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PROPOSED AD GENERAL ELECTRIC COMPANY: Docket No. FAA-2019-0766; Product Identifier 2019-NE-23-AD.
(a) COMMENTS DUE DATE

    The FAA must receive comments by January 17, 2020.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to all General Electric Company (GE)  CF34-8C1,  CF34-
    8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3,  CF34-8E2,  CF34-
    8E2A1,  CF34-8E5,  CF34-8E5A1,  CF34-8E5A2,  CF34-8E6,  and CF34-8E6A1
    turbofan engine models,  including engine models marked on engine data
    plate as CF34-8C5/B,  CF34-8C5/M,  CF34-8C5A1/B,  CF34-8C5A1/M,  CF34-
    8C5B1/B, CF34-8C5A2/B, and CF34-8C5A2/M.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD was prompted  by a predicted reduction  in the cyclic life  of
    the combustion chamber assembly aft flange. The FAA is issuing this AD
    to  prevent failure  of the  combustion chamber  assembly. The  unsafe
    condition,  if  not  addressed,  could  result  in  combustion chamber
    assemblies  failing  before  reaching  their  published  life   limit,
    uncontained release of the combustion chamber assembly, damage to  the
    engine, and damage to the airplane.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) Within 90 days after  the  effective  date  of  this  AD,  revise  the
    Airworthiness Limitations Section of the GE Instructions for Continued
    Airworthiness. For air  carrier operations, within  90 days after  the
    effective  date  of  this  AD,  also  revise  the  approved continuous
    airworthiness maintenance  program. These  revisions must  incorporate
    the following requirements for fluorescent penetrant inspections (FPI)
    of the combustion chamber assembly aft flange.

(i) For a combustion chamber assembly  with part number  (P/N) 4145T11G08,
    P/N 4145T11G09, P/N 4180T27G01, or P/N 4180T27G03 installed on GE CF34
    -8E turbofan engine models, revise CF34-8E Engine Manual GEK112031 by:

(A) Replacing Table 801, Static Structures-Life Limits ("Table 801"), with
    the revised Table 801  in Task 05-11-05-200-801  of  GE CF34-8E Engine
    Manual Temporary Revision (TR) 05-0085, dated February 21, 2019, and

(B) Adding Task 05-21-03-200-801 of GE CF34-8E TR 05-0086,  dated February
    13, 2019 ("GE CF34-8E TR 05-0086").

(ii) For a combustion chamber assembly with P/N 4126T87G04, P/N 4126T87G05
     P/N 4126T87G07, P/N 4126T87G08, P/N 4180T27G04, P/N 4923T82G01 or P/N
     4923T82G02 installed on GE CF34-8C1 turbofan engine models,  or  with
     P/N 4145T11G08, P/N 4145T11G10, P/N 4180T27G02, P/N 4180T27G04 or P/N
     4923T82G02 installed on GE CF34-8C5,  CF34-8C5/M,  CF34-8C5A1,  CF34-
     8C5A1/M, CF34-8C5A2, CF34-8C5A2/M, CF34-8C5A3, or CF34-8C5B1 turbofan
     engine models, revise CF34-8C Engine Manual GEK105091 by:

(A) Replacing  Table  801,  (For -8C1)  and  Table 802  (For -8C5)  Static
    Structures-Life Limits ("Table 801" and "Table 802"), with the revised
    Tables 801 and 802  in  Task  05-11-05-200-801  of  GE CF34-8C  Engine
    Manual TR 05-0141, dated February 21, 2019, and

(B) Adding Task 05-21-03-200-801 of GE CF34-8C TR 05-0142,  dated February
    13, 2019 ("GE CF34-8C TR 05-0142").

(iii) For  a  combustion  chamber  assembly   with  P/N  4145T11G08,   P/N
      4145T11G10, P/N 4180T27G02,  P/N 4180T27G04,  or  P/N 4923T82G02 in-
      stalled on GE CF34-8C5B1/B CF34-8C5/B, CF34-8C5A1/B, or CF34-8C5A2/B
      turbofan engine models (Business Jet),  revise CF34-8C Engine Manual
      GEK105091 by:

(A) Replacing Table 801 (For/B -8C5 Models) Static Structures- Life Limits
    with the  revised Table 801  in Task 05-11-25-200-801 of GE CF34-8C TR
    05-143, dated February 13, 2019, and

(B) Adding Task 05-21-03-200-801 of GE CF34-8C TR 05-0142.

(2) For any combustion chamber assembly  that has exceeded the initial in-
    spection threshold (in cycles) specified  in GE CF34-8E TR 05-0086  or
    GE CF34-8C TR 05-0142:

(i) Perform the initial FPI of the combustion chamber assembly  aft flange
    within 2,200 cycles after the effective date of this AD  in accordance
    with GE CF34-8E TR 05-0086 or GE CF34-8C TR 05-0142.  Thereafter, per-
    form repetitive FPIs in accordance with the intervals in GE CF34-8E TR
    05-0086 or GE CF34-8C TR 05-0142.

