Results
2002-26-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-26-51 that was sent previously to all known U.S. owners and operators of certain EMBRAER Model EMB-135 and -145 series airplanes by individual notices. This AD requires revising the Limitations Section of the Airplane Flight Manual to advise the flightcrew of the possibility of locking of the elevator during takeoff and to provide the appropriate procedures to prevent it. This action is prompted by a report indicating that the elevator locked during the takeoff run on a Model EMB-145 series airplane. The actions specified by this AD are intended to prevent locking of the elevator during takeoff, which could result in loss of controllability of the airplane.
98-26-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection to verify correct installation of the lockplates of the roll spoiler actuators, and corrective actions, 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 prevent fatigue cracking of the fork flanges of the roll spoiler actuators due to incorrect installation of the lockplates, which could result in reduced structural integrity of the components of the roll spoiler actuators, and consequent reduced controllability of the airplane.
2011-10-12: We are adopting a new airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the aviation authority of the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The superseding MCAI AD states that several engine flameouts have involved failure of the 41-tooth pinion in the engine accessory gearbox. Each affected helicopter had a starter-generator manufactured by one company. Investigation revealed the torque damping system of the starter-generator was inoperative due to incorrect adjustment that caused bending stresses on the 41-tooth pinion. Failure of the pinion causes the engine fuel pump to stop operating, resulting in an engine flameout. The EASA AD requires a new adjustment procedure to optimize the performance of the specified starter-generator damping assembly. This AD is intended to prevent failure of a pinion and a fuel pump, engine flameout, and subsequent loss of control of the helicopter.
2011-10-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by the aviation authority of Italy to identify and correct an unsafe condition related to the rescue hoist hook installed on this model helicopter. The aviation authority of Italy, with which we have a bilateral agreement, states in the MCAI that a missing lock pin may cause the loss of the hoist hook and any load. The absence of the lock pin constitutes an unsafe condition, and this AD is intended to detect the presence of an identification plate marked ``BT 412-124,'' which indicates that the hook assembly has the lock pin installed to prevent the loss of a rescue hoist hook and its load.
97-07-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. It requires a one-time template inspection of the rear pressure bulkhead to detect dents; repetitive eddy current inspections of dents greater than a certain depth to detect cracking; and repair, if necessary. This amendment is prompted by a report indicating that cracking has been found in the vicinity of a dent in the rear pressure bulkhead of one airplane. The actions specified by this amendment are intended to prevent fatigue cracking resulting from a dent in the rear pressure bulkhead; that condition, if not corrected, could reduce the structural integrity of the bulkhead and, consequently, lead to rapid depressurization of the airplane.
2011-10-15: 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: Electrical discontinuity has been detected on terminal modules Part Number (P/N) NSA 937901M1604, manufactured by Deutsch, due to an insufficient crimping of the female contacts on the shunt, caused by a wrong setting of the crimping tool. * * * * * This condition, if not corrected, could potentially result in in-flight failure of the Electrical Flight Control System (EFCS) and consequent loss of control of the aeroplane. In addition, this condition could lead to a non detected passenger oxygen loss, which, in case of emergency, could result in a large number of passenger oxygen masks not being supplied with oxygen, possibly causing personal injuries. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-10-05: 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: A specific area, the lower tail plane cut-out located in the tail cone is subject to an inspection programme [for cracking] * * *. * * * * * The unsafe condition is reduced structural integrity of the tail cone. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-20-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of the struts for the stowage box located forward of galley 2. 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 prevent failure of the struts, which could result in displacement of the stowage box, and possible injury to passengers and flight crew.
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.
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.
96-23-18: This amendment adopts a new airworthiness directive (AD) that applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N24A, and N22S airplanes that are not equipped with a part number (P/N) 1E/N-12-57 fuselage stub fin plate (MOD N759). This action requires replacing the existing fuselage stub fin plate with one of improved design, P/N 1E/N-12-57. This action results from several reports of cracks along the forward flange of the fuselage stub fin plate in the area of Rib Water Line (WL) 138.87. The actions specified by this AD are intended to prevent structural failure of the fuselage area caused by a cracked stub fin plate, which could result in loss of control of the airplane.
2025-09-04: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Inc. Model BD-700-1A10 and BD-700-1A11 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. The FAA is issuing this AD to address the unsafe condition on these products.