Results
97-02-07: This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A300-600 and Model A310 series airplanes, that requires testing to verify if the smoke detection system can detect smoke within 60 seconds; and cleaning the installation and duct, if necessary. It also requires operators to submit a report of the test findings to the manufacturer. This amendment is prompted by a report that, during testing of the smoke detection system on in-service airplanes, the system failed to detect smoke within 60 seconds due to dust accumulation in the extraction ducts. The actions specified by this AD are intended to ensure that dust accumulation does not reduce the effectiveness of the smoke detection system and, consequently, lead to undetected smoke or fire in the lavatory of the airplane.
96-09-02: This amendment supersedes two existing airworthiness directives (AD), that are applicable to Airbus Model A310 and A300-600 series airplanes. One AD currently requires repetitive operational tests of feel and limitation computers (FLC) 1 and 2; the other AD requires replacement of certain FLC's on Model A300-600 series airplanes. Those AD's were prompted by reports indicating that the elevator control operated with stiffness. The actions specified by those AD's are intended to prevent stiff operation of the elevator control and undetected loss of rudder travel limitation function, which could adversely affect the controllability of the airplane. This new amendment requires installation of new FLC's, which terminates the currently required repetitive operational tests. This amendment also revises the applicability of the rule to delete airplanes on which these new FLC's have been installed previously.
96-09-07: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Boeing Model 757 series airplanes equipped with certain Abex spoiler actuator electro-hydraulic servo valves (EHSV) installed in certain spoiler actuators. The existing AD currently requires a one- time inspection of the spoiler actuator to determine if a suspect EHSV is incorrectly installed, and replacement of the EHSV, if necessary. That amendment was prompted by reports that a bias spring in the EHSV of certain spoiler actuators was found to be incorrectly installed. The actions specified by that AD are intended to prevent a significant control upset of the airplane as a result of problems associated with an incorrectly installed EHSV in the spoiler actuator assembly. This amendment adds additional suspect EHSV's that require inspection; it also corrects the actuator manufacturer's name and corrects the serial number of one EHSV.
2021-05-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model SA330J helicopters. This AD was prompted by report of failure of a second stage planet gear of the main gear box (MGB). This AD requires replacement of the MGB particle detector assembly with an improved, elongated MGB particle detector assembly, 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.
95-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Avro Model BAe 146 series airplanes. This action requires inspections to detect cracking and damage of the fastener holes in the butt strap at rib 2 at the lower surface of the right-hand wing; repair of discrepancies; and replacement of the fastener bolts. This amendment is prompted by a report that certain wings were manufactured with a reduction in the amount of edge margin between the fastener hole centers and the edge of the butt strap; this condition can result in a decrease in the long-term damage tolerance residual strength of the wing. The actions specified in this AD are intended to prevent cracking and other problems associated with a such decrease in the long-term damage tolerance residual strength of the wing.
96-01-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to verify that the attachment screws at a pressure switch located on the trim tank fuel transfer line are properly torqued, and that lockwires are installed. This amendment is prompted by reports of loose screws and missing lockwires at this attachment. The actions specified in this AD are intended to prevent loose or missing screws, which could allow fuel to leak from the pressure switch connection; if a leak were to occur during flight with a full trim tank, there would be no warning indication to the flight crew, and the airplane may not have enough fuel to complete the flight safely.
96-07-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect chafing of or damage to the wire bundle in the overhead switch panel of the cockpit, application of spiral wrap to the wire bundle, and corrective actions, if necessary. That AD was prompted by reports of chafed and shorted wires that resulted in smoke emanating from the overhead switch panel of the cockpit. This amendment expands the applicability of the rule to include certain Model DC-9 and MD-90-30 series airplanes, and C-9 (military) series airplanes. This amendment also adds a requirement to reroute the wire bundle to preclude chafing and damage. The actions specified by this AD are intended to prevent the potential for fire and uncontrolled smoke throughout the cockpit as a result of chafing and shorting in the electrical wire bundles.
2009-04-04: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, and 402B airplanes. This AD requires an inspection of the auxiliary wing spar near the location where the main landing gear trunnion is mounted for cracks; immediate replacement if cracks of 0.5 inch or more are found; repetitive inspections with replacement at a later time as long as cracks of less than 0.5 inch are found; and a report to the FAA and Cessna if any cracks are found. This AD results from several reports of fatigue cracking on the affected airplanes in the auxiliary wing spar. We are issuing this AD to detect and correct such cracks, which, if not corrected, could result in failure of the wing auxiliary spar web and cause landing gear collapse during normal landing. This could lead to loss of control and passenger injury.
2021-05-05: The FAA is superseding Airworthiness Directive (AD) 2016-23- 05, which applied to certain Airbus Helicopters Model SA-365N1, AS- 365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2016- 23-05 required repetitive checks of the oil level of the tail rotor gearbox and, if necessary, filling the oil to the maximum level; and replacement of a certain control rod double bearing (bearing) with a new bearing. This AD retains the requirements of AD 2016-23-05 and also requires modifying the helicopter by replacing the tail gearbox (TGB) control shaft guide bushes; repetitive inspections of the TGB magnetic plug and corrective actions if necessary; repetitive replacements of the bearing; and modifying the helicopter by replacing the TGB; as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. This AD also adds helicopters to the applicability. This AD was prompted by reports of occurrencesof loss of yaw control due to failure of the TGB bearing. The FAA is issuing this AD to address the unsafe condition on these products.
98-08-02: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires repetitive replacement of the universal joints and steady bearings of the flap transmission system with new parts at regular intervals, or overhaul. This amendment is prompted by a report of a malfunction of a universal joint in the flap transmission system on one wing due to fatigue failure. The actions specified by this AD are intended to ensure replacement or overhaul of certain universal joints and bearings of the transmission system when they have reached their maximum life limit. Failure of universal joints and bearings could lead to an asymmetric condition of the flaps, which could adversely affect controllability of the airplane.
96-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain AlliedSignal Inc. (formerly Garrett Engine Division) TPE331 series turboprop engines, that establishes cyclic retirement lives for certain compressor components. This amendment is prompted by manufacturer's engine testing and analysis that indicate that if these compressor components continue in service without an established retirement life, accumulative cyclic effects may result in a fatigue failure. The actions specified by this AD are intended to prevent fatigue failure of engine compressor components and an inflight engine shutdown.
95-25-08: This amendment adopts a new airworthiness directive (AD), applicable to Royal Inventum Company DR1 and DR6 Series Galley Water Heaters, that requires the installation of a pressure relief valve, and 3-phase safety devices on each Royal Inventum Company DR1 and DR6 series galley water heater. This amendment is prompted by a report of a Royal Inventum DR6 water heater explosion during an overheat test at a maintenance facility. The actions specified by this AD are intended to prevent explosions of Royal Inventum Company DR1 and DR6 series galley water heaters, which could cause personal injury or galley damage to the aircraft.
98-11-28: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe Avro 146-RJ series airplanes, that requires a one-time inspection of certain electrical wires in the electrical equipment bay to determine if ERMA terminal lugs are installed; and replacement with new parts, 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 failure of the electrical circuit terminal lugs, which could result in electrical system failure, and consequent reduced controllability of the airplane.
2021-04-01: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. (Leonardo) Model AB139 and AW139 helicopters. This AD requires removing certain forward facing center seats (seats). This AD was prompted by a design deficiency that affects seats on certain main cabin floor installations. The actions of this AD are intended to address an unsafe condition on these products.
96-02-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes, that currently requires visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly, if necessary. That amendment was prompted by several occurrences of failure of the rudder pedals adjuster hub assembly due to broken detent lugs. This amendment provides an optional terminating action for the required inspections, and expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent loss of rudder pedals control and reduction of braking capability.
2021-04-16: The FAA is adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD was prompted by the manufacturer discovering nonconforming threads, resulting in a life limit reduction on multiple landing gear components including threaded hinge pins and main landing gear (MLG) and nose landing gear (NLG) actuator pins. This AD requires a one-time inspection of the landing gear for components with non- conforming threads and removal of any nonconforming threaded hinge pin and MLG and NLG actuator pin. The FAA is issuing this AD to address the unsafe condition on these products.
98-09-21: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time inspection for corrosion of electrical connectors in certain areas on the pressure bulkhead and rear baggage bay areas, and repair, if necessary; and installation of improved sealing. 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 the accumulation of moisture inside the electrical connectors, which could result in a short circuit and consequent autopilot disconnect, or a latent failure of the stick pusher system.
98-06-19: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires draining and sealing of the ground spoiler and speed brake actuators. This action also requires replacement of the spoiler actuator assembly and the speed brake actuator assembly with modified actuator assemblies. 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 asymmetric deployment of the speed brakes during flight and consequent reduced controllability of the airplane; or failure of the ground spoilers to deploy during landing or rejected takeoff, which could result in increased aircraft stopping distances.
96-03-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires replacement of electrical wiring to the fuel shutoff valve for each engine. This amendment requires replacement of the fuel shutoff valve wire and sleeve with a wire in two non-metallic sleeves in the conduit in the struts of each engine. This amendment is prompted by reports of additional occurrences of chafing and shorting of the wiring of the engine fuel shutoff valves. The actions specified by this AD are intended to prevent such chafing and shorting, which could result in the pilot's inability to shut off the supply of fuel in the event of an engine fire.
2021-04-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, and AS350D helicopters; Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters; and Model EC130 B4 and EC130 T2 helicopters. This AD requires a one-time inspection to verify the presence and correct installation of the main rotor mast (MRM) upper bearing retaining rings, a repetitive inspection of the sealant bead on the MRM for damage, and corrective actions if necessary. This AD was prompted by a report of a missing retaining ring of the inner race of the MRM upper bearing. The actions of this AD are intended to address an unsafe condition on these products.
98-11-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection of the double shuttle valve in the upper fuselage fairing for incorrectly labeled part numbers, 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 ensure replacement of the double shuttle valves when they have reached their maximum life limit; incorrectly labeled part numbers of the double shuttle valves that are not replaced could result in the failure of the roll control spoilers, and, consequently, lead to reduced controllability of the airplane.
95-24-10: 95-24-10 MICHELIN AIRCRAFT TIRE CORPORATION: Priority Letter issued on November 21, 1995. Docket No. 95-CE-88-AD. Applicability: Part number (P/N) 028-520-1 (22x5.75-12/10PR) tires with the following serial numbers that are installed on the main landing gear of, but not limited to, Cessna Model 650 (Citation III, VI, and VII) airplanes that are certificated in any category: Serial Nos. Serial Nos. Serial Nos. Serial Nos. 4279N00339 4279N00340 4279N00341 4279N00342 4279N00343 4279N00597 4279N00598 4279N00599 4279N00600 4279N00601 4280N00075 4280N00199 4280N00200 4280N00201 4280N00203 4280N00204 4280N00205 4280N00206 4280N00360 4280N00361 4282N00352 4283N00099 4283N00100 4283N00101 4283N00102 4283N00200 4283N00201 4283N00202 4283N00453 4283N00454 4283N00455 4283N00456 4284N00612 4284N00613 4284N00614 4284N00615 4284N00616 4285N00100 4285N00101 4285N00102 4285N00103 4285N00104 4285N00105 4285N00106 4285N00107 4285N00108 4285N00347 4285N00348 4285N00349 4285N00353 4285N00354 4285N00355 4285N00356 4285N00608 4285N00609 4286N00103 4286N00104 4286N00105 4286N00106 4286N00442 4286N00443 4286N00444 4286N00445 4286N00446 4286N00447 4286N00448 4286N00449 4286N00450 4286N00600 4286N00601 4286N00602 4286N00603 4286N00604 4286N00605 4286N00606 4286N00608 4286N00609 4287N00088 4287N00089 4287N00090 4287N00091 4287N00092 4287N00093 4287N00094 4287N00095 4287N00096 4287N00097 4287N00357 4287N00358 4287N00359 4287N00360 4287N00361 4287N00362 4287N00363 4287N00364 4288N00118 4288N00119 4288N00120 4288N00121 4288N00302 4288N00303 4288N00304 4288N00305 4288N00306 4288N00307 4290N00111 4290N00113 4290N00114 4290N00115 4290N00116 4290N00117 4290N00355 4290N00356 4290N00606 4290N00607 4290N00608 4290N00609 4290N00610 4290N00611 4290N00612 4291N00082 4291N00083 4291N00084 4291N00085 4291N00086 4291N00087 4291N00088 4291N00089 4291N000914291N00273 4291N00274 4291N00275 4291N00276 4291N00277 4291N00278 4291N00620 4291N00621 NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required prior to further flight after receipt of this AD and thereafter upon installation of one of the affected tires, unless already accomplished. To prevent loss of control of the airplane during landing operations because of P/N 028-520-1 (22x5.75-12/10PR) tire failure, accomplish the following: (a) Replace any of the affected P/N 028-520-1 (22x5.75-12/10PR) tires with an FAA-approved tire. (b) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office (ACO), Campus Building, 1701 Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 2: Information concerning the existence ofapproved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (d) Copies of the applicable service information may be obtained from Michelin Aircraft Tire Corporation, 9700 Research Drive, Charlotte, North Carolina. This information may also be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (e) Priority Letter AD 95-24-10, issued November 21, 1995, becomes effective immediately upon receipt.
2004-03-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-1A10 and CL-215- 6B11 series airplanes, that currently requires repetitive inspections to detect cracking of main landing gear (MLG) axles that have been reworked by chromium plating, and replacement of cracked axles with serviceable axles. This amendment requires a dimensional check and follow-on corrective actions, mandates terminating action for certain airplanes, and adds three airplanes to the applicability in the existing AD. The actions specified by this AD are intended to prevent cracking of the inner bearing surface of the MLG axles, which could result in failure of an axle, subsequent separation of the wheel from the airplane, and consequent reduced controllability of the airplane during takeoff or landing. This action is intended to address the identified unsafe condition.
2021-02-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A330-900 series airplanes, Model A340-200 series airplanes, Model A340-300 series airplanes, Model A340-500 series airplanes, Model A340-600 series airplanes, Model A380-800 series airplanes; and Model A350-941 and -1041 airplanes. This AD was prompted by a report of a quality issue with a certain repair method of damage-through honeycomb core cargo linings by speed patches applied to both sides. This AD requires repair of each affected part, or replacement with a serviceable part, 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.
2004-03-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive general visual inspections, lubrication, and tests of the release mechanism for the service/emergency door; and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections and lubrication. This action is necessary to prevent failure of the release mechanism on the service/emergency door, which could result in the inability to open the service/emergency door during an emergency evacuation. This action is intended to address the identified unsafe condition.