70 Airworthiness Directives: 57 airplane, 4 rotorcraft, 7 engine, 1 propeller, 1 balloon.
AD 2000-02-06 · published Feb 1, 2000, effective Feb 16, 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 a one-time visual inspection to determine the part numbers of the beta back-up test switches of the propeller control system, and replacement of the switches, 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 loss of the automatic overspeed protection of the propeller control system, which could result in a propeller overspeed condition and possible damage to the engine and propeller.
AD 2000-02-10 · published Feb 1, 2000, effective Mar 7, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect broken fasteners and cracking of the forward edge frame for main entry door number 3, and repair, if necessary. This amendment is prompted by reports of fatigue cracks at the inner chord and web of the body station 1265 edge frame between stringers 23 and 27. The actions specified by this AD are intended to detect and correct such cracking, which could result in rapid depressurization of the airplane.
AD 2000-02-15 · published Feb 1, 2000, effective Feb 18, 2000
Raytheon Aircraft Company Beech Models 65-90, 65-A90, B90, and C90 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Beech Models 65-90, 65- A90, B90, and C90 airplanes that incorporate a certain engine and propeller configuration. This AD prohibits you from operating any affected airplane with this engine and propeller configuration and prohibits its future installation. Results of an accident investigation involving one of the affected airplanes reveals installation discrepancies with the engine and propeller configuration. These discrepancies, if not corrected, could lead to engine failure and the inability to feather the propeller. The actions specified by this AD are intended to prevent an uncontained engine failure due to suspect engine and propeller installation, which could result in loss of control of the airplane.
AD 99-26-03 · published Feb 2, 2000, effective Jan 4, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-11 series airplanes. That AD currently requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. This document revises the statement of the unsafe condition to correct the location of where potential smoke and fire may occur and to correct the description of the locations of the power feeder cables. This correction is necessary to ensure that operators have a clear understanding of the unsafe condition.
AD 2000-02-18 · published Feb 3, 2000, effective Mar 9, 2000
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes; that currently requires an inspection of reworked aileron/elevator power control units (PCU's) and rudder PCU's to determine if reworked PCU manifold cylinder bores containing chrome plating are installed, and replacement of the cylinder bores with cylinder bores that have been reworked using the oversize method or the steel sleeve method, if necessary. This amendment, among other items, expands the applicability of the existing AD to include airplanes equipped with certain rudder PCU's. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent a reduced rate of movement of the elevator, aileron, or rudder due to contamination of hydraulic fluid from chrome plating chips; such reduced rate of movement, if not corrected, could result in reduced controllability of the airplane.
AD 2000-02-19 · published Feb 3, 2000, effective Mar 9, 2000
Boeing Model 727 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires repetitive inspections of the front spar web between the upper and lower seals of the center section of the wings, and repair, if necessary. That amendment also provides for an optional terminating modification for the repetitive inspections. This amendment requires a new terminating modification for the repetitive inspections. For certain airplanes, this amendment also requires new repetitive inspections to detect discrepancies of the front spar web. This amendment is prompted by a report indicating that the optional terminating modification in the existing AD does not adequately address the identified unsafe condition. The actions specified by this AD are intended to prevent fatigue cracks in the front spar web, which could lead to fuel leakage into the air-conditioning distribution bay and/or depressurization of the cabin, and to prevent fuel fumes in the cabin of the airplane.
AD 2000-02-20 · published Feb 3, 2000, effective Mar 9, 2000
Boeing Model 767 Series Airplanes Equipped With General Electric Model CF6-80C2 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires tests, inspections, and adjustments of the thrust reverser system. That AD also requires installation of a terminating modification, and repetitive follow-on actions. This amendment reduces the repetitive intervals for the follow-on actions. This amendment is prompted by reports indicating that several center drive units (CDU's) of the thrust reverser system were returned to the manufacturer of the CDU's because of low holding torque of the CDU cone brake. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 2000-02-21 · published Feb 3, 2000, effective Mar 9, 2000
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires manufacture and installation of a placard on the left- hand instrument panel in the cockpit to prohibit push-backs of the airplane while the engines are running. In lieu of accomplishing the placard installation, this amendment requires repetitive installation of a new tow bracket sub-assembly that has the serial number and date of installation vibro etched on it. 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 towing bracket. Failure of the towing bracket could cause a towing vehicle to collide into the propeller while the airplane engines are running, and consequently, cause damage to the airplane, and injure ground personnel, flight crew, or passengers.
AD 2000-02-22 · published Feb 3, 2000, effective Feb 18, 2000
Boeing Model 747-400 Series Airplanes Equipped with Rolls-Royce RB211-524G/H and RB211-524G-T/H-T Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive operational checks of that installation to detect discrepancies, 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 a 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.
AD 2000-02-23 · published Feb 3, 2000, effective Mar 9, 2000
McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to determine the type of engine ignition switch installed in the hinged forward overhead switch panel, and replacement of certain rotary ignition switches with new design rotary ignition switches. This amendment is prompted by reports of smoke in the flight compartment during engine ignition selection. The actions specified by this AD are intended to prevent an internal electrical short in the engine ignition switch, which could result in smoke in the flight compartment.
AD 2000-02-24 · published Feb 3, 2000, effective Mar 9, 2000
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires either replacement of the spring rod assemblies of the rudder servo controls with improved spring rod assemblies; or modification of the existing spring rod assemblies. For certain airplanes, this amendment requires a one-time visual inspection to determine whether certain parts of the spring rod assemblies of the rudder servo controls are installed; 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 corrosion of the spring rod assemblies of the rudder servo controls, which could result in the jamming of the rudder servo controls and consequent reduced controllability of the airplane.
AD 2000-02-25 · published Feb 4, 2000, effective Mar 24, 2000
Mitsubishi Heavy Industries, Ltd. Model MU-2B Series Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) Model MU- 2B series airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-26 · published Feb 4, 2000, effective Mar 27, 2000
Harbin Aircraft Manufacturing Corporation Model Y12 IV Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Harbin Aircraft Manufacturing Corporation (Harbin) Model Y12 IV airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-27 · published Feb 4, 2000, effective Mar 24, 2000
Empresa Brasileira de Aeronautica S.A. Models EMB-110P1 and EMB-110P2 Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Empresa Brasileira de Aeronautica S.A. (Embraer) Models EMB-110P1 and EMB-110P2 airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-28 · published Feb 4, 2000, effective Mar 27, 2000
AeroSpace Technologies of Australia Pty Ltd. Models N22B and N24A Airplanes
This document adopts a new airworthiness directive (AD) that applies to all AeroSpace Technologies of Australia Pty Ltd. (AeroSpace Technologies) Models N22B and N24A airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-29 · published Feb 4, 2000, effective Mar 27, 2000
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
This document adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-30 · published Feb 4, 2000, effective Mar 24, 2000
Twin Commander Aircraft Corporation 600 Series Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Twin Commander Aircraft Corporation (Twin Commander) 600 series airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-02-31 · published Feb 4, 2000, effective Mar 27, 2000
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
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 replacing the stick pusher capstan and the stick pusher servo with parts of improved design. The 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 improper operation of the stick pusher system caused by the existing design configuration, which could result in loss of control of the airplane during a stall.
AD 2000-02-33 · published Feb 7, 2000, effective Mar 13, 2000
Boeing Model 747-400 Series Airplanes Equipped With General Electric CF6-80C2 Series Engines
This amendment adopts a new airworthiness directive (AD) applicable to certain Boeing Model 747-400 series airplanes that requires various inspections and functional tests to detect discrepancies of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment is prompted by reports indicating that several center drive units (CDU) were returned to the manufacturer of the CDU's because of low holding torque of the CDU cone brake. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 2000-02-34 · published Feb 7, 2000, effective Mar 13, 2000
Bombardier Model CL-600-2B19 (Regional Jet Series 100) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. This amendment is prompted by an accident report indicating that possible accretion of ice on the wings of the airplane, due to the wing anti-ice system not being activated by the flightcrew, could have contributed to the source of the accident. The actions specified by this AD are intended to prevent undetected accretion of ice on the wings, which could result in reduced controllability of the airplane during normal icing conditions.
AD 2000-02-35 · published Feb 7, 2000, effective Mar 13, 2000
Raytheon Model Hawker 800 and 1000 Airplanes and Model DH.125, HS.125, BH.125, and BAe.125 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800 and 1000 airplanes and Model DH.125, HS.125, BH.125, and BAe.125 series airplanes, that requires replacement of cadmium plated fittings and cone caps in the oxygen system plumbing with improved fittings and cone caps, a detailed visual inspection of the oxygen system plumbing in the area of the replaced parts, and corrective actions, if necessary. This amendment is prompted by reports indicating that a field survey of the affected parts revealed that a reaction process was occurring, which resulted in cadmium flaking. The actions specified by this AD are intended to prevent flaking of cadmium from certain oxygen system plumbing fittings and cone caps from blocking the valves and impairing the function of the oxygen system, which could deprive the crew and passengers of necessary oxygen during an emergency that requires oxygen.
AD 2000-02-36 · published Feb 7, 2000, effective Mar 13, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires relocation of the engine/master 1 relay from relay box 103VU to shelf 95VU in the avionics bay. This amendment continues to require the relocation using new electrical contacts, and, for certain airplanes, adds a requirement to replace certain contacts installed in shelf 95VU during relocation of the relay with new contacts. 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 a simultaneous cutoff of the fuel supply to both engines, which could result in a loss of engine power and consequent reduced controllability of the airplane.
AD 2000-02-37 · published Feb 7, 2000, effective Mar 13, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection to determine whether latch pins on the lower lobe and main deck side cargo doors are installed backward, and corrective actions, if necessary. This amendment also requires eventual modification of the latch pin fittings on certain cargo doors. This amendment is prompted by reports that latch pins have been found installed backward on the cargo doors of several airplanes. The actions specified by this AD are intended to prevent improper latching of latch pins and the mating latch cam on the cargo door, which could result in damage to the structure of the cargo door and doorway cutout and consequent opening of the cargo door during flight.
AD 2000-02-38 · published Feb 7, 2000, effective Mar 13, 2000
Airbus Model A300, A300-600, and A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, and A310 series airplanes, equipped with a welded auxiliary power unit (APU) fuel feedline adapter. That AD currently requires repetitive dye penetrant inspections to detect cracks, rupture, or fuel leaks of the fuel feedline adapter; and replacement of the adapter, if necessary. That AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. 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 fuel leakage in the APU compartment, which could result in a fire in the APU compartment.
AD 2000-02-39 · published Feb 7, 2000, effective Feb 22, 2000
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. This action requires either a one-time ultrasonic inspection, or repetitive visual inspections and eventual ultrasonic inspection, to detect cracking of the longitudinal skin splice above the mid-passenger door panels, 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 in this AD are intended to detect and correct cracking of the longitudinal skin splice above the mid-passenger door panels, which could result in reduced structural integrity of the fuselage pressure vessel.
AD 2000-03-01 · published Feb 7, 2000, effective Mar 13, 2000
Boeing Model 747-100 and −200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100 and -200 series airplanes, that requires repetitive inspections of the upper and lower chords of the wing front spar for cracks, and corrective action, if necessary. For airplanes on which no cracking is detected, this AD also provides an optional terminating action in lieu of repetitive inspections. This amendment is prompted by reports of cracks in the upper chord of the wing front spar. The actions specified by this AD are intended to detect and correct fatigue cracking of the upper and lower chords of the wing front spar, which could result in reduced structural capability and possible fuel leakage onto an engine and a resultant fire.
AD 2000-03-05 · published Feb 10, 2000
Boeing Model 737-200 Series Airplanes Modified in Accordance with Supplemental Type Certificate (STC) ST00969AT
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-200 series airplanes that requires removal of the existing emergency floor path lighting system and replacement with an FAA-approved emergency floor path lighting system. This amendment is prompted by information indicating that the existing emergency floor path lighting system does not provide adequate lighting and cueing for safe evacuation of the airplane in the event of an emergency. The actions specified by this AD are intended to prevent such inadequate lighting and cueing, which could delay or impede the flight crew and passengers when exiting the airplane during an emergency.
AD 2000-03-08 · published Feb 16, 2000, effective Mar 22, 2000
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires repetitive fluorescent penetrant and magnetic particle inspections to detect fatigue cracking of the main landing gear (MLG) piston, and repair, if necessary. This amendment is prompted by reports of MLG failures during towing of in-service airplanes due to fatigue cracks. The actions specified by this AD are intended to detect and correct fatigue cracking of MLG pistons, which could result in failure of the pistons, and consequent damage to the airplane structure and injury to flight crew, passengers, or ground personnel.
AD 2000-03-18 · published Feb 16, 2000, effective Apr 7, 2000
Partenavia Costruzioni Aeronauticas S.p.A. Models AP68TP 300 “Spartacus” and AP68TP 600 “Viator” Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Partenavia Costruzioni Aeronauticas S.p.A. (Partenavia) Models AP68TP 300 "Spartacus" and AP68TP 600 "Viator" airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-03-19 · published Feb 16, 2000, effective Apr 7, 2000
Industrie Aeronautiche e Meccaniche Model Piaggio P-180 Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with pneumatic deicing boots. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-03-10 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. For certain airplanes, this amendment requires the installation or modification of a flapper door ramp deflector on the forward entry drop ceiling structure. For certain other airplanes, this amendment requires inspection of the wire assembly support installation for evidence of chafing, and corrective actions, if necessary. This amendment is prompted by a report indicating that damaged electrical wires were found above the forward passenger doors due to flapper panels moving inboard and chafing the electrical wire assemblies of this area. The actions specified by this AD are intended to prevent such chafing, which could result in an electrical fire in the passenger compartment.
AD 2000-03-11 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacement of 10 amp circuit breakers with 5 amp circuit breakers in the left and right windshield anti-ice power controllers; and replacement of the anti-ice control panel with a new or modified panel, or modification and reidentification of the anti-ice control panel. This amendment is prompted by reports of smoke and sparks emanating from the anti-ice control panel in the cockpit. The actions specified by this AD are intended to prevent burnt internal circuit boards caused by a short in either the engine or airfoil anti-ice valve, or the windshield anti-ice controller, which could result in smoke in the cockpit.
AD 2000-03-12 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacement of the air driven generator (ADG) wire assembly with a new, increased length wire assembly. This amendment is prompted by a report of loose terminal attachment hardware on the ADG power monitor relay due to a stress condition on the terminal attachment points. The actions specified by this AD are intended to prevent loss of the charging capability of the aircraft battery. Loss of the charging capability of the aircraft battery, coupled with a loss of all normal electrical power, could prevent continued safe flight and landing of the airplane.
AD 2000-03-13 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment is prompted by a report indicating that the wire bundle contained in the feedthrough behind the first observer's station was contacting the bottom portion of the feedthrough. The actions specified by this AD are intended to prevent such contact, which could cause cable chafing, electrical arcing, smoke, or fire in the cockpit.
AD 2000-03-14 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires modification of the battery ground cable installation in the center accessory compartment. This amendment is prompted by reports of battery ground studs that had arced due to loose ground stud attachments. The actions specified by this AD are intended to prevent such arcing, which could cause smoke and/or fire in the center accessory compartment.
AD 2000-03-15 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 and MD-11F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that requires replacement of the existing terminal strips and supports above the main cabin area; and installation of spacers between terminal strips and mounting brackets in the avionics compartment; as applicable. This amendment is prompted by a report indicating that, during flight, an incident of electrical arcing occurred at a terminal strip located overhead in the main cabin. The actions specified by this AD are intended to prevent electrical arcing caused by power feeder cable terminal lugs grounding against terminal strip support brackets, which could result in smoke and fire in the main cabin or avionics compartment.
AD 2000-03-16 · published Feb 17, 2000, effective Mar 23, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time visual inspection of the 90 percent brake pedal position switch to determine if certain date codes are present; and corrective action, if necessary. This amendment is prompted by reports indicating that the threaded insert connectors pulled free from the casing of the 90 percent brake pedal position switch, which allowed the insert connector contact to burn through the nose wheel steering cable. The actions specified by this AD are intended to prevent the threaded insert connector from pulling free from the casing of the 90 percent brake pedal position switch and burning through the nose wheel steering cable, which could result in reduced aircraft directional control while on the ground.
AD 2000-03-17 · published Feb 17, 2000, effective Apr 10, 2000
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-23- 01, which currently requires the following on Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series airplanes that are equipped with a certain Simmonds-Precision pitch trim actuator or a certain Barber-Colman pitch trim actuator: repetitively measuring the freeplay of the pitch trim actuator and repetitively inspecting the actuator for rod slippage; immediately replacing any actuator if certain freeplay limitations are exceeded or rod slippage is evident; and eventually replacing the actuator regardless of the inspection results. This AD retains the actions of AD 97-23-01, and adds these requirements on airplanes with different design pitch trim actuators installed. This AD is the result of the manufacturer developing different design pitch trim actuators and the Federal Aviation Administration (FAA) determining that these actuators should be subject to the actions of AD 97-23-01. The actions specified by this AD are intended to detect excessive freeplay or rod slippage in the pitch trim actuator, which, if not detected and corrected, could result in pitch trim actuator failure and possible loss of control of the airplane.
AD 2000-03-20 · published Feb 22, 2000, effective Mar 28, 2000
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires repetitive ultrasonic inspections to detect cracks on the forward fittings in the radius of frame 40 adjacent to the tension bolts in the center section of the wings, and various follow-on actions. This amendment is prompted by reports of cracking due to fatigue-related stress in the radius of frame 40 adjacent to the tension bolts at the center/outer wing junction. The actions specified by this AD are intended to detect and correct fatigue cracking on the forward fittings in the radius of frame 40 adjacent to the tension bolts in the center section of the wings, which could result in reduced structural integrity of the wings.
AD 2000-03-21 · published Feb 22, 2000, effective Mar 28, 2000
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a one-time detailed visual inspection to detect discrepancies of the wire expando sleeve of the wire bundles adjacent to the landing gear control lever module; certain follow-on actions and repair, if necessary; and wrapping the wire expando sleeve with tape, or with zippertubing and tape. This amendment is prompted by reports indicating that the landing gear failed to extend on an in-service airplane, and that the landing gear control cable was severed on a second in-service airplane. The actions specified by this AD are intended to prevent interference between the landing gear control lever and wire bundles adjacent to the landing gear control lever module, and to prevent wire chafing and arcing between the landing gear control cable and adjacent wire bundles, which could result in the inability to extend the landing gear prior to landing.
AD 2000-03-22 · published Feb 22, 2000, effective Mar 28, 2000
Boeing Model 747-100, -200, and 747SP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and 747SP series airplanes, that requires repetitive detailed visual and ultrasonic inspections to detect missing, damaged, or broken taperlock bolts in the diagonal brace underwing fittings; and corrective actions, if necessary. This AD also requires eventual replacement of the aft 10 taperlock bolts with new bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by reports of damaged, broken, and corroded taperlock bolts of the diagonal brace underwing fittings on the outboard strut due to stress corrosion cracking. The actions specified by this AD are intended to prevent loss of the underwing fitting load path due to missing, damaged, or broken taperlock bolts, which could result in separation of the engine and strut from the airplane.
AD 2000-04-01 · published Feb 22, 2000, effective Mar 11, 2000
Cessna Aircraft Company Models 172R, 172S, 182S, 206H, and T206H Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 206H, and T206H airplanes. This AD requires that you accomplish the following:
AD 2000-04-03 · published Feb 22, 2000, effective Mar 28, 2000
McDonnell Douglas Models DC-3 and DC-4 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Models DC-3 and DC-4 series airplanes that requires an inspection to determine the type of airframe pneumatic deicing boots installed. This amendment also requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the pneumatic deicing boots for those airplanes equipped with "modern" boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
AD 2000-04-02 · published Feb 23, 2000, effective Mar 29, 2000
Boeing Model 737-100, -200, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive testing of certain main tank fuel boost pumps to identify those with degraded performance, and replacement of degraded pumps with new or serviceable pumps. This AD also requires eventual replacement of the existing low pressure switches for boost pumps located in the main fuel tanks with higher threshold low pressure switches, which, when accomplished, terminates the repetitive testing. This amendment is prompted by reports of engine power loss caused by unsatisfactory performance of the fuel boost pumps. The actions specified by this AD are intended to prevent fuel suction feed operation on both engines without flight crew indication, and possible consequent multiple engine power loss.
AD 2000-04-05 · published Feb 23, 2000, effective Mar 29, 2000
Israel Aircraft Industries, Ltd., Model Astra SPX Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Israel Aircraft Industries Model Astra SPX series airplanes, that requires a one-time inspection to measure the countersink angle of the bolt holes in the lower scissors fitting of the horizontal stabilizer, 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 cracks in the lower scissors fitting and fitting attachment bolts of the horizontal stabilizer, which could result in possible in-flight loss of the horizontal stabilizer and consequent reduced controllability of the airplane.
AD 2000-04-04 · published Feb 24, 2000, effective Mar 30, 2000
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a measurement of the resistance of the electrical connectors of the auxiliary power unit (APU) to detect a short circuit; an inspection to determine if the grommets or shrink sleeves are present; and modification, 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 detect and prevent a short circuit of a fire extinguisher electrical system due to a lack of shrink sleeves or grommets, and consequent disabling of the affected fire extinguisher system.
AD 2000-04-06 · published Feb 24, 2000, effective Mar 30, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modification of the forward and aft evacuation slide systems by replacing the Velcro restraints for the support logs with frangible link restraints. 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 ingestion of sill support-log material into the aspirator of the escape slide, which could result in failure of the escape slide to inflate.
AD 2000-04-07 · published Feb 24, 2000, effective Mar 30, 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 detailed visual inspection to detect incorrect installation or discrepancies (damage, bending, overheating, discoloration) of the circuit breaker and the cable terminations of the circuit breaker of the engine de-ice panel. 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 engine intake de-icing system, which could result in loss of engine intake de-icing capability, accretion of ice in the intake duct, ice ingestion, and consequent engine flameout.
AD 2000-04-08 · published Feb 24, 2000, effective Mar 10, 2000
Boeing Model 737-200C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200C series airplanes. This action requires repetitive inspections to detect cracking in the lower skin at the stringer 4R lap joint, and certain fuselage frames; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by a report of a fractured frame located at body station (BS) 480. The actions specified in this AD are intended to detect and correct cracking in certain frames, which, in conjunction with multiple site cracking in the lower skin of the lap joint, could result in failure of certain lap joints, and consequent rapid decompression of the airplane fuselage.
AD 2000-04-09 · published Feb 24, 2000, effective Mar 10, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires various inspections to detect discrepancies of the elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, 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 the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane.
AD 2000-04-11 · published Feb 24, 2000, effective Mar 10, 2000
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires a revision to the Limitations and Normal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM) to limit the use of the radio altimeter of the flight management guidance system (FMGS) during the approach phase of flight. This action also provides for an optional terminating modification, which, if accomplished, would terminate the requirement 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 erroneous display of decision height information to the flight crew during final approach, which could result in an increased risk of collision with the terrain.
AD 2000-03-09 · published Feb 28, 2000, effective Apr 3, 2000
Cessna Model 560 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Cessna Model 560 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with limitations, operational procedures, and performance information to be used during approach and landing when residual ice is present or can be expected. This amendment is prompted by reports indicating that, while operating in icing conditions or when ice is on the wings, some of these airplanes have experienced uncommanded roll at (or slightly higher than) the speed at which the stall warning system is activated. This amendment requires revising the AFM and revises the applicability of the existing AD. This amendment also requires modification of the stall warning system of the angle-of-attack computer. The actions specified by this AD are intended to prevent uncommanded roll of the airplane during approach and landing when residual ice is present or can be expected.
AD 2000-03-51 · published Feb 28, 2000, effective Mar 6, 2000
McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-NM-58-AD that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes by individual telegrams. This AD requires inspecting the general condition of the jackscrew assembly and the area around the jackscrew assembly to detect the presence of metal shavings and flakes. This action is prompted by a report from an operator that indicated two instances of metallic shavings in the vicinity of the jackscrew assembly and gimbal nut of the horizontal stabilizer. The actions specified by this AD are intended to prevent loss of pitch trim capability due to excessive wear of the jackscrew assembly of the horizontal stabilizer, which could result in loss of vertical control of the airplane.
AD 2000-04-13 · published Feb 28, 2000, effective Apr 3, 2000
Aerospatiale Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires initial and repetitive inspections to detect fatigue cracking in certain areas of the fuselage, 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 fatigue cracking of the fuselage and the passenger and service doors, which could result in reduced structural integrity of the airplane.
AD 2000-04-17 · published Feb 29, 2000, effective Mar 15, 2000
Boeing Model 747-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200, and -300 series airplanes. This action requires repetitive inspections to detect fatigue cracking in the upper deck floor beams located at certain body stations, and repair, if necessary. This amendment is prompted by a report by the manufacturer that, during a fatigue test, the upper chord and web of the upper deck floor beams located at body stations (BS) 340 and 360 were found severed at approximately 34,000 total flight cycles. Another report by an operator indicated that a severed upper chord and web were found in the upper deck floor beam at BS 380 at approximately 33,000 total flight cycles. In addition, cracking was found at multiple fastener hole locations. The actions specified in this AD are intended to prevent failure of the upper deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression and consequent reduced controllability of the airplane.
AD 2000-04-18 · published Feb 29, 2000, effective Apr 4, 2000
Boeing Model 757 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires replacement of transmission assemblies for the trailing edge flaps with modified transmission assemblies. This amendment is prompted by reports of broken bolts that attach the transmission assemblies for the trailing edge flaps. The actions specified by this AD are intended to prevent damage to the flap system, adjacent system, or structural components; and excessive skew of the trailing edge flap; which could result in reduced controllability of the airplane.
AD 2000-04-19 · published Feb 29, 2000, effective Apr 4, 2000
Dassault Model Mystere-Falcon 50 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that currently requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to include procedures to use certain values to correctly gauge the minimum allowable N1 speed of the operative engines during operation in icing conditions. This amendment adds a new requirement for operators to adjust the thrust reverser handle stop, install new wiring, and modify the Digital Electronic Engine Control (DEEC) software, which terminates the AFM revision. 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 flightcrew use of erroneous N1 thrust setting information displayed on the Engine Indication Electronic Display (EIED), which could result in in-flight shutdown of engine(s).
AD 2000-02-32 · published Feb 7, 2000, effective Mar 13, 2000
Eurocopter France Model SA. 315B Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SA. 315B helicopters, that currently requires initial and repetitive visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment requires the same corrective actions as the existing AD and would require an additional dye-penetrant inspection of the half-shell attachment clamps (clamps). This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation of the horizontal stabilizer and impact with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 2000-03-06 · published Feb 15, 2000, effective Mar 21, 2000
Eurocopter France Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SE 3130, SA 3180, SE 313B, SA 318B, and SA 318C helicopters, that currently requires visual inspections and modification, if necessary, of the horizontal stabilizer spar tube (spar tube). This amendment requires the same actions required by the existing AD, visually inspecting the four half- shell attachment clamps for cracks, and fitting a safety wire around the attachment clamps. This amendment is prompted by an in-service report of fatigue cracks that initiated from corrosion pits. The actions specified by this AD are intended to prevent fatigue failure of the spar tube, separation of the horizontal stabilizer and impact with the main or tail rotor, and subsequent loss of control of the helicopter.
AD 2000-02-12 · published Feb 17, 2000, effective Mar 3, 2000
Bell Helicopter Textron Canada Model 407 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-02-12, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (BHTC) Model 407 helicopters by individual letters. This AD requires inspecting engine oil cooler blower shaft bearings (bearings) for roughness at specified time intervals and replacing any rough bearings before further flight. This amendment is prompted by several bearing failures. The actions specified by this AD are intended to prevent bearing failure, loss of tail rotor drive, and a subsequent forced landing.
AD 2000-04-15 · published Feb 28, 2000, effective Mar 14, 2000
Bell Helicopter Textron Canada Model 222, 222B, 222U, and 230 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters. This action requires inspecting the swashplate assembly drive pin (drive pin) for damage or looseness, torque testing to determine if the interference fit between the drive pin and rotating ring (ring) is adequate, and replacing any unairworthy drive pin. This amendment is prompted by an accident investigation that revealed fatigue failure of a drive pin. The actions specified in this AD are intended to prevent fatigue failure of a drive pin and subsequent loss of control of the helicopter.
AD 2000-02-17 · published Feb 1, 2000, effective Feb 16, 2000
Rolls-Royce plc RB211 Trent 768-60, 772-60, and 772B-60 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211 Trent 768-60, 772-60, and 772B- 60 series turbofan engines. This action requires initial and repetitive visual inspections for flank wear on intermediate pressure turbine (IPT) shaft splines and intermediate pressure compressor (IPC) rear stub shaft splines. Components that show excessive flank wear must be replaced with serviceable parts. This amendment is prompted by reports of worn IPT shaft splines discovered at overhaul. The actions specified in this AD are intended to prevent IPT and IPC shaft spline flank wear, which could result in loss of drive between the IPT and IPC, leading to an IPT overspeed and possible disk burst, uncontained engine failure, and potential damage to the aircraft.
