Results
2014-12-09: We are adopting a new airworthiness directive (AD) for Agusta Model AB412 helicopters. This AD requires inspecting the main transmission lubricating system oil outlet hose (hose) for damage, and, if required, replacing the hose. This AD is prompted by reports of damage found on the hose. These actions are intended to prevent loss of main gear box (MGB) lubrication, which could lead to failure of the MGB and subsequent loss of control of the helicopter.
83-14-02: 83-14-02 PILATUS BRITTEN-NORMAN, LTD.: Amendment 39-4682. Applies to BN-2A MK. III Trislander Series (S/Ns 1001 thru 1042, 1048 thru 1054, 1057 thru 1061, 350, 360, 361 and 363) airplanes certificated in any category. Compliance: Required within the next 500 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent defects in the wing attachment pins which can adversely affect the safe life of the wing-to-fuselage attachments, accomplish the following: (a) Remove the wing attachment pins, one at a time, in accordance with the instructions contained in the "ACTION" section of the Pilatus Britten-Norman, Ltd., Service Bulletin No. BN2/SB 146, Issue 1, dated December 31, 1980 (hereinafter referred to as the SB), or an FAA-approved equivalent. (b) Visually inspect the wing attachment pins for corrosion, fretmarks, file/grinding marks and thread binding of the inboard nut in accordance with the instructions contained in the "ACTION" section of the SB, and if defects are found, before further flight, replace the defective wing attachment pins with new attachment pins. NOTE: Refer to SB and Trislander Illustrated Parts Catalog (Pub. Ref. PC/2, Sec. 3.5./1). (c) Visually inspect the wing joint gaps to ensure shim washers fill the gaps, and before further flight, replace shim washers as required to fill the wing joint gaps. NOTE: Refer to SB and Trislander Maintenance Manual (Pub. Ref. MM/2). (d) Reinstall wing attachment pins in accordance with the instructions contained in the "ACTION" section of the SB. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomeseffective on August 19, 1983.
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.