45 Airworthiness Directives: 35 airplane, 5 rotorcraft, 4 engine, 1 glider.
AD 99-27-05 · published Jan 4, 2000, effective Feb 8, 2000
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes, that requires replacement of the hydraulic reducer fitting in the return port of the alternate brake selector valve with a new restrictor fitting. This amendment is prompted by a report indicating that a brake housing had fractured due to high loads associated with brake vibration during landing gear retraction, which allowed the torque rod to swing free. The actions specified by this AD are intended to prevent failure of the brake housing in the torque rod region, which could reduce the braking capability of the airplane and/or prevent the extension of a main landing gear by any method.
AD 99-27-07 · published Jan 4, 2000, effective Feb 8, 2000
Airbus Model A300 B4-600R and A300 F4- 600R Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-600R and A300 F4-600R series airplanes, that currently requires a one-time visual inspection for damage of the center tank fuel pumps and fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This amendment also requires repetitive visual inspections of the fuel pumps and repetitive eddy current inspections of the fuel pump canisters, and replacement of damaged fuel pumps and fuel pump canisters with new or serviceable parts. This amendment also reduces the applicability to include only those airplanes that have a trim tank system installed. 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 detect damage to the fuel pump and fuel pump canister, which could result in loss of flame trap capability and could provide a fuel ignition source in the center fuel tank.
AD 99-27-08 · published Jan 4, 2000, effective Feb 8, 2000
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive inspections of the control quadrant for loose screws, and replacement of the control quadrant with a modified part, which constitutes terminating action for the repetitive inspections. 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 the power levers from binding due to the backing out of screws that secure the solenoid bracket within the flight idle stop assembly, which could result in the malfunction of the flight idle stop mechanism and the override function, and the inability to move the power levers aft of flight idle.
AD 99-27-09 · published Jan 4, 2000, effective Jan 19, 2000
Airbus Model A300 B4-203 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-203 series airplanes. This action requires repetitive inspections of the attachment bolts of the brake bar on the main landing gear (MLG) to detect missing or damaged bolts, and replacement with new bolts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent detachment of the brake bar from the MLG strut, which could result in failure of the main landing gear to extend.
AD 99-27-10 · published Jan 4, 2000, effective Feb 8, 2000
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires wiring modifications to the engine and auxiliary power unit (APU) fire detection system. 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 the fire warning from terminating prematurely, which could result in an unnoticed, uncontained engine/APU fire.
AD 99-27-11 · published Jan 4, 2000, effective Feb 8, 2000
British Aerospace Model BAC 1-11 200 and 400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to to all British Aerospace Model BAC 1-11 200 and 400 series airplanes, that requires replacing the thrust reverser control unit selector valve with a new or modified valve and inspecting for proper rigging of the thrust reverser cable drums and thrust reverser control unit selector valve detent, and corrective actions, if necessary. This amendment also requires revising the Airplane Flight Manual to provide the flight crew with procedures to address uncontrolled operation of the thrust reverser system. 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 provide the flight crew with procedures in the event of uncommanded deployment of the thrust reverser, and to prevent uncommanded deployment of the thrust reverser in flight or on the ground, which could result in reduced controllability of the airplane.
AD 99-27-13 · published Jan 6, 2000, effective Jan 21, 2000
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 050 series airplanes. This action requires using a torque wrench to repetitively tighten the screws for the attachment of the leading edges of the elevators, rudder, and ailerons. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent loose attachment screws on the leading edges of the elevators, rudder, and ailerons due to vibration, which could result in interference with adjacent structure and consequent reduced controllability of the airplane.
AD 99-27-14 · published Jan 6, 2000, effective Jan 21, 2000
Airbus Model A340-211, -212, -213, - 311, -312, and -313 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A340-211, -212, -213, -311, -312, and -313 series airplanes, that currently requires repetitive operational tests to ensure proper operation of the actuator of the secondary locks of the thrust reversers, and corrective actions, if necessary. The previously optional modifications that would have allowed an extension of the repetitive test intervals have been removed from this amendment. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the inadvertent opening of a thrust reverser door in the event of failure of the primary and secondary locks of the thrust reverser. Such inadvertent opening could result in reduced controllability of the airplane.
AD 2000-01-05 · published Jan 7, 2000, effective Jan 24, 2000
Boeing Model 747 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD) applicable to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane. This action identifies certain repetitive operational checks that were inadvertently omitted from the existing AD, and revises certain procedures for accomplishment of the operational checks and certain follow-on corrective actions.
AD 2000-01-01 · published Jan 11, 2000, effective Feb 15, 2000
Airbus Model A300 B2-1A, B2-1C, B2-203, B2K-3C, B4-103, B4-2C, and B4-203 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2-1A, B2-1C, B2-203, B2K-3C, B4-103, B4-2C, and B4-203 series airplanes, that requires modification of the wire harness routing next to the pitch artificial feel unit, and removal of the green and yellow colors from various connectors. 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 the electrical connections of the actuators of the green and yellow hydraulic systems for the pitch artificial feel unit from being cross connected due to the design of the wire harness routing, which could result in a stiff elevator control at takeoff, and consequent reduced controllability of the airplane.
AD 2000-01-02 · published Jan 11, 2000, effective Feb 15, 2000
Raytheon Model BAe.125 Series 1000A and 1000B Airplanes and Model Hawker 1000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model BAe.125 series 1000A and 1000B airplanes and Model Hawker 1000 series airplanes, that requires an inspection to determine the integrity of the duct connection on both ends of the turbine air discharge duct in the air conditioning system; an inspection to measure the bead height on the ends of the turbine air discharge duct; and corrective actions, if necessary. This amendment is prompted by reports indicating that the turbine air discharge duct disconnected from the cold air unit (CAU) or water separator due to insufficient bead height on the ends of the turbine air discharge duct. The actions specified by this AD are intended to prevent such disconnection from the CAU or water separator, which could result in cabin depressurization.
AD 98-19-15 R1 · published Jan 11, 2000, effective Mar 3, 2000
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This amendment revises Airworthiness Directive (AD) 98-19-15, which currently requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement for Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with Barber- Colman pitch trim actuators, part number (P/N) 27-19008-001/-004 or P/N 27-19008-002/-005. Since AD 98-19-15 became effective, improved design pitch trim actuators have been developed that, when installed, will eliminate the speed restriction and minimum pilot requirements of the current AD. This AD requires incorporating these installations as a method of complying with the current AD. The actions specified by this AD are intended to lessen the possibility of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
AD 2000-01-03 · published Jan 12, 2000, effective Feb 16, 2000
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a measurement of the extension of the piston in the retract actuator of the main landing gear (MLG); and corrective action, if necessary. This amendment also requires repetitive replacement of the retract actuator with a repaired retract actuator, or repetitive replacement of the piston in the retract actuator with a new piston. 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 failure of the piston in the retract actuator of the MLG, and reduced structural integrity of the MLG.
AD 2000-01-04 · published Jan 12, 2000, effective Feb 16, 2000
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Saab Model SAAB 2000 series airplanes, that requires a one-time general visual inspection to verify the proper orientation of the aft exterior light; and corrective actions, if necessary. 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 improper illumination of the ground under the service door due to incorrect installation of the aft exterior light, which could result in injury to the passengers or crew members during an emergency evacuation.
AD 2000-01-07 · published Jan 12, 2000, effective Jan 27, 2000
Bombardier Model DHC-8-100, -200, and - 300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes. This action requires the removal and testing of sections of bonded skin from the upper and lower skin panels of the horizontal stabilizer, repair of those areas, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent reduced strength capability and consequent failure of the horizontal stabilizer, which could result in loss of controllability of the airplane.
AD 2000-01-08 · published Jan 12, 2000, effective Feb 16, 2000
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes, that requires a one-time inspection of the orientation of certain bolts of the rudder standby control system (SCS), and reinstallation of the bolts, if necessary. 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 uncommanded engagement of the rudder SCS, which could result in reduced controllability of the airplane.
AD 2000-01-10 · published Jan 12, 2000, effective Mar 3, 2000
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-08- 07, which currently requires replacing the rudder and elevator pivot arms with parts of improved design on certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires replacing the rudder and elevator pivot arms with parts that have been improved since issuance of AD 98-08-07. 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 failure of the elevator and rudder caused by fatigue cracking of the pivot arms, which could result in reduced airplane controllability and possible loss of control of the airplane.
AD 2000-01-12 · published Jan 13, 2000, effective Feb 17, 2000
Bombardier Model CL-600-2B19 (Regional Jet Series 100) Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes, that currently requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This amendment revises the repetitive inspection intervals for certain airplanes, and requires modification or repair, as applicable. This amendment is prompted by the development of a modification that will adequately address the identified unsafe condition. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
AD 2000-01-14 · published Jan 14, 2000, effective Feb 18, 2000
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires the replacement of fuse pins in the attachment fittings and support fittings of the main landing gear with new, improved fuse pins. This amendment is prompted by a report of corrosion of a fuse pin of a similar design on the main landing gear of a Boeing Model 767 series airplane. The actions specified by this AD are intended to prevent corrosion and subsequent fracture of the fuse pins, which could result in collapse of the main landing gear and the loss of the inboard flap and spoilers.
AD 2000-01-15 · published Jan 14, 2000, effective Jan 31, 2000
Fokker Model F27 Mark 050 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. For certain airplanes, this action requires modification of the electrical power supply of the landing gear anti-skid unit. For certain airplanes, this action also requires a revision to the Airplane Flight Manual (AFM) to provide the flight crew with procedures for calculating the accelerate-stop distance for certain conditions, and installation of a new ground idle stop assembly and new placards on the top cover of the pedestal, which terminates the requirements for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interruption of the anti- skid system function, or inadvertent selection of reverse thrust during a rejected takeoff. Either of these conditions could result in reduced controllability of the airplane.
AD 99-26-21 · published Jan 14, 2000, effective Jan 31, 2000
Boeing Model 737-300, -400, -500, -600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-300, -400, -500, -600, -700, and -800 series airplanes. This action requires a one-time detailed visual inspection of certain wire bundles and hydraulic hoses for the electric motor driven pump (EMDP) for hydraulic system ``B'' located in the right main wheel well to detect discrepancies; and corrective actions, if necessary. This amendment is prompted by a report that the wire bundle to the EMDP had been chafed by the pressure hose for hydraulic system ``B'' on a Model 737-700 series airplane, and reports of failed or damaged case drain or pressure hoses on the EMDP for hydraulic system ``B'' on Model 737-400 series airplanes. The actions specified in this AD are intended to prevent electrical arcing due to chafing between certain hydraulic hoses and adjacent wire bundles, which could result in a consequent increased risk of fire.
AD 2000-01-16 · published Jan 19, 2000, effective Feb 15, 2000
Cessna Aircraft Company Airplanes
This amendment supersedes Airworthiness Directive (AD) 75-23-08 R5, which currently requires repetitively inspecting and replacing or repairing the exhaust system on certain Cessna Aircraft Company (Cessna) 300 and 400 series airplanes. The requirements of this AD replace the inspections and replacements that are required by AD 75-23-08 R5 with inspections and replacements containing new simplified procedures for all 300 and 400 series airplanes (models affected by the current AD plus additional models). This AD also revises the inspection intervals and requires replacing certain unserviceable parts and removing the exhaust system for a detailed inspection. This AD is the result of numerous incidents and accidents relating to the exhaust systems on Cessna 300 and 400 series airplanes dating from the middle 1970's to the present, including six incidents since issuance of AD 75-23-08 R5 where exhaust problems were cited. The actions specified by this AD are intended to detect and correct cracks and corrosion in the exhaust system, which could result in exhaust system failure and a possible uncontrollable in-flight fire with pilot and/or passenger injury.
AD 2000-01-17 · published Jan 19, 2000, effective Feb 23, 2000
McDonnell Douglas Model MD-90 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90 series airplanes, that requires a one-time detailed visual inspection to detect fatigue cracking of certain longerons and the attaching frames of the lower left nose; and repair, if necessary. This amendment also requires installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of the airplane.
AD 2000-01-18 · published Jan 19, 2000, effective Feb 23, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires a one-time eddy current conductivity test to determine the material type of the lower cap of the wing front spar; and modification of the lower cap of the wing front spar, if necessary. This amendment is prompted by reports of stress corrosion cracking in the forward tang of the lower caps of the wing front spar. The actions specified by this AD are intended to prevent such stress corrosion cracking, which if not corrected, could result in reduced structural integrity of the wing.
AD 2000-01-51 · published Jan 21, 2000, effective Jan 7, 2000
CL-604 Variant of Bombardier Model Canadair CL-600-2B16 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA8060NM-D, SA8072NM-D, or SA8086NM-D
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-01-51 that was sent previously by individual notices to all known U.S. owners and operators of Model CL-604 variant of Bombardier Model Canadair CL-600-2B16 series airplanes modified in accordance with Supplemental Type Certificate SA8060NM-D, SA8072NM-D, or SA8086NM-D. This AD requires that the fuel service panel maintenance light be disconnected. This action is prompted by a report indicating that an electrical spark was noted when the fuel cap chain contacted the maintenance light housing of the fuel service panel. The actions specified by this AD are intended to prevent electrical sparks from a grounded object from coming into contact with the maintenance light housing of the fuel service panel, which could result in a fuel fire due to the close proximity of the fuel service panel to the fuel port.
AD 2000-02-01 · published Jan 25, 2000, effective Feb 29, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires detailed visual and eddy current inspections of the lower wing skin at the 3 outboard fasteners of the stringer 64 end fitting to detect cracks; and corrective actions, if necessary. This amendment is prompted by reports of fatigue cracks found in the lower wing skin initiating from the outboard fasteners of the stringer 64 end fitting. The actions specified by this AD are intended to prevent such fatigue cracking, which could reduce structural integrity and loss of fail-safe capability of the airplane.
AD 2000-02-02 · published Jan 25, 2000, effective Feb 29, 2000
Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, and SD3-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA and SD3-SHERPA series airplanes, and certain Model SD3-30 series airplanes, that requires replacement of existing oxygen system "O" rings with improved wear-resistant "O" rings. 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 the loss of oxygen from the aircraft oxygen system, which could result in an insufficient supply of oxygen being provided to the airplane flight crew and passengers in the event of an emergency.
AD 2000-02-03 · published Jan 25, 2000, effective Feb 29, 2000
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400 and -500 series airplanes, that requires replacement, with new parts, of the existing actuators or the rod ends on the existing actuators at wing leading edge slat positions 1, 2, 5, and 6. This amendment is prompted by reports indicating that the rod ends on several leading edge slat actuators have fractured. The actions specified by this AD are intended to prevent fatigue cracking of the rod ends of the leading edge slat actuators, which could result in uncommanded deployment of the wing leading edge slat and consequent reduced controllability of the airplane.
AD 2000-02-04 · published Jan 25, 2000, effective Feb 9, 2000
Airbus Model A300, A300-600, and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 and all Model A300-600 and A310 series airplanes. This action requires performing a pitch trim system test to detect any continuity defect in the autotrim function, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent a sudden change in pitch due to an out- of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane.
AD 2000-02-13 · published Jan 26, 2000
de Havilland Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-8-100, -200, and -300 series airplanes, that requires installation of a placard on the instrument panel of the cockpit to advise the flightcrew that positioning of the power levers below the flight idle stop during flight is prohibited. This amendment also requires eventual installation of a system that will prevent such positioning of the power levers during flight. Such installation will terminate the requirement for installation of a placard. This amendment is prompted by reports of operation of the airplane with the power levers positioned below the flight idle stop during flight. The actions specified by this AD are intended to prevent such positioning of the power levers below the flight idle stop during flight, which could cause engine overspeed, possible engine damage or failure, and consequent reduced controllability of the airplane.
AD 2000-02-05 · published Jan 27, 2000, effective Mar 2, 2000
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires repetitive detailed visual inspections to detect cracking or other damage of certain diaphragm support structures of the forward equipment compartment; and repair, if necessary. This amendment continues to require repetitive inspections, but also requires replacement of cracked or damaged diaphragm support structures with improved parts, which terminates the requirement for repetitive inspections. This amendment also adds airplanes to the applicability of the AD. This amendment is prompted by the development of improved diaphragms. The actions specified by this AD are intended to prevent failure of the two diaphragms that support the upper structure of the forward equipment compartment, which could accelerate fatigue damage in adjacent structure and result in reduced structural integrity of the airframe.
AD 2000-02-07 · published Jan 27, 2000, effective Mar 2, 2000
Bombardier Model DHC-7-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-7-100 series airplanes, that requires repetitive high frequency eddy current inspections to detect cracks on the locking pin fittings of the baggage door and locking pin housings of the fuselage; repetitive detailed visual inspections to detect cracks of the inner door structure on all four door locking attachment fittings; and corrective actions, if necessary. In lieu of accomplishing the corrective actions, this amendment also provides a temporary option, for certain cases, for revising the Airplane Flight Manual (AFM), and installing a placard. 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 detect and correct fatigue cracking of the baggage door fittings and the support structure, which could result in structural failure, and consequent rapid decompression of the airplane during flight.
AD 2000-02-08 · published Jan 27, 2000, effective Mar 2, 2000
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, equipped with ground spoiler actuators having part number 1059A0000-02, that requires removal of the gland attachment bolts of the ground spoiler actuator and replacement with new bolts installed with higher torque. 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 hydraulic fluid leakage due to loose or broken gland attachment bolts, and consequent loss of the main hydraulic system.
AD 2000-02-11 · published Jan 27, 2000, effective Mar 2, 2000
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires the application of sealant to the upper surface on the wing center section to ensure the integrity of the secondary fuel barrier. This amendment is prompted by reports from the airplane manufacturer that the sealant was inadvertently not applied to portions of the wing center section on certain Boeing Model 777-200 series airplanes. The actions specified by this AD are intended to prevent fuel or fuel vapors from entering the cargo and passenger compartments in the event of a failure of the primary seal or development of a crack in the wing center section structure. Leakage of fuel or fuel vapors into the cargo and passenger compartments could be hazardous to personnel, and could cause a fire in those compartments.
AD 2000-02-14 · published Jan 27, 2000, effective Mar 17, 2000
Cessna Aircraft Company Model 182S Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-13- 10, which currently requires repetitively inspecting all engine exhaust muffler end plates (four total) for cracks on all Cessna Aircraft Company (Cessna) Model 182S airplanes, and replacing any muffler where an end plate is found cracked. AD 98-13-10 also requires fabricating and installing a placard that specifies immediate inspection of all engine exhaust muffler end plates any time the engine backfires upon start-up. This AD is the result of Cessna developing an improved design exhaust system for the Model 182S airplanes. This AD retains the actions of AD 98-13-10 on all affected airplanes, and requires replacing the exhaust system with an improved design exhaust system within a certain period of time, as terminating action for those requirements retained from AD 98-13-10. This AD also limits the effectivity to exclude those airplanes manufactured with the improved design exhaust system. The actions specified by this AD are intended to detect and correct damage to the engine exhaust mufflers caused by cracking and the high stresses imposed on the attachment of the exhaust system at the area the firewall, which could result in exhaust gases entering the airplane cabin with consequent crew and passenger injury.
AD 99-27-12 · published Jan 5, 2000, effective Jan 5, 2000
Agusta S.p.A. Model A109A and A109A II Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires, before further flight, inspecting any tail rotor blade (blade) with 400 or more hours time-in-service (TIS) for a crack and replacing any cracked blade before further flight. This amendment contains the same requirements as the current AD but corrects the paragraph that requires ``replacing any cracked blade with an unairworthy blade.'' This amendment is prompted by the need to correct the requirement to mandate ``replacing any cracked blade with an airworthy blade.'' The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
AD 2000-01-11 · published Jan 13, 2000, effective Jan 28, 2000
Eurocopter Deutschland GMBH Model MBB- BK 117 Helicopters
This amendment supersedes an existing emergency priority letter airworthiness directive (AD), applicable to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopters, that currently requires, before further flight, creating a component log card or equivalent record and determining the age and number of flights on the tension-torsion (TT) strap. The AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment requires the same actions as the emergency priority letter AD but clarifies the compliance requirements specified in the emergency priority letter AD. This amendment is prompted by an accident in which a main rotor blade (blade) separated from a helicopter due to fatigue failure of a TT strap. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 99-26-04 · published Jan 24, 2000, effective Feb 8, 2000
Kaman Aerospace Corporation Model K1200 Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Priority Letter Airworthiness Directive (AD) 99-26- 04, which was sent previously to all known U.S. owners and operators of Kaman Aerospace Corporation (Kaman) Model K1200 helicopters by individual letters. This AD requires, before the first flight of each day, inspecting for clutch assembly integrity. Replacing any unairworthy clutch assembly with an airworthy clutch assembly is required before further flight. This amendment is prompted by two incidents of engine adapter flange failure and loss of power to the main rotors. The actions specified by this AD are intended to prevent failure of the engine adapter flange, loss of power to the main rotors, and a subsequent forced landing.
AD 2000-01-19 · published Jan 25, 2000, effective Feb 4, 2000
Eurocopter Deutschland GMBH Model EC 135 P1 and EC 135 T1 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter Deutschland GMBH (ECD) Model EC 135 P1 and EC 135 T1 helicopters. This action requires inspecting main rotor expansion bolt safety wires, bolt heads, and bolt nuts; replacing any unairworthy expansion bolt with a hexagon bolt; and, as necessary, replacing any bolt nut before further flight. This AD also requires replacing each expansion bolt, regardless of condition, no later than January 31, 2000. This amendment is prompted by reports of main rotor blade expansion bolt nuts becoming loose. This condition, if not corrected, could result in severe vibration during flight and subsequent loss of control of the helicopter.
AD 2000-02-09 · published Jan 26, 2000, effective Feb 10, 2000
Agusta S.p.A. (Agusta) Model AB412 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta Model AB412 helicopters with certain rescue hoists installed. This action requires replacing the rescue hoist hook assembly retention pin (retention pin) and periodically inspecting the rescue hoist. This amendment is prompted by an incident in which a rescue hoist hook assembly separated from a helicopter due to a missing retention pin. The actions specified in this AD are intended to prevent separation of the rescue hoist hook assembly from the helicopter due to failure of the retention pin. Loss of the rescue hoist hook assembly could result in loss of the person on the rescue hoist. Also, with the loss of the weight of the hoist cable assembly, the rescue hoist cable could become entangled with a main rotor or tail rotor blade, and result in damage or separation of a rotor blade and subsequent loss of control of the helicopter.
AD 99-27-15 · published Jan 6, 2000, effective Jan 11, 2000
General Electric Company GE90 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain General Electric Company GE90 series turbofan engines. This action requires visually inspecting Ps3 and P3B sense lines and full authority digital engine control (FADEC) Ps3 and P3B sensing ports and fittings, cleaning Ps3 and P3B fittings and sensing ports, purging the Ps3 and P3B systems of moisture, and, if necessary, blending of high metal, nicks, burrs, or scratches on Ps3 and P3B fitting threads. This amendment is prompted by seven reports of loss of thrust control due to corruption of the signals to the FADEC caused by water freezing in the Ps3 sensing system. The actions specified in this AD are intended to prevent loss of thrust control due to corruption of the Ps3 and P3B signals to the FADEC which if it occurs in a critical phase of flight, could result in loss of aircraft control.
AD 99-27-16 · published Jan 6, 2000, effective Feb 10, 2000
CFE Company Model CFE738-1-1B Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFE Company Model CFE738-1-1B turbofan engines. This AD requires, on certain engines identified by serial numbers: a one-time visual inspection of Stage 2 high pressure turbine (HPT) aft cooling plates for nicks, dents, and scratches, and if present, dimensional inspection of indentation depth; repair, if indentation is within acceptable limits, and, if necessary, replacement with serviceable parts. This AD also requires inspection for raised metal on the Stage 2 HPT rotor disk post aft surface that mates with the Stage 2 HPT aft cooling plate, and removal of the raised metal, if present. This amendment is prompted by reports of Stage 2 HPT aft cooling plates that were dented during the assembly of the cooling plate to the Stage 2 disk due to raised metal on the stage 2 HPT disk post aft mating surface. The actions specified by this AD are intended to prevent aft HPT cooling plate failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-01-09 · published Jan 12, 2000, effective Feb 11, 2000
GE Aircraft Engines CJ610 Series Turbojet Engines and CF700 Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines. This action requires removal of certain unapproved parts before further flight. This amendment is prompted by findings that life-limited parts, with forged and inaccurate records, have been introduced into the field and might be installed on the affected engines. The actions specified in this AD are intended to prevent the use of unapproved parts. This condition, if not corrected, could lead to an uncontained engine failure and damage to the airplane.
AD 2000-01-13 · published Jan 19, 2000, effective Feb 23, 2000
Pratt & Whitney JT9D Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT9D series turbofan engines, that currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-01-06 · published Jan 12, 2000, effective Feb 4, 2000
Rolladen Schneider Flugzeugbau GmbH Model LS6-c Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Rolladen Schneider Flugzeugbau GmbH (Rolladen Schneider) Model LS6-c sailplanes. This AD requires that you accomplish the following: --install a deflector on the cockpit instrument panel for sailplanes equipped with an instrument panel that is 40 centimeters (15.75 inches) wide; --inspect the canopy emergency jettison system on all sailplanes; and --adjust the system, as necessary, for all sailplanes, including installing a deflector for sailplanes equipped with an instrument panel that is not 40 centimeters (15.75 inches) wide if proper clearance is not met. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to assure that the instrument panel does not jam against the canopy frame of the emergency jettison system. This could restrict the pilot's ability to safely exit the sailplane.
