Results
68-03-04: 68-03-04 VICKERS: Amendment 39-551. Applies to Viscount Models 744, 745D, and 810 Series airplanes. Compliance required as indicated, unless already accomplished To detect cracking of the upper and lower torsion link hinge pins of the nose landing gear, accomplish the following: (a) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with less than 4,000 landings on the effective date of this AD, before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (b) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 4,000 or more landings but less than 9,000 landings on the effective date of this AD, within the next 1,000 landings after the effective date of this AD and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings, comply with paragraph (d). (c) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 9,000 or more landings on the effective date of this AD, within the next 500 landings or before the accumulation of 10,000 landings, whichever occurs later, and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (d) Remove pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins and inspect for cracks using Magnaflux examination or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 233, Issue 3 (700 Series) and No. 99, Issue 3 (800 Series), or later ARB-approved issued, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (e) If cracked hinge pins are found during the inspections required by paragraphs (a), (b) and (c), before further flight, replace the pins with serviceable pins of the same part number and comply with the inspection requirements of paragraph (a), or replace the pins with Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (f) The repetitive inspections required by paragraphs (a), (b) and (c) may be discontinued on those hinge pins replaced by Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective March 7, 1968.
98-05-11: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-215-6B11 (CL-215T) series airplanes. This action requires either replacement of the switching valve-to-rear inlet case sealing air tube assembly with a tube assembly that includes an integral fire detector (intercompressor case [ICC] fire detector loop), and modification of the nacelle fire detection system; or modification of the No. 5 bearing air system. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect internal engine fire within the ICC; or to prevent air/oil from leaking into the ICC, which could result in such fire.
2020-07-11: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by reports of interference and chafing between a propeller brake hydraulic pipe and an electrical wire bundle bracket screw installed in the underwing box of the right-hand (RH) engine nacelle. This AD requires modification of the electrical wiring routing in the engine nacelles, a one-time detailed visual inspection (DVI) of the propeller brake hydraulic pipe and electrical wire bundle bracket screw head in the underwing box of the RH engine nacelle and, depending on findings, accomplishment of applicable corrective actions, 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. \n\n((Page 20397))
2020-06-12: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD requires determining the accumulated hours time-in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment bolts and fittings, applying a life limit add-on factor, and inspecting the torque of certain MGB suspension bar attachment nuts. This AD was prompted by a report of torque loss on an MGB suspension bar bolt. The actions of this AD are intended to address an unsafe condition on these products.
99-16-05: This amendment adopts a new airworthiness directive (AD), applicable to Saab Model SAAB 2000 series airplanes, that requires repetitive inspections for excessive wear of the aileron control cables, cable guides, and cable pulleys located at the rear wing spars; and corrective actions, if necessary. This amendment also requires repetitive replacement of the control cables and cable guides with new or serviceable components. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness. The actions specified by this AD are intended to detect and correct excessive wear on the aileron control cables, cable guides, and cable pulleys located at the rear wing spars, which could result in broken aileron control cables and consequent reduced controllability of the airplane.
99-02-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models B300 and B300C airplanes (commonly referred to as Beech Models B300 and B300C airplanes). This AD requires modifying the elevator trim tab actuators by incorporating a new elevator trim tab actuator assembly kit, replacing the elevator trim tab pushrod assembly, or modifying the elevator spar opening, whichever is applicable. Reports from operators of ice forming on the elevator trim tab actuators and jamming the trim tab control prompted this action. The actions specified by this AD are intended to prevent jamming of the elevator trim tab actuator caused by ice formations, which could result in loss of control of the airplane.
2006-07-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100 and A319-100 series airplanes; Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive detailed inspections of the trimmable horizontal stabilizer actuator (THSA) attachments for proper clearances, and any crack, damage, or metallic particles; related corrective actions if necessary; and a report of the inspection results to the manufacturer. This AD results from a report that during lab testing to verify the performance of the THSA's secondary load path with a simulated failure of the THSA's primary load path, the secondary load path's nut did not jam (as it was supposed to do). We are issuing this AD to ensure the integrity of the THSA's primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane.
99-19-41: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires modification of the insulation pads in the lower side of the fuselage at the wing aft area. 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 loose insulation from interfering with an aileron control cable, which could result in reduced aileron control.
99-08-08: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive lubrication of the engine control push-pull cables, and installation of heating tubes on the control cables in the cockpit area and in the left-hand and right-hand engine balconies, which terminates the repetitive lubrication requirement. 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 ice from building up on the engine control push-pull cables, which could result in friction or jamming of the engine controls, and consequent reduced controllability of the airplane.
99-04-02: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive visual inspections for damage or "electrical spark marks" on the cover plates for the fuel pumps, and corrective actions, if necessary. This AD also requires modification of the fuel pump installation by incorporating a non-conductive film on the cover plate, which constitutes terminating action for this AD. 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 electrical shorting between the fuel pump electrical connections and the fuel pump cover plate, which could result in the ignition of fuel vapor and consequent fuel tank explosion/fire.