Results
2000-03-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C helicopters, that currently requires visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment requires the same actions required by the existing AD, visually inspecting the four half-shell attachment clamps for cracks, and fitting a safety wire around the attachment clamps. This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation of the horizontal stabilizer and impact with the main or tail rotor, and subsequent loss of control of the helicopter.
94-26-14: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 series airplanes, that requires inspections to detect cracks in the chassis side bracing structure and in the chassis top strut support intercostals inside the wings, and replacement of discrepant parts with new parts. This proposal would also require inspection of the intercostals to determine the specification of the material, if necessary; and replacement of discrepant parts with new parts. This amendment is prompted by a report of cracking in the chassis top strut support intercostal in the side bracing structure inside the wing due to the effects of metal fatigue. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could lead to the failure of the chassis side bracing structure inside the wings and consequent reduced structural integrity of the chassis support structure.
2003-16-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -100B, -100B SUD, -200B, - 200C, -200F, -300, -400, -400D, and -400F series airplanes; and Model 747SR series airplanes. For certain airplanes, this AD requires repetitive inspections of the clevis bushings on the inboard and outboard sequence carriages of the wing foreflap for bushing migration, and corrective action if necessary; replacement of existing bushings with new bushings, which terminates the repetitive inspections; and replacement of the bushing markers with new markers, if necessary, to indicate the correct bushing orientation. For certain other airplanes, this AD requires a one-time inspection to determine whether the bushings are in the correct orientation, and follow-on actions. The actions specified by this AD are intended to prevent the loss of an inboard trailing edge foreflap during flight, and subsequent damage to the airplane in flight. This action is intended to address the identified unsafe condition.
2020-19-06: The FAA is adopting a new airworthiness directive (AD) for certain model McCauley Propeller Systems (McCauley) governors installed on airplanes. This AD was prompted by reports of an unapproved variant McCauley idler gear bearing, part number (P/N) A-20028, that could be installed in the affected governors. This AD requires replacing the governor with a governor that is eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2000-03-04: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This amendment requires removal from service of affected fan mid shafts prior to reaching a new, lower cyclic life limit, and replacement with serviceable parts. This amendment is prompted by recent component test data. The actions specified by this AD are intended to prevent fan mid shaft failure, which could result in an uncontained engine failure and damage to the aircraft.
2003-15-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that currently requires repetitive visual checks or inspections to verify that the flight idle stop system circuit breakers are closed, and functional tests to determine if the backup flight idle stop system is operative. This amendment requires modification of the secondary flight idle stop system (SFISS), which terminates the repetitive actions. 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 inadvertent or intentional operation with the power levers below the flight idle stop during flight for airplanes that are not certificated for in-flight operation, which could result in engine overspeed and consequent loss of controllability of the airplane.
2020-19-10: The FAA is adopting a new airworthiness directive (AD) for Piaggio Aero Industries S.p.A. Model P-180 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 insufficient sealing of a steering select/bypass valve installed in the nose landing gear (NLG) manifold. The FAA is issuing this AD to address the unsafe condition on these products.
2020-20-06: The FAA is adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 429 helicopters. This AD requires repetitive inspections of certain cyclic and collective assembly bearings. This AD was prompted by reports that precipitation can lead to reduced effectiveness of the grease in the bearings. The actions of this AD are intended to address an unsafe condition on these products.
2000-02-36: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires relocation of the engine/master 1 relay from relay box 103VU to shelf 95VU in the avionics bay. This amendment continues to require the relocation using new electrical contacts, and, for certain airplanes, adds a requirement to replace certain contacts installed in shelf 95VU during relocation of the relay with new contacts. 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 a simultaneous cutoff of the fuel supply to both engines, which could result in a loss of engine power and consequent reduced controllability of the airplane.
59-18-04: 59-18-04 LOCKHEED: Applies to All Models 1049C, 1049D, 1049E, 1049G and 1049H Aircraft. Compliance required as indicated. The following inspections have been established as a result of recently found cracking in the inner wing rear spar web at Wing Station 458. At the next block overhaul or 4,000 flight-hours, whichever occurs first, on all aircraft (regardless of accumulated flight time) inspect the inner wing rear spar web at Station 458 for cracks in the upper and lower notched web area shown in Lockheed Drawing 555353. Inspection is applicable to both left and right wings. If cracks are discovered incorporate the reinforcements shown in Lockheed Drawing 555353, or equivalent. If no cracks are discovered, the reinforcements shown in Lockheed Drawing 555353 may be incorporated. Otherwise, reinspection at 4,000 flight-hour periods or block overhaul, whichever is less, is required to insure detection of cracks. (Lockheed Service Letter FS/231094 covers thissame subject.)