[Federal Register Volume 78, Number 229 (Wednesday, November 27, 2013)]
[Notices]
[Page 70953]
[FR Doc No: 2013-28392]

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DEPARTMENT OF HEALTH AND HUMAN SERVICES

Food and Drug Administration

[Docket No. FDA-2012-D-0880]

Draft Guidance for Industry on Generic Drug User Fee Amendments
of 2012: Questions and Answers (Revision 1); Reopening of the Comment
Period

AGENCY: Food and Drug Administration, HHS.

ACTION: Notice; reopening of the comment period.

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

SUMMARY: The Food and Drug Administration (FDA) is reopening the
comment period for the notice of availability entitled ``Draft Guidance
for Industry on Generic Drug User Fee Amendments of 2012: Questions and
Answers (Revision 1)'', published in the Federal Register of September
10, 2013 (78 FR 55261). In that notice, FDA requested public comment on
the draft guidance. FDA is reopening the comment period due to the
inability of some commenters to submit comments through the
www.regulations.gov Web site from November 4, 2013, through November
13, 2013, due to technical difficulties.

DATES: Submit either electronic or written comments to the docket by
December 11, 2013.

ADDRESSES: Submit electronic comments to http://www.regulations.gov.
Submit written comments to the Division of Dockets Management (HFA-
305), Food and Drug Administration, 5630 Fishers Lane, rm. 1061,
Rockville, MD 20852.

FOR FURTHER INFORMATION CONTACT: Jaewon Hong, Center for Drug
Evaluation and Research, Food and Drug Administration, 10001 New
Hampshire Ave., rm. 4145, Silver Spring, MD 20993-0002,<PHONE_NUMBER>,
email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

I. Background

    In the Federal Register of September 10, 2013 (78 FR 55261), FDA
announced the notice of availability for the draft guidance entitled
``Draft Guidance for Industry on Generic Drug User Fee Amendments of
2012: Questions and Answers (Revision 1).'' Interested persons were
given until November 12, 2013, to provide comments. The Agency is
reopening the comment period until December 11, 2013 to allow
interested persons additional time to submit comments.

II. Requests for Comments

    Following publication of the September 10, 2013, notice of
availability, there were technical difficulties with the
www.regulations.gov Web site from November 4, 2013, through November
13, 2013, which would have prevented comments from being submitted.

III. How To Submit Comments

    Interested persons may submit either electronic comments regarding
this document to http://www.regulations.gov or written comments to the
Division of Dockets Management (see ADDRESSES). It is only necessary to
send one set of comments. Identify comments with the docket number
found in brackets in the heading of this document. Received comments
may be seen in the Division of Dockets Management between 9 a.m. and 4
p.m., Monday through Friday, and will be posted to the docket at http://www.regulations.gov.

    Dated: November 20, 2013.
Leslie Kux,
Assistant Commissioner for Policy.
[FR Doc. 2013-28392 Filed 11-26-13; 8:45 am]
BILLING CODE 4160-01-P


[Federal Register Volume 79, Number 26 (Friday, February 7, 2014)]
[Notices]
[Pages 7481-7482]
[FR Doc No: 2014-02601]

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SECURITIES AND EXCHANGE COMMISSION

Submission for OMB Review; Comment Request

Upon Written Request, Copies Available From: Securities and Exchange
Commission, Office of Investor Education and Advocacy, Washington, DC
20549-0213.

Extension:
    Rule 206(3)-3T, OMB Control No. 3235-0630, SEC File No. 270-571.

    Notice is hereby given that, pursuant to the Paperwork Reduction
Act of 1995

(44 U.S.C. 3501 et seq.), the Securities and Exchange Commission (the
``Commission'') has submitted to the Office of Management and Budget
(``OMB'') a request for extension and approval of the collections of
information discussed below.
    Temporary rule 206(3)-3T (17 CFR 275.206(3)-3T) under the
Investment Advisers Act of 1940 (15 U.S.C. 80b-1 et seq.) is entitled:
``Temporary rule for principal trades with certain advisory clients.''
The temporary rule provides investment advisers who are registered with
the Commission as broker-dealers an alternative means to meet the
requirements of section 206(3) of the Advisers Act (15 U.S.C. 80b-6(3))
when they act in a principal capacity in transactions with certain of
their advisory clients.
    Temporary rule 206(3)-3T permits investment advisers also
registered as broker-dealers to satisfy the Advisers Act's principal
trading restrictions by: (i) Providing written, prospective disclosure
regarding the conflicts arising from principal trades; (ii) obtaining
written, revocable consent from the client prospectively authorizing
the adviser to enter into principal transactions; (iii) making oral or
written disclosure and obtaining the client's consent before each
principal transaction; (iv) sending to the client confirmation
statements disclosing the capacity in which the adviser has acted; and
(v) delivering to the client an annual report itemizing the principal
transactions.
    The Commission staff estimates that approximately 278 investment
advisers make use of rule 206(3)-3T, including an estimated 11 advisers
(on an annual basis) also registered as broker-dealers who do not offer
non-discretionary services, but whom the Commission staff estimates
will choose to do so and rely on rule 206(3)-3T. The Commission staff
estimates that these advisers spend, in the aggregate, approximately
139,358 hours annually in complying with the requirements of the rule,
including both initial and annual burdens. The aggregate hour burden,
expressed on a per-eligible-adviser basis, is therefore approximately
501 hours per eligible adviser (139,358 hours divided by the estimated
278 advisers that will rely on rule 206(3)-3T).
    Rule 206(3)-3T does not require recordkeeping or record retention.
The collection of information requirements under the rule are required
to obtain a benefit. The information collected pursuant to the rule is
not required to be filed with the Commission, but rather takes the form
of disclosures to, and responses from, clients. The collection of
information delivered by clients to advisers would be subject to the
confidentiality strictures that govern those relationships, and we
would expect them to be confidential communications. To the extent
advisers include any of the information required by the rule in a
filing, such as Form ADV, the information will not be kept
confidential. An agency may not conduct or sponsor, and a person is not
required to respond to, a collection of information unless it displays
a currently valid control number.
    The public may view the background documentation for this
information collection at the following Web site, www.reginfo.gov.
Comments should be directed to: (i) Desk Officer for the Securities and
Exchange Commission, Office of Information and Regulatory Affairs,
Office of Management and Budget, Room 10102, New Executive Office
Building, Washington, DC 20503, or by sending an email to<EMAIL_ADDRESS>and (ii) Thomas Bayer, Chief Information Officer,
Securities and Exchange Commission, c/o Remi Pavlik-Simon, 100 F Street
NE., Washington, DC 20549 or send an email to<EMAIL_ADDRESS>
Comments must be submitted to OMB within 30 days of this notice.

    Dated: February 3, 2014.
Kevin M. O'Neill,
Deputy Secretary.
[FR Doc. 2014-02601 Filed 2-6-14; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 88, Number 57 (Friday, March 24, 2023)]
[Rules and Regulations]
[Pages 17679-17682]
[FR Doc No: 2023-05472]

========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents.

