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2023-08-07 ALLIED AG CAT PRODUCTIONS, INC.: Amendment 39-22422; Docket No. FAA-2022-1656; Project Identifier AD-2022-01081-A.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective June 21, 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 Controlling
    System.

(e) UNSAFE CONDITION

    This AD was prompted by a report of an accident  caused by the detach-
    ment of the airplane's propeller pitch control  (PPC) linkage from the
    PPC of the engine. The FAA is issuing this AD to prevent the PPC link-
    age 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 sec-
    ondary retention feature (bolt, washer, and safety wire)  on  the  PPC
    lever and the PPC assembly. If rework of the PPC assembly (specifical-
    ly, the shouldered shaft within the cam assembly within the PPC assem-
    bly) is required to do this installation,  do the rework in accordance
    with the procedures in Section 3.C(3)(d)2  of Honeywell Service Bulle-
    tin TPE331-72-2190, Revision 0, dated December 21, 2011. After the re-
    work 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.

Note 1 to paragraph (g): Honeywell TPE331 Propeller  Pitch  Control  Lever
letter, dated August 26, 2011, to the original equipment manufacturer con-
tains 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 April 19, 2023. Christina Underwood, Acting Director, Compliance
& Airworthiness Division, Aircraft Certification Service.

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.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1656; Project Identifier AD-2022-01081-A;
Amendment 39-22422; AD 2023-08-07]
RIN 2120-AA64

Airworthiness Directives; Allied Ag Cat Productions, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting 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 AD was prompted by an accident involving an Allied Ag Cat Model G-
164B airplane where the airplane's 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 AD
requires installing a secondary retention feature (bolt, washer, and
safety wire) on the PPC lever and the PPC assembly. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective June 21, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 21,
2023.

ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating 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 final rule, 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.
Material Incorporated by Reference:
For service information identified in this final rule,
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. It is also available at
regulations.gov by searching for and locating Docket No. FAA-2022-1656.

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:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Allied Ag Cat Model G-
164A and G-164B airplanes with certain STCs installed. The NPRM
published in the Federal Register on December 28, 2022 (87 FR 79821).
The NPRM was prompted by a report of an accident involving an Allied Ag
Cat Model G-164 airplane where the airplane's 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. In
the NPRM, the FAA proposed to require installing a secondary retention
feature (bolt, washer, and safety wire) on the PPC lever and the PPC
assembly. The FAA is issuing this AD to address the unsafe condition on
these products. 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.

Discussion of Final Airworthiness Directive

Comments

The FAA received two comments from Honeywell, Inc. (Honeywell). The
following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Clarify Unsafe Condition

Honeywell requested that paragraph (e), Unsafe Condition, of the
proposed AD be revised to specify ``detachment of the airplane's
propeller pitch control linkage (PPC)'' instead of ``detachment of the
propeller pitch control (PPC) linkage.'' The commenter explained that
this change would differentiate the linkage of the aircraft type design
from the linkage of the engine type design.
The FAA agrees and revised paragraph (e) of this AD accordingly.
The FAA also revised the SUMMARY and Background sections of this final
rule to clarify detachment of the airplane's PPC.

Request To Revise Paragraph (g) of the Proposed AD

Honeywell requested that the FAA delete the last sentence, ``Part
re-identification is required only if rework is done'' from paragraph
(g), Install Secondary Retention Feature, of the proposed AD. The
commenter explained that this sentence could be misinterpreted as
negating re-identification instructions that are included elsewhere in
Honeywell Service Bulletin TPE331-72-2190, Revision 0, dated December
21, 2011. The commenter noted that the intent of this sentence is
adequately addressed by ``After the rework is completed, re-identify
the part number of the PPC assembly, cam assembly, and shouldered shaft
. . .'' which is also in paragraph (g) of the proposed AD.
The FAA agrees and deleted ``Part re-identification is required
only if rework is done'' from paragraph (g) of this AD.

Conclusion

The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for changes described previously,
this AD is adopted as proposed in the NPRM. None of the changes will
increase the economic burden on any operator.

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).

Costs of Compliance

The FAA estimates that this AD affects 200 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
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

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) 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.

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: