Results
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.