Results
2018-02-07: We are adopting a new airworthiness directive (AD) for Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with a Helicopter Technology Company (HTC) main rotor (M/R) blade installed. This AD requires cleaning and visually inspecting the M/R blades and, depending on the outcome of the inspection, repairing or replacing the M/R blades. This AD is prompted by a report of an M/R blade with a fatigue crack in the grip plate and doublers at the blade retention bolt hole. The actions of this AD are intended to correct an unsafe condition on these products.
85-08-06: 85-08-06 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 5042. Applies to all Models P 68, P 68B, P 68C, P 68C-TC, and P 68 OBSERVER (Serial Numbers (S/N) 001 thru 335, XXX-01TC thru XXX-23TC, and XXX-26TC) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent the loss of aileron control, accomplish the following: (a) On all P 68 models from S/N 001 through S/N 335, safety lockwire the aileron cable chain safety lock, Part Number (P/N) 68-5.2017-3, as described in PARTENAVIA Service Bulletin (S/B) No. 64, Revision 1, dated September 10, 1984. (b) On all P 68, P 68B, P 68C, P 68C-TC, and P 68 OBSERVER Models from S/Ns 001 to and including 293, 305 and 312, except 261, 279, 284, 286, 290, 291, and 292 visually inspect the aileron control cable behind the engine compartment firewall for wear caused by rubbing against the cable guardplates as described in the Instructions of PARTENAVIA S/B No. 59, Revision 1, dated November 30, 1983, and replace any cables that exhibit wear damage as defined in this S/B. (c) On all P 68C-TC Models from S/N XXX-01TC to and including XXX-23TC, and XXX-26TC, replace aileron cable guard plates (P/Ns 1.2091B-1 and 1.2091B-2) as described in PARTENAVIA S/B No. 59, Revision 2, dated June 27, 1984. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance may be used, if approved, by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on May 28, 1985.
95-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10, -30, and -40 series airplanes, and KC-10 (military) airplanes, that requires inspections to detect corrosion or cracking of the lower front spar cap and the skin panel of the horizontal stabilizer, and repair of corroded or cracked parts. This amendment also requires eventual modification of the horizontal stabilizer, which terminates the inspection requirements. This action is prompted by reports indicating that corrosion, caused by water entrapment, was found on the horizontal stabilizer. The actions specified by this AD are intended to prevent water entrapment and subsequent damage to the horizontal stabilizer, which could result in reduced controllability of the airplane.
2002-22-10: This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTCL) Model 407 helicopters that requires visually inspecting the brackets that attach the horizontal stabilizer slat (slat) to the stabilizer for a crack. If a crack is found, that AD also requires replacing the slat assembly before further flight. Also, that AD requires installing airworthy, segmented slat assemblies by a specified date. Installing segmented slat assemblies was considered terminating action for the requirements of that AD. This amendment requires, initially and at certain time intervals, checking each slat assembly for a cracked bracket and, if a crack is found, replacing any unairworthy slat assembly with an improved, airworthy slat assembly. This amendment also requires replacing, modifying, and installing identification plates on slats on certain helicopters at specified time intervals. This amendment is prompted by two additional reports of cracked brackets. The actions specified by this AD are intended to prevent a slat from separating, contacting a rotor blade, and resulting in subsequent loss of control of the helicopter.
2024-04-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, 777-200LR, 777-300, 777- 300ER, and 777F series airplanes. This AD was prompted by reports of wing anti-ice (WAI) valve failure that can result in undetected structural damage to leading edge (LE) slat assemblies, and separately a failure of the autothrottle (A/T) to disconnect after the pilot manually advanced the throttle levers, which caused a low-speed condition during a go-around. This AD was also prompted by a determination that insufficient low-speed protection exists in the 777 fleet and a determination that the flightcrew may not recognize and properly respond to a multi-channel unreliable airspeed event. This AD requires installing certain new software and doing a software configuration check. The FAA is issuing this AD to address the unsafe condition on these products.
2002-22-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) FMC-4200, FMC-5000, and FMC-6000 flight management computers (FMC) that are installed on airplanes. This AD requires you to remove the affected FMC unit and replace it with a new FMC unit or an FMC unit that has been modified to correct a problem with the flight management system (FMS) accepting new information when an existing procedure or flight plan is changed. This AD is the result of a report that an aircraft proceeded beyond the published altitude constraint on an arrival procedure. The actions specified by this AD are intended to prevent the FMC from retaining and displaying original altitude constraints when an edit or a replacement is made to a procedure or flight plan that shares a waypoint with another procedure or an airway, and there is an altitude constraint on the shared waypoint. Such a condition could cause the pilot to fly the airplane out of the range of the correct altitude constraint. This condition could result in air traffic control or the pilot making flight decisions that put the airplane in unsafe flight conditions.
2025-09-08: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747 airplanes. This AD was prompted by a report that a right-hand outboard elevator was received and installed without balance weights. This AD requires doing a maintenance records check to determine if certain outboard elevators are installed or an inspection to determine if outboard elevators have balance weights, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
95-18-10: This amendment supersedes Airworthiness Directive (AD) 81-10-11, which currently requires repetitively inspecting the elevator root ribs for cracks on de Havilland DHC-6 series airplanes, and replacing any cracked part. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate, or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action requires modifying the elevator root rib as terminating action for the repetitive inspections currently required by AD 81-10-11. The actions specified by this AD are intended to prevent failure of the elevator root rib, which could result in loss of control of the airplane.
2018-02-01: We are superseding Airworthiness Directive (AD) 2015-08-51 for the Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280, F-28C, F-28C-2, F-28C-2R, 280C, F-28F, F-28F-R, 280F, 280FX, and 480 helicopters. AD 2015-08-51 required an inspection of the main rotor spindle (spindle) and reporting the inspection results to the FAA. This new AD was prompted by additional reports of cracked spindles and requires establishing a life limit and a recurring inspection. The actions of this AD are intended to prevent the unsafe condition on these products.
2002-22-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) LF507 and ALF502R series turbofan engines with combustion chamber liner assembly part number (P/N) 2-131-520-03 installed. This action requires initial and repetitive borescope inspections of the combustion chamber liner assembly to determine if the combustion liner assembly condition is acceptable for continued operation, requires the removal from service of certain serial number (SN) combustion chamber liner assemblies, and provides an optional terminating action to the repetitive borescope inspections. This amendment is prompted by three reports of separation of the combustor dome baffle from the combustion chamber liner assembly resulting in engine combustion chamber liner assembly burn through. The actions specified in this AD are intended to prevent separation of the combustor dome baffle from the combustion chamber liner assembly and the flow of hot combustor gases on oil and fuel lines which could result in engine fire, in-flight shutdown, and damage to the airplane.
95-22-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospace Lighting Corporation (ALC) lamp connectors and fluorescent lamps, that currently requires an inspection, and adjustment or replacement of improperly installed, damaged, or improperly configured lamp connectors and fluorescent lamps used in cabin fluorescent lighting systems. This amendment adds an optional replacement of certain power units and power supplies with new technology parts as terminating action to the repetitive inspections. This amendment is prompted by the availability of new technology components. The actions specified by this AD are intended to prevent smoke, fire, electrical shock, and possible electromagnetic interference caused by high voltage arcing in the cabin which, if undetected, could result in personal hazard or loss of the aircraft.
93-15-10: 93-15-10 THE ENSTROM HELICOPTER CORPORATION: Amendment 39-8766. Docket Number 93-SW-21-AD. Final Rule of a Priority Letter AD. Applicability: Model F-28A, F-28C, F-28C2, F-28F, 280, 280C, 280F, and 280FX helicopters equipped with composite-wrapped main rotor shaft, part number (P/N) 28-13183, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the main rotor shaft (shaft), loss of the main rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, after the effective date of this airworthiness directive (AD), perform a one-time inspection of the shaft in accordance with paragraph 5.1 of The Enstrom Helicopter Corporation Service Directive Bulletin No. 0083, dated July 16, 1993. (b) If the shaft is found with composite-wrapping separation, corrosion, red color residue or cracks during the inspections in paragraph (a) of this AD, remove the shaft from further service and install an airworthy shaft, P/N 28-13140-11 or P/N 28-13104-1. (c) If main rotor (M/R) vibrations occur that cannot be corrected with track and balance procedures; or, if M/R track and balance procedures are required more than once, replace the shaft with an airworthy shaft, P/N 28-13140-11 or P/N 28-13104-1, before further flight. (d) Within the next 10 hours' time-in-service, or at the next annual inspection after the effective date of this AD, whichever occurs first, remove the shaft, P/N 28-13183, and install an airworthy shaft, P/N 28-13140-11 or P/N 28-13104-1. (e) Installation of airworthy shafts, P/N 28-13140-11 or P/N 28-13104-1, constitutes terminating action for the requirements of this AD. (f) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Chicago Aircraft Certification Office, 2300 East Devon Avenue, room 232, Des Plaines, IL 60018. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Chicago Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago Aircraft Certification Office. (g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of only paragraphs (a) and (d) of this AD can be accomplished. (h) The inspection, removal and replacement shall be done in accordance with The Enstrom Helicopter Corporation Service Directive Bulletin No. 0083, dated July 16, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from The Enstrom Helicopter Corporation, Twin County Airport, P.O. Box 490, Menominee, Michigan 49858. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Boulevard, room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective January 28, 1994, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 93-15-10, issued August 3, 1993, which contained the requirements of this amendment.
95-22-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model Viscount 744, 745D, and 810 airplanes, that currently establishes time-in-service limits for components of the fuselage pressure vessel, and requires modifications and inspections of various fuselage components to assure the continued structural integrity of these airplanes through the manufacturer's design life goal. This amendment requires additional modifications and inspections of the fuselage pressure vessel to extend the fuselage pressure vessel life from 30 to 45 years since new. This amendment is prompted by results of a review of fatigue test findings, stress analysis, and in-service history associated with pressure vessel components. The actions specified by this AD are intended to prevent reduced structural capability of the fuselage pressure vessel.
2025-08-06: The FAA is superseding Airworthiness Directive (AD) 2021-09-14 which applied to certain Airbus Helicopters (Airbus) Model SA330J helicopters. AD 2021-09-14 required repetitively inspecting for a gap between the main gearbox (MGB) oil cooling fan assembly (fan) rotor blade and the upper section of the guide vane bearing housing, installing improved MGB fan rotor shaft bearings, and repetitively inspecting the improved MGB fan rotor shaft bearings. Since the FAA issued AD 2021-09-14, Airbus has developed modifications to the components of the MGB fan bearing assembly and issued new material regarding these modifications. This AD retains the actions required by AD 2021-09-14 and also requires installing the improved MGB fan rotor bearing assembly, which constitutes terminating action for the repetitive inspections. These actions are 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.
2002-22-03: This amendment adopts a new airworthiness directive (AD) that applies to certain PILATUS Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to repetitively inspect the main landing gear front attachment brackets for cracks, and, if cracks are found, install improved-design brackets. Installing the improved-design brackets terminates the required inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to detect and correct cracks in the main landing gear front attachment brackets, which could result in failure of the brackets. Such failure could lead to the main landing gear leg detaching from the wing main spar.
95-21-16: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires an inspection to detect evidence of sealant around the lug bushing flanges of certain actuator attach pin assemblies of the main landing gear (MLG), and replacement of the pin assembly with a serviceable unit if no sealant is present. This amendment is prompted by reports of cracks emanating from corrosion pits of the lug bores on the actuator attach pin assemblies of two MLG's. The actions specified by this AD are intended to prevent failure of the actuator attach pins as a result of corrosion and subsequent cracking of the lug bores. Such failure could result in the MLG failing to extend completely or rapidly free-falling during extension and causing additional damage to the landing gear.
98-09-27R1: We are rescinding an existing airworthiness directive (AD) for the products listed above. The existing AD, AD 98-09-27, resulted from aircraft certification testing which revealed that stresses on the thrust reverser hinge were higher than had been anticipated during engine certification, and the United Kingdom Civil Aviation Authority, issuing AD 008-03-97. Since we issued AD 98-09-27, we discovered that its requirements were duplicated in airplane-level AD 2001-09-14, issued by the FAA Transport Airplane Directorate. We proposed to rescind the engine-level AD.
2025-07-01: The FAA is adopting a new airworthiness directive (AD) for certain THOMMEN AIRCRAFT EQUIPMENT AG (THOMMEN) AC32 Digital Air Data Computers. This AD results from occurrences of AC32 Digital Air Data Computers (ADCs) that stop functioning below certain temperatures. This AD requires replacing an affected AC32 Digital ADC with a serviceable part. The FAA is issuing this AD to address the unsafe condition on these products.
2011-05-07: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires repetitively inspecting the interior and the exterior of the main tubular spar of the rudder assembly for corrosion, taking necessary corrective action if corrosion is found, and applying corrosion protection. This AD retains the requirements of the previous AD and changes the compliance time for certain products listed above. This AD was prompted by our determination that the compliance time specified for Models G-164, G- 164A, and G-164B airplanes does not adequately address the unsafe condition. We are issuing this AD to detect and correct corrosion in the rudder main tubular spar, which could result in failure of the rudder main spar tube. This failure could lead to loss of directional control.
2024-04-51: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) Model PT6A-64, PT6A-66, PT6A-66A, PT6A-66B, PT6A-66D, PT6A-67, PT6A-67A, PT6A-67AF, PT6A-67AG, PT6A-67B, PT6A-67D, PT6A-67F, PT6A-67P, PT6A-67R, PT6A-67RM, PT6A-67T, PT6A-68, PT6A-68D, PT6E-67XP, and PT6E-66XT engines. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these engines. This AD was prompted by reports of second-stage power turbine (PT2) blade failures. This AD requires removal of affected PT2 blades prior to the next flight and prohibits installation of affected PT2 blades, as specified in a Transport Canada Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-22-01: This amendment adopts a new airworthiness directive (AD) that applies to certain MORAVAN a.s. (Moravan) Models Z-143L and Z-242L airplanes. This AD requires you to modify the engine secondary vent line. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent the engine crankcase ventilation lines from freezing during flight in cold weather (winter) conditions, which could result in oil leaking from the engine. Such a condition could lead to engine failure.
2002-22-02: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2, BN-2A, BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD requires you to repetitively inspect the bottom corner of the engine mount bracket for cracks and replace any cracked bracket with a new one. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct cracks in the engine mount bracket. Such a condition could cause the engine mount assembly to fail, which could result in the engine separating from the airplane and lead to loss of control of the airplane.
2024-03-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of corrosion on lavatory floor fittings at various locations. This AD requires repetitive general visual inspections of the affected parts, applicable corrective actions, and reporting of the inspection results, 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.
2025-09-11: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company 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, and Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD was prompted by the discovery of jammed elevators during takeoff. This AD requires revising the "Certificate Limitations" section of the existing airplane flight manual (AFM) to include a procedure to confirm elevator surfaces are not jammed in the trailing edge down (TED) position. The FAA is issuing this AD to address the unsafe condition on these products.
96-18-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 60 airplanes, that requires modification of the aft core cowl nozzle of the engine nacelles. This amendment is prompted by a report that the sealant material in the aft core cowl nozzle of the engine nacelle was found to extend higher than the nozzle's forward flange, which can allow it to interfere with the proper operation of the emergency fuel shutoff actuating mechanism. The actions specified by this AD are intended to prevent physical interference of the emergency fuel shutoff actuating mechanism and resultant engine shutdown.