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PROPOSED AD GENERAL ELECTRIC COMPANY: Docket No. FAA-2022-0690; Project Identifier AD-2021-01360-E.
(a) COMMENTS DUE DATE

    The FAA must receive comments  on this airworthiness directive (AD) by
    August 5, 2022.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD  applies  to  General Electric Company CT7-8A model turboshaft
    engines.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 7240,  Turbine Engine Com-
    bustion Section; 7250, Turbine Section.

(e) UNSAFE CONDITION

    This AD was prompted by the manufacturer  revising  the  airworthiness
    limitations section  (ALS) of  the existing  engine maintenance manual
    (EMM) to incorporate reduced life  limits for certain stage 1  turbine
    aft cooling plates,  stage 2 turbine  forward cooling plates,  turbine
    interstage seals, and stage 4  turbine disks. The FAA is  issuing this
    AD to prevent failure of the stage 1 turbine aft cooling plates, stage
    2 turbine forward cooling plates, turbine interstage seals, and  stage
    4 turbine disks. The unsafe condition, if not addressed, could  result
    in  uncontained part  release,  damage  to the  engine, damage  to the
    helicopter, and possible loss of control of the helicopter.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) Within 90 days after the effective date of this AD,  revise the ALS of
    the existing  GE CT7-8 Turboshaft  EMM  and  the  operator's  existing
    approved maintenance or inspection program, as applicable, by incorpo-
    rating the following reduced life limits:

(i) For stage 1 turbine aft cooling plate,  part number  (P/N) 6064T09P02,
    change the life limit cycles  from  6,600  cycles since new  (CSN)  to
    4,900 CSN;

(ii) For stage 2 turbine forward cooling plate, P/N 4106T80P01, change the
     life limit cycles from 8,000 CSN to 7,200 CSN;

(iii) For turbine interstage seal,  P/N 4111T86P03,  change the life limit
      cycles from 29,200 CSN to 19,000 CSN; and

(iv) For stage 4 turbine disk,  P/N  6068T32P04,  change  the  life  limit
     cycles from 24,100 CSN to 12,100 CSN.

(2) After performing the actions  required by paragraph (g)(1) of this AD,
    except as provided in paragraph (h) of this AD,  no  alternative  life
    limits may be approved.

(h) 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
    (i) of this AD and email 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.

(i) RELATED INFORMATION

    For more information about this AD, contact Sungmo Cho, Aviation Safe-
    ty Engineer,  ECO Branch,  FAA,  1200 District Avenue,  Burlington, MA
    01803; phone: (781) 238-7241; email: Sungmo.D.Cho@faa.gov.

Issued on June 14, 2022. Christina Underwood, Acting Director,  Compliance
& Airworthiness Division, Aircraft Certification Service.

DATES: The FAA must receive comments  on  this  proposed  AD  by August 5,
2022.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration


14 CFR Part 39


[Docket No. FAA-2022-0690; Project Identifier AD-2021-01360-E]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turboshaft
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all General Electric Company (GE) CT7-8A model turboshaft engines.
This proposed AD was prompted by the manufacturer revising the
airworthiness limitations section (ALS) of the existing engine
maintenance manual (EMM) to incorporate reduced life limits for certain
stage 1 turbine aft cooling plates, stage 2 turbine forward cooling
plates, turbine interstage seals, and stage 4 turbine disks. This
proposed AD would require revising the ALS of the existing EMM and the
operator's existing approved maintenance or inspection program, as
applicable, to incorporate reduced life limits for these parts. The FAA
is proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by August 5,
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact General
Electric Company, 1 Neumann Way, Cincinnati, OH 45215; phone: (513)
552-3272; email: aviation.fleetsupport@ae.ge.com; website: https://www.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.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2022-0690; 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 NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Sungmo Cho, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7241; email: Sungmo.D.Cho@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0690; Project Identifier
AD-2021-01360-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.

Confidential Business Information


CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI
should be sent to Sungmo Cho, Aviation Safety Engineer, ECO Branch,
FAA, 1200 District Avenue, Burlington, MA 01803. Any commentary that
the FAA receives which is not specifically designated as CBI will be
placed in the public docket for this rulemaking.

Background

The FAA was notified that the manufacturer revised the ALS of the
existing EMM to incorporate reduced life limits for certain stage 1
turbine aft cooling plates, stage 2 turbine forward cooling plates,
turbine interstage seals, and stage 4 turbine disks (life-limited
parts) installed on CT7-8A model turboshaft engines. Additionally, the
manufacturer published service information that introduced the reduced
life limits. The life limits were reduced by the manufacturer as the
result of an analysis of the life management models for these parts.
This condition, if not addressed, could result in uncontained part
release, damage to the engine, damage to the helicopter, and possible
loss of control of the helicopter.

FAA's Determination

The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.

Related Service Information


The FAA reviewed GE CT7-8 Service Bulletin 72-0062, Revision 01,
dated December 22, 2021. This service information provides the reduced
life limits for certain life-limited parts.

Proposed AD Requirements in This NPRM

This proposed AD would require revising the ALS of the applicable
GE CT7-8 EMM and the operator's existing approved maintenance or
inspection program, as applicable, to incorporate reduced life limits
for certain life-limited parts.

Costs of Compliance

The FAA estimates that this AD, if adopted as proposed, would
affect 126 engines installed on helicopters of U.S. registry. The FAA
estimates the following costs to comply with this proposed AD:

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Revise ALS of EMM and the operator's existing approved maintenance or inspection program
1 work-hour x $85 per hour = $85
$0
$85
$10,710

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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: