Airworthiness Directives; Ontic Engineering and Manufacturing, Inc. (Type Certificate Previously Held by Swearingen, Fairchild Aircraft, and M7 Aerospace) Airplanes

Issuing agencies

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain Ontic Engineering and Manufacturing, Inc. Model SA226-T, SA226- AT, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-PC, SA227-CC, SA227-DC (C-26B), and SA227-TT (300) airplanes. This AD was prompted by reports of in-flight pitch trim actuator failures. This AD requires repetitively inspecting the pitch trim actuator for cracked, missing, or compromised sealant, replacing and sealing the pitch trim actuator if cracked, missing, or compromised, repetitively measuring the pitch trim actuator travel time, and depending on the results of the measurements, replacing and sealing the pitch trim actuator. This AD also requires certain pitch trim actuators to be sealed after installation. The FAA is issuing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 91 Issue 206 (Tuesday, October 27, 2026)</title>
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[Federal Register Volume 91, Number 206 (Tuesday, October 27, 2026)]
[Rules and Regulations]
[Pages 67435-67439]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-21902]



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Rules and Regulations
                                                Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
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Federal Register / Vol. 91, No. 206 / Tuesday, October 27, 2026 / 
Rules and Regulations

[[Page 67435]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-2723; Project Identifier AD-2024-00429-A; 
Amendment 39-23502; AD 2026-21-13]
RIN 2120-AA64


Airworthiness Directives; Ontic Engineering and Manufacturing, 
Inc. (Type Certificate Previously Held by Swearingen, Fairchild 
Aircraft, and M7 Aerospace) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Ontic Engineering and Manufacturing, Inc. Model SA226-T, SA226-
AT, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), 
SA227-PC, SA227-CC, SA227-DC (C-26B), and SA227-TT (300) airplanes. 
This AD was prompted by reports of in-flight pitch trim actuator 
failures. This AD requires repetitively inspecting the pitch trim 
actuator for cracked, missing, or compromised sealant, replacing and 
sealing the pitch trim actuator if cracked, missing, or compromised, 
repetitively measuring the pitch trim actuator travel time, and 
depending on the results of the measurements, replacing and sealing the 
pitch trim actuator. This AD also requires certain pitch trim actuators 
to be sealed after installation. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective December 1, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 1, 
2026.

ADDRESSES: 
    AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under 
Docket No. FAA-2026-2723; 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 Ontic material identified in this AD, contact Ontic, 
1176 Telecom Drive, Creedmoor, NC 27522; phone: (919) 956-4300; email: 
<a href="/cdn-cgi/l/email-protection#84e9e1f0f6ebe8edeae1f6c4ebeaf0ede7aae7ebe9"><span class="__cf_email__" data-cfemail="036e6677716c6f6a6d6671436c6d776a602d606c6e">[email&#160;protected]</span></a>; website: <a href="http://metromerlin.com">metromerlin.com</a>.
    <bullet> You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 1100 Main, Kansas City, MO 
64105. 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> under 
Docket No. FAA-2026-2723.

FOR FURTHER INFORMATION CONTACT: Trevor Carlton, Aviation Safety 
Engineer, FAA, East Certification Branch, FAA, 1701 Columbia Avenue, 
College Park, GA 30337; phone: (404) 474-5597; email: <a href="/cdn-cgi/l/email-protection#024741402f414d51426463632c656d74"><span class="__cf_email__" data-cfemail="afeaeced82ece0fcefc9cece81c8c0d9">[email&#160;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 certain Ontic 
Engineering and Manufacturing, Inc. Model SA226-T, SA226-AT, SA226-
T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-PC, 
SA227-CC, SA227-DC (C-26B), and SA227-TT (300) airplanes. The NPRM was 
published in the Federal Register on April 2, 2026 (91 FR 16595). The 
NPRM was prompted by reports of in-flight pitch trim actuator failures. 
In the NPRM, the FAA proposed to require repetitively inspecting the 
pitch trim actuator for cracked, missing, or compromised sealant, 
replacing and sealing the pitch trim actuator if the sealant is found 
cracked, missing, or compromised, repetitively measuring the pitch trim 
actuator travel time, and depending on the results of the measurements, 
replacing and sealing the pitch trim actuator. The proposed AD would 
prohibit the installation of certain pitch trim actuators unless the 
pitch trim actuator is sealed.
    The FAA is issuing this AD to prevent moisture intrusion into the 
pitch trim actuator body through the rod end keyway and pitch trim 
actuator piston. The unsafe condition, if not addressed, could result 
in pitch trim actuator failure and reduced control of the airplane.
    The FAA is issuing this AD to address the unsafe condition on these 
products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from two commenters. The commenters were 
Ontic Engineering and Manufacturing, Inc. and World Class Accessory, 
Inc. The commenters requested changes to the proposed service 
information, compliance requirements, and installation provisions. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request To Incorporate the Latest Revisions of the Service Information

    Ontic Engineering and Manufacturing, Inc. requested that the latest 
revisions of the service bulletins be incorporated into the NPRM: Ontic 
Engineering and Manufacturing, Inc. SA227 Service Bulletin (SB) 227-27-
067R3 dated March 2, 2026, and Ontic Engineering and Manufacturing, 
Inc. SA226 Service Bulletin 226-27-087R3 dated March 2, 2026.
    The FAA agrees. The latest revisions clarify the repetitive travel 
time measurements for the different actuators, update manpower 
requirements, and align the allowable system voltage for the actuator 
time travel measurements for the DL5040M5, Mod 1 actuator. None of 
these changes substantively affect the required actions for operators 
but instead are clarifying. This AD has been revised to incorporate the 
latest revisions of the applicable service bulletins while retaining 
credit for actions accomplished before the effective date of this AD 
using the service bulletin revisions referenced in the NPRM.

[[Page 67436]]

Request To Revise Paragraph (h) Required Actions for Model Group 1 
Airplanes

    World Class Accessory, Inc. requested editorial changes to the 
Required Actions for Model Group 1 Airplanes in paragraphs (h)(2) and 
(3) of the proposed AD. The commenter requested changing the phrase 
``seal the pitch trim actuator in accordance with'' to ``seal the pitch 
trim actuator rod ends in accordance with'' for clarification.
    The FAA disagrees. The FAA reviewed the requested editorial changes 
and determined that a revision is not necessary. The language in this 
AD is consistent with the service information from the design approval 
holder (DAH). The FAA did not change this AD as a result of this 
comment.

Request To Maintain the Repetitive Measurement Interval

    Ontic Engineering and Manufacturing, Inc. requested that the 
repetitive measurement interval for airplanes equipped with an 
originally installed Simmonds-Precision pitch trim actuator, part 
number DL5040M5, remain identical by maintaining the current interval 
of not to exceed 250 flight hours or 6 calendar months, whichever 
occurs first.
    The FAA agrees. This AD has the repetitive measurement intervals 
for both Group 1 and Group 2 airplanes equipped with an original 
DL5040M5 pitch trim actuator at intervals of not to exceed 250 flight 
hours or 6 calendar months, whichever occurs first. These intervals 
were selected to align with the repetitive inspection intervals 
required by AD 2007-16-03, Amendment 39-15142 (72 FR 43139, August 3, 
2007) (AD 2007-16-03), and the DAH service information. Operators 
should already be accomplishing these repetitive inspections at the 
established intervals; therefore, this AD can be done at already 
established maintenance activity. The FAA did not change this AD as a 
result of this comment.

Request To Require Accomplishment by a Repair Station

    World Class Accessory, Inc. requested revising paragraph (h)(1) of 
the proposed AD to require that the inspection of the ram of each 
actuator be accomplished only by a repair station. The commenter stated 
that the inspection cannot be accomplished in the field.
    The FAA disagrees. The applicable Ontic service bulletins provide 
the information necessary to accomplish the required actions. It is the 
owner/operator's responsibility to ensure that those actions are 
performed by a qualified and licensed mechanic per FAA regulations. The 
FAA did not change this AD as a result of this comment.

Request To Revise the Installation Prohibition

    World Class Accessory, Inc. requested revising the installation 
prohibition because the pitch trim actuator (PTA) rod ends cannot be 
sealed until the actuator is installed on the airplane, adjusted, and 
rigged. The commenter stated that the rod ends must be adjusted, 
secured, and sealed after installation on the airplane before the 
actuator can be returned to service.
    The FAA agrees with the intent of the comment. The FAA acknowledges 
that the PTA must be installed on the airplane before sealant can be 
applied to the rod ends. However, the FAA disagrees that the 
installation prohibition prevents compliance with the AD. The return-
to-service procedures in the applicable Ontic service bulletins account 
for this step. Specifically, Step 2.C.1.a of the Ontic service bulletin 
instructs maintenance personnel to apply sealant to each ram rod end in 
accordance with Step 2.B.8 after the actuator is installed on the 
airplane and rigging/adjustment is complete. The actuator must be 
sealed before the airplane is returned to service. The FAA revised 
paragraph (j) of this AD to clarify the installation prohibition 
language to ensure the return to service procedures in the applicable 
service bulletins are followed.

