphs (f)(1),
(f)(2), and (f)(3) of this AD, inspect the blades from the forward
and aft directions. Inspect all areas of the blade airfoil: Your
inspection must include blade leading and trailing edges, and their
convex and concave airfoil surfaces. Inspect for signs of impact,
cracking, burning, damage, or distress.
(1) Perform an initial borescope inspection of the HPT rotor
stage 1 and stage 2 blades, within 10 cycles after the effective
date of this AD.
(2) Thereafter, repeat the borescope inspection of the HPT rotor
stage 1 and stage 2 blades within every 75 cycles-since-last-
inspection (CSLI).
(3) Borescope-inspect the HPT rotor stage 1 and stage 2 blades
within the cycle limits after the engine has experienced any of the
events specified in Table 2 of this AD.
(4) Remove any engine from service before further flight if the
engine fails any of the borescope inspections required by this AD.
Table 2--Conditional Borescope Inspection Criteria
----------------------------------------------------------------------------------------------------------------
If the engine has experienced: Then Borescope-Inspect:
----------------------------------------------------------------------------------------------------------------
(i) An exhaust gas temperature (EGT) above redline......... Within 10 cycles.
(ii) A shift in the smoothed EGT trending data that exceeds Within 10 cycles.
18 [deg]F (10 [deg]C), but is less than or equal to 36
[deg]F (20 [deg]C).
(iii) A shift in the smoothed EGT trending data that Before further flight.
exceeds 36 [deg]F (20 [deg]C).
(iv) Two consecutive raw EGT trend data points that exceed Within 10 cycles.
18 [deg]F (10 [deg]C) above the smoothed average, but is
less than or equal to 36 [deg]F (20 [deg]C).
(v) Two consecutive raw EGT trend data points that exceed Before further flight.
36 [deg]F (20 [deg]C) above the smoothed average.
----------------------------------------------------------------------------------------------------------------
Actions Required for Engines With Damaged HPT Rotor Blades
(g) For those engines that fail any borescope inspection
requirements of this AD, before returning the engine to service,
fluorescent-penetrant inspect the inner diameter surface forward
cone body (forward spacer arm) of the LPT rotor stage 3 disk. If a
crack is found or if a circumferential band of fluorescence appears,
remove the disk from service.
EGT Thermocouple Probe Inspections
(h) Inspect the EGT thermocouple probe for damage within 50
cycles after the effective date of this AD or before accumulating
750 CSLI, whichever occurs later.
(i) Thereafter, re-inspect the EGT thermocouple probe for damage
within every 750 CSLI.
(j) If any EGT thermocouple probe shows wear through the
thermocouple guide sleeve, remove and replace the EGT thermocouple
probe before further flight, and ensure the turbine mid-frame liner
does not contact the EGT thermocouple probe.
EGT System Resistance Check Inspections
(k) Perform an EGT system resistance check within 50 cycles from
the effective date of this AD or before accumulating 750 cycles-
since-the-last-resistance check on the EGT system, whichever occurs
later.
(l) Thereafter, repeat the EGT system resistance check within
every 750 cycles-since-the-last-resistance check.
(m) Remove and replace, or repair any EGT system component that
fails the resistance system check before further flight.
Ultrasonic Inspection (UI) of the LPT Rotor Stage 3 Disk Forward Spacer
Arm
(n) Within 75 cycles after the effective date of this AD,
perform a UI of the forward cone body (forward spacer arm) of the
LPT rotor stage 3 disk. Use paragraphs E. through K. of Appendix A
of GE Service Bulletin (SB) No. CF6-50-SB 72-1312, Revision 1, dated
October 18, 2010, to do the UI.
Engine Core Vibration Survey
(o) Within 75 cycles after the effective date of this AD,
perform an initial engine core vibration survey.
(1) Use approximately a one-minute acceleration and a one-minute
deceleration of the engine between ground idle and 84% N2 (about
8,250 rpm) to perform the engine core vibration survey.
(2) Use a spectral/trim balance analyzer or equivalent, to
determine the N2 rotor vibration.
(p) Thereafter, within every 350 cycles-since-the-last-engine
core vibration survey, perform the engine core vibration survey as
required in paragraphs (o)(1) through (o)(2) of this AD.
