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70-23-04: 70-23-04 AEROSTAR: Amdt. 39-1109 as amended by Amendment 39-1270. Applies to Model 600 and 601 airplanes, Serial Numbers 60-0001 through 60-0056 and 61-0001 through 61-0070. Compliance required as indicated unless already accomplished. To prevent failure of the wing flap tracks, jamming of the ailerons and possible loss of lateral control, accomplish the following: a. Before further flight after the effective date of this AD, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed: (1) Install wing flap speed placard in accordance with Aerostar Service Bulletin No. 600-22A, dated August 12, 1970, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. (2) Inspect flap tracks in accordance with Aerostar Service Bulletin 600-22A, dated August 12, 1970, or by an equivalent method approved by the Chief, Engineering and ManufacturingBranch, Southwest Region, FAA, Fort Worth, Texas. (3) If cracks are found, repair before further flight in accordance with Parts II, III and IV of Aerostar Service Bulletin 600-23, dated November 4, 1970, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. b. At the next annual inspection, or within the next 100 hours' time in service, whichever comes first after the effective date of this AD, install Aerostar Kit No. SB 600-23-1 in accordance with Aerostar Service Bulletin No. 600-23, dated November 4, 1970, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. NOTE: Additional holes must be drilled in the wing mount brackets (wing fairing rib) in accordance with Drawing No. A200094 before accomplishing item III A of SB 600-23. c. When the modification has been incorporated, the placard required by paragraph (a)above may be removed. Amendment 39-1109 became effective to all known owners of Aerostar Model 600 and 601 airplanes upon receipt of individual copies mailed November 6, 1970 and to all other persons on November 16, 1970. This Amendment 39-1270 becomes effective August 23, 1971.
2021-11-17: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (AHD) Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. This AD was prompted by a report of increased control force in the collective axis. This AD requires a one-time visual inspection of the main rotor actuator (MRA), as specified in a European Aviation Safety Agency (now 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.
2021-14-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A- 3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by a report of sudden severe vibrations and a cracked open blade trailing edge caused by a loosened lead inner weight. This AD requires inspections to determine if any bolted main rotor blades are installed, and replacement of the affected main rotor blades. The FAA is issuing this AD to address the unsafe condition on these products.
2004-08-06: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model BAe 146-100A and -200A series airplanes, that requires an inspection to determine the part number of the inner links of the side stays for the main landing gear (MLG), and replacement of the inner links with new parts, if necessary. This action is necessary to prevent the failure of the MLG, which could result in damage to the airplane structure or injury to airplane occupants. This action is intended to address the identified unsafe condition.
2004-08-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-300 series airplanes, that requires a general visual inspection for clearance between the corners of the A1 galley and the aft pressure bulkhead, and corrective actions, if necessary. This amendment also requires modification of the A1 galley. This action is necessary to prevent interference of the A1 galley with the radial stiffener on the aft pressure bulkhead, which could result in fatigue crack propagation. Fatigue crack propagation could lead to possible rapid decompression of the airplane or to damage and/or interference with the airplane control systems that pass through the bulkhead and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2019-24-16: The FAA is superseding Airworthiness Directive (AD) 2017-16- 08, which applied to certain Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, and -100 ECJ airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. AD 2017-16-08 required revising the existing maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD also adds airplanes to the applicability. This AD was prompted by the FAA's determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-08-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-IV series airplanes. For certain airplanes, this AD requires installation of an additional indicator located on the pilot's instrument panel in primary view of the flightcrew. The indicator will inform the flightcrew that the airplane main batteries are powering the direct current (DC) essential bus, which supplies power to vital communication and navigation equipment. For certain other airplanes, this AD will require the EICAS (Engine Instruments/Caution Advisory System) to be used for this indication. This action is necessary to ensure that the flightcrew is aware that an electrical system failure has occurred and that the airplane main batteries are powering the essential DC bus. If the flightcrew is unaware of this situation, action to stop depletion of the airplane batteries will not be taken, and critical communications and navigation equipment could fail. This action is intended to address the identified unsafe condition.
2016-20-14: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900 and -900ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fastener locations in the window corner surround structure are subject to widespread fatigue damage (WFD). This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking in certain fastener locations in the window corner surround structure, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking around certain fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and consequent loss of structural integrity of the airplane.
55-19-01: 55-19-01 HILLER: Applies to All UH-12, UH-12A, and UH-12B Model Helicopters. Compliance required as indicated. There have been several instances of cracking and failure of the tail boom rear bulkhead casting adjacent to the gearbox attachment holes. Cause of the cracking is not definitely known, but may be caused by flight loads or by damage incurred when the bulkhead is riveted to the tail boom. The following inspections are required: (1) Prior to the next flight and every 25 hours operating time thereafter, remove the tail rotor gearbox in accordance with the pertinent Hiller Service Manual. Inspect the tail boom rear bulkhead P/N 62201 for evidence of cracking, using dye or fluorescent penetrant methods. (2) Daily inspect the visible portions of the tail boom rear bulkhead P/N 62201 for visible evidence of cracking or failure. (3) If cracks or other damage are found during the above inspections, the P/N 62201 (magnesium) bulkhead must be scrapped andreplaced with the P/N 62202 (aluminum) bulkhead in accordance with Hiller Service Bulletin No. 49, revised August 23, 1955, prior to further flight. If a P/N 62202 bulkhead is not available, a new P/N 62201 bulkhead may be installed provided the inspections called for in paragraphs (1) and (2) are continued.
2024-17-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. This AD was prompted by a report of water in the oil of a main gearbox (MGB). This AD requires replacing certain main rotor (M/R) mast upper stops assembly screws. This AD also requires inspecting certain M/R mast cover plates and accomplishing MGB oil analyses and, depending on the results, taking corrective action. This AD prohibits installing certain M/R mast upper stops assembly screws, M/R masts with an affected M/R mast upper stops assembly screw installed, and used M/R mast cover plates on any helicopter. Lastly, this AD prohibits installing affected M/R masts unless the inspections are done. These actions are 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.