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2021-20-21 GE AVIATION CZECH S.R.O. (TYPE CERTIFICATE PREVIOUSLY HELD BY WALTER ENGINES A.S., WALTER A.S., AND MOTORLET A.S.): Amendment 39-21759; Docket No. FAA-2021-0836; Project Identifier MCAI-2020-01629-E.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective November 18, 2021.

(b) AFFECTED ADS

    This AD replaces AD 2018-16-10, Amendment 39-19350(83 FR 43742, August
    28, 2018) (AD 2018-16-10).

(c) APPLICABILITY

    This AD applies to:

(1) GE Aviation Czech s.r.o.  (GEAC)  H80-200 model turboprop engines with
    propeller governor part number (P/N) P-W22-1 and Avia Propeller AV-725
    propellers installed.

(2) GEAC H85-200 model turboprop engines  (build configuration BC04)  with
    Avia Propeller AV-725 propellers installed.

(d) SUBJECT

    Joint Aircraft  System Component  (JASC) Code  7600, Engine  Controls;
    6122, Propeller Governor.

(e) UNSAFE CONDITION

    This AD was prompted by an accident involving an Aircraft Industries L
    410  UVP-E20 airplane  caused  by  one propeller  going to  a negative
    thrust position during the landing  approach. The FAA is issuing  this
    AD  to  prevent  asymmetric  thrust.  The  unsafe  condition,  if  not
    addressed, could result in failure of the beta switch, loss of  engine
    thrust control, and reduced control of the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

(1) For Group 1 engines:  Within 25 flight hours (FHs) or 20 flight cycles
    after September 12, 2018 (the effective date of AD 2018-16-10), or be-
    fore further flight,  whichever occurs later,  inspect  and adjust the
    engine push-pull control,  P/N M601-76.3, and replace beta switch, P/N
    P-S-2, with beta switch,  P/N P-S-2A,  using paragraphs 1.6 and 1.7 of
    GEAC Service Bulletin  (SB)  SB-H80-76-00-00-0036 [03],  (formatted as
    service bulletin identifier [revision number]),  dated  April 12, 2019
    (GEAC SB SB-H80-76-00-00-0036 [03])  or paragraphs 1.6 and 1.7 of GEAC
    SB-H80-76-00-00-0036 [02], Revision No. 02, dated March 29, 2018.

(2) For Group 1, Group 2, and Group 3 engines: Before further flight after
    any maintenance, repair,  or modification on the engine, propeller, or
    airplane that can affect the settings  of the engine push-pull control
    after the effective date of this AD,  inspect  and  adjust  the engine
    push-pull control,  P/N M601-76.3,  using  paragraph 1.6 of GEAC Alert
    Service Bulletin (ASB) ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-0015
    [01] (single document,  formatted as service bulletin identifier  [re-
    vision number]), dated April 12, 2019  (GEAC ASB ASB-H80-76-00-00-0048
    [01]/ASB-H85-76-00-00-0015 [01]).

(3) For Group 1, Group 2, and Group 3 engines:  Within 270 days  after the
    effective date of this AD,  replace the engine push-pull control,  P/N
    M601-76.3,  with  engine push-pull control  P/N M601-76.4 or P/N M601-
    76.5, as applicable to the engine model,  using Appendix 1 of GEAC ASB
    ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00-0018[04]  (single document,
    formatted as service bulletin identifier [revision number]), dated May
    8, 2020 (GEAC ASB ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00-0018[04])

(4) For engines modified as required by paragraph (g)(3) of this AD: With-
    in 100 FHs or during a subsequent Type 2 inspection,  whichever occurs
    first after the engine modification  required  by  paragraph (g)(3) of
    this AD,  and thereafter,  at intervals not to exceed 100 FHs from the
    previous inspection,  inspect the engine push-pull control,  P/N M601-
    76.4 or P/N M601-76.5,  using  the  Accomplishment Instructions, para-
    graph 2.1.2,  of  GEAC ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00-0018
    [04].

Note 1 to paragraph (g)(4):  A non-cumulative tolerance  of 10 FH  may  be
applied to the 100 FH repetitive inspection interval to allow synchroniza-
tion of the required checks  with  other  required  maintenance tasks  for
which a non-cumulative tolerance is already granted  in the applicable en-
gine maintenance manual (EMM).

(5) For all affected engines  not required to be modified  as specified in
    paragraph (g)(3) of this AD:  Within 300 FHs or at the next Type 3 in-
    spection,  whichever occurs later  since first installation of the en-
    gine on an airplane,  inspect the engine push-pull control,  P/N M601-
    76.4 or P/N M601-76.5, as applicable,  using the instructions in Table
    601 (Sheet 1-4) of Section 72-00-00,  dated December 14, 2012,  of the
    GE Aviation-Business & General Aviation-Turboprops Maintenance Manual,
    Manual Part No. 0983402, Rev. 22, dated December 18, 2020 (the GE Avi-
    ation Maintenance Manual).

(6) If, during any inspection  required by paragraph (g)(1) or (2) of this
    AD, as applicable, any deficiencies are detected,  before next flight,
    perform the actions  in  paragraphs 1.6.2, 1.7.1 and 1.7.2  of GEAC SB
    SB-H80-76-00-00-0036 [03] or paragraph 1.6.1 of GEAC ASB ASB-H80-76-00
    -00-0048[01]/ASB-H85-76-00-00-0015 [01], as applicable.

(7) If, during any inspection required by paragraph (g)(4) of this AD, any
    deficiencies are detected, before next flight,  perform the actions in
    paragraph 2.1.2 of GEAC ASB ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-00
    -0018[04].

(8) If, during the inspection as required by paragraph (g)(5)  of this AD,
    any deficiencies are detected,  before next flight,  correct those de-
    ficiencies using the instructions in Table 601 (Sheet 1-4), Section 72
    -00-00, Engine-Planned Inspections, dated December 14, 2012, of the GE
    Aviation Maintenance Manual.

(h) INSTALLATION PROHIBITION

    After the effective date of this AD:

(1) For Group 1 engines: Do not install a beta switch,  P/N P-S-2,  on any
    engine,  after modification of the engine as required by paragraph (g)
    (1) of this AD.

(2) For Group 2, Group 3, Group 4, and Group 5 engines:  Do not  install a
    beta switch, P/N P-S-2, on any engine.

(3) For Group 1, Group 2, and Group 3 engines:  Do not  install  an engine
    push-pull control, P/N M601-76.3,  on any engine after modification of
    the engine as required by paragraph (g)(3) of this AD.

(i) TERMINATING ACTION

    Accomplishing the inspection of the engine push-pull control, P/N M601
    -76.4 or P/N M601-76.5,  as  required  by paragraph (g)(4) of this AD,
    without finding  any deficiencies  during six consecutive inspections,
    constitutes a terminating action  for  the  repetitive inspections re-
    quired by paragraph (g)(4) of this AD for that engine.

(j) NO COMMUNICATION OR REPORTING REQUIREMENTS

    The instructions to contact the manufacturer  for further instructions
    in paragraph 2.1, of GEAC ASB ASB-H80-76-00-00-0047[04]/ASB-H85-76-00-
    00-0018[04], are not required by this AD.

(k) DEFINITIONS

(1) Group 1 engines are GEAC H80-200 model turboprop engines  that have an
    engine push-pull control, P/N M601-76.3, and a beta switch, P/N P-S-2,
    installed.

(2) Group 2 engines are GEAC H80-200 model turboprop engines  that have an
    engine push-pull control, P/N M601-76.3, but no beta switch, P/N P-S-2
    installed.

(3) Group 3 engines are GEAC H85-200 model turboprop engines (build config
    -uration BC04)  that have an engine push-pull control,  P/N M601-76.3,
    installed.

(4) Group 4 engines are GEAC H80-200 model turboprop engines  that have an
    engine push-pull control, P/N M601-76.5, installed.

(5) Group 5 engines are GEAC H85-200 model  turboprop engines  (build con-
    figuration BC04) that have an engine push-pull control, P/N M601-76.4,
    installed.

(6) For the purpose of this AD,  "deficiencies"  occur  when the push-pull
    control settings are changed, thereby allowing the propeller to go be-
    yond fine pitch into negative thrust position  during  certain  engine
    failure modes.

(l) CREDIT FOR PREVIOUS ACTIONS

(1) You may take credit  for the inspection  and  adjustment of the engine
    push-pull control  required by paragraph (g)(2) of this AD if you per-
    formed the actions before the effective date of this AD using GEAC ASB
    -H80-76-00-00-0048[00] / ASB-H85-76-00-00-0015[00]  (single document),
    dated April 12, 2019.

(2) You may take credit  for the installation of the engine push-pull con-
    trol required by paragraph (g)(3) of this AD  and  the initial inspec-
    tion of the engine push-pull control required  by paragraph (g)(4)  of
    this AD,  if you performed these actions  before the effective date of
    this AD using GEAC ASB ASB-H80-76-00-00-0047[03]/ASB-H85-76-00-00-0018
    [03]  (single document),  Revision No. 03,  dated  August 7, 2019,  or
    earlier revisions.

(m) 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 ECO Branch, send it
    to the attention of the person identified  in paragraph (n)(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.

(n) RELATED INFORMATION

(1) For more information about this AD, contact Barbara Caufield, Aviation
    Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA
    01803;  phone: (781) 238-7146;  fax: (781) 238-7199;  email:  barbara.
    caufield@faa.gov.

(2) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD
    2020-0143, dated June 25, 2020, for related information. This MCAI may
    be found in the AD docket at https://www.regulations.gov  by searching
    for and locating Docket No. FAA-2021-0836.

(o) 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 Czech (GEAC)  Service Bulletin  (SB)  SB-H80-76-00-00-0036
    [02], Revision No. 02, dated March 29, 2018.

(ii) GEAC SB SB-H80-76-00-00-0036 [03],  Revision No. 03,  dated April 12,
     2019.

(iii) GEAC Alert SB ASB-H80-76-00-00-0048[01] / ASB-H85-76-00-00-0015 [01]
      (single document), Revision No. 01, dated April 12, 2019.

(iv) GEAC Alert SB  ASB-H80-76-00-00-0047[04] / ASB-H85-76-00-00-0018 [04]
     (single document), Revision No. 04, dated May 8, 2020.

(v) Section 72-00-00, pages 603 through 605,  dated December 14, 2012; and
    page 606,  dated December 18, 2020,  of GE Aviation Business & General
    Aviation-Turboprops Maintenance Manual,  Manual Part No. 0983402, Rev.
    22, dated December 18, 2020.

(3) For GEAC and GE Aviation  service information  identified  in this AD,
    contact GE Aviation Czech s.r.o.,  Beranovych 65, 199 02 Praha 9, Let-
    nany, Czech Republic; phone: +420 222 538 111.

(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: fr.
    inspection@nara.gov,   or   go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on September 23, 2021.  Lance T. Gant,  Director, Compliance & Air-
worthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT:  Barbara Caufield,  Aviation Safety Engi-
neer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;  phone:
(781) 238-7146; fax: (781) 238-7199; email: barbara.caufield@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0836; Project Identifier MCAI-2020-01629-E;
Amendment 39-21759; AD 2021-20-21]
RIN 2120-AA64

Airworthiness Directives; GE Aviation Czech s.r.o. (Type
Certificate Previously Held by WALTER Engines a.s., Walter a.s., and
MOTORLET a.s.) Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-16-10
which applied to certain GE Aviation Czech s.r.o. (GEAC) H80-200 model
turboprop engines. AD 2018-16-10 required an adjustment of the engine
push-pull control and replacement of the beta switch to prevent the
propeller governor control from going to a negative thrust position.
This AD requires an initial inspection and adjustment of the engine
push-pull control and replacement of the beta switch. This AD also
requires inspection and adjustment of the engine push-pull control
after any maintenance, repair or modification that affects the push-
pull control and installation of an improved push-pull control. This AD
also expands the applicability to include GEAC H85-200 model turboprop
engines with Avia Propeller AV-725 propellers installed. This AD was
prompted by an accident involving an Aircraft Industries (AI) L 410
UVP-E20 airplane caused by one propeller going to a negative thrust
position during the landing approach. The FAA is issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective November 18, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 18,
2021.
The FAA must receive any comments on this AD by December 20, 2021.

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 final rule, contact GE
Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9,
Let[ncaron]any, Czech Republic; phone: +420 222 538 111. 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 at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0836.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0836; 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 street address for the Docket
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone: (781) 238-7146; fax: (781) 238-7199; email:
barbara.caufield@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued AD 2018-16-10, Amendment 39-19350 (83 FR 43742,
August 28, 2018) (AD 2018-16-10), for certain GE Aviation Czech H80-200
model turboprop engines. AD 2018-16-10 required replacement of the beta
switch and adjustment of the engine push-pull control to prevent the
propeller governor control from going to a negative thrust position. AD
2018-16-10 resulted from an accident involving an AI L 410 UVP-E20
airplane caused by one propeller going to a negative thrust position
during the landing approach. The FAA issued AD 2018-16-10 to require
engine modification to prevent asymmetric thrust. The unsafe condition,
if not addressed, could result in failure of the beta switch, loss of
engine thrust control, and reduced control of the airplane.

Actions Since AD 2018-16-10 Was Issued

Since the FAA issued AD 2018-16-10, the European Union Aviation
Safety Agency (EASA), which is the Technical Agent for the Member
States of the European Community, has issued EASA AD 2020-0143, dated
June 25, 2020, to address an unsafe condition for the specified
products. The MCAI states:

In 2017, a fatal accident was reported of an L 410 UVP-E20
aeroplane. The investigation determined that there was an
annunciation of Beta mode on the right-hand engine, that the
propeller went inadvertently beyond the fine pitch position and
reached a negative thrust position, and that the pitch lock system
did not intervene. The event occurred on approach at a speed and
altitude which did not allow the flight crew to recover this control
system malfunction.
This condition, if not corrected, could lead to reduced control
or loss of control of the aeroplane.
To address this unsafe condition, GEAC issued the SB, providing
inspection and modification instructions, and EASA issued AD 2018-
0075 to require a one-time inspection and adjustment of the engine
push-pull control and replacement of the beta switch with an
improved part. Addressing the same unsafe condition at aeroplane
level, EASA also issued AD 2018-0057, requiring modification of
affected AI L 410 UVP-E20 and L 410 UVP-E20 CARGO aeroplanes, if
equipped with H80-200 engines and Avia Propeller AV 725 propellers.
After EASA AD 2018-0075 was issued, it was identified that the
engine push-pull control settings may be inadvertently changed after
certain maintenance, repair, or modification action. For that
reason, the engine push-pull control needed further inspection and
adjustment. Affected maintenance, repair, or modification procedures
include, but are not limited to, the replacement of a fuel control
unit or a propeller governor. Furthermore, it was determined that
H85-200 engines are also affected by the new requirements.
Consequently, EASA issued AD 2019-0089, retaining the requirements
of EASA AD 2018-0075, which was superseded, and requiring
conditional repetitive inspections and, depending on findings,
adjustment of the push-pull control settings. That [EASA] AD also
expanded the applicability to include H85-200 engines.
After EASA AD 2019-0089 was issued, GEAC developed an improved
engine push-pull control which reduces further the risk of
uncommanded in-flight reverse of the propeller, and published the
original issue of the ASB-2. Consequently, EASA issued AD 2019-0244,
retaining the requirements of EASA AD 2019-0089, which was
superseded, and requiring installation of the new engine push-pull
controls. That [EASA] AD also required inspections of modified
engines.
Since that [EASA] AD was issued, based on the field experience
gained from the inspections and replacements of Push-Pull Control
System performed in accordance with the ASB-2 revision 03, GEAC
issued the ASB-2 (now at revision 04), as defined in this [EASA] AD,
which provides additional clarifications and more accurate
description of the adjustments of the controls and regulation and
engine testing after hardware replacement. The ASB-2 also improves
the sequence of steps, thus helping to prevent erroneous
accomplishment of the inspection and modification instructions. It
has also been determined that for certain engines no repetitive
inspections are required.
For the reason described above, this [EASA] AD partially retains
the requirements of EASA AD 2019-0244, which is superseded, but
requires accomplishment of required actions in accordance with the
improved GEAC instructions.

You may obtain further information by examining the MCAI in the AD
docket at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0836.
The FAA is issuing this AD to address the unsafe condition on these
products.