========================================================================

Federal Register / Vol. 88, No. 57 / Friday, March 24, 2023 / Rules
and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1416; Project Identifier AD-2022-00725-E;
Amendment 39-22358; AD 2023-04-11]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turbofan
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2012-02-07
for certain General Electric Company (GE) CF6-45 and CF6-50 series
model turbofan engines with a specified low-pressure turbine (LPT)
rotor stage 3 disk installed. AD 2012-02-07 required inspections of
high-pressure turbine (HPT) and LPT rotors, engine checks, vibration
surveys, an optional LPT rotor stage 3 disk removal after a failed HPT
blade borescope inspection (BSI) or a failed engine core vibration
survey, established a lower life limit for the affected LPT rotor stage
3 disks, and required removing these disks from service at times
determined by a drawdown plan. This AD was prompted by the occurrence
of four events of separation of the LPT rotor assembly, which resulted
in the LPT rotor assembly departing the rear of the engine. This AD
requires inspections of HPT and LPT rotor stage 1 and stage 2 blades,
vibration surveys, and use of a lower life limit for the affected LPT
rotor stage 3 disks and, as terminating action to the inspections,
engine checks, and vibration surveys, this AD requires removal and
replacement of the LPT rotor stage 3 disk with a redesigned LPT rotor
stage 3 disk. This AD also requires revising the compliance time of the
drawdown plan for the removal and replacement of the LPT rotor stage 3
disk and prohibits the installation or reinstallation of certain LPT
rotor stage 3 disks. The FAA is issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective April 28, 2023.

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2022-1416; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket
Operations is 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: Sungmo Cho, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7241; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2012-02-07, Amendment 39-16930 (77 FR 4650,
January 31, 2012), (``AD 2012-02-07''). AD 2012-02-07 applied to
certain GE CF6-45A, CF6-45A2, CF6-50A, CF6-50C, CF6-50CA, CF6-50C1,
CF6-50C2, CF6-50C2B, CF6-50C2D, CF6-50E, CF6-50E1, CF6-50E2, and CF6-
50E2B model turbofan engines, including engines marked on the engine
data plate as CF6-50C2-F and CF6-50C2-R, with a specified LPT rotor
stage 3 disk, identified by part number (P/N), installed. The NPRM
published in the Federal Register on December 08, 2022 (87 FR 75181).
The NPRM was prompted by the occurrence of four events of separation of
the LPT rotor assembly, occurring after the effective date of AD 2012-
02-07, which resulted in the LPT rotor assembly departing the rear of
the engine. Following the most recent separation event, the FAA
determined that due to the complexity of AD 2012-02-07, the limitations
of certain operators to access required equipment and training needed
to accomplish the inspections, and the manufacturer's redesign of the
LPT rotor stage 3 disk, AD 2012-02-07 required supersedure. The
redesigned LPT rotor stage 3 disk, P/N 2453M80P01, has a thicker
forward spacer arm, which reduces stress on the forward arm area and
increases its high cycle fatigue alternating stress capability. In the
NPRM, the FAA proposed to continue to require inspections of HPT and
LPT rotor stage 1 and stage 2 blades, vibration surveys, and use of a
lower life limit for the affected LPT rotor stage 3 disks. As a
terminating action to the inspections, engine checks, and vibration
surveys, the FAA also proposed to require removal and replacement of
the LPT rotor stage 3 disk with a redesigned LPT rotor stage 3 disk. In
the NPRM, the FAA also proposed to require revision of the compliance
time of the drawdown plan for the removal and replacement of the LPT
rotor stage 3 disk, and to prohibit the installation or reinstallation
of certain LPT rotor stage 3 disks.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from two commenters. Commenters included
Air Line Pilots Association, International and The Boeing Company. All
commenters supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM.

Costs of Compliance

    The FAA estimates that this AD affects 26 engines installed on
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
HPT blade inspection, vibration         28 work-hours x $85 per               $0          $2,380         $61,880
 survey, UI, EGT resistance check, EGT   hour = $2,380.
 thermocouple inspection, cleaning and
 FPI of the LPT rotor stage 3 disk.
Remove and replace LPT rotor stage 3    620 work-hours x $85 per         276,300         329,000       8,554,000
 disk.                                   hour = $52,700.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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

    The FAA has determined that 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) Will not affect intrastate aviation in Alaska, and
    (3) 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.

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:
0
a. Removing Airworthiness Directive 2012-02-07, Amendment 39-16930 (77
FR 4650, January 31, 2012); and
0
b. Adding the following new airworthiness directive:

2023-04-11 General Electric Company: Amendment 39-22358; Docket No.
FAA-2022-1416; Project Identifier AD-2022-00725-E.

