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2023-21-07 GENERAL ELECTRIC COMPANY: Amendment 39-22579; Docket No. FAA-2022-1314; Project Identifier AD-2021-00811-E.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective December 11, 2023.

(b) AFFECTED ADS

    This AD replaces AD 2018-03-13, Amendment 39-19186 (83 FR 6125, Febru-
    ary 13, 2018).

(c) APPLICABILITY

    This AD applies to General Electric Company  (GE)  Model CT7-5A2, CT7-
    5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1,  CT7-9B2,  CT7-9C,  and CT7-9C3
    engines.

(d) SUBJECT

    Joint Aircraft System Component (JASC)  Code 7210,  Turbine Engine Re-
    duction Gear.

(e) UNSAFE CONDITION

    This AD was prompted by an in-flight failure of a main propeller shaft
    on  a  GE  Model CT7-9B  model engine,  resulting in  the loss  of the
    propeller. The FAA is issuing this  AD to prevent failure of the  main
    propeller shaft. The unsafe  condition, if not addressed,  could cause
    in-flight loss of  the propeller,  loss of engine thrust control,  and
    damage to the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

(1) For affected CT7-5A2, CT7-5A3, CT7-9B, CT7-9B1, and CT7-9B2  model en-
    gines,  using the compliance times  specified in Figure 1 to paragraph
    (g)(1) of this AD,  perform initial and repetitive visual inspections,
    fluorescent penetrant inspections (FPIs),  and  ultrasonic inspections
    (USIs) of the main propeller shaft.

    FIGURE 1 TO PARAGRAPH (G)(1)  COMPLIANCE TIMES FOR CT7-5A2, CT7-5A3, 
                                   CT7-9B, CT7-9B1, AND CT7-9B2 MODEL     
                                   ENGINES                                
    ______________________________________________________________________
    INSPECTION      INITIAL INSPECTION OF         REPEAT INSPECTION INTER-
    TYPE            THE MAIN PROPELLER SHAFT      VAL OF MAIN PROPELLER
                                                  SHAFT
    ______________________________________________________________________
    Cleaning        During first propeller        During every propeller
    and visual      removal after the             removal
    inspection      effective date of this
                    AD

    FPI             Before exceeding 20,000       During every propeller
                    cycles since new (CSN) or     removal or within 2,100
                    within 2,100 flight hours     FHs from performance of
                    (FHs) after the effective     the previous FPI, which-
                    date of this AD, whichever    ever occurs later
                    occurs later

    USI             Before exceeding 20,000       Before exceeding 5,000
                    CSN or within 1,600 FHs       FHs from performance of
                    after the effective date      the previous USI
                    of this AD, whichever
                    occurs later
    ______________________________________________________________________

(2) For affected CT7-7A, CT7-7A1, CT7-9C, and CT7-9C3 model engines, using
    the compliance times specified in Figure 2 to paragraph (g)(2) of this
    AD, perform initial and repetitive visual inspections, FPIs,  and USIs
    of the main propeller shaft.


     FIGURE 2 TO PARAGRAPH (G)(2)  COMPLIANCE TIMES FOR CT7-7A, CT7-7A1, 
                                    CT7-9C, AND CT7-9C3 MODEL ENGINES     
    ______________________________________________________________________
    INSPECTION      INITIAL INSPECTION OF         REPEAT INSPECTION INTER-
    TYPE            THE MAIN PROPELLER SHAFT      VAL OF MAIN PROPELLER
                                                  SHAFT
    ______________________________________________________________________
    Cleaning        During the first propeller    During every propeller
    and visual      removal after the effective   removal
    inspection      date of this AD

    FPI             Before exceeding 20,000       During every propeller
                    CSN or within 2,400 FHs       removal or within 2,400
                    after the effective date      FHs from performance of
                    of this AD, whichever         the previous FPI, which-
                    occurs later                  ever occurs later

    USI             Before exceeding 20,000       Before exceeding 4,800
                    CSN or within 1,600 FHs       FHs from performance of
                    after the effective date      the previous USI
                    of this AD, whichever
                    occurs later
    ______________________________________________________________________

(3) Perform the visual inspections, FPIs,  and USIs required by paragraphs
    (g)(1) and (2) of this AD as follows:

(i) Prior to performance  of the inspections,  clean  the  main  propeller
    shaft flange using the Accomplishment Instructions, paragraph 3.B., of
    GE Service Bulletin (SB) CT7-TP 72-0541 R01,  dated  November 18, 2021
    (GE SB CT7-TP 72-0541).

(ii) Visually inspect the main propeller shaft  for wear,  corrosion,  and
     cracking using the Accomplishment Instructions, paragraph 3.C.(1), of
     GE SB CT7-TP 72-0541.

(iii) Spot-FPI the area on the main propeller shaft flange face  using the
      Accomplishment Instructions,  paragraph 3.C.(2)(a),  of GE SB CT7-TP
      72-0541.

(iv) USI the two dowel pin holes  of  the main propeller shaft  using  the
     Accomplishment Instructions, paragraph 3.C.(3)(a), of GE SB CT7-TP 72
     -0541.

(4) If a crack or rejectable indication is found  during  the  initial and
    repetitive visual inspections, FPIs,  or  USIs  required by paragraphs
    (g)(1) through (3) of this AD, before further flight,  remove the main
    propeller shaft from service and replace it with  a  part eligible for
    installation.

(5) For all affected engines,  if the main propeller shaft CSN is unknown,
    use the propeller gearbox (PGB) CSN. If the PGB CSN is unknown, assume
    the inspection threshold is exceeded.

(h) OPTIONAL TERMINATING ACTION

    Accomplishing the actions in paragraphs (h)(1) through (4) of this AD,
    as applicable by engine model,  constitutes terminating action for the
    inspections required by paragraphs (g)(1) through (3) of this AD.

(1) For affected  CT7-5A2, CT7-5A3, CT7-7A, and CT7-7A1 model engines, re-
    vise the airworthiness limitations section (ALS) of the existing main-
    tenance manual (MM)  and  the operator's existing approved maintenance
    program or inspection program, as applicable, by incorporating the in-
    formation in Figure 3 to paragraph (h)(1) of this AD.

                        ILLUSTRATION (Figure 3)

(2) For affected CT7-9B, CT7-9B1, CT7-9B2, CT7-9C,  and  CT7-9C3 model en-
    gines, revise the ALS of the existing MM  and  the operator's existing
    approved maintenance program or inspection program,  as applicable, by
    incorporating the information in Figure 4 to paragraph (h)(2)  of this
    AD.

                        ILLUSTRATION (Figure 4)

(3) Thereafter, except as provided in paragraph (k) of this AD,  no alter-
    native inspection times  or  intervals  may be approved  for this main
    propeller shaft.

(4) The optional terminating actions in paragraphs (h)(1) and (2)  of this
    AD may be performed by the owner / operator (pilot) holding at least a
    private pilot certificate  and  must  be  entered  into  the  aircraft
    records showing compliance with this AD in accordance with 14 CFR 43.9
    (a) and 91.417(a)(2)(v).  The record must be maintained as required by
    14 CFR 91.417, 121.380, or 135.439.

(i) DEFINITION

    For the purpose  of this AD,  a  "part eligible for installation" is a
    main propeller shaft that has been inspected  in accordance with para-
    graphs (g)(1) or (2), and (3) of this AD,  and  there  was no crack or
    rejectable indication.

(j) CREDIT FOR PREVIOUS ACTIONS

    You may take credit for the initial visual inspection,  FPI,  and  USI
    required by paragraphs (g)(1) through (3) of this AD  if you performed
    these initial  inspections before  the effective  date of  this AD  in
    accordance with GE SB CT7-TP 72-0541 R00, dated September 9, 2021.

(k) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, AIR-520 Continued Operational Safety 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  AIR-520 Continued Operational  Safety
    Branch, send it to the attention of the person identified in paragraph
    (l) of this AD and email it to: ANE-AD-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector,  or  lacking a principal inspector,  the manager of the local
    flight standards district office/certificate holding district office.

(l) ADDITIONAL INFORMATION

    For more information about this AD, contact Sungmo Cho, Aviation Safe-
    ty Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone
    (781) 238-7241; email: Sungmo.D.Cho@faa.gov.

(m) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference  (IBR)  of the service information  listed in this paragraph
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) General  Electric  Company  (GE)  Service Bulletin CT7-TP 72-0541 R01,
    dated November 18, 2021.

(ii) [Reserved]

(3) For GE service information  identified  in  this AD,  contact  General
    Electric Company,  1 Neumann Way,  Cincinnati, OH 45215;  phone: (513)
    552-3272; email: aviation.fleetsupport@ae.ge.com; website: ge.com.

(4) You may view this service information at FAA,  Airworthiness  Products
    Section, Operational Safety Branch,  1200 District Avenue, Burlington,
    MA 01803.  For information on the availability of this material at the
    FAA, call (817) 222-5110.

(5) You may view this material at the National Archives and Records Admin-
    istration (NARA). For information on the availability of this material
    at NARA,  visit www.archives.gov/federal-register/cfr/ibr-locations or
    email fr.inspection@nara.gov.

Issued on October 20, 2023.  Ross Landes,  Deputy Director  for Regulatory
Operations,  Compliance & Airworthiness Division,  Aircraft  Certification
Service.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer, FAA
2200 South 216th Street, Des Moines, WA 98198; phone (781) 238-7241; email
Sungmo.D.Cho@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1314; Project Identifier AD-2021-00811-E;
Amendment 39-22579; AD 2023-21-07]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-03-13
for certain General Electric Company (GE) Model CT7-5A2, CT7-5A3, CT7-
7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C, and CT7-9C3 engines. AD
2018-03-13 required initial and repetitive visual inspections and
fluorescent penetrant inspections (FPIs) of the main propeller shaft.
This AD was prompted by an in-flight failure of a main propeller shaft
on a GE Model CT7-9B engine, resulting in the loss of the propeller.
This AD requires initial and repetitive visual inspections, FPIs, and
ultrasonic inspections (USIs) of the main propeller shaft. Depending on
the results of these inspections, this AD requires replacement of the
main propeller shaft. As an optional terminating action to these
inspections, this AD requires revising the airworthiness limitations
section (ALS) of the existing maintenance manual (MM) and the
operator's existing approved maintenance program or inspection program,
as applicable, to incorporate incorporating the tasks and reduced
inspection thresholds for the main propeller shaft. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective December 11, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 11,
2023.

ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1314; 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.
Material Incorporated by Reference:
For GE service information identified in this final rule,
contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552-3272; email: aviation.fleetsupport@ae.ge.com; website:
ge.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110. It is
also available at regulations.gov under Docket No. FAA-2022-1314.

FOR FURTHER INFORMATION CONTACT
: Sungmo Cho, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (781) 238-
7241; email: Sungmo.D.Cho@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede AD 2018-03-13, Amendment 39-19186
(83 FR 6125, February 13, 2018) (AD 2018-03-13). AD 2018-03-13 applied
to certain GE Model CT7-5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1,
CT7-9B2, CT7-9C and CT7-9C3 engines. The SNPRM published in the Federal
Register on July 11, 2023 (88 FR 44068). The SNPRM was prompted by a
comment from GE Aerospace on the notice of proposed rulemaking (NPRM).
GE Aerospace stated that certain engine models were included in
incorrect Figures within the Required Actions paragraph of the NPRM,
which would attribute inaccurate inspection thresholds to those engine
models. Therefore, the FAA issued the SNPRM with a revision to Figures
1 and 2 to include the correct engine models. The FAA also updated the
affected engine models listed in paragraphs (g)(1) and (g)(2) of the
SNPRM to correspond with the corrected engine models referenced in
Figures 1 and 2.
In the SNPRM, the FAA proposed to require initial and repetitive
visual inspections, FPIs, and USIs of the main propeller shaft.
Depending on the results of these inspections, the SNPRM proposed to
require replacing the main propeller shaft. As an optional terminating
action to these inspections, the SNPRM proposed to require revising the
ALS of the existing MM and the operator's existing approved maintenance
program or inspection program, as applicable, to incorporate the tasks
and reduced inspection thresholds for the main propeller shaft. The FAA
is issuing this AD to address the unsafe condition on these products.

Discussion of Final Airworthiness Directive

Comments

The FAA received comments from one commenter, GE Aerospace. The
following presents the comment received on the SNPRM and the FAA's
response to that comment.

Request To Remove Typographical Error From SNPRM

GE noted that there is a typological [typographical] error in the
``Proposed AD Requirements in This SNPRM'' paragraph of the SNPRM in
which the words ``at least'' are repeated in succession.
The FAA agrees, however, the ``Proposed AD Requirements in This
SNPRM'' paragraph is not included in this Final Rule. The FAA did not
change this AD as a result of this comment.

Conclusion

The FAA reviewed the relevant data, considered any 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 and any
other changes described previously, this AD is adopted as proposed in
the SNPRM. None of the changes will increase the economic burden on any
operator.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GE Service Bulletin (SB) CT7-TP 72-0541 R01, dated
November 18, 2021 (GE SB CT7-TP 72-0541). This service information
specifies procedures for performing initial and repetitive visual
inspections, FPIs, and USIs of the main propeller shaft.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Costs of Compliance


The FAA estimates that this AD affects 176 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Visually inspect, FPI, and USI the main propeller shaft 2 work-hours x $85 per hour = $170
$0
$170
$29,920

The FAA estimates the following costs to perform the optional
terminating action or to do any necessary replacement that would be
required based on the results of the inspections. The agency has no way
of determining the number of operators that will perform the optional
terminating action or engines that might need this replacement:

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Replace the main propeller shaft 8 work-hours x $85 per hour = $680
$48,360
$49,040
Revise the ALS of the MM 1 work-hour x $85 per hour = $85
0
85

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

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]


2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 2018-03-13, Amendment 39-19186 (83
FR 6125, February 13, 2018); and

b. Adding the following new airworthiness directive: