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2019-12-05 CFM INTERNATIONAL S.A.:
Amendment 39-19660; Docket No. FAA-2019-0212; Product Identifier 2019-NE-05-AD.

(a) EFFECTIVE DATE

    This AD is effective July 5, 2019.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to:

(1) CFM International S.A. (CFM)  CFM56-5B1, -5B2, -5B4, -5B5, -5B6, -5B7,
    -5B1/P, -5B2/P, -5B3/P, -5B4/P, -5B5/P, -5B6/P, -5B7/P, -5B8/P,  -5B9/
    P, -5B3/P1, -5B4/P1, -5B1/2P, -5B2/2P, -5B3/2P, -5B4/2P, -5B6/2P, -5B9
    /2P, -5B3/2P1, -5B4/2P1, -7B20, -7B22, -7B24, -7B26, -7B27,  -7B22/B1,
    -7B24/B1, -7B26/B1, -7B26/B2, -7B27/B1,  -7B27/B3,  -7B20/2,  -7B22/2,
    -7B24/2, -7B26/2, -7B27/2, -7B27A model turbofan engines with a:

(i) rotating air high-pressure turbine (HPT) front seal:

(A) with part number (P/N) 1795M36P01 or P/N 1795M36P02 and serial numbers
    (S/Ns) GWNDN949  through GWNSE969  or S/Ns  GWN000CE through GWN0990L,
    not including S/Ns  GWN08ND7, GWN0923A, GWN0971E,  GWN098A1, GWN098W6,
    GWN098W8, GWN098WA, and GWN0990G, installed;

(B) that has been removed from the original HPT disk and re-assembled to a
    different HPT disk; and

(C) that has 6,001 or more cycles since being reconfigured.

(ii) [Reserved]

(2) CFM CFM56-5C2, -5C2/4, -5C2/F, -5C2/F4, -5C2/G, -5C2/G4, -5C2/P, -5C3/
    F, -5C3/F4, -5C3/G, -5C3/G4, -5C3/P,  -5C4,  -5C4/1,  -5C4/P,  -5C4/1P
    model turbofan engines with a:

(i) rotating air HPT front seal:

(A) with  P/N 1795M36P01  or  P/N 1795M36P02  and  S/Ns  GWNDN949  through
    GWNSE969  or  S/Ns  GWN000CE  through  GWN0990L,  not  including  S/Ns
    GWN08ND7, GWN0923A, GWN0971E, GWN098A1, GWN098W6, GWN098W8,  GWN098WA,
    and GWN0990G, installed;

(B) that has been removed from the original HPT disk and re-assembled to a
    different HPT disk; and

(C) that has 3,751 or more cycles since being reconfigured.

(ii) [Reserved]

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 7250, Turbine Section.

(e) UNSAFE CONDITION

    This  AD  was prompted  by cracks found  in the rotating air HPT front
    seal. The FAA is  issuing this AD to  prevent failure of the  rotating
    air HPT  front seal.  The unsafe condition,  if  not addressed,  could
    result in the uncontained release of the rotating air HPT front  seal,
    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) For all affected CFM CFM56-5B and CFM56-7B model turbofan engines:

(i) If, on the effective date of this AD,  the rotating air HPT front seal
    has 7,000 cycles or greater since being reconfigured,  remove the part
    from service within 50 cycles after the effective date of this AD  and
    replace with a part eligible for installation.

(ii) If, on the effective date of this AD, the rotating air HPT front seal
     has between 6,001 and 6,999 cycles, inclusive,  since being reconfig-
     ured, remove the part from service within 500 cycles after the effec-
     tive date of this AD,  but not to exceed 7,050 cycles since being re-
     configured, and replace with a part eligible for installation.

(2) For all affected CFM CFM56-5C model turbofan engines:

(i) If, on the effective date of this AD,  the rotating air HPT front seal
    has 4,250 cycles or greater since being reconfigured, remove the  part
    from service within 25 cycles after the effective date of this AD,  or
    within 1,500  cycles since  the last  fluorescent penetrant inspection
    (FPI) of the rotating air HPT front seal, whichever occurs later,  and
    replace with a part eligible for installation.

(ii) If, on the effective date of this AD, the rotating air HPT front seal
     has between 3,751 and 4,249 cycles, inclusive,  since being reconfig-
     ured, remove the part from service within 250 cycles after the effec-
     tive date of this AD,  before  accumulating 4,275 cycles  since being
     reconfigured, or within 1,500 cycles since the last FPI of the rotat-
     ing air HPT front seal,  whichever occurs later,  and  replace with a
     part eligible for installation.

(h) DEFINITION

    For the purpose of this AD,  reconfigured  is  when a rotating air HPT
    front  seal  has  been  removed from  the  original  HPT disk and  re-
    assembled to a different HPT disk.

(i) 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
    (j) 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.

(j) 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.

(k) MATERIAL INCORPORATED BY REFERENCE

    None.

Issued in Burlington, Massachusetts, on June 14, 2019. Karen M Grant, Act-
ing Manager, Engine and 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-2019-0212; Product Identifier 2019-NE-05-AD; Amendment
39-19660; AD 2019-12-05]
RIN 2120-AA64

Airworthiness Directives; CFM International S.A. Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain CFM International S.A. (CFM) CFM56-5B, CFM56-5C, and CFM56-7B
model turbofan engines with a certain rotating air high-pressure
turbine (HPT) front seal. This AD requires replacement of the affected
rotating air HPT front seal with a part eligible for installation. This
AD was prompted by cracks found in the rotating air HPT front seal. The
FAA is issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective July 5, 2019.
The FAA must receive comments on this AD by August 5, 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-2019-0212.

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-2019-
0212; 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 the Docket Operations 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

The FAA received reports that cracks were found in the rotating air
HPT front seal on CFM56-5B model turbofan engines during a scheduled
shop visit. After further analysis, CFM determined that when a single
rotating air HPT front seal is mated to more than one HPT disk some
seals develop microcracks. These cracks resulted from variations in the
geometry of the parts being mated.
This AD pertains to the highest risk engines and therefore
addresses certain CFM CFM56-5B, CFM56-5C, and CFM56-7B model turbofan
engines with an affected rotating air HPT front seal that has a
specified number of cycles since being reconfigured. The FAA expects to
propose future rulemaking for additional CFM CFM56-5B, CFM56-5C, and
CFM56-7B model turbofan engines with this same rotating air HPT front
seal that have fewer cycles since being reconfigured. These engines
have the same unsafe condition as the engines affected by this AD but
represent a lower safety risk due to the lower number of cycles since
being reconfigured on the affected rotating air HPT front seal.
This condition, if not addressed, could result in the uncontained
release of the rotating air HPT front seal, damage to the engine, and
damage to the airplane. The FAA is issuing this AD to address the
unsafe condition on these products.

Related Service Information

The FAA reviewed CFM Service Bulletin (SB) CFM56-5B S/B 72-1074,
Revision 01, dated December 5, 2018; CFM SB CFM56-5C S/B 72-0794,
Revision 01, dated January 2, 2019; and CFM SB CFM56-7B S/B 72-1042,
Revision 01, dated January 2, 2019. CFM SB CFM56-5B S/B 72-1074,
Revision 01, describes procedures for replacement of the affected
rotating air HPT front seal on CFM CFM56-5B turbofan engines. CFM SB
CFM56-5C S/B 72-0794, Revision 01, describes procedures for replacement
of the affected rotating air HPT front seal on CFM CFM56-5C turbofan
engines. CFM SB CFM56-7B S/B 72-1042, Revision 01, describes procedures
for replacement of the affected rotating air HPT front seal on CFM
CFM56-7B turbofan engines.

FAA's Determination

The FAA is issuing 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.

AD Requirements

This AD requires replacement of the affected rotating air HPT front
seal with a part eligible for installation.

FAA's Justification and Determination of the Effective Date

No domestic operators use the affected higher risk CFM CFM56-5B,
CFM56-5C, and CFM56-7B model turbofan engines. Therefore, the FAA finds
good cause that notice and opportunity for prior public comment
are impracticable. In addition, for the reason stated above, the FAA
finds 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 was not preceded by notice and an opportunity for public
comment. However, the FAA invites 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-2019-
0212 and Product Identifier 2019-NE-05-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
The FAA will post all comments received, without change, to http://www.
regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this final rule.

Regulatory Flexibility Act


The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects no 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
Replace the rotating air HPT front seal. 1 work-hour x $85 per hour = $85
$344,600
$344,685
$0

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

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, and
(2) Will not affect intrastate aviation in Alaska.

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 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):