(a) Effective Date

    This airworthiness directive (AD) is effective April 28, 2023.

(b) Affected ADs

    This AD replaces AD 2012-02-07, Amendment 39-16930 (77 FR 4650,
January 31, 2012) (AD 2012-02-07).

(c) Applicability

    This AD applies to 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, CF6-50E2, and CF6-50E2B model turbofan
engines, including engines marked on the engine data plate as CF6-
50C2-F and CF6-50C2-R, with an installed low-pressure turbine (LPT)
rotor stage 3 disk having a part number listed in Table 1 to
paragraph (c) of this AD.

                                        Table 1 to Paragraph (c)--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
--------------------------------------------------------------------------------------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.

(e) Unsafe Condition

    This AD was prompted by the occurrence of four events of
separation of the LPT rotor assembly, occurring after the effective
date of AD 2012-02-07, which resulted in the LPT rotor assembly
departing the rear of the engine. The FAA is issuing this AD to
prevent critical life-limited rotating engine part failure. The
unsafe condition, if not addressed, could result in an uncontained
engine failure and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Required Actions

    (1) Borescope Inspections (BSI) of High-Pressure Turbine (HPT)
Rotor Stage 1 and Stage 2 Blades. For the BSIs required by
paragraphs (g)(1)(i) through (iii) of this AD, inspect the blades
from the forward and aft directions. Inspect all areas of the blade
airfoil. The inspection must include blade leading and trailing
edges and their convex and concave airfoil surfaces. Inspect for
signs of impact, cracking, burning, damage, and distress.
    (i) Within 75 cycles since last inspection (CSLI) or before
further flight, whichever occurs later, perform an initial BSI of
the HPT rotor stage 1 and stage 2 blades.
    (ii) Thereafter, within every 75 CSLI, repeat the BSI of the HPT
rotor stage 1 and stage 2 blades.
    (iii) Within the cycle limits after the engine has experienced
any of the events specified in Table 2 to paragraph (g)(1)(iii) of
this AD, perform a BSI of the HPT rotor stage 1 and stage 2 blades.

       Table 2 to Paragraph (g)(1)(iii)--Conditional BSI Criteria
------------------------------------------------------------------------
  If the engine has experienced:           Then borescope inspect:
------------------------------------------------------------------------
An exhaust gas temperature (EGT)    Within 10 cycles.
 above redline.
A shift in the smoothed EGT         Within 10 cycles.
 trending data that exceeds 18
 [deg]F (10 [deg]C), but is less
 than or equal to 36 [deg]F (20
 [deg]C).
A shift in the smoothed EGT         Before further flight.
 trending data that exceeds 36
 [deg]F (20 [deg]C).
Two consecutive raw EGT trend data  Within 10 cycles.
 points that exceed 18 [deg]F (10
 [deg]C), but are less than or
 equal to 36 [deg]F (20 [deg]C),
 above the smoothed average.
Two consecutive raw EGT trend data  Before further flight.
 points that exceed 36 [deg]F (20
 [deg]C) above the smoothed
 average.
------------------------------------------------------------------------

    (iv) If the engine fails any of the BSIs required by this AD,
before further flight, remove the engine from service.
    (2) Engines with Damaged HPT Rotor Blades, For those engines
that fail any BSI requirements of this AD, before returning the
engine to service, accomplish the actions required by paragraph
(g)(2)(i) or (ii) of this AD:
    (i) Remove the LPT rotor stage 3 disk from service; or
    (ii) Perform a fluorescent-penetrant inspection (FPI) of the
inner diameter surface forward cone body (forward spacer arm) of the
LPT rotor stage 3 disk as specified in paragraphs (g)(6)(i)(A)
through (C) of this AD.
    (3) EGT Thermocouple Probe Inspections. (i) Within 750 CSLI, or
before further flight, whichever occurs later, inspect the EGT
thermocouple probe for damage.

