Results
96-24-11: This amendment adopts a new airworthiness directive (AD), applicable to all IAI, Ltd., Model 1123, 1124, and 1124A series airplanes, that requires repetitive inspections of the aileron push-pull tubes for excessive wear and the guide rollers for smooth rotation; and repair or replacement of worn parts with serviceable parts. This amendment is prompted by reports of excessive wear on the aileron push-pull tube in the area of the guide rollers. The actions specified by this AD are intended to prevent such wear, which could result in uneven movement of the control wheel, perforation of the aileron push-pull tube, and consequent reduced roll control of the airplane.
2011-10-08: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede two existing ADs. 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: DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 1992-106-132(B) * * * has been issued in order to mandate a set of inspections/modifications which address JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * The unsafe condition is reduced structural integrity of the wings, fuselage, and stabilizers. We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-09-18: 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: Following investigation of an in service event, it has been determined that in case a short circuit occurs on a weight-on-wheels (WOW) proximity sensor wiring, both circuit breakers that supply power to that wiring will trip, causing simultaneous de-power of all WOW proximity sensors of that part of the system. The loss of the corresponding WOW information would lead to untimely inhibition of warnings that could compromise the pilot capacity to react to abnormal or failure landing conditions. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-06-21: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive inspections to detect uneven wear of the heat pack of the main landing gear (MLG) brake unit; measurement and setting of the wear remaining length (WRL) of the wear indicator pin (WIP); and replacement of the brake heat pack unit with a serviceable unit, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect uneven wear of the brake heat pack unit and prevent failure of the pressure stator of the MLG brake unit, which could result in reduced braking efficiency and consequent longer stopping distances upon landing.
2002-26-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This amendment requires replacement of the emergency power switch knob on the overhead switch panel in the flight compartment with a new, improved knob made of non-conductive material. The actions specified by this AD are intended to prevent the knob from conducting electricity, which could result in delivery of an electrical shock and consequent injury to flightcrew or maintenance personnel. This action is intended to address the identified unsafe condition.
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.