Proposed Rule2026-06459
Airworthiness Directives; Ontic Engineering and Manufacturing, Inc. Airplanes (Type Certificate Previously Held by M7 Aerospace LLC)
Primary source
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Published
April 2, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt 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-CC, SA227-DC (C-26B), and SA-227-TT (300) airplanes. This proposed AD was prompted by reports of in-flight pitch trim actuator failures. This proposed AD would require 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 proposed AD would prohibit the installation of certain pitch trim actuators unless the pitch trim actuator is sealed. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 63 (Thursday, April 2, 2026)</title>
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[Federal Register Volume 91, Number 63 (Thursday, April 2, 2026)]
[Proposed Rules]
[Pages 16595-16599]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-06459]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-2723; Project Identifier AD-2024-00429-A]
RIN 2120-AA64
Airworthiness Directives; Ontic Engineering and Manufacturing,
Inc. Airplanes (Type Certificate Previously Held by M7 Aerospace LLC)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt 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-CC, SA227-DC (C-26B), and SA-227-TT (300) airplanes.
This proposed AD was prompted by reports of in-flight pitch trim
actuator failures. This proposed AD would require 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 proposed AD would
prohibit the installation of certain pitch trim actuators unless the
pitch trim actuator is sealed. 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 May 18,
2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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 <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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For Ontic Engineering and Manufacturing, Inc. material
identified in this proposed AD, contact Ontic, 1176 Telecom Drive,
Creedmoor, NC 27522; phone: (919) 956-4300; email:
<a href="/cdn-cgi/l/email-protection#fd9098898f92919493988fbd929389949ed39e9290"><span class="__cf_email__" data-cfemail="d3beb6a7a1bcbfbabdb6a193bcbda7bab0fdb0bcbe">[email 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, 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: Trevor Carlton, Aviation Safety
[[Page 16596]]
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#d4919796f9979b8794b2b5b5fab3bba2"><span class="__cf_email__" data-cfemail="c4818786e9878b9784a2a5a5eaa3abb2">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2026-2723;
Project Identifier AD-2024-00429-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 revise 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
<a href="http://regulations.gov">regulations.gov</a>, 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
Trevor Carlton, Aviation Safety Engineer, FAA, East Certification
Branch, FAA, 1701 Columbia Avenue, College Park, GA 30337. 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 six reports of in-flight failures of the pitch
trim actuator on Ontic Engineering and Manufacturing, Inc. SA226 and
SA227 airplanes due to corrosion. The corrosion failures are caused by
the piston rod of the Simmonds-Precision pitch trim actuators with part
number (P/N) DL5040M5, DL5040M6, and DL5040M8 being drilled through.
This allows moisture intrusion into the pitch trim actuator body
through the rod end keyway and pitch trim actuator piston.
AD 2007-16-03, Amendment 39-15142 (72 FR 43139, August 3, 2007) (AD
2007-16-03) was issued to detect excessive freeplay or rod slippage in
the pitch trim actuator that could result in pitch trim actuator
failure, which could lead to a pitch upset. AD 2007-16-03 places life
limits on certain P/N pitch trim actuators and requires the replacement
of certain P/N pitch trim actuators with one of an improved design.
Since the issuance of AD 2007-16-03, corrosion has been observed on
pitch trim actuators with P/N DL5040M5, DL5040M6, and DL5040M8.
Therefore, this proposed AD, while not superseding AD 2007-16-03, would
address moisture intrusion into the pitch trim actuator body through
the rod end keyway and pitch trim actuator piston.
The FAA is proposing this AD to prevent moisture intrusion into the
pitch trim actuator body through the rod end keyway and pitch trim
actuator piston. This condition, if not addressed, could result in
pitch trim actuator failure and consequent reduced control of the
airplane.
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 the same type design.
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 227-27-067R2, dated November 8, 2024; and Ontic Engineering
and Manufacturing, Inc. SA226 Service Bulletin 226-27-087R2, dated
November 8, 2024. 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.
Proposed AD Requirements in This NPRM
For airplanes with a Simmonds-Precision pitch trim actuator, P/N
DL5040M5, DL5040M6, or DL5040M8 installed, this proposed AD would
require 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. For
all affected airplanes, this proposed AD would prohibit the
installation of certain pitch trim actuators unless the pitch trim
actuator is sealed.
Differences Between This Proposed AD and the Referenced Material
Although the material specifies to submit certain information to
the manufacturer, this proposed AD would not include that requirement.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 198 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
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.
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[[Page 16597]]
The FAA estimates the following costs to do any necessary
replacement that would be required based on the results of the proposed
inspection. The agency has no way of determining the number of
airplanes that might need these replacements.
On-Condition Costs
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Cost per
Action Labor cost Parts cost 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.
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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
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
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:
Ontic Engineering and Manufacturing, Inc. (Type Certificate
Previously Held by M7 Aerospace LLC): Docket No. FAA-2026-2723;
Project Identifier AD-2024-00429-A.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 18, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Ontic Engineering and Manufacturing, Inc.
(type certificate previously held by M7 Aerospace LLC) 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 SA-227-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 consequent 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
227-27-067R2, dated November 8, 2024 (Ontic SB 227-27-067R2) or
Ontic Engineering and Manufacturing, Inc. SA226 Service Bulletin
226-27-087R2, dated November 8, 2024 (Ontic SB 226-27-087R2), 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 227-27-067R2 or Ontic SB 226-27-087R2, 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 trim actuator in
accordance with the
[[Page 16598]]
Accomplishment Instructions, Step 2.B., of Ontic SB 227-27-067R2 or
Ontic SB 226-27-087R2, 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 227-27-067R2 or Ontic SB 226-27-
087R2, 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 227-27-067R2 or
Ontic SB 226-27-087R2, 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 of 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.
------------------------------------------------------------------------
(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 16599]]
(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 the sealant is not cracked, missing, or compromised
per the applicable inspection required in paragraphs (h)(1) or
(i)(1) of this AD.
(k) 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 227-27-067R1, 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.
(l) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are not allowed.
(m) 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 (n)(1) of this AD
and email to: <a href="/cdn-cgi/l/email-protection#793834363a391f1818571e160f"><span class="__cf_email__" data-cfemail="eeafa3a1adae888f8fc0898198">[email 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.
(n) 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#327771701f717d61725453531c555d44"><span class="__cf_email__" data-cfemail="cd888e8fe08e829e8dabacace3aaa2bb">[email protected]</span></a>.
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (o)(3)
of this AD.
(o) 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 227-27-067R2, dated November 8, 2024.
(iii) Ontic Engineering and Manufacturing, Inc. SA226 Service
Bulletin 226-27-087R2, dated November 8, 2024.
(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#6d0008191f02010403081f2d020319040e430e0200"><span class="__cf_email__" data-cfemail="c8a5adbcbaa7a4a1a6adba88a7a6bca1abe6aba7a5">[email 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, 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 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#4325316d2a2d30332620372a2c2d032d2231226d242c35"><span class="__cf_email__" data-cfemail="076175296e6974776264736e6869476966756629606871">[email protected]</span></a>.
Issued on March 24, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-06459 Filed 4-1-26; 8:45 am]
BILLING CODE 4910-13-P
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