    Note 1 to paragraph (g)(3)(i):  Damage to the EGT thermocouple
probe may be indicated by wear through the thermocouple guide sleeve
or contact between the turbine mid-frame liner and the EGT
thermocouple probe.

    (ii) Thereafter, within every 750 CSLI, re-inspect the EGT
thermocouple probe for damage.
    (iii) If any EGT thermocouple probe shows wear through the
thermocouple guide sleeve or contact between the turbine mid-frame
liner and the EGT thermocouple probe, before further flight, remove
and replace the EGT thermocouple probe and ensure the turbine mid-
frame liner does not contact the EGT thermocouple probe.
    (4) EGT System Resistance Checks. (i) Within 750 cycles since
the last resistance check on the EGT system or before further
flight, whichever occurs later, perform an EGT system resistance
check.
    (ii) Thereafter, within every 750 cycles since the last
resistance check, repeat the EGT system resistance check.
    (iii) If an EGT system component fails the resistance system
check, before further flight, remove and replace, or repair the EGT
system component.
    (5) Engine Core Vibration Survey. (i) Within 350 cycles since
the last engine core vibration survey or before further flight,
whichever occurs later, perform an initial engine core vibration
survey.
    (ii) Use about 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.
    (iii) Use a spectral/trim balance analyzer or equivalent to
measure the N2 rotor vibration.
    (iv) If the vibration level is above 5 mils Double Amplitude,
before further flight, remove the engine from service.
    (v) For those engines that fail any engine core vibration survey
requirements of this AD, before returning the engine to service:
    (A) Remove the LPT rotor stage 3 disk from service; or
    (B) Perform an FPI of the inner diameter surface forward spacer
arm of the LPT rotor stage 3 disk as specified in paragraph
(g)(6)(i)(A) through (C) of this AD.
    (vi) Thereafter, within every 350 cycles since the last engine
core vibration survey, perform the engine core vibration survey as
required in paragraphs (g)(5)(i) through (v) of this AD.
    (vii) If the engine has experienced any vibration reported by
maintenance or flight crew that is suspected to be caused by the
engine core (N2), within 10 cycles after the report, perform the
engine core vibration survey as required in paragraphs (g)(5)(i)
through (v) of this AD.
    (viii) Vibration surveys carried out in an engine test cell as
part of an engine manual performance run fulfill the vibration
survey requirements of paragraphs (g)(5)(ii) and (iii) of this AD.
    (6) Initial and Repetitive FPI of LPT Rotor Stage 3 Disk. (i) At
the next shop visit after accumulating 1,000 cycles since the last
FPI of the LPT rotor stage 3 disk forward spacer arm or before
further flight, whichever occurs later:
    (A) Clean the LPT rotor stage 3 disk forward spacer arm,
including the use of a wet-abrasive blast, to eliminate residual or
background fluorescence;
    (B) Perform an FPI of the LPT rotor stage 3 disk forward spacer
arm for cracks and for a band of fluorescence. Include all areas of
the disk forward spacer arm and the inner diameter surface forward
spacer arm of the LPT rotor stage 3 disk; and
    (C) If a crack or a band of fluorescence is present, before
further flight, remove the disk from service.
    (ii) Thereafter, at each engine shop visit that occurs after
accumulating 1,000 cycles since the last FPI of the LPT rotor stage
3 disk forward spacer arm, clean and perform an FPI of the LPT rotor
stage 3 disk forward spacer arm, as specified in paragraph
(g)(6)(i)(A) through (C) of this AD.
    (7) Removal of LPT Rotor Stage 3 Disk. (i) For any installed LPT
rotor stage 3 disk having a part number listed in Table 1 to
paragraph (c) of this AD, at the first occurrence of any one of the
conditions identified in paragraphs (g)(7)(i)(A) through (C) of this
AD, remove the LPT rotor stage 3 disk from service and replace with
LPT rotor stage 3 disk part number 2453M80P01.
    (A) For a disk that has accumulated fewer than 3,200 cycles
since new (CSN) as of March 6, 2012 (the effective date of AD 2012-
02-07), remove the disk from service before accumulating 6,200 CSN.
    (B) For a disk that accumulated 3,200 or more CSN as of March 6,
2012 (the effective date of AD 2012-02-07), do the actions required
by paragraphs (g)(7)(i)(B)(1) or (2) of this AD, as applicable to
your engine.
    (1) If the engine has a shop visit before the disk accumulates
6,200 CSN, remove the disk from service at that shop visit.
    (2) If the engine does not have a shop visit before the disk
accumulates 6,200 CSN, remove the disk from service at the next shop
visit after accumulating 6,200 CSN, not to exceed 3,000 cycles from
March 6, 2012 (the effective date of AD 2012-02-07).
    (C) Before exceeding 18 months from the effective date of this
AD.

(h) Terminating Action

    Replacement of the LPT rotor stage 3 disk in accordance with
paragraph (g)(7) of this AD constitutes terminating action for the
inspections, engine checks, and vibration surveys required by
paragraphs (g)(1) through (6) of this AD.

(i) Installation Prohibition

    After the effective date of this AD, do not install or reinstall
onto any engine an LPT rotor stage 3 disk listed in Table 1 to
paragraph (c) of this AD that has accumulated 6,200 CSN or more.

(j) Definitions

    For the purposes of this AD:
    (1) An EGT above redline is a confirmed over-temperature
indication that is not a result of EGT system error.
    (2) A shift in the smoothed EGT trending data is a shift in a
rolling average of EGT readings that can be confirmed by a
corresponding shift in the trending of fuel flow or fan speed/core
speed (N1/N2) relationship.

    Note 2 to paragraph (j)(2): You can find further guidance about
evaluating EGT trend data in GE Company Service Rep Tip 373
``Guidelines For Parameter Trend Monitoring.''

    (3) An engine shop visit is the induction of an engine into the
shop, where the separation of a major engine flange occurs; except
the following maintenance actions, or any combination, are not
considered engine shop visits:
    (i) Induction of an engine into a shop solely for removal of the
compressor top or bottom case for airfoil maintenance or variable
stator vane bushing replacement;

    (ii) Induction of an engine into a shop solely for removal or
replacement of the stage 1 fan disk;
    (iii) Induction of an engine into a shop solely for replacement
of the turbine rear frame;
    (iv) Induction of an engine into a shop solely for replacement
of the accessory gearbox or transfer gearbox, or both; and
    (v) Induction of an engine into a shop solely for replacement of
the fan forward case.
    (4) A raw EGT trend data point above the smoothed average is a
confirmed temperature reading over the rolling average of EGT
readings that is not a result of EGT system error.

(k) Credit for Previous Actions

    You may take credit for the actions required by paragraph (g) of
this AD if they were performed before the effective date of this AD
using GE Service Bulletin (SB) No. CF6-50 SB 72-1315, Initial Issue,
dated June 3, 2011, or GE SB No. CF6-50 SB 72-1315, Revision 1,
dated June 30, 2011.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39 19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
certification office, send it to the attention of the person
identified in paragraph (m) of this AD and email it to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
    (3) AMOCs approved previously for AD 2010-12-10, Amendment 39-
16331 (75 FR 32649, June 9, 2010); AD 2011-02-07, Amendment 39-16580
(76 FR 6323, February 4, 2011); or AD 2011-18-01, Amendment 39-16783
(76 FR 52213, August 22, 2011) are approved as AMOCs for the
corresponding provisions of this AD.

(m) Related Information

    For more information about this AD, contact Sungmo Cho, Aviation
Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington,
MA 01803; phone:<PHONE_NUMBER>; email: [email protected].

(n) Material Incorporated by Reference

    None.

    Issued on February 17, 2023.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2023-05472 Filed 3-23-23; 8:45 am]
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