Results
2022-02-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC120B helicopters. This AD was prompted by a report of geometrical non-conformities in the tail rotor blade (TRB) root section discovered during an accident investigation of a Model EC130B helicopter. Due to the similarity of design and production requirements, certain TRBs for the Model EC120B helicopters were inspected and geometrical non-conformities were also found. This AD requires an inspection (dimensional check) to verify conformity, and replacement of certain TRBs if necessary, 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.
47-10-37: 47-10-37 LOCKHEED: (Was Service Note 8 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2071. At periods not to exceed 500 hours, check the tightness of the inboard pair of bolts in the outboard fulcrum and the outboard pair of bolts in the inboard fulcrum of each main landing gear, using a torque wrench. A continuous record should be kept to show whether these bolts become more loose with time; therefore, these bolts should not be tightened during the periodic inspections. When any of these 8 bolts loosen to a torque wrench reading of approximately 900 inch-pounds, all fulcrum bolts (16 per airplane) should be removed, the fitting holes countersunk 0.064 x 45 degrees to accommodate the bolt head fillets, the bolts replaced and tightened to a torque wrench reading of 2,300-2,500 inch-pounds. The 500-hour inspection may then be discontinued. (Lockheed Service Bulletin 49/SB-51, revised March 3, 1947, covers this same subject.)
2022-02-07: 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 reports of wear damage found between the bonding clamps and the fuel feed tubes inside the left- and right-hand fuel tanks. This AD requires repetitive inspections of the fuel feed tubes for damage, replacement if necessary, and modification of the fuel feed line installation inside the left- and right-hand fuel tanks, which would terminate the repetitive inspections, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-13-23: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-82 (MD-82) and DC-9-83 (MD-83) airplanes; and Model MD-88 airplanes, that requires inspection of the captain's and first officer's seat track locking pins for insufficient engagement caused by seat track misalignment, and corrective actions if necessary. This action is necessary to prevent uncommanded movement of the captain's and first officer's seats during takeoff and landing, which could result in interference with the operation of the airplane and consequent temporary loss of control of the airplane. This action is intended to address the identified unsafe condition.
48-34-02: 48-34-02 Applies to All Aircraft Engaged In Sulphur Dusting. Replaces Airworthiness Maintenance Bulletin No. 63. Compliance at time of original certification or if previously certificated and Airworthiness Maintenance Bulletin No. 63 has not been complied with compliance required by October 1, 1948. To decrease the hazards from fire during dusting operations involving the use of sulphur dust the following fire preventive measures, formerly in Airworthiness Maintenance Bulletin No. 63 must be complied with: (1) The engine exhaust system must be so arranged that it will not discharge exhaust gases under or along the bottom of the airplane. (2) The fuselage aft of and in the vicinity of the hopper must be completely bonded. All fittings and struts adjacent to the hopper should be bonded to each other and the hopper to the fuselage. (3) The agitator should be provided with sealed bearings or the bearings should be readily accessible for lubrication. (4) The hopper gate should be of nonferrous material, well fitted to irs guide channels to prevent friction and accumulation of dust in the channels and should be bonded to the hopper. (5) The lower surface of the fuselage, in the immediate vicinity and 3 feet aft of the spreader discharge opening must be covered with thin-gage metal, plywood or equivalent fire resistant material. Where fabric on the bottom of the fuselage is not eliminated in this installation, the protective covering, to be installed on the outside of the fabric, must be secured in such a manner that will prevent accumulation of dust between the protective covering and the fabric. This may be accomplished by using sealants such as acetate doped fabric tape or other adhesives to bond the protective covering to the fabric. Aircraft which do not comply with these measures shall be restricted, against the use of sulphur for dusting, on the operation limitations.
99-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time detailed visual inspection of the outboard sequence carriage attachment fitting for the presence and condition of a shim and any loose fastener, and follow-on corrective actions, if necessary. This amendment is prompted by a report that a piece of the left wing inboard foreflap came off during a landing approach and struck and penetrated the airplane fuselage. The actions specified by this AD are intended to prevent the failure of the outboard sequence carriage fitting, which could allow the wing inboard foreflap to separate and penetrate the fuselage, possibly injuring passengers and crewmembers.
2004-14-03: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a one-time inspection of the ailerons to determine if certain actions were accomplished previously, and related investigative and corrective actions if necessary. This action is necessary to prevent damage to the rear spar rib-to-rib attachment cleats and the aft rib elements of the fixed tabs of the ailerons. Such damage could lead to reduced structural integrity and consequent failure of the ailerons, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
99-04-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires inspections to detect discrepancies of the support straps of the flaps and adjacent areas, and corrective action, if necessary. This amendment also requires replacement of the support straps with new straps made of steel. 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 fatigue cracking of the support straps of the flaps, which could result in further damage to the flap structure, and consequently lead to reduced controllability of the airplane.
2022-01-07: The FAA is superseding Airworthiness Directive (AD) 2021-11- 23, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-11-23 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and, for certain airplanes, updating the hydraulic monitoring system to include additional redundancy. Since the FAA issued AD 2021-11-23, the FAA has determined 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. This AD also revises the applicability to include different airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-400 airplanes. That AD currently requires revising the Normal and Abnormal sections of the airplane flight manual (AFM) to include procedures that enable the flightcrew to determine if the main landing gear (MLG) is extended before landing, and to take appropriate actions if necessary. This amendment adds an airplane to the applicability, and requires replacing the existing MLG downlock proximity sensors with new, improved sensors. After the replacement, this action also requires removing from the AFM the revision to the Normal and Abnormal sections required by the existing AD. The actions specified by this AD are intended to prevent failure of the MLG downlock proximity sensors on the same MLG at the same time, which could result in the MLG's failure to extend during landing, and cause injury to flightcrew and passengers. This action is intended to address the identified unsafe condition.