(ii) If,  during the FPI required  by paragraph (g)(2)(i)  of  this  AD, a
     crack is found in the combustion chamber assembly aft flange,  dispo-
     sition the assembly  in accordance  with paragraph 2.A. of GE CF34-8E
     TR 05-0086, or paragraph 2.A. of GE CF34-8C TR 05-0142.

(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)(1) of this AD. You may email your request 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

(1) For more information about this AD,  contact  David Bethka,  Aerospace
    Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
    phone: 781-238-7129; fax: 781-238-7199; email: david.bethka@faa.gov.

(2) For service information identified in this AD contact General Electric
    Company,  GE Aviation,  Room 285, 1 Neumann Way, Cincinnati, OH 45215;
    phone: 513-552-3272; email: aviation.fleetsupport@ge.com. You may view
    this referenced service information  at the FAA,  Engine and Propeller
    Standards Branch, 1200 District Ave., Burlington, MA.  For information
    on the availability of this material at the FAA, call 781-238-7759.

Issued in Burlington, Massachusetts, on November 25, 2019. Robert J Ganley
Manager,  Engine and Propeller  Standards  Branch,  Aircraft Certification
Service.

DATES: The FAA must receive comments  on this proposed AD  by  January 17,
2020.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0766; Product Identifier 2019-NE-23-AD]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turbofan 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) CF34-8C1, CF34-8C5, CF34-8C5A1,
CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5,
CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 turbofan engine
models. This proposed AD was prompted by a predicted reduction in the
cyclic life of the combustion chamber assembly aft flange, which could
result in certain combustion chamber assemblies failing before reaching
their published life limit. This proposed AD would require revisions to
the Airworthiness Limitations Section (ALS) of the manufacturer's
Instructions for Continued Airworthiness (ICA) and to the air carrier's
approved Continued Airworthiness Maintenance Programs (CAMP) to
incorporate initial and repetitive fluorescent penetrant inspections
(FPIs) of the combustion chamber assembly. 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 January 17,
2020.

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, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH
45215; phone: 513-552-3272; email: aviation.fleetsupport@ge.com. You
may view this service information at the FAA, Engine and Propeller
Standards Branch, 1200 District Avenue, Burlington, MA. For information
on the availability of this material at the FAA, call 781-238-7759.

Examining the AD Docket

You may examine the AD docket on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2019-
0766; 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, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: David Bethka, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7129; fax: 781-238-7199; email: david.bethka@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 the ADDRESSES section. Include "Docket No. FAA-2019-0766;
Product Identifier 2019-NE-23-AD" at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.

The FAA will post all comments received, without change, to https://www.
regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact it receives about this NPRM.

Discussion

The FAA was notified by the manufacturer that they found a
reduction in the cyclic life of the combustion chamber assembly when
updating their life analysis. As a result, the manufacturer added a
scheduled maintenance check. This condition, if not addressed, could
result in combustion chamber assemblies failing before reaching their
published life limit.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GE CF34-8E Engine Manual Temporary Revision (TR)
05-0085, dated February 21, 2019; GE CF34-8C TR 05-0141, dated February
21, 2019; and GE CF34-8C TR 05-143, dated February 13, 2019. These TRs,
differentiated by GE CF34-8 turbofan engine model, identify the
combustion chamber assembly part number, life limit cycles, and new
inspections.

The FAA also reviewed GE CF34-8E TR 05-0086, dated February 13,
2019, and GE CF34-8C TR 05-0142, dated February 13, 2019. These TRs,
differentiated by GE CF34-8 turbofan engine model, describe new
inspection threshold limits and re-inspection interval limits for the
combustion chamber assembly.

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.

FAA's Determination

The FAA is proposing this AD because it 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.

Proposed AD Requirements

This proposed AD would require revisions to the ALS of the
manufacturer's ICA and the air carrier's approved CAMP to incorporate
initial and repetitive FPIs of the combustion chamber assembly.

Costs of Compliance

The FAA estimates that this proposed AD affects 1,216 GE CF34-8C
turbofan engine models and 638 GE CF34-8E turbofan engine models
installed on airplanes 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 the ALS and CAMP (GE CF34-8C and CF34-8E). 1 work-hour x $85 per hour = $85 $0 $85 $157,590
FPI combustion chamber assembly (GE CF34-8C). 6 work-hours x $85 per hour = $510 0 510 620,160
FPI combustion chamber assembly (GE CF34-8E). 5 work-hours x $85 per hour = $425 0 425 271,150

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.

This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.

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) 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 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 (AD):