Results
2003-14-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections for cracking of the forward end clevis lugs of the flap track, and replacement of the flap track with a new flap track if necessary. That AD also currently provides for an optional modification of the forward end clevis lugs, which terminates the required inspections. This amendment expands the applicability of the existing AD, and requires new repetitive inspections for evidence of rotation or migration of the bushings or cracking of the lugs of the forward end clevis of the flap tracks that support the wing trailing edge flaps, corrective actions if necessary, and eventual accomplishment of a terminating action. These actions are necessary to prevent cracking and fracture of the forward end clevis of the flap track, which could result in reduced structural capability of the flap and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-12-11: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires a one-time ultrasonic inspection of the maneuvering actuator piston rod of the main landing gear (MLG) to ensure adequate wall thickness of the piston rods, and replacement of any discrepant piston rod with a new piston rod. 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 failure of the maneuvering actuator piston rod of the MLG, which would impede retraction of the MLG, and consequent reduced controllability of the airplane.
2003-14-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and Model ATR72 series airplanes; that requires replacement of a certain Automatic Takeoff Power Control System (ATPCS) test selector switch with a different test selector switch. This action is necessary to prevent shorting of a contact in the ATPCS test selector switch due to abnormal wear of contact surfaces, which could result in dual engine power drop with associated loss of both alternating current wild and main hydraulic power during ground maneuvers, and consequent reduced controllability of the airplane and increased flightcrew workload. This action is intended to address the identified unsafe condition.
2003-14-07: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/ 45 airplanes. This AD requires you to repetitively replace the nose landing gear (NLG) drag link right-hand part every 4,000 landings until an improved design NLG drag link right-hand part is installed. This AD also requires you to install an improved design NLG drag link right- hand part as terminating action for the repetitive replacements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent structural failure of the nose landing gear (NLG) caused by fatigue damage to the NLG drag link right-hand part that develops over time. Such failure could result in either an unintended NLG extension during flight or the NLG not properly locking upon extension, which could lead to loss of airplane control during landingoperations.
2003-14-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain transport category airplanes as listed above. This action requires modification of the reinforced flight deck door installed on the airplane. This action is necessary to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door. If an airplane crewmember is in close proximity to the flight deck door when the decompression panel opens, the decompression panel could hit and injure the crewmember. This action is intended to address the identified unsafe condition.
2003-13-15: This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters, that currently requires inspecting the lugs on certain aft cluster fittings and each aluminum end fitting on certain tailboom struts. Modifying or replacing each strut assembly within a specified time period and serializing certain strut assemblies are also required by the existing AD. This amendment requires the same actions as the existing AD, and also requires a one-time inspection and repair, if necessary, of certain additional cluster fittings, and replacement and modification of certain cluster fittings within 150 hours time-in-service (TIS) or 6 months, whichever occurs first. This amendment is prompted by the need to expand the applicability to include certain Hughes-manufactured cluster fittings and to provide a terminating action for the repetitive dye-penetrant inspections of the clusterfittings. The actions specified by this AD are intended to prevent failure of a tailboom support strut or a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.
2003-13-08: This amendment adopts a new airworthiness directive (AD) that applies to all Goodrich Avionics Systems, Inc. (Goodrich) TAWS8000 terrain awareness warning systems (TAWS) that are installed on airplanes. This AD requires you to inspect the TAWS installation and remove any TAWS where both the TAWS and any other device are connected to the same baro set potentiometer. This AD also prohibits future installation of any TAWS8000 TAWS that incorporates hardware "Mod None", "Mod A", or "Mod B". This AD is the result of a test that showed that TAWS8000 TAWS cause altitude errors in other instruments. The actions specified by this AD are intended to prevent the loading of the baro set potentiometer, which could result in an unacceptable attitude error. Such a condition could cause the pilot to make flight decisions that put the airplane in unsafe flight conditions.
2003-13-12: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) RB211-22B series turbofan engines with intermediate pressure (IP) compressor stage 6 to 7 rotor shaft assembly part number (P/N) UL37094 installed. This amendment requires removal from service of IP compressor stage 6 to 7 rotor shaft assemblies P/N UL37094 before reaching newly reduced life limits. This amendment is prompted by the discovery of corrosion during inspection and analysis of IP compressor stage 6 to 7 rotor shaft assemblies returned from the field. The actions specified by this AD are intended to prevent corrosion-induced cracking of the IP compressor stage 6 to 7 rotor shaft assembly, resulting in an uncontained engine failure and damage to the airplane.
2003-13-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, this amendment also requires a one-time inspection to determine if a tool runout procedure has been performed in the area. The actions specified by this AD are intended to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury. This action is intended to address the identified unsafe condition.
2003-12-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arriel 1 series turboshaft engines. This amendment requires initial and repetitive visual inspections for ingestive erosion, and cleaning if necessary, of M02 and M03 modules. This amendment is prompted by reports from the manufacturer of an unbalance due to accumulation of dust in the M03 module. The actions specified by this AD are intended to prevent an unbalance of the gas generator rotating assembly which may lead to deterioration of the gas generator rear bearing and uncommanded engine shutdown.