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ADs updated daily at www.Tdata.com
2020-15-03 GE AVIATION CZECH S.R.O.: Amendment 39-21166; Docket No. FAA-2019-1021; Project Identifier MCAI-2019-00120-E.
(a) EFFECTIVE DATE

    This AD is effective August 31, 2020.

(b) AFFECTED ADS

    This AD replaces AD 2016-07-13, Amendment 39-18458 (81 FR 20222, April
    7, 2016) ("2016-07-13"), and AD 2018-03-22, Amendment 39- 19195 (83 FR
    6455, February 14, 2018) ("2018-03-22").

(c) APPLICABILITY

    This AD applies to all  GE Aviation  Czech s.r.o. M601D-11,  M601E-11,
    M601E-11A, M601E-11AS, M601E-11S, and M601F model turboprop engines.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD  was prompted  by the  discovery of  damage to  certain engine
    power  turbine  (PT)  disks  and a  review  by  the  manufacturer that
    determined that certain  engine PT rotors  have less overspeed  margin
    than originally  declared during  product certification.  This AD  was
    also prompted by the manufacturer identifying additional part  numbers
    (P/Ns) and serial numbers (S/Ns) of engine PT disks affected by damage
    or non-conformity  since publishing  AD 2016-07-13  and AD 2018-03-22.
    The FAA is issuing  this AD to prevent  failure of the engine  PT disk
    and rotor.  The unsafe  condition, if  not addressed,  could result in
    uncontained release  of the  engine PT  disk and  rotor, 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 Group  1 engines: Before  the affected engine  PT disk accumulates
    the number  of cycles  since new  as specified  in Attachment  B of GE
    Aviation  Alert  Service  Bulletin  (ASB) ASB-M601E-72-50-00-0069[02],
    ASB-M601D-72-50-00-0052[02],  ASB-M601T-72-50-00-0028[02],   ASB-M601F
    -72-50-00-0035[02], and ASB-M601Z-72-50-00-0038[02] (single  document;
    formatted as service bulletin identifier[revision number]), dated June
    11, 2019  ("the ASB"),  or at  the next  engine shop  visit, whichever
    occurs first  after the  effective date  of this  AD, perform a visual
    inspection,   dimensional   inspection,   and   fluorescent  penetrant
    inspection  on  the  affected  engine  PT  disk  using  Attachment  G,
    Inspection Instruction, of the ASB.

(2) If, during  the inspections required  by paragraph (g)(1)  of this AD,
    any damage is detected, or a non-conforming slot radius is found  that
    exceeds the acceptability criteria as defined in Table 1--PT Disc  P/N
    M601-3220.5  inspection  limits  of the  ASB,  before  further flight,
    remove the affected engine PT disk from service and replace it with  a
    part  eligible  for  installation  using  Attachment  F,   Replacement
    Instruction, of the ASB.

(3) For Group 2 engines: Within the compliance time identified in Table  1
    to paragraph  (g)(3) of  this AD,  modify the  engine by  removing the
    affected engine  PT disk  from service  and replacing  it with  a part
    eligible for installation using Attachment F, Replacement Instruction,
    of the ASB.

         TABLE 1 TO PARAGRAPH (G)(3)  COMPLIANCE TIME REQUIREMENTS
                         FOR GROUP 2 ENGINES
    ______________________________________________________________________
    COMPLIANCE TIME (A, B, C, D, or E, Whichever occurs first after the
    effective date of this AD)
    ______________________________________________________________________
    A   Before the engine exceeds the Time Between Overhaul (TBO) cycle
        limit specified in the Applicable Engine Maintenance Manual (EMM).
    B   Before the engine PT disk accumulates the number of cycles since
        overhaul as specified in Attachment D of the ASB.
    C   Before the engine PT disk accumulates the number of cycles since
        new as specified in Attachment D of the ASB.
    D   Within 180 days.
    E   During the next shop visit (engine overhaul or rebuild), or within
        five years after March 21, 2018 (the effective date of AD 2018-03-
        22), whichever occurs first.
    ______________________________________________________________________

(4) For  Group 3  engines: Within  five years  after March  21, 2018  (the
    effective date of AD 2018-03-22), or during the next engine shop visit
    after the effective  date of this  AD, whichever occurs  first, remove
    the affected engine PT  disk from service and  replace it with a  part
    eligible for installation using Attachment F, Replacement Instruction,
    of the ASB.

(h) DEFINITIONS

(1) For the purpose of  this AD, a Group 1  engine is a GE Aviation  Czech
    s.r.o. turboprop  engine that  has an  engine PT  disk having P/N M601
    -3220.5  and  S/N 407560-158,  407560-164,  406380-196 or  407560-190,
    installed.

(2) For the purpose of  this AD, a Group 2  engine is a GE Aviation  Czech
    s.r.o. turboprop  engine that  has an  engine PT  disk having P/N M601
    -3220.6 or P/N M601-3220.7,  and a S/N listed  in Attachment C of  the
    ASB, installed.

(3) For the purpose of  this AD, a Group 3  engine is a GE Aviation  Czech
    s.r.o. turboprop  engine that  has an  engine PT  disk having P/N M601
    -3220.6 or P/N M601-3220.7, and any S/N not listed in Attachment C  of
    the ASB, installed.

(4) For the purpose of this  AD, an "affected engine PT disk" is an engine
    PT disk having P/N M601-3220.5 and S/N 407560-158, 407560-164,  406380
    -196 or 407560-190, except those that passed an inspection (no defects
    detected) using Attachment G,  Inspection Instruction, of the  ASB. An
    "affected engine PT disk"  is also an engine  PT disk having P/N  M601
    -3220.6 or M601-3220.7.

(i) CREDIT FOR PREVIOUS ACTIONS

    You  may  take  credit  for the  inspections  and  replacement  of the
    affected engine PT disk that are required by paragraph (g) of this  AD
    if you performed the inspections and replacement before the  effective
    date of this AD using the ASB, Revision 01 or the original issue.

(j) NO REPORTING REQUIREMENT

    The   reporting   requirements  in   the   Attachment  G,   Inspection
    Instruction, of the ASB, are not required by this AD.

(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 ECO Branch, send
    it to the  attention of the  person identified in  paragraph (l)(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
    inspector, or lacking a principal inspector, the manager of the  local
    flight standards district office/certificate holding district office.

(l) RELATED INFORMATION

(1) For more  information about this  AD, contact Mehdi  Lamnyi, Aerospace
    Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
    phone: 781-238-7743; fax: 781-238-7199; email: Mehdi.Lamnyi@faa.gov.

(2) Refer to  European Union Aviation  Safety Agency (EASA)  AD 2019-0143,
    dated June 13, 2019, for more information. You may examine the EASA AD
    in the  AD docket  on the  internet at  https://www.regulations.gov by
    searching for and locating Docket No. FAA- 2019-1021.

(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.

(i) GE Aviation Alert Service Bulletin (ASB)  ASB-M601E-72-50-00-0069[02],
    ASB-M601D-72-50-00-0052[02],  ASB-M601T-72-50-00-0028[02],   ASB-M601F
    -72-50-00-0035[02], and ASB-M601Z-72-50-00-0038[02] (single  document;
    formatted as service bulletin identifier[revision number]), dated June
    11, 2019.

(ii) [Reserved]

(3) For GE Aviation Czech service information identified in this AD,  con-
    tact GE Aviation Czech s.r.o.,  Beranovych 65, 199 02 Praha 9-Letnany,
    Czech Republic; phone: +420 222 538 111;  fax +420 222 538 222; email:
    tp.ops@ge.com.

(4) You may view this  service information at 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 781-238-7759.

(5) You may view this  service information that is  incorporated by refer-
    ence at the National  Archives and Records Administration  (NARA). For
    information  on  the availability  of  this material  at  NARA, email:
    fedreg.legal@nara.gov,  or  go  to:   https://www.archives.gov/federal
    -register/cfr/ibr-locations.html.

Issued on July 9, 2020. Lance T Gant, Director, Compliance & Airworthiness
Division, Aircraft Certification Service.

FOR FURTHER  INFORMATION CONTACT:  Mehdi Lamnyi,  Aerospace Engineer,  ECO
Branch, FAA, 1200  District Avenue, Burlington,  MA 01803; phone:  781-238
-7743; fax: 781-238-7199; email: Mehdi.Lamnyi@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration


14 CFR Part 39

[Docket No. FAA-2019-1021; Project Identifier MCAI-2019-00120-E;
Amendment 39-21166; AD 2020-15-03]
RIN 2120-AA64

Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-07-13
and AD 2018-03-22 which apply to certain GE Aviation Czech s.r.o.
M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, and M601F model
turboprop engines. AD 2016-07-13 required inspection of the engine
power turbine (PT) disk and, if found damaged, its replacement with a
part eligible for installation. AD 2018-03-22 required the removal of
certain engine PT disks identified by part number (P/N) installed on
the affected engines. This AD requires an inspection of the engine PT
disk and, if found damaged, its replacement with a part eligible for
installation. This AD also requires the removal of certain engine PT
disks identified by P/N installed on the affected engines. This AD was
prompted by the discovery of damage to certain engine PT disks and a
review by the manufacturer that determined that certain engine PT
rotors have less overspeed margin than originally declared during
product certification. This AD was also prompted by the manufacturer
identifying additional P/Ns and serial numbers (S/Ns) of engine PT
disks affected by damage or non-conformity since publishing AD 2016-07-
13 and AD 2018-03-22. The FAA is issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective August 31, 2020.

The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 31, 2020.

ADDRESSES: For service information identified in this final rule,
contact GE Aviation Czech s.r.o., Beranovych 65, 199 02 Praha
9--Letnany, Czech Republic; phone: +420 222 538 111; fax +420
222 538 222; email: tp.ops@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 781-
238-7759. It is also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2019-1021.

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-
1021; 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 mandatory continuing airworthiness information
(MCAI), any comments received, and other information. The address for
Docket Operations is U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7743; fax: 781-238-7199; email: Mehdi.Lamnyi@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion


The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2016-07-13, Amendment 39-18458 (81 FR
20222, April 7, 2016) ("AD 2016-07-13"), and AD 2018-03-22, Amendment
39-19195 (83 FR 6455, February 14, 2018) ("AD 2018-03-22"). AD 2016-
07-13 and AD 2018-03-22 applied to certain GE Aviation Czech s.r.o.
M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, and M601F model
turboprop engines. The NPRM published in the Federal Register on
February 21, 2020 (85 FR 10099). The NPRM was prompted by the discovery
of damage to certain engine PT disks and a review by the manufacturer
that determined that certain engine PT rotors have less overspeed
margin than originally declared during product certification. The NPRM
was also prompted by the manufacturer
identifying additional P/Ns and S/Ns of engine PT disks affected by
damage or non-conformity since publishing AD 2016-07-13 and AD 2018-03-
22. The NPRM proposed to require an inspection of the engine PT disk
and, if found damaged, its replacement with a part eligible for
installation. The NPRM also proposed to require the removal of certain
engine PT disks identified by P/N installed on the affected engines.
The FAA is issuing this AD to address the unsafe condition on these
products.

The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA AD 2019-0143, dated June 13, 2019 (referred to after this
as "the MCAI"), to address the unsafe condition on these products.
The MCAI states:

During engine shop visits or overhauls, certain PT discs may
have been damaged in the area of the balance weights. Additional PT
discs with non-conforming geometry of the slot radius may also have
been released to service as a result of incorrect machining of the
PT disc slot.

This condition, if not detected and corrected, could lead to PT
disc failure, with subsequent release of high-energy debris,
possibly resulting in damage to, and/or reduced control of, the
aeroplane.

After [EASA] ADs [2016-0025-E and 2017-0100] were issued, GEAC
identified additional P/N and s/n of PT discs affected by damage or
non-conformity. For those, as well as for the PT discs affected by
the reduction of the declared theoretical PT rotor overspeed limit,
an update of the risk assessment was performed, and GEAC issued the
original issue of the ASB, later revised, providing applicable
instructions.

Consequently, EASA issued AD 2019-0061, retaining the
requirements of EASA AD 2016-0025-E and EASA AD 2017-0100, which
were superseded, and requiring a one-time inspection and, depending
on findings, replacement of certain PT discs identified by P/N and
s/n. That [EASA] AD also required replacement of certain PT discs
identified by P/N, and prohibited (re)installation of affected
parts.

Since that [EASA] AD was issued, it has been determined that the
compliance time for replacement of affected part on Group 2 engines
has to be amended, and GEAC published the ASB (now at Revision 02).

For the reason stated above, this [EASA] AD retains the
requirements of EASA AD 2019-0061, which is superseded, introducing
amended compliance times for Group 2 engines.

You may obtain further information by examining the MCAI in the AD
docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2019-1021.

Comments


The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.

Conclusion


The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this AD as proposed except for
minor editorial changes. The FAA has determined that these minor
changes.

Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and

Do not add any additional burden upon the public than was
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51


The FAA reviewed GE Aviation Alert Service Bulletin (ASB) ASB-
M601E-72-50-00-0069[02], ASB-M601D-72-50-00-0052[02], ASB-M601T-72-50-
00-0028[02], ASB-M601F-72-50-00-0035[02], and ASB-M601Z-72-50-00-
0038[02] (single document; formatted as service bulletin
identifier[revision number]), dated June 11, 2019. The ASB provides
procedures for replacing the engine PT disk. 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.

Costs of Compliance


The FAA estimates that this AD affects 24 GE Aviation Czech s.r.o.
M601 turboprop engines installed on airplanes of U.S. registry. The FAA
estimates that 12 affected turboprop engines are "Group 1" engines
and 12 are "Group 2" engines.
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
Inspect the engine PT disk (Group 1 engines). 52 work-hours x $85 perhour = $4,420.
$0
$4,420
$53,040
Replace the engine PT disk (Group 2 and 3 engines). 56 work-hours x $85 per hour = $4,760.
6,989
11,749
140,988

The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
required inspections. The FAA has no way of determining the number of
engines that might need this replacement:

On-Condition Costs

ACTION
LABOR COST
PARTS COST
COST PER
PRODUCT
Replace the engine PT disk (Group 1 engines) 8 work-hours x $85 per hour = $680.
$6,989
$7,669

g to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. The FAA does not control warranty coverage for affected
individuals. As a result, the FAA has included all costs in its cost
estimate.

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


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 this AD:

(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.

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:

a. Removing Airworthiness Directive (AD) 2016-07-13, Amendment 39-18458
(81 FR 20222, April 7, 2016), and AD 2018-03-22, Amendment 39-19195 (83
FR 6455, February 14, 2018); and

b. Adding the following new AD: