preamble attached >>>
ADs updated daily at www.Tdata.com
2018-10-11 CFM INTERNATIONAL S.A.:
Amendment 39-19286; Docket No. FAA-2018-0443; Product Identifier 2018-NE-14-AD.

(a) EFFECTIVE DATE

    This AD is effective June 1, 2018.

(b) AFFECTED ADS

    This AD replaces AD 2018-09-10,  Amendment 39-19267  (83 FR 19176, May
    2, 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
    engine models.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD was  prompted by a  recent engine failure  due to a  fan blade
    fracture 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 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 al-
    ready 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) Within 30 days after the effective date of this AD, perform an initial
    inspection of the fan blades identified using the criteria in Planning
    Information,  either  paragraph 1.C.2.(a), 1.C.2.(b), or 1.C.2.(c), of
    CFM Service Bulletin (SB) CFM56-7B S/B 72-1033, Revision 01, dated May
    9, 2018.

(ii) For all fan blades not inspected in accordance  with paragraph (g)(1)
     (i) of this AD, perform  an initial inspection prior to  accumulating
     20,000 flight  cycles on  the fan  blade or  within 90  days from the
     effective date of this AD, whichever occurs later.

(iii) Thereafter,  repeat this inspection no later than 3,000 cycles since
      the last inspection.

(iv) Use  the  Accomplishment Instructions,  paragraphs 3.A.(3)(a) through
     (i), of CFM SB CFM56-7B S/B 72-1033, Revision 01,  dated May 9, 2018,
     to perform a USI or use the instructions 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)(iv)  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 20,000 cycles since new, or;

(2) The replacement fan blade has been inspected  in accordance with para-
    graph (g) of this AD.

(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 previous-
    ly 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

(1) You may take credit for the USI required by paragraph (g)  of this AD,
    if those actions were performed  before  the effective date of this AD
    using CFM SB CFM56-7B S/B 72-1019, dated March 24, 2017; or Revision 1
    dated June 13, 2017;  or  CFM SB CFM56-7B S/B 72-1024,  dated July 26,
    2017; CFM SB CFM56-7B S/B 72-1033,  dated April 20, 2018;  or  General
    Electric Field Support Technology  procedure 2370,  dated  December 9,
    2016.

(2) You may take credit for an ECI using the instructions in Subtask 72-21
    -01-220-091,  of Task 72-21-01-200-001,  from the 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 in-
    spector 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, includ-
     ing substeps and identified figures,  can still be done as specified,
     and the airplane can be put back in an airworthy condition.

(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 June 1, 2018

(i) CFM Service Bulletin (SB) CFM56-7B S/B 72-1033, Revision 01, dated May
    9, 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, Policy and Innovation Division, 1200 District Avenue
    Burlington, MA.  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  May 15, 2018.  Robert J. Ganley,
Manager,  Engine  &  Propeller  Standards  Branch,  Aircraft Certification
Service.

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-2018-0443; Product Identifier 2018-NE-14-AD; Amendment
39-19286; AD 2018-10-11]
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) 2018-09-10 for
all CFM International S.A. (CFM) Model CFM56-7B engines. AD 2018-09-10
required initial and repetitive inspections of the concave and convex
sides of the fan blade dovetail to detect cracking and replacement of
any blades found cracked. This AD requires the same initial and
repetitive inspections but revises the compliance time for the initial
inspections of certain higher-risk fan blades. This AD was prompted by
a recent engine failure due to a fractured fan blade that resulted in
the engine inlet cowl disintegrating and debris penetrating the
fuselage, causing a loss of pressurization, and prompting an emergency
descent. We are issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective June 1, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 1,
2018.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of May
14, 2018 (83 FR 19176, May 2, 2018).
We must receive any comments on this AD by July 2, 2018.

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. 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-2018-0443.

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-
0443; 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 2018-09-10, Amendment 39-19267 (83 FR 19176, May 2,
2018), (``AD 2018-09-10''), for all CFM model CFM56-7B engines. AD
2018-09-10 required initial and repetitive inspections of the concave
and convex sides of the fan blade dovetail to detect cracking and
replacement of any blades found cracked. AD 2018-09-10 resulted from a
recent event involving an engine failure due to 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 2018-09-10 to prevent failure of the fan blade due to
cracking, which could lead to an engine in-flight shutdown (IFSD),
uncontained release of debris, damage to the airplane, and possible
airplane decompression.

Actions Since AD 2018-09-10 Was Issued

Since we issued AD 2018-09-10, an investigation of this event has
determined new methods for identifying applicable parts as well as the
need to reduce the compliance time for certain fan blades. Therefore,
this AD requires inspection of higher risk fan blades, identified using
one of the methods in CFM Service Bulletin (SB) CFM56-7B S/B 72-1033,
Revision 01, dated May 9, 2018, within 30 days from the effective date
of the AD. The remaining fan blades must be inspected within 90 days
from the effective date of the AD or prior to accumulating 20,000
flight cycles. We are issuing this AD to address the unsafe condition
on these products.

Related Service Information Under 1 CFR Part 51

We reviewed CFM SB CFM56-7B S/B 72-1033, Revision 01, dated May 9,
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 SB CFM56-7B S/B 72-1033, Revision 01, describes procedures for
performing an ultrasonic inspection (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 eddy current inspection
(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,
and Revision 1, dated June 13, 2017; CFM SB CFM56-7B S/B 72-1024, dated
July 26, 2017; and 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 ultrasonic or eddy current
inspection of certain fan blades and, if they fail the inspection,
their replacement with parts eligible for installation.

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
because certain fan blades must be inspected, and, if needed, replaced
before further flight. Failure to inspect and replace these parts
within the required compliance times could lead to failure of the fan
blades, engine IFSD, uncontained release of debris, damage to the
airplane, and possible airplane decompression. 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-2018-0443 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
airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated 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 do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:

On-Condition Costs

Action Labor cost Parts cost Cost per product
Replace fan blade 1 work-hour x $85 per hour = $85 $8,500 $8,585

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.

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)
2018-09-10, Amendment 39-19267 (83 FR 19176, May 2, 2018) and adding
the following new AD: