Results
2025-03-06: The FAA is superseding Airworthiness Directive (AD) 2017-22- 03, AD 2023-13-10, and AD 2024-04-03, which applied to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2017-22-03, AD 2023-13-10, and AD 2024-04-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD continues to require certain actions in AD 2023-13-10 and all actions in AD 2024-04- 03, and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2020-23-03: The FAA is superseding Airworthiness Directive (AD) 2017-09-05 for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2017-09-05 required repetitively checking screws in the emergency flotation gear. This new AD retains the requirements of AD 2017-09-05 but also requires installing a modification (MOD), which is a terminating action for the repetitive checks. This AD was prompted by the development of the MOD by Airbus Helicopters that addresses the unsafe condition. The actions of this AD are intended to address an unsafe condition on these products.
2003-15-01: The FAA is adopting a new airworthiness directive (AD) for certain McCauley Systems, Inc. propellers that are installed on BAE Systems (Operations) Limited Jetstream Model 4101 airplanes. This AD requires a fluorescent penetrant inspection (FPI) of the propeller blades for cracks. This AD is prompted by a report of a significant crack in a propeller blade shank and two reports of cracks in the hubs of the same propeller model. We are issuing this AD to detect cracks in the propeller blade shank that could cause a failure of the propeller blade and loss of control of the airplane.
81-10-09: 81-10-09 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4106. Applies to Model SA 365C series helicopters, certificated in all categories, which have skid type landing gear P/N 365A82.1370 and/or P/N 365A82.1400 installed, and either do not have tail ballast installed in accordance with Aerospatiale Drawing 365MR0351, or are not modified in accordance with Aerospatiale Service Bulletin Dauphin No. 53.04, dated May 10, 1979. Compliance required as indicated, unless already accomplished. To prevent failure of the tail rotor gearbox tripod mount assembly, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD, and every five hours thereafter, and prior to the first flight of each day, inspect the tail rotor gearbox tripod mount assembly, P/N 360A23.0024 (hereinafter referred to as TRGB mount assembly) for cracks in accordance with Aerospatiale Work Card No. 53.10.605, dated March 1979, or an FAA- approved equivalent. (b) If any crack or cracks are found, remove the TRGB mount assembly from service and replace with a new TRGB mount assembly, and thereafter inspect in accordance with paragraph (a) until compliance with paragraph (c) is accomplished. (c) Within the next 100 hours time in service: (1) Incorporate a tail ballast weight in accordance with Aerospatiale Dauphin Service Bulletin NO. 53.04, dated May 10, 1979, or an FAA-approved equivalent. (2) Remove the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, dated March 1979, or an FAA-approved equivalent. (3) Inspect the three leg-to-ring junction welds of the TRGB with Aerospatiale Standard Practice Manual, Section 02.80, dated August 1976, or an FAA-approved equivalent, and - (i) If no cracks are found, reinstall the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, dated March 1979, or an FAA-approved equivalent, and return to service. (ii) If any cracks are found, remove the TRGB mount assembly from service, replace with a new TRGB mount assembly, reinstall the tail rotor and tail rotor gearbox in accordance with Aerospatiale Work Card No. 65.42.401, or an FAA-approved equivalent, and return to service. (d) After accomplishment of paragraph (c) of this AD, the inspection requirements of this AD may be discontinued. (e) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to SocieteNationale Industrielle Aerospatiale (SNIAS), 37, blvd. de Montmorency, 75781 Paris Cedex 16, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective April 30, 1981, as to all persons except those persons to whom it was made immediately effective by the telegraphic AD issued May 25, 1979, which contained this amendment.
2001-24-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200C and -200F series airplanes, that requires installation of drip shields over certain shelves in the main equipment bay. This action is necessary to prevent water from dripping through floor panels of the main deck cargo bay onto wire bundles and electronic components, which could lead to the loss of function of multiple electronic components and, consequently, could reduce the flight crew's ability to operate in adverse conditions. This action is intended to address the identified unsafe condition.
2025-03-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reported events of annunciated horizontal stabilizer trim actuator (HSTA) jams occurring at the end of the cruise phase of flight. This AD requires lubricating the HSTA using an improved method, at a reduced interval, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-13-08: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000EX airplanes. This AD requires revising the airplane flight manual to include a procedure for addressing minimum fan speed rotation (N1) values during stand-alone engine anti-ice system operation for engines equipped with certain air inlets. This AD was prompted by a quality review of recently delivered airplanes which identified a manufacturing deficiency of some engine air inlet anti-ice piccolo tubes. We are issuing this AD to detect and correct reduced performance of the engine anti-ice protection system, leading to ice accretion and ingestion into the engines, which could result in dual engine power loss and consequent reduced controllability of the airplane.
2000-12-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect fatigue cracking or loose or missing fasteners of the aft torque bulkheads of the outboard nacelle struts; and repair, if necessary. This amendment expands the applicability of the existing AD to include certain additional airplanes, and removes certain other airplanes from the applicability of the existing AD. For all airplanes subject to this AD, this amendment also requires accomplishment of a new terminating action. This action is necessary to prevent fatigue cracking and loose or missing fasteners in the aft torque bulkheads of the outboard nacelle struts, which could result in failure of an outboard nacelle strut diagonal brace load path and possible separation of the nacelle from the wing. This action is intended to address the identified unsafe condition.
2025-03-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, 747-400F, 747-8F, and 747-8 series airplanes. This AD was prompted by a report that, during potable water servicing, there were multiple engine indicating and crew alerting system messages. The cause was the separation of a fitting and steel water supply tube above an electronics equipment cooling air filter, behind the forward cargo compartment left sidewall. This AD requires, depending on configuration, installing at certain locations: conduits on exposed potable water supply lines, envelope assemblies over all exposed potable water line fittings and exposed potable water supply lines, a slitted spray shield, a two-piece deflector shield around the equipment cooling system (ECS) air inlet, and/or a shroud on exposed potable water supply lines. The FAA is issuing this AD to address the unsafe condition on these products.
2024-04-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series 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, 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.
2015-12-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of corrosion found during the manufacturing process for some oxygen pipe assemblies that are used to supply oxygen to the flightcrew. This AD requires an inspection to determine the batch number or installation date of the oxygen pipe assembly that is installed at the end of the right-hand crew distribution line, and, if necessary, replacement of the pipe. We are issuing this AD to detect and correct corrosion, which could lead to blocked or reduced oxygen supply to a flightcrew member during a decompression event or a smoke/ fire event in the cockpit. Under certain conditions, corrosion particles could increase the risk of fire in the cockpit.
97-10-03: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires repetitive ultrasonic inspections to detect cracking of the lugs of the engine mounting beams, and replacement of the beam with a serviceable part, if necessary. This amendment is prompted by reports of fatigue cracking of the lugs of the engine mounting beams. The actions specified by this AD are intended to detect and correct such cracking of the engine mounting lugs, which could result in reduced structural capability of the engine mount.
2001-24-23: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes, that requires modification of the battery ground cable installation in the center accessory compartment (CAC). The actions specified by this AD are intended to prevent a loose ground stud and/or cable attachments, and consequent chafing of adjacent structure and electrical arcing, which could result in smoke/fire in the CAC in the event of fuel leakage. This action is intended to address the identified unsafe condition.
2023-13-10: The FAA is superseding Airworthiness Directive (AD) 2020-20-05 and AD 2022-09-16, which applied to certain Airbus SAS Model A318 series; A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, and -153N; A320 series; and A321 series airplanes. AD 2020-20-05 and AD 2022-09-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2022-09-16, 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. The FAA is issuing this AD to address the unsafe condition on these products.
2015-12-06: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 45 airplanes. This AD was prompted by reports of non-conforming windshield supports (coupe rails). This AD requires a general visual inspection of the coupe rails to detect gouging and scratches, and to determine if a radius has been removed; an ultrasound inspection to measure the dimensions of the lower coupe rails; an eddy current inspection to detect cracks of the lower coupe rails; replacement of [[Page 34259]] the lower coupe rails if necessary; and revision of the maintenance or inspection program, as applicable. We are issuing this AD to detect and correct non-conforming windshield supports, which could result in uncontrolled cabin depressurization and compromise of the capability of the windshield to withstand a bird strike.
98-21-34: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive inspections to detect corrosion and cracks on the bottom area of the wing skin, and corrective action, 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 and correct corrosion and cracks on the bottom area of the wing skin, which could result in reduced structural integrity of the airplane.
98-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model C-212 series airplanes, that requires a one-time inspection of the lower shaft and support structure of the rudder for corrosion, repair of any discrepancy found, and modification of the structure. 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 corrosion from developing in the lower shaft and support structure of the rudder, which could result in the failure of the rudder lower shaft and consequent reduced controllability of the airplane.
2021-04-18: The FAA is superseding Airworthiness Directive (AD) 2020-23- 02, which applied to all Airbus Helicopters Model EC225LP helicopters. AD 2020-23-02 required repetitive inspections of the bearing in the swashplate assembly of the main rotor mast assembly for discrepancies (ceramic balls that have a hard point or sensitive axial play or both) and, depending on the findings, replacement of an affected main rotor mast assembly with a serviceable main rotor mast assembly. Since the FAA issued AD 2020-23-02, the FAA has determined additional main rotor mast assemblies are affected by the unsafe condition. This AD continues to require the actions specified in AD 2020-23-02, and also includes additional affected main rotor mast assemblies; 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.
2015-12-03: We are superseding Airworthiness Directive (AD) 2007-13-05 for all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2007-13-05 required repetitive measurements of the freeplay of the right and left elevators, rudder, and rudder tab, and related \n\n((Page 34253)) \n\ninvestigative and corrective actions if necessary. This new AD requires repetitive freeplay inspections and lubrication of the right and left elevators, rudder, and rudder tab, and related investigative and corrective actions if necessary. This AD was prompted by the manufacturer's determination that the procedure for the rudder freeplay inspection does not properly detect excessive freeplay in the rudder control load loop. We are issuing this AD to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane.
98-04-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes, that requires activation of a spoiler function that allows partial ground spoiler activation with only one main landing gear compressed. 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 possible delays in deceleration when landing with strong cross winds and/or on a contaminated runway, which could increase the potential for landing overrun.
98-04-38: This amendment adopts a new airworthiness directive (AD), applicable to certain Cessna Model 500, 501, 550, 551, and 560 series airplanes, that requires revising the Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2019-14-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series 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 fuel airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2015-10-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of hydraulic fluid loss from the reservoir of the main landing gear (MLG) alternate extension system. This AD requires inspection for correct assembly of the MLG alternate extension system reservoir lid, and corrective action if necessary. We are issuing this AD to, in the event of a failure of the primary MLG extension system, prevent failure of the alternate MLG extension system to fully extend the MLG into a down-and-locked position, which could result in collapse of both left-hand and right-hand MLG sides during touchdown.
98-23-18: This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (Bell) Model 214B, 214B-1, and 214ST helicopters. This action requires a visual inspection of thin-flanged attachment barrel nuts (barrel nuts) manufactured by Kaynar Technologies, Inc. for cracks or lubrication residue, and replacement of the barrel nuts and corresponding attaching bolts, as necessary. These barrel nuts have been installed in main rotor grips, pitch horns, and tailboom assemblies. This amendment is prompted by a report of a cracked barrel nut, which was discovered on a helicopter being prepared for shipment. The actions specified in this AD are intended to detect cracks in a barrel nut, which could lead to failure of a main rotor grip, pitch horn, or tailboom, and subsequent loss of control of the helicopter.
2001-24-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model EC120B helicopters and currently requires adjusting the clearance of the cabin sliding door if necessary. This amendment requires adding an end stop to the front rail and modifying the rear stop of the middle rail to increase its adjustment range for certain cabin sliding doors. This amendment is prompted by an in-flight loss of a cabin sliding door, which had been locked in the open position. The actions specified by this AD are intended to prevent in-flight loss of a cabin sliding door, impact with the horizontal stabilizer or fenestron tail rotor, and subsequent loss of control of the helicopter.