Results
99-10-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires replacing the wing attachment bolts and associated hardware. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent a wing from separating from the airplane caused by damaged wing attachment bolts, which could result in loss of control of the airplane.
76-04-09: 76-04-09 BELL: Amendment 39-2528. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters certificated in all categories, except those having installed main rotor hub yokes delivered as replacement spare parts from Bell Helicopter Company after August 11, 1974, and Models 206A and 206B bearing serial numbers 1174, 1192, 1252, 1355, 1381, 1382, 1390, 1398, 1399, 1400, 1408 through 1411, 1444, 1464, 1466, and subsequent. Compliance required within 200 hours' time in service after the effective date of this AD unless already accomplished. To detect and prevent possible cracks in the main rotor hub yokes, accomplish the following: (a) Remove the main rotor hub assembly form the helicopter and remove the pillow blocks and trunnion from the hub assembly in accordance with the pertinent model maintenance manual. (b) Inspect the yoke for cracks in each trunnion bore and in each tooling hole in the yoke web section using a 10-power or higher magnifying glass or an equivalent inspection method. (c) If a crack is found, remove and replace the discrepant yoke before further flight. (d) Inspect each yoke trunnion bore edge for nicks, scratches, or tool marks using a 10-power or higher magnifying glass or an equivalent inspection method. (e) If nicks, scratches, or tool marks are found on these edges, they must be removed, before further flight, as prescribed in Bell Helicopter Company Service Bulletin No. 206-04-1-74-1, Revision A, dated August 22, 1974, or later approved revision or in accordance with an equivalent FAA approved procedure. (f) Assemble and install the main rotor hub on the helicopter in accordance with the pertinent model maintenance manual. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from themanufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective March 30, 1976.
91-12-11: 91-12-11 BEECH: Amendment 39-7022. Docket No. 90-CE-44-AD. Applicability: Model F90 airplanes (serial number (S/N) LA-2 through LA-236); Models 200 and B200 airplanes (S/N BB-2 through BB-1212); Models 200C and B200C airplanes (S/N BL-1 through BL-72); Models 200CT and B200CT airplanes (S/N BN-1 through BN-4); Models 200T and B200T airplanes (S/N BT-1 through BT-30); and Model 300 airplanes (S/N FA-2 through FA-56), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent cracking and possible blowout of cast acrylic cockpit "D" side windows that could result in decompression injuries, accomplish the following: (a) Within the next 150 hours time-in-service after the effective date of this AD, accomplish the following: (1) Determine if the airplane "D" side window contains a placard bearing one of the part numbers presented below. If it does, then the window is made of stretched acrylic and no further action per this AD is required. MODEL PART NO. F90, 200, 200C, 200CT, 200T, B200 101-420081-5 through 101-420081-10; B200C, B200CT, and B200T 50-420066-419, 50-420066-420, 50-420066-437, or 50-420066-438. 300 101-420081-9 through 101-420081-12. (2) If a Model 300 airplane has a "D" side window installed in accordance with Beech Service Bulletin (SB) 2273, Revision 1, dated April 1990, then the window is stretched acrylic and no further action per this AD is required. (3) If a cast acrylic "D" side window is installed or if the window material cannot be determined, prior to further flight, inspect the window for cracks, chips, stress crazes, fissure scratches, or other damage in accordance with Part I of Beech SB No. 2208, Revision 1, dated July 1990. (i) If cracks, chips, stress crazes, fissure scratches, or other damage that exceeds the limits specified in Beech SB No. 2208, Revision 1, dated July 1990, is found, prior to further flight, except as noted in paragraph (b) of this AD, replace the window with the applicable stretched acrylic window listed in paragraph (a)(1) of this AD. (ii) If no cracks, chips, stress crazes, fissure scratches, or other damage that exceeds the limits specified in Beech SB No. 2208, Revision 1, dated July 1990, is found, within the next 12 calendar months, except as noted in paragraph (b) of this AD, replace each cast acrylic "D" side window in the crew compartment with the applicable stretched acrylic window listed in paragraph (a)(1) of this AD. (b) If stretched acrylic windows are not available, but have been ordered, the airplane may be operated unpressurized until the stretched acrylic windows are installed provided that the placards specified on page 10 of Beech SB No. 2208, Revision 1, dated July 1990, are installed in clear view of the pilot's position. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. (e) All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085 or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7022, AD 91-12-11) becomes effective on July 15, 1991.
2022-13-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 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.
2022-13-15: The FAA is adopting a new airworthiness directive (AD) for certain Williams International Co., L.L.C. (Williams) FJ44-2A, FJ44-2C, FJ44-3A, and FJ44-3A-24 model turbofan engines. This AD was prompted by a report of cracks in the high-pressure turbine (HPT) disk posts and failure of an HPT disk post, resulting in the contained fracture of an HPT disk post and blade. This AD requires removing the HPT disk, part number (P/N) 67093, from service before reaching defined cycle limits and replacing it with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
99-09-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR42 and ATR72 series airplanes. This action requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in severe icing conditions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the airplane from stalling due to prolonged exposure to severe icing conditions, which could result in reduced performance and controllability of the airplane.
2013-22-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted by reports of corrosion found on certain trimmable horizontal stabilizer actuators (THSA), affecting the ballscrew lower splines between the tie bar and the screw-jack. This AD requires repetitive detailed inspections for corrosion of certain THSAs, ballscrew integrity tests if necessary; and replacing any affected THSA with a serviceable or new and improved THSA, if necessary. We are issuing this AD to detect and correct corrosion of the THSAs, which could lead, in the case of ballscrew rupture, to the loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, and possibly resulting in loss of control of the airplane.
2013-20-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-211 -212, -213, -311, -312, -313, -541, and -642 airplanes. This AD requires revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements are not adequate to address the unsafe condition. We are issuing this AD to address the aging effects of aircraft systems. Such aging effects could change the characteristics of systems life-limited components leading to an increased potential for failure, which, in isolation or in combination with one or more other specific failures or events, could result in failure of certain life limited parts, which could reduce the structural integrity or the controllability of the airplane.
99-09-15: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, 58, 58A, C90A, B200, B300, and 1900D airplanes. This AD requires inspecting for interference or inadequate clearance between the flight control mechanism and any component located forward of the instrument panel. If interference or inadequate clearance is found, this AD requires securing all components so that they are clear of the flight control mechanism. This AD is the result of an incident where the electrical/avionics wires made contact with and restricted the control system of the affected airplanes. The actions specified by this AD are intended to prevent any components or wiring from interfering with the flight control mechanism caused by inadequate clearance, which could result in reduced or loss of aileron and/or elevator control. Comments for inclusion in the Rules Docket must be received on or before June 18, 1999.
99-09-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires modifications to the attachment installation of the forward lavatory. This amendment is prompted by a stress analysis report indicating that the forward lavatory could break free from the upper and/or lower attachments during an emergency landing. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers.