Results
2008-09-20: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-200F, 747-300, 747-400, and 747-400D series airplanes. This AD requires a detailed inspection to detect missing fasteners from the shear clip at a certain stub frame to auxiliary sill joint, and applicable related investigative and corrective actions. This AD results from reports of missing fasteners from the shear clip of the stub frame to auxiliary sill joint and cracking of the adjacent exterior skin and internal doubler. We are issuing this AD to ensure that fasteners are installed in the shear clip of the stub frame to auxiliary sill joint. Missing fasteners could result in cracks in the adjacent exterior skin and internal doubler, which can propagate and result in loss of structural integrity and sudden in-flight decompression of the airplane.
2000-17-10 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires modifications of the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. That AD was prompted by reports of an undetected fire breaching the high speed gearbox (HSGB) case on certain Rolls Royce engines installed on in-service airplanes due to lack of an internal fire detection system within the HSGB. The actions specified by that AD are intended to prevent undetected fires originating within the HSGB from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire. This action removes certain airplanes from the applicability of the existing AD. The incorporation by reference of Lockheed Service Bulletin 093-77-059, dated February 25, 1998; and Lockheed Service Bulletin 093-77-059, Revision 1, dated February 2, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 6, 2000 (65 FR 53157, September 1, 2000).
2017-06-02: We are adopting a new airworthiness directive (AD) for Fokker Services B.V. Model F28 Mark 0100 airplanes equipped with Rolls-Royce TAY 650-15 engines. This AD was prompted by reports of uncontained engine fan blade failures in Rolls-Royce TAY 650-15 engines. This AD requires installation of a caution placard in the flight compartment. We are issuing this AD to address the unsafe condition on these products.
95-11-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires replacement of the existing pressure relief valve in the potable water system with a non-adjustable, single setting valve. This amendment is prompted by reports of potable water tanks that ruptured and resulted in damage to the passenger compartment. The actions specified by this AD are intended to prevent injury to the crew and passengers and damage to the passenger compartment due to an explosive failure of the potable water tank.
2008-09-23: 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that it is necessary to introduce Critical Design Configuration Control Limitations (CDCCL), in order to preserve critical fuel tank system ignition source prevention features during configuration changes such as modifications and repairs, or duringmaintenance actions. Failure to preserve critical fuel tank system ignition source prevention features could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2017-24-03: We are removing Airworthiness Directive (AD) 2017-01-06, which applied to certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 airplanes. AD 2017-01-06 required inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG). We issued AD 2017-01-06 to detect and correct the absence of cadmium plating on the rod end threads of the tie rod assemblies. Since we issued AD 2017- 01-06, we have determined that although cadmium plating might be absent, the rod end threads of the tie rod assemblies can withstand the expected environmental conditions, therefore the unsafe condition, as initially determined, does not exist.
95-11-01: This amendment supersedes an existing airworthiness directive (AD), applicable to Turbomeca Arriel 1 series turboshaft engines, that currently requires repetitive checks for engine rubbing noise during gas generator shutdown, and for free rotation of the gas generator by rotating the compressor manually after the last flight of the day. This amendment continues to require these checks, but eliminates the reference to the Turbomeca service bulletin, allows the pilot to perform all the checks required in this AD, clarifies the inspection interval requirement for daily checks, and specifies terminating action for the repetitive checks required by this AD. In addition, this AD allows the check for engine rubbing noise to be performed during engine motoring, and specifies that the engine turbine (T4) temperature must be below 150 degrees Centigrade when performing the check for free rotation. This amendment is prompted by comments submitted by operators of the affected enginesin response to the existing AD and the availability of an improved design 2nd stage nozzle guide vane. The actions specified by this AD are intended to prevent engine failure due to rubbing of the 2nd stage turbine disk on the 2nd stage turbine nozzle guide vane, which could result in complete engine failure and damage to the aircraft.
2018-20-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. This AD was prompted by the results of a fleet survey, which revealed cracking in bulkhead frame webs at a certain body station. This AD requires repetitive inspections of the bulkhead frame web at a certain body station and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
95-10-15: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, -300A and Model Avro 146-RJ70A, -RJ85A, and -RJ100A airplanes, that requires repetitive inspections to verify proper deployment of the evacuation slide at each door position, and various follow-on actions to correct discrepancies. This amendment is prompted by a report that, during operational checks of evacuation slides on in- service airplanes, the inflation valves failed to deploy the evacuation slide properly. The actions specified by this AD are intended to prevent failure of the evacuation slide to deploy automatically on demand, which would necessitate the flightcrew to manually deploy the slide; this situation could delay or impede the evacuation of passengers during an emergency.
2008-09-25: 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were then assessed using Transport Canada Policy Letter No. 525-001, to determine if mandatory corrective action is required. The assessment showed that it is necessary to introduce Critical Design Configuration Control Limitations (CDCCL), in order to preserve critical fuel tank system ignition source prevention features during configuration changes such as modifications and repairs, or duringmaintenance actions. Failure to preserve critical fuel tank system ignition source prevention features could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.