Rule2023-10408
Airworthiness Directives; Allied Ag Cat Productions, Inc. Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
May 17, 2023
Effective
June 21, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 88 Issue 95 (Wednesday, May 17, 2023)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="http://regulations.gov">regulations.gov</a> 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:
<bullet> For service information identified in this final rule,
contact Honeywell International, Inc., 111 South 34th Street, Phoenix,
AZ 85034; phone: (800) 601-3099; website: <a href="http://aerospace.honeywell.com">aerospace.honeywell.com</a>.
<bullet> 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
<a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#49233c3a3d2027672a283b3d2c3b092f2828672e263f"><span class="__cf_email__" data-cfemail="79130c0a0d1017571a180b0d1c0b391f1818571e160f">[email protected]</span></a>.
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:
<bullet> Model G-164A airplanes with STC No. SA7769SW, SA7966SW, or
SA8720SW installed; and
<bullet> 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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Installation of secondary retention 4 work-hours x $85 per $1,000 $1,340 $268,000
feature. hour = $340.
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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:
<a href="/cdn-cgi/l/email-protection#5c36292f283532723f3d2e28392e1c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="eb819e989f8285c5888a999f8e99ab8d8a8ac58c849d">[email protected]</span></a>.
(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: <a href="http://aerospace.honeywell.com">aerospace.honeywell.com</a>.
(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: <a href="/cdn-cgi/l/email-protection#dbbda9f5b2b5a8abbeb8afb2b4b59bb5baa9baf5bcb4ad"><span class="__cf_email__" data-cfemail="573125793e3924273234233e3839173936253679303821">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
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
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