2025-01-04: TE Flap Control System; TE Flap Actuator

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: 2025-01-04 DAHER AEROSPACE (Type Certificate Previously Held by SOCATA): Amendment 39-22928; Docket No. FAA-2024-2321; Project Identifier MCAI-2024-00126-A. (a) Effective Date This airworthiness directive (AD) is effective March 11, 2025. (b) Affected ADs None. (c) Applicability This AD applies to DAHER AEROSPACE (type certificate previously held by SOCATA) (DAHER) Model TBM 700 airplanes, all serial numbers, certificated in any category, except those with DAHER Modification (MOD) 70-0777-27 installed during production. (d) Subject Joint Aircraft System Component (JASC) Code 2750, TE Flap Control System; 2752, TE Flap Actuator. (e) Unsafe Condition This AD was prompted by reports of wear of the inner flap actuator drive nut. The FAA is issuing this AD to prevent wear of the drive nut threading on the internal actuator flaps. The unsafe condition, if not addressed, could result in improper play between the actuator threaded rod and the drive nut, which could result in loss of flap control and consequent reduced or loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Clean and lubricate the left-hand (LH) and right-hand (RH) internal actuator rods in accordance with Paragraph C. in the Description of Accomplishment Instructions of Daher Aerospace Service Bulletin SB 70-118 Revision 3, dated December 2023 (Daher SB 70-118) within the compliance times identified in paragraph (g)(1)(i) or (ii) of this AD, whichever occurs later. (i) Before the accumulation of 400 hours time-in-service (TIS) or 12 months, whichever occurs first, since the first installation of a LH and RH inner flap actuator, and thereafter at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first. (ii) Within 10 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first. (2) Within the compliance time identified in paragraph (g)(2)(i) or (ii) of this AD, whichever occurs later, and thereafter, at intervals not to exceed 400 hours TIS or 12 months, whichever occurs first, for each inner flap actuator, measure the play between the drive nut and the internal actuator rod in accordance with Section A, Paragraphs (1) through (9), in the Description of Accomplishment Instructions of Daher SB 70-118. Where Section A, Paragraph (3), in the Description of Accomplishment Instructions of Daher SB 70-118 specifies "With the help of a second operator" this AD requires this action be performed by persons authorized under 14 CFR 43.3. (i) 3,000 hours TIS since first installation of the inner flap actuator on your airplane. (ii) 400 hours TIS or 12 months, whichever occurs first since the last play measurement accomplished for that inner flap actuator in accordance with Section A, Paragraphs (1) through (9), in the Description of Accomplishment Instructions of Daher SB 70-118. (3) If, during any measurement required by paragraph (g)(2) of this AD, any play is found, as identified in Section A, Paragraphs (8)(b) and (9)(b), of the Description of Accomplishment Instructions, Daher SB 70-118, before further flight, accomplish the applicable corrective actions in accordance with Section A, Paragraphs (10) through (15) and (17), and Section C, Paragraph (1), in the Description of Accomplishment Instructions of Daher SB 70-118. Where Section B, Paragraph (4), in the Description of Accomplishment Instructions of Daher SB 70-118, specifies to discard an old drive nut, this AD requires removing the old drive nut from service. (4) If, during any measurement as required by paragraph (g)(2) of this AD, no play is found, as identified in Section A, Paragraphs (8)(a) and (9)(a), in the Description of Accomplishment Instructions of Daher SB 70-118, before further flight, accomplish the actions in accordance with Section A, Paragraphs (13) through (15) and (17), and Section C, Paragraph (1), in the Description of Accomplishment Instructions of Daher SB 70-118. (h) Terminating Action Replacing the drive nuts in accordance with Section B, Paragraphs (1) through (10), in the Description of Accomplishment Instructions of Daher SB 70-118, constitutes terminating action for all of the actions required by paragraphs (g)(1) and (2) of this AD, provided, after that replacement, no LH flap actuator having part number (P/N) 1-5295-B or RH flap actuator having P/N 2-5295-B is installed. Where Section B, Paragraph (4) in the Description of Accomplishment Instructions of Daher SB 70-118, specifies to discard an old drive nut, this AD requires removing the old drive nut from service. (i) Alternative Methods of Compliance (AMOCs) The Manager, International Validation 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 International Validation Branch, mail it to the address identified in paragraph (j) of this AD or email to: AMOC@faa.gov. If mailing information, also submit information by email. 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. (j) Additional Information For more information about this AD, contact Fred Guerin, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: (206) 231-2346; email: fred.guerin@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) Daher Aerospace Service Bulletin SB 70-118, Revision 3, dated December 2023. (ii) [Reserved] (3) For Daher Aerospace material identified in this AD, contact DAHER, Customer Support, Airplane Business Unit, Tarbes Cedex 9, France; phone: (833) 826-2273; email: tbmcare@daher.com; website: daher.com . (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 www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov . Issued on January 6, 2025. Steven W. Thompson, Acting Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2025-02188 Filed 2-3-25; 8:45 am]BILLING CODE 4910-13-P