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2018-26-01 CFM INTERNATIONAL S.A.:
Amendment 39-19531; Docket No. FAA-2018-1039; Product Identifier 2018-NE-14-AD.

(a) EFFECTIVE DATE

    This AD is effective January 10, 2019.

(b) AFFECTED ADS

    This  AD  replaces  AD  2018-18-01,  Amendment 39-19380  (83 FR 49272,
    October 1, 2018).

(c) APPLICABILITY

    This AD applies to CFM International S.A.(CFM) CFM56-7B20, CFM56-7B22,
    CFM56-7B22/B1, CFM56-7B24, CFM56-7B24/B1,  CFM56-7B26,  CFM56-7B26/B2,
    CFM56-7B27, CFM56-7B27A, CFM56-7B26/B1, CFM56-7B27/B1,  CFM56-7B27/B3,
    CFM56-7B20/2, CFM56-7B22/2, CFM56-7B24/2, CFM56-7B26/2,  CFM56-7B27/2,
    CFM56-7B20/3, CFM56-7B22/3, CFM56-7B22/3B1, CFM56-7B24/3,  CFM56-7B24/
    3B1, CFM56-7B26/3, CFM56-7B26/3B1, CFM56-7B26/3B2, CFM56-7B27/3, CFM56
    -7B27/3B1, CFM56-7B27/3B3, CFM56-7B27A/3,  CFM56-7B26/3F,  CFM56-7B26/
    3B2F, CFM56-7B27/3F, CFM56-7B27/3B1F, CFM56-7B20E, CFM56-7B22E, CFM56-
    7B22E/B1, CFM56-7B24E,  CFM56-7B24E/B1,  CFM56-7B26E,  CFM56-7B26E/B1,
    CFM56-7B26E/B2, CFM56-7B27AE, CFM56-7B27E, CFM56-7B27E/B1, CFM56-7B27E
    /B3, CFM56-7B26E/F, CFM56-7B26E/B2F, CFM56-7B27E/F and CFM56-7B27E/B1F
    turbofan engine models.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 7230,  Turbine Engine Com-
    pressor Section.

(e) UNSAFE CONDITION

    This AD was prompted by further analysis by the manufacturer  that in-
    dicated a need to reduce the initial fan blade inspection  requirement
    based on its ongoing root cause investigation of an April 2018  engine
    failure  that resulted  in one  fatality. We  are issuing  this AD  to
    prevent  failure  of  the  fan blade.  The  unsafe  condition,  if not
    addressed, could result in failure of the fan blade, the engine  inlet
    cowl disintegrating  and debris  penetrating the  fuselage,  causing a
    loss of pressurization, and prompting an emergency descent.

(f) COMPLIANCE

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

(g) REQUIRED ACTIONS

(1) Perform an ultrasonic inspection  (USI)  or  eddy  current  inspection
    (ECI) of the  concave and convex  sides of the  fan blade dovetail  as
    follows:

(i) For a fan blade  with less than  or  equal  to 16,000 cycles since new
    (CSN), inspect prior to accumulating 17,000 CSN.

(ii) For a fan blade with more than 16,000  and  less than 20,000 CSN, in-
     spect within 1,000 cycles but no later than 20,000 CSN.

(iii) For a fan blade with 20,000 or  more  CSN,  inspect  before  further
      flight.

(iv) Thereafter,  repeat this inspection  no later than 1,600 cycles since
     the last inspection, or within 450 cycles after October 16, 2018, the
     effective date of AD 2018-18-01, whichever occurs later.

(v) Use the Accomplishment Instructions, paragraphs 3.A.(3)(a) through (i)
    of  CFM  International  Service  Bulletin  (SB)  CFM56-7B S/B 72-1033,
    Revision 3,  dated  November 6, 2018,  to perform a USI or use the in-
    structions in subtask 72-21-01-220-091, of task 72-21-01-200-001, from
    CFM CFM56-7B Engine Shop Manual, Revision 57,  dated January 15, 2018,
    to perform an ECI.

(2) If any unserviceable indication,  as specified  in the applicable ser-
    vice information in paragraph (g)(1)(v) of this AD,  is  found  during
    the inspections required by paragraph (g) of this AD,  replace the fan
    blade before further flight with a part eligible for installation.

(h) INSTALLATION PROHIBITION

    Do not install  any replacement  fan blade  unless it meets one of the
    following criteria:

(1) The replacement fan blade has fewer than 17,000 CSN, or;

(2) The replacement fan blade has been inspected,  per paragraph (g)(1) of
    this AD, within the last 1,600 cycles before installation.

(i) DEFINITION

    For the purpose of this AD,  a "replacement fan blade" is a  fan blade
    that  is  being  installed  into  an  engine  from  which  it  was not
    previously  removed.  Removing and reinstalling  a fan  blade for  the
    purpose  of   relubrication  is   not  subject   to  the  Installation
    Prohibition of this AD.

