Results
2001-17-32: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS350B, B1, B2, B3, BA, D, AS355E, F, F1, F2, and N helicopters. That AD requires inspecting certain versions of the tail rotor pitch change spider assembly (spider assembly) for the proper rotational torque, axial play, and any brinelling of the bearing. This AD requires identifying the spider assembly with index marks to detect bearing spacer rotation, visually checking to ensure that the index marks are aligned before the first flight of each day, and subsequently modifying the spider assembly. This AD also adds the ECF Model AS350D1 helicopters to the applicability. This AD is prompted by operator reports that the spider assembly bearing spacers are rotating. The actions specified by this AD are intended to detect rotation of the spider assembly bearing spacers, prevent seizure of the bearing, loss of tail rotor control, and subsequent loss of control of the helicopter.
2008-10-15: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD requires an inspection to determine if acceptable external skin doublers are installed at the stringer 6 (S-6) lap splices, between station (STA) 340 and STA 400. For airplanes without the acceptable external skin doublers, this AD requires repetitive related investigative actions and corrective actions if necessary. This AD also provides an optional terminating modification for the repetitive related investigative actions. This AD results from a report of cracked fastener holes at the right S-6 lap splice between STA 340 and STA 380. We are issuing this AD to detect and correct cracking in the fuselage skin, which could result in rapid decompression and loss of structural integrity.
95-14-02: This amendment supersedes Airworthiness Directive (AD) 91-24-15, which currently requires modifying the instrument air plumbing system on Beech Aircraft Corporation (Beech) Models 1900 and 1900C airplanes. This action requires an additional modification to the plumbing of the instrument air system on the Models 1900 and 1900C airplanes, and adds the Model 1900D airplanes to the applicability. Eight reports of moisture freezing in this system on airplanes with the modification required by AD 91-24-15 incorporated prompted this action. In addition, recent testing on the Model 1900D indicates that the design of the instrument air system on these airplanes is also conducive to moisture freeze-ups. The actions specified by this AD are intended to prevent ice formation in the plumbing of the instrument air system, which, if not detected and corrected, could result in aerodynamic problems and subsequent loss of control of the airplane.
2001-17-29: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 B2 and B4 series airplanes, and certain Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes. This action requires a one-time inspection to detect cracks in gear rib 5 (left and right) of the main landing gear (MLG) attachment fittings at the lower flange and vertical web, and repair if necessary. This action is necessary to detect and correct fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2001-17-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that requires a preventive modification of the front spar fitting on the outboard engine nacelle. This action is necessary to prevent fatigue cracking of the front spar fitting on the outboard engine nacelle, which could reduce the structural integrity of the nacelle, and result in separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
95-12-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747SP series airplanes, that currently requires repetitive inspections for cracks in the web of the wing front spar over engine numbers 2 and 3, and repair, if necessary. This amendment requires additional inspections in an area beyond that specified in the existing AD. This action also would provide for a new, optional modification, which, if accomplished, would constitute terminating action for the repetitive inspections. This amendment is prompted by a report of cracking in the web in an area outside the inspection zone specified in the existing AD. A crack in the web that is not detected before it extends outside the chord footprints can allow fuel leakage. The actions specified by this AD are intended to prevent fuel leakage onto an engine and a resultant fire due to cracking in the web of the wing front spar.
95-11-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-11-10 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R44 helicopters by individual letters. This AD requires installation of a placard in the helicopter, and insertion of a prohibition against low-gravity (G) cyclic pushover maneuvers into the LIMITATIONS section of the Rotorcraft Flight Manual. This amendment is prompted by a recent Federal Aviation Administration (FAA) analysis of the manufacturer's data that indicates a low-G cyclic pushover maneuver may result in mast- bumping on the Robinson Model R44 helicopters. The actions specified by this AD are intended to prevent in-flight main rotor separation or contact between the main rotor blades and the airframe of the helicopter, and subsequent loss of control of the helicopter.
2008-10-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A rupture of the alternator and vapour cycle cooling system pulley drive assembly has reportedly been found. Such a failure could lead to the loss of the alternator and vapour cycle cooling systems and could also cause mechanical damage inside the powerplant compartment. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-17-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspection of the aft trunnion of the wing landing gear for cracks and corrosion, and corrective action, if necessary. This amendment requires new repetitive inspections for cracks or corrosion of the aft trunnion outer cylinders of the wing landing gear, follow-on actions, and repetitive overhaul of the wing landing gear. The new actions also apply to airplanes not included in the applicability of the existing AD. The actions specified by this AD are intended to find and fix cracking or corrosion of the aft trunnion of the wing landing gear, which could result in collapse of the wing landing gear and consequent reduced controllability of the airplane.
95-11-09: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-11-09 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R22 helicopters by individual letters. This AD requires installation of a placard in the helicopter, and insertion of a prohibition against low-gravity (G) cyclic pushover maneuvers into the LIMITATIONS section of the Rotorcraft Flight Manual. This amendment is prompted by a recent Federal Aviation Administration (FAA) analysis of the manufacturer's data that indicates a low-G cyclic pushover maneuver may result in mast-bumping on the Robinson Model R22 helicopters. The actions specified by this AD are intended to prevent in-flight main rotor separation or contact between the main rotor blades and the airframe of the helicopter, and subsequent loss of control of the helicopter.