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2004-25-51: The FAA is adopting a new airworthiness directive (AD) for all Raytheon Aircraft Company (Raytheon) Beech Models 45 (YT-34), A45 (T- 34A, B-45), and D45 (T-34B) airplanes. This AD requires you to perform an inspection and/or modification program approved specifically for this AD by the FAA Wichita Aircraft Certification Office (ACO). This AD is the result of a total of three accidents on the affected airplanes, including a recent accident where the wing separated from the airplane in flight. We are issuing this AD to detect and correct cracking in the wing structure of the affected airplanes, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
2008-21-07R1: We are revising airworthiness directive (AD) 2008-21-07 for certain Dowty Propellers model R408/6-123-F/17 propellers. AD 2008-21- 07 required initial and repetitive inspections of the blade bonded metallic leading edge (L/E) guards for correct bonding until they accumulate more than 1,200 flight hours (FH) time-in-service. This AD requires the same inspection and replacement requirements of AD 2008- 21-07. This AD also provides an optional terminating action to those requirements. This AD was prompted by updated service bulletins that identify terminating action to the requirements of AD 2008-21-07. We are issuing this AD to prevent the loss of the bonded metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel.
2023-07-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 airplanes. This AD was prompted by reports the overwing emergency exit door (OWEED) escape line may be incorrectly routed. This AD requires inspecting the OWEED escape line and correcting the routing if required, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-07-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate 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.
79-15-05: 79-15-05 MCDONNELL DOUGLAS: Amendment 39-3515. Applies to Model DC-10-10, -10F, -30, -30F, -40 series airplanes certificated in all categories. Compliance required as indicated. To assure immediate indication to the flight crew of any asymmetric wing slat condition, accomplish the following: \n\n\ta.\tBefore further flight, after the effective date of this AD: \n\n\t\t(1)\tInstall two auto throttle/speed control computers in accordance with FAA approved type design data to provide stall warning based on both right and left angle of attack sensors and on the positions of both outboard wing slat groups in addition to previously required inputs, or; \n\n\t\t(2)\tModify the stall warning and auto slat system to provide information from two angle of attack sensors and the positions of both outboard wing slat groups to a single auto throttle/speed control computer in accordance with design data approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tNOTE: The stall warning and auto slat functions of the auto throttle/speed control computer are the functions required by this AD. \n\n\tb.\tWithin 30 days after the effective date of this AD, add the following to the limitations section of the FAA approved Airplane Flight Manual: \n\n\t"TAKEOFF WARNING \n\n\tThe slat function of the takeoff warning system must be operative for takeoff." \n\n\tc.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\td.\tAlternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective July 13, 1979.
96-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires repetitive tests of the integrity of the electrical circuit between the windshear computer and the flap position sensor, and repair of the electrical wiring, if necessary. This amendment also requires replacement of certain windshear computers with new computers, which, when accomplished, terminates the repetitive tests. This amendment is prompted by a report indicating that the existing windshear computer is not capable of detecting a signal indicating loss of flap position; this could result in the flightcrew following erroneous computer-generated guidance. The actions specified by this AD are intended to prevent the incapability of the windshear computer to detect the true flap position, which, if not corrected, could result in the inability of the flightcrew to avoid a windshear encounter, and consequent reduced controllability of the airplane.
2008-18-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been found cases where the pressure equalization valve was not installed in the left-hand bulkhead blowout panel, on the forward and/or aft cargo compartments, thus affecting the effectiveness of fire detection, containment and suppression. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-06-05: The FAA is adopting a new airworthiness directive (AD) for all Bell Textron Canada Limited Model 206A, 206A-1 (OH-58A), 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD was prompted by a loss of tail rotor (TR) drive due to a failure of an adhesively bonded joint between an adapter and a tube on one of the segmented TR drive shaft (TRDS) assemblies. This AD requires determining if an affected TRDS is installed; repetitively inspecting the bond line for damage; repetitively performing a proof load test of the TRDS assembly; and depending on the results of the inspections or the proof load tests, removing an affected TRDS from service and replacing it with a serviceable TRDS. This AD also prohibits installing a TRDS unless it meets certain requirements, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-19-01: The FAA adopts a new airworthiness directive (AD) that will supersede AD 86-26-04, which applies to certain Cessna Aircraft Company (Cessna) 120, 140, 140A, 150, F150, 170, 172, F172, FR172, P172D, 175, 177, 180, 182, 185, A185E, 190, 195, 205, 205A, 206, P206, P206E, TP206A, TU206, TU206E, U206, U206E, 207, T207, 210, T210, 336, 337, and T337 series airplanes. AD 86-26-04 currently requires you to inspect and, if necessary, modify the pilot/co-pilot upper shoulder harness adjusters that have certain Cessna accessory kits incorporated. This AD is the result of reports that additional airplanes have the same unsafe condition and the manufacturer revised the service information to add these airplanes and correct the part number of the shoulder harness adjusters. Consequently, this AD retains the actions of 86-26-04, adds additional airplanes to the applicability section of this AD, and incorporates the revised service information. We are issuing this AD to prevent slippage of the pilot/co-pilot shoulder harness, which could result in failure of the shoulder harness to maintain proper belt length adjustment and tension. Such failure could result in pilot/co- pilot injury.
97-02-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires, among other things, replacing certain yaw damper servos in the autopilot system, or rendering the servo inoperative. The actions specified by that AD are intended to prevent overheat failure of the Flight Control Computer (FCC), which could result in smoke in the flight deck that could inhibit the ability of the flightcrew to safely operate and land the airplane. This new amendment requires installation of circuit breakers on the avionics relay panel, which, when accomplished, constitutes terminating action for the previous requirements of the AD.