Changes Since the NPRM Was Issued

    In Table 1 of paragraph (h)(5)(ii), the NPRM was missing a row for 
Simmonds-Precision pitch trim actuator P/N DL5040M8. The FAA has 
corrected the table in this final rule.

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 minor editorial changes, and 
any other changes described previously, this AD is adopted as proposed 
in the NPRM. None of the changes will increase the economic burden on 
any operator.

Material Incorporated by Reference Under 1 CFR Part 51

    The FAA reviewed Ontic Engineering and Manufacturing, Inc. SA227 
Commuter Category Series Service Bulletin CC7-27-038R3, dated January 
27, 2026; Ontic Engineering and Manufacturing, Inc. SA227 Service 
Bulletin 227-27-067R3, dated March 2, 2026; and Ontic Engineering and 
Manufacturing, Inc. SA226 Service Bulletin 226-27-087R3, dated March 2, 
2026. This material specifies procedures for inspections and functional 
checks of the pitch trim actuator and measurement of the pitch trim 
actuator travel time. These documents are distinct because they apply 
to different airplane models. This material is reasonably available 
because the interested parties have access to it through their normal 
course of business or by the means identified in the ADDRESSES section.

Differences Between This AD and the Referenced Material

    Although the material specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

Costs of Compliance

    The FAA estimates that this AD affects 198 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Measure pitch trim actuator        3 work-hours x $85               $0  $255 per cycle.....  $50,490 per cycle.
 travel time.                       per hour = $255.
Inspect pitch trim actuator......  3 work-hours x $85                0  $255 per inspection  $50,490 per
                                    per hour = $255.                     cycle.               inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 67437]]

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                    Action                                  Labor cost             Parts cost   Cost per product
----------------------------------------------------------------------------------------------------------------
Seal pitch trim actuator rod ends.............  2 work-hours x $85 per hour =            $149               $319
                                                 $170.
Replace pitch trim actuator...................  5 work-hours x $85 per hour =          20,000             20,425
                                                 $425.
----------------------------------------------------------------------------------------------------------------

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:

2026-21-13 Ontic Engineering and Manufacturing, Inc. (Type 
Certificate Previously Held by Swearingen, Fairchild Aircraft, and 
M7 Aerospace): Amendment 39-23502; Docket No. FAA-2026-2723; Project 
Identifier AD-2024-00429-A.

(a) Effective Date

    This airworthiness directive (AD) is effective December 1, 2026.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Ontic Engineering and Manufacturing, Inc. 
(type certificate previously held by Swearingen, Fairchild Aircraft, 
and M7 Aerospace) model and serial number airplanes, certificated in 
any category, as identified in paragraphs (c)(1) and (2) of this AD.
    (1) Group 1 airplanes: Model SA226-T, SA226-AT, SA226-T(B), 
SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-PC, 
and SA227-TT (300) airplanes, all serial numbers with a pitch trim 
actuator Simmonds-Precision part number (P/N) DL5040M5, DL5040M6, or 
DL5040M8 installed.
    (2) Group 2 airplanes: Model SA227-CC and SA227-DC (C-26B), all 
serial numbers with a pitch trim actuator Simmonds-Precision P/N 
DL5040M5, DL5040M6, or DL5040M8 installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 2731, Elevator Tab 
Control System.

(e) Unsafe Condition

    This AD was prompted by reports of in-flight pitch trim actuator 
failure. The FAA is issuing this AD to prevent moisture intrusion 
into the pitch trim actuator body through the rod end keyway and 
pitch trim actuator piston. The unsafe condition, if not addressed, 
could result in pitch trim actuator failure and reduced control of 
the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definitions

    For the purpose of this AD:
    (1) A new part is a pitch trim actuator with zero-hours time-in-
service (TIS).
    (2) An overhauled part is a pitch trim actuator that has zero 
hours TIS since the last overhaul.

