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72-23-03: 72-23-03 CESSNA: Amdt. 39-1551. Applies to Models 336 (Serial Numbers 336-0001 thru 336-0195) and 337 (Serial Numbers 337-0001 thru 337-0239) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent inadvertent retraction of wing flap and to insure positive operation of the electrical wing flap actuators, accomplish the following: A) On all aircraft with more than 100 hours' time in service, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the previous 75 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service, visually inspect the actuator jack screw for condition of lubricant and presence of contamination and scale in accordance with the procedure described in Cessna Service Letter SE70-16, Supplement 1, dated July 10, 1970, or later FAA-approved revision. If any of the conditions prescribed in the inspection criteria are noted, prior to further flight, remove, clean and relubricate the actuator jack screw in accordance with Cessna Service Letter SE70-16, dated June 12, 1970, or later FAA-approved revision, or any equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. B) On all aircraft with more than 500 hours' time in service, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the previous 75 hours' time in service, remove, clean and relubricate the actuator jack screw in accordance with the procedure described in Cessna Service Letter SE70-16, dated June 12, 1970, or later FAA-approved revision, or any equivalent procedure approved by Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) In addition, on all aircraft at each annual inspection, or at intervals not to exceed 12 months, whichever occurs first, remove, clean and relubricate the actuator jack screw in accordance withthe procedure described in Cessna Service Letter SE70-16, dated June 12, 1970, or later FAA-approved revision or any equivalent procedure approved by Chief, Engineering and Manufacturing Branch, FAA, Central Region. NOTE: Cessna Service Letter SE70-16, Supplement 2, dated August 28, 1970, specified some brand names of Molybdenum Disfulfide Grease. D) On or before April 1, 1973, modify the aircraft in accordance with Cessna Service Letter ME72-19, dated October 6, 1972, or later revisions. Equivalent methods of compliance with this paragraph must be approved by Chief, Engineering and Manufacturing Branch, FAA Central Region. E) Upon compliance with Paragraph D, the requirements of Paragraphs A, B, and C are no longer applicable. NOTE: The agency recommends that the procedures for maintaining the flap system as specified in applicable Cessna Service Manuals be followed. This amendment becomes effective November 10, 1972.
2023-05-02: The FAA is superseding Airworthiness Directive (AD) 2020-21- 10, which applied to certain Airbus SAS Model A318, A320, and A321 series airplanes; and Model A319-111, -112, -113, -114, -115, -131, - 132, -133, -151N, and -153N airplanes; and AD 2022-07-08, which applied to all Airbus SAS Model A318, A319, A320 and A321 series airplanes. AD 2020-21-10 and AD 2022-07-08 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2020-21- 10 and AD 2022-07-08 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-04-19: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD requires a general visual inspection of the rudder control system to confirm correct alignment and installation of the adjustment device, and repair if necessary. This AD was prompted by a report of disconnection of the kinematic chain from the co-pilot rudder pedals to the rudder control bars located under the cockpit floor; subsequent investigation revealed that the failure was caused by disconnection of the pedal adjustment device from the adjustment actuator. We are issuing this AD to detect and correct incorrect alignment and incorrect installation of the adjustment device, which could lead to loss of the rudder control from the affected side and possibly result in reduced control of the airplane.
71-25-03: 71-25-03 BEECH: Amdt. 39-1351. Applies to Models A23A, B23, C23 (Serial Numbers M-1069 thru M-1310); Models 19A, M19A, B19 (Serial Numbers MB-289 thru MB-500); Models A23-24 and A24 (Serial Numbers MA-273 thru MA-368); and Models A24R (Serial Numbers MC-3 thru MC-72, except MC-22, MC-23, MC-39, MC-43, MC-63, MC-64 and MC- 71) airplanes, and to other serial numbers of those model airplanes listed herein which have had the fuel and/or the oil pressure instrument lines replaced with the Beech Part No. 130524-3 fire sleeved lines. Compliance: Required as indicated, unless already accomplished. To eliminate a hazard to the safe operation of these airplanes, within the next 100 hours' time in service after the effective date of this AD, or at the next annual inspection, whichever occurs first, accomplish the following: Install fuel restrictor assembly and oil restrictor assembly at appropriate engine positions in accordance with Beechcraft Service Instruction 0411-240, Rev. 1, or a later approved revision. Equivalent methods of compliance are satisfactory if referred to and approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective December 3, 1971.