(q) If the vibration level is above 5 mils Double Amplitude then
before further flight, remove the engine from service.
(r) For those engines that fail any engine core vibration survey
requirements of this AD, before returning the engine to service,
fluorescent-penetrant inspect the inner diameter surface forward
cone body (forward spacer arm) of the LPT rotor stage 3 disk. If a
crack is found or if a circumferential band of fluorescence appears,
remove the disk from service.
(s) If the engine has experienced any vibration reported by
maintenance or flight crew that is suspected to be caused by the HPT
rotor (N2), perform the engine core vibration survey as required in
paragraphs (o)(1) through (o)(2) of this AD within 10 cycles after
the report.
(t) You can find further guidance about performing the engine
core vibration survey in GE SB No. CF6-50-SB 72-1313, Revision 1,
dated October 18, 2010.
Reporting Requirements
(u) Report to the FAA within 10 days after any of the following:
(1) Any crack findings; and
(2) Any disks that failed a UI performed as specified in
paragraph (n) of this AD; and
(3) Any engines that failed an engine core vibration survey as
specified in paragraphs (o) and (p) of this AD.
(4) Submit these findings to FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
[[Page 6326]]
mail: tomasz.rakowski@faa.gov; phone: 781-238-7735; fax: 781-238-
7199.
Paperwork Reduction Act Burden Statement
(5) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Definitions
(v) For the purposes of this AD, an EGT above redline is a
confirmed over-temperature indication that is not a result of EGT
system error.
(w) For the purposes of this AD, a shift in the smoothed EGT
trending data is a shift in a rolling average of EGT that can be
confirmed by a corresponding shift in the trending of fuel flow or
fan speed/core speed (N1/N2) relationship. You can find further
guidance about evaluating EGT trend data in GE Company Service Rep
Tip 373 ``Guidelines For Parameter Trend Monitoring.''
Previous Credit
(x) A borescope inspection performed before the effective date
of this AD using AD 2010-06-15, Amendment 39-16240 (75 FR 12661,
March 17, 2010) or AD 2010-12-10, Amendment 39-16331 (75 FR 32649,
June 9, 2010) within the last 75 cycles, satisfies the initial
borescope inspection requirement in paragraph (f)(1) of this AD.
(y) A UI performed before the effective date of this AD using GE
SB No. CF6-50-SB 72-1312, dated August 9, 2010 or GE SB No. CF6-50-
SB 72-1312 Revision 1, dated October 18, 2010, satisfies the
inspection requirement in paragraph (n) of this AD.
(z) An engine core vibration survey performed before the
effective date of this AD using GE SB No. CF6-50-SB 72-1313, dated
August 9, 2010 or GE SB No. CF6-50-SB 72-1313 Revision 1, dated
October 18, 2010, within the last 350 cycles, satisfies the initial
survey requirement in paragraph (o) of this AD.
Alternative Methods of Compliance (AMOCs)
(aa) AMOCs previously approved for AD 2010-06-15, Amendment 39-
16240 (75 FR 12661, March 17, 2010) are not approved for this AD.
However, AMOCs previously approved for AD 2010-12-10, Amendment 39-
16331 (75 FR 32649, June 9, 2010) are approved for this AD.
(bb) 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
(cc) Contact Tomasz Rakowski, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7735;
fax: 781-238-7199; e-mail: tomasz.rakowski@faa.gov, for more
information about this AD.
Material Incorporated by Reference
(dd) You must use GE Service Bulletin No. CF6-50-SB 72-1312,
Revision 1, dated October 18, 2010, to do the ultrasonic inspections
required by this AD.
(1) The Director of the Federal Register approved the
incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) Contact General Electric Company, GE-Aviation, Room 285, 1
Neumann Way, Cincinnati, OH 45215, telephone (513) 552-3272; fax
(513) 552-3329; e-mail: geae.aoc@ge.com for a copy of this service
information.
(3) You may review copies at the FAA, New England Region, 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 that
is 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 January 14, 2011.
Peter A. White,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2011-2387 Filed 2-3-11; 8:45 am]
BILLING CODE 4910-13-P
