Results
96-24-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company Model 250-C47B turboshaft engines. This action supersedes priority letter AD 96-21-12, applicable to Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 407 helicopters, that currently prohibits further flight, due to uncommanded inflight engine shutdowns. This action requires replacing the engine main electrical harness assembly with an improved assembly, disabling the overspeed solenoid, inspecting the engine control unit (ECU) internal PW10 voltage to determine electrical noise characteristics, and replacing units not considered serviceable. In addition, this AD requires adding a placard to the helicopter instrument panel notifying the pilot that the overspeed protection system is disabled and removes a placard which was required by priority letter AD 96-21-12; revises the BHTC Model 407 Rotorcraft Flight Manual (RFM); and requires maintenance actionsto clear the engine electronic control unit (ECU) of faults prior to each flight. Accomplishment of these actions will enable operators to resume flight operations. This amendment is prompted by investigation into the causes of the inflight engine shutdowns. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
96-23-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 and -300 series airplanes, that currently requires repetitive inspections to detect cracks of the upper drag strut trunnion fittings of the nose landing gear (NLG) and to verify tightness of the fitting attachment bolts, and replacement of fittings or fasteners, if necessary. This amendment requires the installation of a modification to terminate the repetitive inspections. This amendment is prompted by the development of a modification that positively addresses the identified unsafe condition. The actions specified by this AD are intended to prevent failure of the upper drag strut trunnion fittings of the NLG, which could lead to collapse of the NLG.
2002-26-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to identify all alloy steel bolts on the body station 1480 bulkhead splice, and corrective action if necessary; and provides for optional terminating action for certain requirements of that AD. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent cracked or broken bolts, which could result in structural damage and rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2025-08-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA341G and SA342J helicopters. This AD was prompted by reports of corrosion on the contact surfaces of the tail rotor inclined and horizontal drive shaft flanges. This AD requires repetitively inspecting the inclined and horizontal drive shaft flanges and, depending on the results, replacing the inclined or horizontal drive shaft. This AD also prohibits installing certain inclined and horizontal drive shafts unless certain requirements are met. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2000-16-02R1: This amendment revises an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series turbofan engines. That AD currently requires initial and repetitive torque checks for loose or broken front pylon mount bolts made from INCO 718 material and MP159 material. That AD also requires initial and repetitive visual inspections of the primary mount thrust load path. This amendment requires extension of the cycles accumulated before performing the initial inspection, reduces the frequency of repetitive inspections for MP159 material bolts, and adds a terminating action to the primary mount thrust load path inspections by introducing a new increased durability forward engine mount bearing housing. This amendment is prompted by component testing to assess the low cycle fatigue (LCF) life of the MP159 material bolts and the development of a new design forward engine mount bearing housing that meets the 8,000 flight cycle design intentfor inspection. The actions specified by this AD are intended to prevent front pylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane.
96-24-04: This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia (ASTA) Nomad Models N22B, N22S, and N24A airplanes. This action requires repetitively inspecting the tailplane stabilizer center section and repairing any cracked tailplane structure. This AD also provides an optional modification as a terminating action, after an inspection in which no cracks are found. A tailplane failure on one of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent cracking in the stabilizer center section, which, if not detected and corrected, could result in tailplane failure and loss of control of the airplane.
96-23-17: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-102 and -103 series airplanes, that requires repetitive external inspections to detect cracks in the skin exterior of the fuselage at floor level, and repair, if necessary. This amendment also requires repetitive internal inspections to detect cracks of the subject area, which terminates the repetitive external inspections. This amendment is prompted by a report that one of the tasks in the Maintenance Program Airworthiness Limitations List inadvertently excluded certain airplanes from the instructions for the inspections. The actions specified by this AD are intended to prevent undetected cracking of the frames and skin panels of the fuselage, which could result in reduced structural integrity of the airplane.
2002-23-12: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A (RR) Olympus 593 Mk. 610-14-28 turbojet engines. This action requires a one-time fluorescent penetrant inspection (FPI) of certain rebroached stage 5 high pressure compressor (HPC) disks, inspecting for cracks, and if necessary, removing cracked disks from service. This amendment is prompted by a manufacturer's analysis that concluded that the rebroaching process failed to achieve the anticipated life before being rejected for cracks and that the original cracks are not being removed. The actions specified in this AD are intended to prevent failure of the HPC stage 5 disk which could result in an uncontained engine failure and damage to the airplane.
2020-21-20: The FAA is superseding Airworthiness Directive (AD) 2019-23- 03, which applied to certain Dassault Aviation Model FALCON 900EX airplanes. AD 2019-23-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. This AD continues to require those maintenance or inspection program revisions, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-26-06: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-300 series airplanes. This action requires revising the Airplane Flight Manual to incorporate revised performance data for certain operations. This action is necessary to prevent operation in weight/altitude/temperature conditions that exceed the performance capabilities of the airplane, which could result in impact with terrain during engine out performance-limited operations. This action is intended to address the identified unsafe condition.