Document ID: FAA-2022-1656-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Allied Ag Cat Productions, Inc. Airplanes
Posted Date: 2023-05-17T04:00Z

[Federal Register Volume 88, Number 95 (Wednesday, May 17, 2023)]
[Rules and Regulations]
[Pages 31472-31474]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2023-10408]

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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.

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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: [email protected].

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

[[Page 31473]]

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

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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

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. 
airplanes, 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 
detachment 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 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 already 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.
    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 inspector, 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: 
[email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is

[[Page 31474]]

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 International, 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 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], 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.
[FR Doc. 2023-10408 Filed 5-16-23; 8:45 am]
BILLING CODE 4910-13-P