FAA's Determination

This product has been approved by EASA and is approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Community, EASA has notified us of the
unsafe condition described in the MCAI. The FAA is issuing this AD
because the agency evaluated the relevant information provided by EASA
and determined the unsafe condition described previously is likely to
exist or develop in other products of the same type design.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GEAC Service Bulletin (SB) SB-H80-76-00-00-0036
[02], Revision No. 02, dated March 29, 2018; GEAC SB SB-H80-76-00-00-
0036 [03], Revision No. 03, dated April 12, 2019; and GEAC Alert SB
ASB-H80-76-00-00-0048[01]/ASB-H85-76-00-00-0015 [01] (single document,
formatted as service bulletin identifier [revision number]), dated
April 12, 2019. The SBs and the Alert SB, differentiated by affected
engine model, describe procedures for inspecting and adjusting the
engine push-pull control, part number (P/N) M601-76.3. The SBs also
describe procedures for replacing beta switch, P/N P-S-2, with beta
switch, P/N P-S-2A. The Alert SB also adds GEAC H85-200 model turboprop
engines to its effectivity.
The FAA also reviewed GEAC Alert SB ASB-H80-76-00-00-0047[04]/ASB-
H85-76-00-00-0018[04] (single document, formatted as service bulletin
identifier [revision number]), dated May 8, 2020. The Alert SB
describes procedures for replacing and inspecting the engine push-pull
control system.
The FAA also reviewed Section 72-00-00, Engine--Planned
Inspections, dated December 14, 2012; of the GE Aviation--Business &
General Aviation--Turboprops Maintenance Manual, Manual Part No.
0983402, Rev. 22, dated December 18, 2020 (the GE Aviation Maintenance
Manual). Section 72-00-00 of the GE Aviation Maintenance Manual
describes procedures for performing Type 2 and Type 3 inspections.
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 ADDRESSES.

AD Requirements

This AD requires inspection and adjustment of the engine push-pull
control, replacement of certain beta switches, inspection and
adjustment of the engine push-pull control after any maintenance,
repair or modification action that affects the push-pull control, and
installation of an improved push-pull control.

Differences Between This AD and the MCAI or Service Information

EASA AD 2020-0143 specifies installation allowances for Group 4 and
Group 5 engines. This AD does not specify allowances, as it simply
allows installation of engines with push-pull control P/N M601-76.5 or
M601-76.4, as applicable, installed.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and
comment procedures for rules when the agency, for ``good cause,'' finds
that those procedures are ``impracticable, unnecessary, or contrary to
the public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without providing notice and seeking
comment prior to issuance. Further, section 553(d) of the APA
authorizes agencies to make rules effective in less than thirty days,
upon a finding of good cause.
The FAA justifies waiving notice and comment prior to adoption of
this rule because no domestic operators use this product. Accordingly,
notice and opportunity for prior public comment are unnecessary,
pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the foregoing
reason, the FAA finds that good cause exists pursuant to 5 U.S.C.
553(d) for making this amendment effective in less than 30 days.

Comments Invited

The FAA invites you to send any written data, views, or arguments
about this final rule. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-0836 and Project Identifier
MCAI-2020-01629-E'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this final rule because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this final rule.

Confidential Business Information

CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure.
If your comments responsive to this AD contain commercial or financial
information that is customarily treated as private, that you actually
treat as private, and that is relevant or responsive to this AD, it is
important that you clearly designate the submitted comments as CBI.
Please mark each page of your submission containing CBI as ``PROPIN.''
The FAA will treat such marked submissions as confidential under the
FOIA, and they will not be placed in the public docket of this AD.
Submissions containing CBI should be sent to Barbara Caufield, Aviation
Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA
01803. Any commentary that the FAA receives which is not specifically
designated as CBI will be placed in the public docket for this
rulemaking.

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 FAA has determined
that it has good cause to adopt this rule without prior notice and
comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 0 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
Inspect and adjust push-pull control after any maintenance, repair or modification. 4 work-hours x $85 per hour = $340
$0
$340
$0
Inspect and adjust push-pull control and replace beta switch. 8 work-hours x $85 per hour = $680
1,916
2,596
0
Install push-pull control 4 work-hours x $85 per hour = $340
5,525
5,865
0

The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The FAA has no way of determining the number of aircraft
that might need these replacements.

On-Condition Costs

Action
Labor cost
Parts cost
Cost per product
Inspect push-pull control (paragraphs (g)(6) through (8)) 2 work-hours x $85 per hour = $170
$0
$170
Remove and replace beta switch (paragraph (g)(6)) 4 work-hours x $85 per hour = $340
1,916
2,256
Adjust push-pull control (paragraph (g)(6)) 3 work-hours x $85 per hour = $255
0
255

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 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:

a. Removing Airworthiness Directive 2018-16-10, Amendment 39-19350 (83
FR 43742, August 28, 2018); and

b. Adding the following new airworthiness directive: