Airworthiness Directive · Amendment 39-21807 · Flight control system
ASI Aviation (Type Certificate Previously Held by Reims Aviation S.A.) Airplanes
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.
The FAA is superseding Airworthiness Directive (AD) 2015-16-07 R1, which applied to certain Reims Aviation S.A. (type certificate now held by ASI Aviation) Model F406 airplanes. AD 2015-16-07 R1 required inspecting the left-hand and right-hand rudder control pedal torque tubes and replacing with a serviceable part as necessary. Since the FAA issued AD 2015-16-07 R1, the European Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on these products. This AD retains the requirements of AD 2015-16-07 R1, expands the applicability, and requires repeating the inspections using updated procedures. The FAA is issuing this AD to address the unsafe condition on these products.
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.
(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.
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.
