preamble attached >>>
ADs updated daily at www.Tdata.com
PROPOSED AD ALLIED AG CAT PRODUCTIONS, INC.: Docket No. FAA-2022-1656; Project Identifier AD2022-01081-A.
(a) COMMENTS DUE DATE

    The FAA must receive comments  on this airworthiness directive (AD) by
    February 13, 2023.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to the following  Allied Ag Cat Productions, Inc. air-
    planes, all serial numbers, certificated in any category.

(1) Model G-164A airplanes  with  Supplemental Type Certificate  (STC) No.
    SA7769SW, SA7966SW, or SA8720SW installed.

(2) Model G-164B airplanes with STC No. SA7546SW,  SA7966SW,  SA7987SW, or
    SA8720SW installed.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 6120,  Propeller Controll-
    ing System.

(e) UNSAFE CONDITION

    This AD was prompted  by a report of an accident caused by the detach-
    ment of the propeller pitch control (PPC) linkage from the PPC of  the
    engine.  The FAA is issuing this  AD to prevent  the PPC linkage  from
    detaching from  the PPC  of the  engine.  The unsafe condition, if not
    addressed, could result in reduced control of the airplane.

(f) COMPLIANCE

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

(g) INSTALL SECONDARY RETENTION FEATURE

    Within  12 months  after the  effective date  of this  AD,  install  a
    secondary retention feature (bolt, washer, and safety wire) on the PPC
    lever  and  the   PPC  assembly.  If   rework  of  the   PPC  assembly
    (specifically, the shouldered shaft within the cam assembly within the
    PPC assembly) is  required to do  this installation, do  the rework in
    accordance  with  the  procedures in  Section 3.C(3)(d)2  of Honeywell
    Service Bulletin TPE331-72-2190, Revision 0,  dated December 21, 2011.
    After the rework is completed, re-identify the part number of the  PPC
    assembly,  cam  assembly,  and shouldered  shaft,  in  accordance with
    Sections  3.C(4),  3.C(5),  and 3.C(7),  as  applicable,  of Honeywell
    Service Bulletin TPE331-72-2190, Revision 0,  dated December 21, 2011.
    Part re-identification is required only if rework is done.

Note 1  to  paragraph (g):  Honeywell TPE331 Propeller Pitch Control Lever
letter, dated  August 26,  2011, to  the original  equipment manufacturer,
contains information related to this subject.

(h) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Fort Worth ACO 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 (i)(1) of this AD.

(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.

(i) RELATED INFORMATION

(1) For more information about this AD,  contact  Justin Carter,  Aviation
    Safety Engineer, Fort Worth ACO Branch,  FAA,  10101 Hillwood Parkway,
    Fort Worth, TX 76177;  phone: (817) 222-5146; email: justin.carter@faa
    .gov.

(2) Service information identified in this AD  that is not incorporated by
    reference is available at the addresses specified in paragraphs (j)(3)
    and (4) of this AD.

(j) 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) Honeywell Service Bulletin TPE331-72-2190, Revision 0,  dated December
    21, 2011.

(ii) [Reserved]

(3) For service information identified in this AD, contact Honeywell Inter
    -national, Inc, 111 South 34th Street, Phoenix, AZ 85034; phone: (800)
    601-3099; website: aerospace.honeywell.com.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section,  Operational Safety Branch, 901 Locust,  Kansas City, MO
    64106. For  information on  the availability  of this  material at the
    FAA, call (817) 222-5110.

(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: www.archives.gov/federal-register/cfr/
    ibr-locations.html.

Issued on December 21, 2022. Christina Underwood, Acting Director, Compli-
ance & Airworthiness Division, Aircraft Certification Service.

DATES: The FAA must receive comments  on this proposed AD  by February 13,
2023.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1656; Project Identifier AD-2022-01081-A]
RIN 2120-AA64

Airworthiness Directives; Allied Ag Cat Productions, Inc.
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Allied Ag Cat Productions, Inc. (Allied Ag Cat) Model G-164A and G-
164B airplanes with certain supplemental type certificates (STCs)
installed. This proposed AD was prompted by an accident involving an
Allied Ag Cat Model G-164B airplane where the propeller pitch control
(PPC) linkage detached from the PPC of the engine and resulted in an
accident that significantly damaged the airplane and injured the pilot.
This proposed AD would require installing a secondary retention feature
(bolt, washer, and safety wire) on the PPC lever and the PPC assembly.
The FAA is proposing this AD to address the unsafe condition on these
products.

DATES: The FAA must receive comments on this proposed AD by February
13, 2023.

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 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.
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-1656; 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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
For service information identified in this NPRM, contact
Honeywell International, Inc., 111 South 34th Street, Phoenix, AZ
85034; phone: (800) 601-3099; website: aerospace.honeywell.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 901 Locust,
Kansas City, MO 64106. For information on the availability of this
material at the FAA, call (817) 222-5110.

FOR FURTHER INFORMATION CONTACT: Justin Carter, Aviation Safety
Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood Parkway, Fort
Worth, TX 76177; phone: (817) 222-5146; email: justin.carter@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-1656; Project Identifier
AD-2022-01081-A'' 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 proposal 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
regulations.gov, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.

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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to
Justin Carter, Aviation Safety Engineer, Fort Worth ACO Branch, FAA,
10101 Hillwood Parkway, Fort Worth, TX 76177. Any commentary that the
FAA receives which is not specifically designated as CBI will be placed
in the public docket for this rulemaking.

Background

The FAA received a report of an accident involving an Allied Ag Cat
Model G-164 airplane where the PPC linkage detached from the PPC of the
engine. The pilot sustained serious injuries, and the airplane was
substantially damaged. The root cause was determined to be a lack of a
secondary retention feature for the PPC of the engine.
This condition, if not addressed, could result in reduced control
of the airplane.
Aircraft configurations for airplanes with the potential for this
condition to exist are as follows:
Model G-164A airplanes with STC No. SA7769SW, SA7966SW, or
SA8720SW installed; and
Model G-164B airplanes with STC No. SA7546SW, SA7966SW,
SA7987SW, or SA8720SW installed.

FAA's Determination


The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of these same type designs.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Honeywell Service Bulletin TPE331-72-2190,
Revision 0, dated December 21, 2011. This service information
identifies the affected PPC assemblies and applicable engines, and
specifies procedures for reworking the affected PPC assemblies to
incorporate a threaded hole in the splined end of the shouldered shaft.
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.

Other Related Service Information

The FAA reviewed the Honeywell TPE331 Propeller Pitch Control Lever
letter, dated August 26, 2011, addressed to the original equipment
manufacturer (OEM). This letter informs the OEM of a report Honeywell
received about the TPE331 PPC lever shaft becoming detached from the
PPC assembly cam shaft and communicates the future development of a
Honeywell service bulletin (released as Honeywell Service Bulletin
TPE331-72-2190, Revision 0, dated December 21, 2011).

Proposed AD Requirements in This NPRM

This proposed AD would require installing a secondary retention
feature (bolt, washer, and safety wire) on the PPC lever and the PPC
assembly.

Costs of Compliance


The FAA estimates that this AD, if adopted as proposed, would
affect 200 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Installation of secondary retention feature 4 work-hours x $85 per hour = $340 $1,000 $1,340 $268,000

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


The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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: