2026-21-13: Elevator Tab Control System

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 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 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 Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed Intervals not to exceed 250 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a replacement Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed where both nut tube assemblies, P/N AA56142, were not replaced with new assemblies Intervals not to exceed 250 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a replacement Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed where both nut tube assemblies, P/N AA56142, were replaced with new assemblies Intervals not to exceed 300 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a replacement Simmonds-Precision pitch trim actuator, P/N DL5040M6, installed. This part can be new, modified from a P/N DL5040M5 pitch trim actuator, or overhauled Intervals not to exceed 300 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a Simmonds-Precision pitch trim actuator P/N DL5040M8, installed Intervals not to exceed 300 flight hours or 6 calendar 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 Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed Intervals not to exceed 250 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a replacement Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed where both nut tube assemblies, P/N AA56142, were not replaced with new assemblies Intervals not to exceed 250 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a replacement Simmonds-Precision pitch trim actuator, P/N DL5040M5, installed where both nut tube assemblies, P/N AA56142, were replaced with new assemblies Intervals not to exceed 300 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a Simmonds-Precision pitch trim actuator, P/N DL5040M6, installed Intervals not to exceed 300 flight hours or 6 calendar months, whichever occurs first. For airplanes that have a Simmonds-Precision pitch trim actuator P/N DL5040M8, installed Intervals not to exceed 300 flight hours or 6 calendar months, whichever occurs first. (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: [email protected] . 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: [email protected]. (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: [email protected]; website: metromerlin.com . (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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected] . 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