Results
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.)
51-28-01: 51-28-01 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. 1. Not later than the first No. 1 inspection after January 15, 1952, lag and shield propeller feathering line in the engine accessory section with asbestos tape, wire, vinylite tubing and steel-sleeve for end fittings as described in Convair Service Bulletin No. 240-419-A or in a manner to provide equivalent resistance to fire and absorption of fuel and oil. 2. Not later than March 1, 1952, revise the engine oil breather line to eliminate aluminum components as described in Convair Service Bulletin 240-419-A to use steel tubing or to use a fire resistant hose assembly. 3. Not later than first scheduled engine change after January 15, 1952, relocate fire detectors and revise detector circuits to employ split systems as described in Convair Service Bulletin Number 240-419-A. 4. Not later than the first scheduled engine change after January 15, 1952, replace fire detector wiring in all circuits forward of firewall with Rockbestos type RSS 74 Firezone wire or wire of equivalent fire resistance. (Wire conforming to Air Forces Spec. 32659 is considered equivalent.) 5. Not later than March 1, 1952, install CO2 operated engine accessory section ventilation outlet closure door. This modification is described in Convair Service Bulletin 240- 374. 6. Not later than the first scheduled engine change after March 1, 1952, either remove all aluminum fire detector terminal junction boxes located forward of the firewall and mount units on fireproof brackets, or change aluminum fire detector terminal boxes and brackets to fireproof material. 7. Not later than the first scheduled engine change after March 1, 1952, check firewalls and firewall access door fasteners to assure that no aluminum rivets or Dzus fasteners or other nonfireproof components have been installed. If any are found, they are to be replaced with fireproof components. Original firewall accessory door fasteners, which are satisfactory, have these Dzus part numbers: Studs AJ5-20 and -35; Grommet GA5-312; and Spring S5-200. 8. Not later than the first scheduled engine change after March 1, 1952, improve ADI valve sealing in accordance with Whittaker Service Bulletin Number 49-9 or install an enclosure which will provide overboard drainage if leakage occurs from this valve.
2006-10-12: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 airplanes and Model Avro 146-RJ airplanes. This AD requires repetitive replacement of the elevator servo tab hinge bearings, elevator servo tab mechanism bearings, elevator trim tab hinge bearings, and elevator trim tab drive rod bearings with new bearings. This AD results from reported incidents of flight control surface restrictions due to the deterioration of flight control surface bearings. We are issuing this AD to prevent corrosion of flight control surface bearings and freezing of moisture inside the bearings, due to loss of lubrication in the bearings, which could lead to flight control restrictions and result in reduced controllability of the airplane.
51-29-01: 51-29-01 BELL: Applies to All Models 47B, 47B3, 47D, 47D1 Helicopters. Compliance required as indicated. 1. Replace the tail rotor gearbox shaft, P/N 47-645-028-1 or 47-645-051-1, when it has accumulated 900 hours of operation. 2. Any shaft having already accumulated 900 hours of operation must be replaced by February 1, 1952. In the interim, conduct the following inspection after every 25 hours of operation: Remove tail rotor and inspect attachment bolt hole for cracks. Replace the shaft if a crack is found, or the hole is elongated over 0.010 inch. (Bell Service Bulletin No. 83 covers this same subject.)
2000-03-02: This amendment adopts a new airworthiness directive (AD), applicable to certain General Electric Company (GE) GE90 series turbofan engines, that requires reducing the cyclic life limits for certain fan mid shafts with undesirable microstructure, and removing from service those mid fan shafts prior to exceeding the new limits and replacing with serviceable parts. This amendment is prompted by reports of magnetic particle inspections conducted by the manufacturer identifying segregation in the raw material, resulting in lower fatigue life properties. The actions specified by this AD are intended to prevent fan mid shaft failure, which could result in a total loss of thrust and inflight engine shutdown.
70-22-01: 70-22-01 BEECH: Amendment 39-1094. Applies to Model 65-90 (Serial Numbers LJ-1 thru LJ-75) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent overheat damage and fire hazard which may result from failure of the ventilating air blower for the fuel burning heater during ground operations, accomplish the following: Within the next 50 hours' time in service, after the effective date of this AD, install Beech Differential Pressure Switch Kit No. 90-3053S in accordance with Beech Service Instruction No. 0372-412, or a later FAA approved revision or any equivalent modification submitted to and approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 24, 1970.