2003-04-14: This amendment adopts a new airworthiness directive (AD) for the specified Bell model helicopters that requires replacing the hydraulic solenoid tee fitting (tee fitting) and tubes. This amendment is prompted by the manufacturer's discovery that tee fittings may be installed improperly and restrict hydraulic fluid flow. The actions specified by this AD are intended to prevent restricted flow of hydraulic fluid to the flight control hydraulic actuators resulting in loss of hydraulic control, excessive stiffness in the flight controls, and a subsequent forced landing of the helicopter.
2023-03-09: The FAA is superseding Airworthiness Directive (AD) 2021-20- 09, which applied to certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72 airplanes. AD 2021-20-09 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive tasks and airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-20-09 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive tasks and airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
67-19-02: 67-19-02 BRITISH AIRCRAFT: Amdt. 39-434, Part 39, Federal Register June 10, 1967. Applies to British Aircraft Corporation Model BAC 1-11, 200 and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To detect honeycomb delamination on all moveable control surfaces and tabs, accomplish the following: (a) Within the next 600 hours' time in service after the effective date of this AD for airplanes with 1000 or more hours' time in service, or for airplanes with less than 1000 hours' time in service as of the effective date of this AD before the accumulation of 1500 hours' time in service, tap test all control surfaces and tabs for evidence of delamination of the skin from the honeycomb structure in accordance with British Aircraft Corporation Alert Service Bulletin No. 55/57-A-PM 2597, dated September 19, 1966, or later ARB-approved issue. (b) If the control surfaces with delamination are within the permissible limits specified in BAC Structural Repair Manual, they may remain in service, but must be inspected in accordance with paragraph (a) at intervals not to exceed 300 hours' time in service from the date of the last inspection. (c) Control surfaces with delaminations exceeding the permissible limits as specified in BAC Structural Repair Manual, must be repaired or replaced, before further flight, in accordance with this Structural Repair Manual, or later ARB-approved issue, or FAA-approved equivalent. This amendment effective July 10, 1967.
2016-04-10: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport Regional Model ATR42-500 airplanes, and Model ATR72-102, -202, -212, and -212A airplanes. This AD was prompted by a report of chafed wires between electrical harnesses. This AD requires inspections for wire discrepancies, and corrective actions if necessary. We are issuing this AD to detect and correct damaged wiring and incorrect installation of the wiring harness and adjacent air ducts that could lead to wire harness chafing and arcing, possibly resulting in an on-board fire.
2021-26-08: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD was prompted by reports of cracked or missing nuts on the tail rotor drive shaft (TRDS) disc pack (Thomas) couplings. This AD requires removing certain nuts from service, installing newly designed nuts, and applying a specific torque and a torque stripe to each newly installed nut. This AD then requires, after the installation of each newly designed nut, inspecting the torque and, depending on the inspection results, either applying a torque stripe or performing further inspections and removing certain parts from service. Finally, this AD prohibits installing any affected nut on any TRDS Thomas coupling. The FAA is issuing this AD to address the unsafe condition on these products.
2018-23-02: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 and A319 series airplanes; Model A320-211, A320- 212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes. This AD was prompted by reports of missing assembly hardware on the trimmable horizontal stabilizer actuator (THSA). This AD requires repetitive inspections and checks of the lower and upper THSA attachments and applicable related investigative and corrective actions; a one-time inspection of the THSA lower attachment and [[Page 59279]] replacement as applicable; and, for certain airplanes, activation of the electrical load sensing device (ELSD) and concurrent modifications. We are issuing this AD to address the unsafe condition on these products.