AD 2000-03-02 · published Feb 7, 2000, effective Apr 7, 2000
General Electric Company GE90 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain General Electric Company (GE) GE90 series turbofan engines, that requires reducing the cyclic life limits for certain fan mid shafts with undesirable microstructure, and removing from service those mid fan shafts prior to exceeding the new limits and replacing with serviceable parts. This amendment is prompted by reports of magnetic particle inspections conducted by the manufacturer identifying segregation in the raw material, resulting in lower fatigue life properties. The actions specified by this AD are intended to prevent fan mid shaft failure, which could result in a total loss of thrust and inflight engine shutdown.
AD 2000-03-03 · published Feb 7, 2000, effective Mar 13, 2000
General Electric Company CF34 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF34 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. 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 2000-03-04 · published Feb 10, 2000
General Electric Company CF6-80C2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This amendment requires removal from service of affected fan mid shafts prior to reaching a new, lower cyclic life limit, and replacement with serviceable parts. This amendment is prompted by recent component test data. The actions specified by this AD are intended to prevent fan mid shaft failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 2000-03-07 · published Feb 16, 2000, effective Mar 2, 2000
Rolls-Royce plc RB211-524H-36 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211-524H-36 series turbofan engines. This action requires, prior to further flight, installing an improved combustion liner with a strengthened head and improved heat shields. This amendment is prompted by a report of burn through of a combustor case that led to burning away of the thrust reverser and translating cowl and subsequent fire damage to the engine pylon. The actions specified in this AD are intended to prevent burn through of the combustor case due to combustion liner cracking, which can result in an engine fire and damage to the aircraft.
AD 99-23-26 R1 · published Feb 17, 2000, effective Feb 17, 2000
General Electric Aircraft Engines CF34 Series Turbofan Engines
This amendment revises an existing airworthiness directive (AD), that is applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines. That AD currently requires: (1) Replacement of Buna-N O-rings with Viton O-rings; or (2) A new location of the vent groove on the MFC mounting flange; or (3) Installation of an MFC with improved overspeed protection.
AD 2000-04-14 · published Feb 29, 2000, effective May 1, 2000
General Electric Company CF6-80C2 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, that requires replacement of the fuel tube connecting the flowmeter to the Integrated Drive Generator (IDG) and the fuel tube(s) connecting the Main Engine Control (MEC) or Hydromechanical (HMU) to the flowmeter with improved fuel tubes. This amendment is prompted by reports of fuel leaking in the core cowl cavity under high pressure that can be ignited by the hot engine case temperatures. The actions specified by this AD are intended to prevent high-pressure fuel leaks caused by improper seating of fuel tube flanges, which could result in an engine fire and damage to the airplane.
AD 2000-04-10 · published Feb 23, 2000, effective Mar 9, 2000
Hoffmann Propeller Co. HO27( ) and HO4/27 Series Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to Hoffmann Propeller Co. HO27( ) and HO4/27 series propellers. This action requires installing improved propeller mounting bolts to a higher torque value, operating the airplane for one flight, checking the torque, and retorquing, as required, to the correct torque value. This amendment is prompted by reports of insufficient torque of propeller mounting bolts due to operating conditions, loads, and environmental conditions such as humidity and temperature. The actions specified in this AD are intended to prevent propeller mounting bolt failure, which could result in propeller separation and loss of control of the airplane.
AD 2000-04-12 · published Feb 22, 2000, effective Mar 13, 2000
Cameron Balloons Ltd. (Thunder & Colt) Titanium Propane Cylinders, Part Number (P/N) CB2380 and P/N CB2383
This amendment adopts a new airworthiness directive (AD) that applies to all aircraft (specifically balloons) that incorporate certain Cameron Balloons Ltd. (Thunder and Colt) titanium propane cylinders, part number (P/N) CB2380 and P/N CB2383. This AD requires that you remove from service any of the affected titanium propane cylinders and replace each affected cylinder with an FAA-approved airworthy propane cylinder. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent titanium propane cylinders from cracking and releasing propane gas vapor while the balloon is in service. This could result in a propane explosion and fire.