(h) Required Actions for Model Group 1 Airplanes

    (1) For all affected airplanes, at whichever compliance time in 
paragraph (h)(1)(i) or (ii) of this AD occurs later, inspect the ram 
of each actuator, specifically the pitch trim actuator rod ends, to 
determine if the sealant is cracked, missing, or compromised in 
accordance with Step 2.B.7, of the Accomplishment Instructions in 
Ontic Engineering and Manufacturing, Inc. SA227 Service Bulletin 
(SB) 227-27-067R3 dated March 2, 2026, (Ontic SB 227-27-067R3) or 
Ontic Engineering and Manufacturing, Inc. SA226 Service Bulletin 
226-27-087R3 dated March 2, 2026, (Ontic SB 226-27-087R3), as 
applicable for your airplane.
    (i) Within 1,000 flight hours or 6 calendar months since the 
pitch trim actuator was put into service, whichever occurs first; or
    (ii) Within 30 days after the effective date of this AD.
    (2) For affected airplanes with any pitch trim actuator whose 
rod ends have been found to have cracked, missing, or compromised 
sealant per the inspection in paragraph (h)(1) of this AD, and have 
at least 1,000 flight hours or at least 6 calendar months, whichever 
is less since the pitch trim actuator was put into service, before 
further flight, replace the pitch trim actuator with a new or 
overhauled pitch trim actuator and install and seal the pitch trim 
actuator in accordance with the Accomplishment Instructions, Step 
2.B.8, Ontic SB 227-27-067R3 or Ontic SB 226-27-087R3, as applicable 
for your airplane.
    (3) For affected airplanes with any pitch trim actuator whose 
rod ends have been found to have cracked, missing, or compromised 
sealant per the inspection in paragraph (h)(1) of this AD, and have 
less than 1,000 flight hours or 6 calendar months, whichever is less 
since the pitch trim actuator was put into service, before further 
flight, inspect and apply sealant to the pitch

[[Page 67438]]

trim actuator in accordance with the Accomplishment Instructions, 
Step 2.B., of Ontic SB 227-27-067R3 or Ontic SB 226-27-087R3, as 
applicable for your airplane.
    (4) For all affected airplanes, repetitively inspect and seal 
the pitch trim actuator every 1,000 flight hours or every 12 
calendar months, whichever occurs first, after the inspection 
required in paragraph (h)(1), in accordance with the Accomplishment 
Instructions, Step 2.B., Ontic SB 227-27-067R3 or Ontic SB 226-27-
087R3, as applicable for your airplane.
    (5) For all affected airplanes, at whichever compliance time in 
paragraph (h)(1)(i) or (ii) of this AD occurs later, measure the 
pitch trim actuator travel time in accordance with the 
Accomplishment Instructions, Step 2.A., Ontic SB 227-27-067R3 or 
Ontic SB 226-27-087R3, as applicable for your airplane.
    (i) If either pitch trim actuator rod does not meet travel time 
criteria, before further flight, replace the pitch trim actuator 
with a new or overhauled pitch trim actuator.
    (ii) If both pitch trim actuator rods meet travel time criteria, 
repeat the measurement of the pitch trim actuator at intervals 
specified below in table 1 to paragraph (h)(5)(ii) of this AD.

     Table 1 to Paragraph (h)(5)(ii)--Group 1 Repetitive Measurement
                                Intervals
------------------------------------------------------------------------
               Condition                 Repetitive measurement interval
------------------------------------------------------------------------
For airplanes that have an original      Intervals not to exceed 250
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed.       months, whichever occurs
                                          first.
For airplanes that have a replacement    Intervals not to exceed 250
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed        months, whichever occurs
 where both nut tube assemblies, P/N      first.
 AA56142, were not replaced with new
 assemblies.
For airplanes that have a replacement    Intervals not to exceed 300
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed        months, whichever occurs
 where both nut tube assemblies, P/N      first.
 AA56142, were replaced with new
 assemblies.
For airplanes that have a replacement    Intervals not to exceed 300
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M6, installed.       months, whichever occurs
 This part can be new, modified from a    first.
 P/N DL5040M5 pitch trim actuator, or
 overhauled.
For airplanes that have a Simmonds-      Intervals not to exceed 300
 Precision pitch trim actuator P/N        flight hours or 6 calendar
 DL5040M8, installed.                     months, whichever occurs
                                          first.
------------------------------------------------------------------------

    (6) If any affected pitch trim actuator was replaced with a 
pitch trim actuator that makes the airplane a Group 1 airplane, the 
actions of this AD still apply at the applicable compliance times.

(i) Required Actions for Group 2 Airplanes

    (1) For all affected airplanes, at whichever compliance time in 
paragraph (i)(1)(i) or (ii) of this AD occurs later, inspect the ram 
of each actuator, specifically the pitch trim actuator rod ends, to 
determine if the sealant is cracked, missing, or compromised, in 
accordance with the Accomplishment Instructions, Step 2.B.7, SA227 
Commuter Category Series Service Bulletin CC7-27-038R3, dated 
January 27, 2026 (Ontic SB CC7-27-038R3).
    (i) Within 1,000 flight hours or 6 calendar months since the 
pitch trim actuator was put into service, whichever occurs first; or
    (ii) Within 30 days after the effective date of this AD.
    (2) For affected airplanes with any pitch trim actuator whose 
rod ends have been found to have cracked, missing, or compromised 
sealant per the inspection in paragraph (i)(1) of this AD, and have 
at least 1,000 flight hours or at least 6 calendar months, whichever 
is less since the pitch trim actuator was put into service, before 
further flight, replace the pitch trim actuator with a new or 
overhauled pitch trim actuator and install and seal the pitch trim 
actuator in accordance with the Accomplishment Instructions, Step 
2.B.8, Ontic SB CC7-27-038R3.
    (3) For affected airplanes with any pitch trim actuator whose 
rod ends have been found to have cracked, missing, or compromised 
sealant per the inspection in paragraph (i)(1) of this AD, and have 
less than 1,000 flight hours or 6 calendar months, whichever is less 
since the pitch trim actuator was put into service, before further 
flight, inspect and apply sealant to the pitch trim actuator in 
accordance with the Accomplishment Instructions, Step 2.B., Ontic SB 
CC7-27-038R3.
    (4) For all affected airplanes, repetitively inspect and seal 
the pitch trim actuator every 1,000 flight hours or every 12 
calendar months, whichever occurs first, after the inspection 
required in paragraph (i)(1), in accordance with the Accomplishment 
Instructions, Step 2.B., Ontic SB CC7-27-038R3.
    (5) For all affected airplanes, at whichever compliance time in 
paragraph (i)(1)(i) or (ii) of this AD occurs later, measure the 
pitch trim actuator travel time in accordance with the 
Accomplishment Instructions, Step 2.A., Ontic SB CC7-27-038R3.
    (i) If either pitch trim actuator rod does not meet travel time 
criteria, before further flight, replace the pitch trim actuator 
with a new or overhauled pitch trim actuator.
    (ii) If both pitch trim actuator rods meet travel time criteria, 
repeat the measurement of the pitch trim actuator at intervals 
specified below in table 2 to paragraph (i)(5)(ii) of this AD.

     Table 2 to Paragraph (i)(5)(ii)--Group 2 Repetitive Measurement
                                Intervals
------------------------------------------------------------------------
               Condition                 Repetitive measurement interval
------------------------------------------------------------------------
For airplanes that have an original      Intervals not to exceed 250
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed.       months, whichever occurs
                                          first.
For airplanes that have a replacement    Intervals not to exceed 250
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed        months, whichever occurs
 where both nut tube assemblies, P/N      first.
 AA56142, were not replaced with new
 assemblies.
For airplanes that have a replacement    Intervals not to exceed 300
 Simmonds-Precision pitch trim            flight hours or 6 calendar
 actuator, P/N DL5040M5, installed        months, whichever occurs
 where both nut tube assemblies, P/N      first.
 AA56142, were replaced with new
 assemblies.
For airplanes that have a Simmonds-      Intervals not to exceed 300
 Precision pitch trim actuator, P/N       flight hours or 6 calendar
 DL5040M6, installed.                     months, whichever occurs
                                          first.
For airplanes that have a Simmonds-      Intervals not to exceed 300
 Precision pitch trim actuator P/N        flight hours or 6 calendar
 DL5040M8, installed.                     months, whichever occurs
                                          first.
------------------------------------------------------------------------


[[Page 67439]]

    (6) If any affected pitch trim actuator was replaced with a 
pitch trim actuator that makes the airplane a Group 2 airplane, the 
actions of this AD still apply at the applicable compliance times.

(j) Installation Prohibition for All Airplane Models in Both Group 1 
and Group 2

    As of the effective date of this AD, do not install a pitch trim 
actuator unless, upon installation, the procedures in Step 2.C 
Return to Service of each applicable Service Bulletin referenced in 
paragraphs (h)(1) or (i)(1) of this AD are followed.

(k) No Reporting Requirement

    Although the applicable Service Bulletins referenced in 
paragraphs (h)(1) and (i)(1) of this AD specify submission of 
certain information to the manufacturer, this AD does not include 
those reporting requirements.

(l) Credit for Previous Actions

    (1) You may take credit for the actions required by paragraphs 
(h)(1) of this AD if those actions were performed before the 
effective date of this AD using Ontic Engineering and Manufacturing, 
Inc. SA227 Service Bulletin 227-27-067R2, dated November 8, 2024; 
Ontic Engineering and Manufacturing, Inc. SA226 Service Bulletin 
226-27-087R2, dated November 8, 2024; Ontic Engineering and 
Manufacturing, Inc. SA227 Service Bulletin 227-27-067R1, dated 
August 16, 2024; or Ontic Engineering and Manufacturing Inc. SA227 
Service Bulletin 227-27-067, dated July 29, 2024.
    (2) You may take credit for the actions required by paragraphs 
(i)(1) of this AD if those actions were performed before the 
effective date of this AD using Ontic Engineering and Manufacturing, 
Inc. SA227 Commuter Category Series Service Bulletin CC7-27-038R2, 
dated November 8, 2024.

(m) Special Flight Permit

    Special flight permits, as described in 14 CFR 21.197 and 
21.199, are not allowed.

(n) Alternative Methods of Compliance (AMOCs)

    The Manager, East Certification 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 East Certification Branch, send it to the 
attention of the person identified in paragraph (o)(1) of this AD 
and email to: <a href="/cdn-cgi/l/email-protection#80c1cdcfc3c0e6e1e1aee7eff6"><span class="__cf_email__" data-cfemail="73323e3c30331512125d141c05">[email&#160;protected]</span></a>. 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.

(o) Additional Information

    (1) For more information about this AD, contact Trevor Carlton, 
Aviation Safety Engineer, FAA, East Certification Branch, FAA, 1701 
Columbia Avenue, College Park, GA 30337; phone: (404) 474-5597; 
email: <a href="/cdn-cgi/l/email-protection#2f6a6c6d026c607c6f494e4e01484059"><span class="__cf_email__" data-cfemail="b6f3f5f49bf5f9e5f6d0d7d798d1d9c0">[email&#160;protected]</span></a>.
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (p)(3) 
of this AD.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the material listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) Ontic Engineering and Manufacturing, Inc. SA227 Commuter 
Category Series, Service Bulletin CC7-27-038R3, dated January 27, 
2026.
    (ii) Ontic Engineering and Manufacturing, Inc. SA227 Service 
Bulletin 227-27-067R3, dated March 2, 2026.
    (iii) Ontic Engineering and Manufacturing, Inc. SA226 Service 
Bulletin 226-27-087R3, dated March 2, 2026.
    (3) For Ontic Engineering and Manufacturing, Inc. material 
identified in this AD, contact Ontic Engineering and Manufacturing, 
Inc., 1176 Telecom Drive, Creedmoor, NC 27522; phone: (919) 956-
4300; email: <a href="/cdn-cgi/l/email-protection#b0ddd5c4c2dfdcd9ded5c2f0dfdec4d9d39ed3dfdd"><span class="__cf_email__" data-cfemail="600d0514120f0c090e0512200f0e1409034e030f0d">[email&#160;protected]</span></a>; website: <a href="http://metromerlin.com">metromerlin.com</a>.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 1100 Main, Kansas City, 
MO 64105. For information on the availability of this material at 
the FAA, call (817) 222-5110.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#4b2d39652225383b2e283f2224250b252a392a652c243d"><span class="__cf_email__" data-cfemail="3f594d1156514c4f5a5c4b5650517f515e4d5e11585049">[email&#160;protected]</span></a>.

    Issued on October 23, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-21902 Filed 10-26-26; 8:45 am]
BILLING CODE 4910-13-P


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