2021-23-09: Flight 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 a. Removing Airworthiness Directive 2015-16-07 R1, Amendment 39-18328 (80 FR 72563, November 20, 2015); and b. Adding the following new airworthiness directive: 2021-23-09 ASI Aviation (Type Certificate Previously Held by Reims Aviation S.A.): Amendment 39-21807; Docket No. FAA-2021-0712; Project Identifier 2019-CE-018-AD. (a) Effective Date This airworthiness directive (AD) is effective January 10, 2022. (b) Affected ADs This AD replaces AD 2015-16-07 R1, Amendment 39-18328 (80 FR 72563, November 20, 2015) (AD 2015-16-07 R1). (c) Applicability This AD applies to ASI Aviation (type certificate previously held by Reims Aviation S.A.) Model F406 airplanes, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC) Code 2700, Flight Control System. (e) Unsafe Condition This AD was prompted by reports of detachment of the pilot's rudder control pedal in flight. The FAA is issuing this AD to detect and correct cracking of the pilot's rudder control pedal. The unsafe condition, if not addressed, could result in detachment of the pedal with possible loss of airplane directional control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition For the purpose of this AD, a serviceable part is: (1) A rudder control pedal torque tube (left-hand (LH) part number (P/N) 5115260-1 or right-hand (RH) P/N 5115260-2) that has had a magnetic particle inspection by following the instructions of Part B of ASI Aviation Service Bulletin No. F406-104, Revision 1, dated December 14, 2018, and no cracks were found; or (2) A new rudder control pedal torque tube (LH P/N 5115260-1 or RH P/N 5115260-2) that has never been installed on an airplane. (h) Repetitive Inspections and Corrective Actions (1) Before further flight after the effective date of this AD, and thereafter at intervals not to exceed 600 hours time-in-service (TIS), do a visual inspection and a dye or fluorescent penetrant inspection for cracks of the LH and RH rudder control pedal torque tubes by following the Accomplishment Instructions, Part A or Part AA, in ASI Aviation Service Bulletin No. F406-104, Revision 1, dated December 14, 2018. (2) Within 100 hours TIS after the effective date of this AD, and thereafter at intervals not to exceed 2,400 hours TIS, do a magnetic particle inspection for cracks of the LH and RH rudder control pedal torque tubes by following the Accomplishment Instructions, Part B, in ASI Aviation Service Bulletin No. F406-104, Revision 1, dated December 14, 2018. (3) If, during any inspection required by paragraph (h)(1) or (2) of this AD, any crack is detected on a rudder control pedal torque tube, you are not required to contact ASI Aviation as specified in steps A.16, AA.5, and B.4 of ASI Aviation Service Bulletin No. F406-104, Revision 1, dated December 14, 2018. Instead, before further flight, replace the rudder control pedal torque tube with a serviceable part as defined by this AD. (i) Installation Limitation As of the effective date of this AD, do not install a rudder control pedal torque tube P/N 5115260-1 (LH) or P/N 5115260-2 (RH) on any airplane unless it is a serviceable part as defined by this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, International Validation Branch, 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 (k)(1) of this AD or email: [email protected]. (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. (k) Related Information (1) For more information about this AD, contact Gregory Johnson, Aviation Safety Engineer, International Validation Section, FAA, 901 Locust, Room 301, Kansas City, MO 64106-2641; phone: (720) 626-5462; email: [email protected]. (2) Refer to European Aviation Safety Agency (EASA) AD 2019-0016, dated January 29, 2019, for more information. You may examine the EASA AD in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-0712. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) ASI Aviation Service Bulletin No. F406-104, Revision 1, dated December 14, 2018. (ii) [Reserved]. (3) For service information identified in this AD, contact ASI Aviation, Aérodrome de Reims Prunay, 51360 Prunay, France; telephone: +33 3 26 48 46 84; fax: +33 3 26 49 18 57; email: [email protected]; website: https://asi-aviation.fr/page-Accueil.html. (4) You may view this service information at 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 (816) 329-4148. (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: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on October 27, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021-26329 Filed 12-3-21; 8:45 am]BILLING CODE 4910-13-P