(j) CREDIT FOR PREVIOUS ACTIONS

    You may take credit for the actions that are required by paragraph (g)
    of this AD,  if you performed those actions  before the effective date
    of this AD  using CFM SB CFM56-7B S/B 72-1019,  dated  March 24, 2017;
    CFM SB CFM56-7B S/B 72-1019,  Revision 1, dated June 13, 2017;  CFM SB
    CFM56-7B S/B 72-1024, dated July 26, 2017; CFM SB CFM56-7B S/B 72-1033
    dated April 20, 2018; CFM SB CFM56-7B S/B 72-1033,  Revision 1,  dated
    May 9, 2018; or CFM International SB CFM56-7B S/B 72-1033, Revision 2,
    dated July 27, 2018 or performed an ECI using the instructions in task
    72-21-01-200-001,  subtask  72-21-01-220-091  of  CFM56-7B Engine Shop
    Manual, earlier than Revision 57, dated January 15, 2018.

(k) 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
    (l) 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.

(3) For service information  that  contains  steps  that  are  labeled  as
    Required for Compliance  (RC),  the provisions of paragraphs (k)(3)(i)
    and (k)(3)(ii) of this AD apply.

(i) The steps labeled as RC,  including substeps  under an RC step and any
    figures identified in an RC step,  must be done to comply with the AD.
    An AMOC is required for any deviations to RC steps, including substeps
    and identified figures.

(ii) Steps not labeled as RC may be deviated  from  using accepted methods
     in accordance with the  operator's maintenance or inspection  program
     without  obtaining  approval  of  an  AMOC,  provided  the  RC steps,
     including  substeps  and identified  figures,  can still  be  done as
     specified,  and  the  airplane  can  be  put  back  in  an  airworthy
     condition.

(4) AMOCs  approved  previously  for  AD 2018-10-11  (83 FR 22836, May 17,
    2018) and AD 2018-18-01 (83 FR 49272, October 1, 2018) are approved as
    AMOCs for the corresponding provisions of this AD.

(l) RELATED INFORMATION

    For more information about this AD, contact Christopher McGuire, Aero-
    space Engineer,  ECO Branch, FAA, 1200 District Avenue, Burlington, MA
    01803; phone: 781-238-7120;  fax: 781-238-7199;  email: chris.mcguire@
    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.

(3) The following service information was approved for IBR  on January 10,
    2019.

(i) CFM International (CFM) Service Bulletin CFM56-7B S/B 72-1033 Revision
    3, dated November 6, 2018.

(ii) [Reserved]

(4) The following service information was approved for IBR on May 14, 2018
    (83 FR 19176, May 2, 2018).

(i) Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from the CFM CFM56
    -7B Engine Shop Manual, Revision 57, dated January 15, 2018.

(ii) [Reserved]

(5) For CFM service information identified in this AD,  contact CFM Inter-
    national Inc, Aviation Operations Center, 1 Neumann Way, M/D Room 285,
    Cincinnati, OH 45125;  phone: 877-432-3272;  fax: 877-432-3329; email:
    aviation.fleetsupport@ge.com.

(6) You may view this service information at the FAA, Engine and Propeller
    Standards  Branch,  1200 District Avenue,  Burlington, MA  01803.  For
    information on the availability of this material at the FAA, call  781
    -238-7759.

(7) You  may  view  this  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: http://www.archives.gov/federal-register/cfr/ibr-
    locations.html.

Issued in Burlington, Massachusetts, on December 18, 2018. Robert J Ganley
Manager, Engine & Propeller Standards Branch,  Aircraft Certification Ser-
vice.

FOR FURTHER INFORMATION CONTACT: Christopher McGuire,  Aerospace Engineer,
ECO Branch, FAA,  1200 District Avenue, Burlington, MA, 01803; phone: 781-
238-7120; fax: 781-238-7199; email: chris.mcguire@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1039; Product Identifier 2018-NE-14-AD; Amendment
39-19531; AD 2018-26-01]
RIN 2120-AA64

Airworthiness Directives; CFM International S.A. Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2018-18-01 for
all CFM International S.A. (CFM) Model CFM56-7B turbofan engines. AD
2018-18-01 required initial and repetitive inspections of certain fan
blades and, if they fail the inspection, their replacement with parts
eligible for installation. This AD requires the same initial and
repetitive inspections but revises the compliance time for the initial
inspections and revises the installation prohibition based on the
updated compliance time. This AD was prompted by further analysis by
the manufacturer that indicated a need to reduce the initial fan blade
inspection interval based on an ongoing root cause investigation of an
April 2018 engine failure. We are issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective January 10, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 10,
2019.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 14,
2018 (83 FR 19176, May 2, 2018).
We must receive any comments on this AD by February 11, 2019.

