Results
2002-21-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (Cirrus) Model SR20 and SR22 airplanes. This AD requires you to replace the self-locking retaining nut on the roll and yaw trim cartridges with a new self- locking retaining nut with a higher axial load capability. This AD is the result of a report that, during a production flight test, the self- locking retaining nut on the yaw trim cartridge came off. The actions specified by this AD are intended to prevent loss of the self-locking retaining nut on the roll and yaw trim cartridges during flight, which could result in jamming of the corresponding flight control system. Such jamming could lead to loss of control of the airplane.
95-15-07: This amendment supersedes an existing airworthiness directive (AD), applicable to British Aerospace Model BAC 1-11 200 and 400 series airplanes, that currently requires structural inspections and repairs or replacements, as necessary. This amendment requires additional inspections of certain Structural Significant Items (SSI) and expansion of the inspection area for certain other SSI's. This amendment is prompted by the results of a structural integrity audit, which indicated that in order to maintain the structural integrity of these airplanes as they approach or exceed the manufacturer's original fatigue design life goal, certain SSI's need to be inspected. The actions specified by this AD are intended to ensure continuing structural integrity of these airplanes.
2023-26-03: The FAA is adopting a new airworthiness directive (AD) for certain WACO Classic Aircraft Corporation Model 2T-1A-2 airplanes. This AD was prompted by reports of multiple types of cracks at the leading edge former ribs and trailing edge former ribs in the upper wing center section. This AD requires installing maneuver restriction placards in the front and rear cockpits, inspecting the leading and trailing edge former ribs for cracking, replacing any cracked ribs, modifying the upper wing center section assembly, and removing the maneuver restriction placards after completing the modification. The FAA is issuing this AD to address the unsafe condition on these products.
2011-05-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Service experience has shown that fracture of the timing chain has occurred due to chain wear. This condition, if not corrected, could lead to in-flight cases of engine shutdown. We are issuing this AD to prevent engine in-flight shutdown leading to loss of control of the airplane by requiring life limits for the timing chain.
2002-21-04: This amendment supersedes an existing emergency airworthiness directive (EAD) for Agusta S.p.A. (Agusta) Model A119 helicopters. EAD 2002-17-52, which was issued on August 21, 2002, was sent to all known U.S. owners and operators of Agusta Model A119 helicopters by individual letters. That AD currently requires installing a placard in the helicopter and marking the airspeed indication at 132 knots indicated airspeed (KIAS) before further flight; visually checking the tail rotor blades on both sides for a crack before each start of the helicopter engine; visually inspecting the tail rotor blades with a 5x or higher magnifying glass and conducting a dye-penetrant inspection if you are unable to determine by the visual inspection whether or not there is a crack; replacing any cracked tail rotor blade; modifying the tail rotor hub and blade assembly, reidentifying the modified tail rotor hub and grips assembly and the modified tail rotor hub and blade assembly, which is a terminating action for the never-exceed speed (Vne) reduction; and establishing a retirement life for the tail rotor control rod. This amendment requires the same actions as that EAD, but corrects the airspeed indication marking, which should have been stated as 122 KIAS instead of 132 KIAS. This amendment is prompted by the failure of a tail rotor blade due to a fatigue crack. The actions specified by this AD are intended to prevent failure of the tail rotor blade and subsequent loss of control of the helicopter.
2023-26-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-AE3, Trent 1000-CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000- P3, Trent 1000-Q3, and Trent 1000-R3 engines. This AD is prompted by a determination that certain intervals for visual inspection of the intermediate-pressure stage 8 (IP8) and high-pressure stage 3 (HP3) air transfer tubes and front bearing housing IP8 air feed tubes need to be reduced. This AD requires initial and repetitive visual inspections of the IP8 and HP3 air transfer tubes and front bearing housing IP8 air feed tubes for cracking, damage, or air leakage wear, and replacement, if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
95-14-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11 200 and 400 airplanes, that currently requires incorporation of certain structural modifications. That AD was prompted by reports of fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design goal. The actions specified by that AD are intended to prevent reduced structural integrity of the airplane. This amendment requires incorporation of additional structural modifications.
2002-21-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires performing a one-time general visual inspection of the pilot's overhead circuit breaker panel wiring for discrepancies; rerouting the P45-12 wire; and repair, if necessary. This action is necessary to prevent circuit breaker wiring from becoming pinched or damaged, causing arcing between the wire and attaching bracket, which could result in smoke and/or fire in the pilot's circuit breaker panel. This action is intended to address the identified unsafe condition.
2023-25-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A321, A330-200, A330-200 Freighter, A330- 300, A330-800, A330-900, A340-200, and A340-300 series airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, - 271N, -272N, and -273N airplanes; and Model A340-541 and A340-642 airplanes. This AD was prompted by a report that a production deficiency of some SafeLav gaseous oxygen container (SLGOC) batches was identified during production testing of newly manufactured oxygen containers. This AD requires replacing affected SLGOCs and prohibiting the installation of affected SLGOCs, 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.
2002-19-51 R1: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-19-51 R1 that was sent previously to all known U.S. owners and operators of all Boeing Model 737 series airplanes by individual notices. This AD revises existing AD 2002-19-51 that currently requires, for certain airplanes, an inspection to determine the serial number of certain flight control modules (FCM), having P/N 65-44891-7, and corrective actions if necessary. That AD was prompted by reports of failed FCMs, which resulted in sluggish response of the aileron, elevator, and rudder surfaces. This AD revises the existing AD to provide operators with additional options for compliance, to specify the serial numbers of the affected compensator, and to make other editorial changes. The actions specified by this AD are intended to prevent operation with one failed FCM, which could result in reduced controllability of the airplane, or with two failed FCMs, which could result inloss of control of the airplane.