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2011-27-51: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. This AD was prompted by reports of the elevator bob-weight (stabilizer weight) traveling past its stop bolt, which allowed the attaching linkage to move over-center, resulting in reduced nose down elevator control, which could result in loss of control of the airplane. We are issuing this AD to detect and correct conditions that could result in reduced nose down elevator control and loss of control of the airplane.
2003-04-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires you to inspect the alternating current (AC) inverter and modify the AC inverter and inverter sync wire shield. This AD is the result of reports that electrical noise causes the inverter to shut down in flight with loss of AC-powered flight instruments. The actions specified by this AD are intended to prevent electrical noise causing the inverter to shut down, which could result in failure of key aircraft electrical systems. Such failure could lead to loss of flight instruments during flight.
55-15-06: 55-15-06 LOCKHEED: Applies to 049, 149 Aircraft, Serial Numbers 1963 Through 1980, 2021 Through 2088; 649-749 Aircraft, Serial Numbers 2503 Through 2590, 2610, 2611, 2614 Through 2618; 1049C Aircraft, Serial Numbers 4501 Through 4548; 1049E Aircraft, Serial Numbers 4549 Through 4555, 4558, 4559, and 4563 Through 4565; 1049D Aircraft, Serial Numbers 4163 Through 4166. Compliance required by April 1, 1956, for Model 1049 aircraft and October 1, 1956, for Models 049/149 and 649/749 aircraft. To improve the fire-resistance integrity of the above aircraft, revisions to the system supplying cooling air to the accessory section of the powerplant installation are considered necessary. For 049-149 aircraft and 649-749 aircraft, the revision consists of installing a shutoff valve in a fireproof duct. For the 1049C and E aircraft, the revision consists of replacing a section of aluminum duct between the oil cooler scoop, and the existing shutoff valve, with a fireproof duct. This section is in zone 1, and provides a possible zone 1 to zone 2 firepath. Lockheed Service Bulletins 49/718, for 049/149 aircraft; 1049/2384, for 1049 aircraft; and 49/391A, for 649-749 aircraft, cover these subjects.
98-08-21: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB10 and TB200 airplanes. This AD requires inspecting the wing rear attachment fittings for cracks, replacing any cracked fitting, and incorporating wing rear attachment fitting reinforcement kits. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing rear attachment fittings caused by cracks in this area, which could result in the wing separating from the airplane if the airplane is operated with cracked wing rear attachment fittings over an extended period of time.
2003-04-09: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections for discrepancies of the internal fuselage skin panels located in the stub wing areas; and corrective action if necessary. This action is necessary to detect and correct heat damage to the fuselage skin panels caused by the leakage of hot air from one of the bleed air ducts inside the stub wing, which could result in reduced structural integrity of the engine support structure. This action is intended to address the identified unsafe condition.
2002-25-51: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-25-51, sent previously to all known U.S. owners and operators of the specified Agusta S.p.A. (Agusta) helicopters by individual letters. This Airworthiness Directive (AD) requires reducing the tail rotor (T/R) blade life limit and modifying and re-identifying the T/R hub and grip assembly. It also clarifies the never-exceed speed (Vne) restrictions and modifies the T/R visual inspection intervals. The actions specified by this AD are intended to prevent fatigue failure of the T/R blade and subsequent loss of control of the helicopter.
2003-04-13: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocoper) Model SA341G and SA342J helicopters. This action requires modifying an electric hoist (hoist) junction box (junction box). This amendment is prompted by the discovery of an anomaly affecting the resistor that is located in the junction box. The actions specified in this AD are intended to prevent failure of the hoist emergency load jettison switch, resulting in an inability of the pilot to cut the rescue hoist cable in the event of cable entanglement or other emergency and subsequent loss of control of the helicopter.
98-08-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires installing aluminum bonding bushings over certain screws in certain fuel tank underwing access panels. Several reports from the field revealing fuel tank access panels insufficiently electrically bonded to the airframe prompted this action. The actions specified by this AD are intended to prevent electrical arcing in the fuel tanks and detonation of the fuel-air mixture, which can be created by poor electrical bonding of fuel tank underwing access panels, and could result in a fire on the airplane.
98-08-27: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires modifying the airplane's left-hand (LH) front side lower panel. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent interference between the side trim of the LH front side lower panel and the roll control compass on the LH wheel assembly, which could result in loss of directional control of the airplane.
56-09-02: 56-09-02 MARTIN: Applies to All Models 202, 202A, and 404 Aircraft. Compliance required by September 1, 1956. In order to eliminate shearing of rivets securing the rudder torque tube flange, P/N 2021U42196, to the rudder torque tube, P/N 2021D19331, caused by gust buffeting with gust locks not engaged and resulting in loss of adequate and/or positive rudder control, it is necessary to replace the 3/16-inch rivets with 1/4-inch 24ST heat treated rivets. (Martin Service Instruction Letters No. 202/202A-36 and No. 404-69 cover this same subject.)