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 http://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.
For service information identified in this final rule, contact CFM
International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room
285, Cincinnati, OH, 45125; phone: 877-432-3272; fax: 877-432-3329;
email: aviation.fleetsupport@ge.com. You may view this service
information at the FAA, Engine and Propeller Standards Branch, 1200
District Avenue, Burlington, MA, 01803. For information on the
availability of this material at the FAA, call 781-238-7759. It is also
available on the internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2018-1039.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2018-
1039; 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, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations (phone:
800-647-5527) is listed above. Comments will be available in the AD
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Christopher McGuire, Aerospace
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803;
phone: 781-238-7120; fax: 781-238-7199; email: chris.mcguire@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued AD 2018-18-01, Amendment 39-19380 (83 FR 49272, October
1, 2018), (``AD 2018-18-01''), for all CFM model CFM56-7B turbofan
engines. AD 2018-18-01 required initial and repetitive ultrasonic
inspections (USI) or eddy current inspection (ECI) of certain fan
blades and, if they fail the inspection, their replacement with parts
eligible for installation. AD 2018-18-01 resulted from analysis by the
manufacturer that indicated a need to reduce the repetitive fan blade
inspection interval based on ongoing root cause investigation of an
April 2018 engine failure. The April 2018 engine failure was the result
of a fractured fan blade leading to the engine inlet cowl
disintegrating and debris penetrating the fuselage, causing a loss of
pressurization and prompting an emergency descent. One passenger
fatality occurred as a result. We issued AD 2018-18-01 to reduce the
repetitive inspection interval from 3,000 cycles to 1,600 cycles.

Actions Since AD 2018-18-01 Was Issued

Since we issued AD 2018-18-01, CFM gained a better understanding of
the fan blade failures based on the inspections and further analysis of
the detected cracks and the April 2018 event. As a result, CFM has
published CFM International Service Bulletin (SB) CFM56-7B S/B 72-1033,
Revision 3, dated November 6, 2018, to reduce the initial inspection
requirement from 20,000 cycles since new (CSN) to 17,000 CSN. We are
issuing this AD to address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

We reviewed CFM International SB CFM56-7B S/B 72-1033, Revision 3,
dated November 6, 2018, and Subtask 72-21-01-220-091, of Task 72-21-01-
200-001, from the CFM56-7B Engine Shop Manual (ESM), Revision 57, dated
January 15, 2018. CFM International SB CFM56-7B S/B 72-1033, Revision
3, describes procedures for performing a USI of the affected fan
blades. Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from the
CFM56-7B ESM, describes procedures for performing an ECI of the
affected fan blades. 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.

Other Related Service Information

We also reviewed CFM SB CFM56-7B S/B 72-1019, dated March 24, 2017;
CFM SB CFM56-7B S/B 72-1019, Revision 1, dated June 13, 2017; CFM SB
CFM56-7B S/B 72-1024, dated July 26, 2017; CFM International SB CFM56-
7B S/B 72-1033, Revision 2, dated July 27, 2018; CFM SB CFM56-7B S/B
72-1033, Revision 1, dated May 9, 2018; CFM SB CFM56-7B S/B 72-1033,
dated April 20, 2018; and General Electric Field Support Technology
(FST) Procedure 2370, dated December 9, 2016. These SBs and the FST
provide information on performing the USI.

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 initial and repetitive USI or ECI of certain fan
blades and, if they fail the inspection, their replacement with parts
eligible for installation.

Interim Action

We consider this AD interim action. An investigation to determine
the cause of the failure is ongoing, and we may consider additional
rulemaking if final action is identified.

FAA's Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule.
Due to the reduction in the initial inspection interval, some fan
blades have reached or exceeded the revised initial inspection
threshold and will require inspection within 1,000 cycles after the
effective date of this AD. Because of this, the compliance time for the
required action is shorter than the time necessary for the public to
comment and for the FAA to issue the final rule to ensure the unsafe
condition is addressed. Therefore, we find good cause that notice and
opportunity for prior public comment are impracticable. In addition,
for the reasons stated above, we find 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 final
rule. Send your comments to an address listed under the ADDRESSES
section. Include the docket number FAA-2018-1039 and product identifier
2018-NE-14-AD at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this final rule. We will consider all comments received by
the closing date and may amend this final rule because of those
comments.
We will post all comments we receive, without change, to http://www.
regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this final rule.

Costs of Compliance

We estimate that this AD affects 3,716 engines installed on 1,858
airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Inspection Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Inspect engine fan blade 2 work-hours x $85 per hour = $170
$0
$170
$631,720

We estimate the following costs to complete any necessary
replacement of a single fan blade that would be required based on the
results of the inspection. We have no way of determining the number of
engines that might need fan blades to be replaced.

On-Condition Costs

Action
Labor cost
Parts cost Cost per product
Replace fan blade 1 work-hour x $85 per hour = $85
$51,400
$51,485

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.
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

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

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 removing Airworthiness Directive (AD)
2018-18-01, Amendment 39-19380 (83 FR 49272, October 1, 2018) and
adding the following new AD: