58 Airworthiness Directives: 38 airplane, 10 rotorcraft, 8 engine, 2 various.
AD 2000-06-13 · published Apr 4, 2000, effective May 9, 2000
Boeing Model 737-200, -200C, -300, and -400 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200, -200C, -300, and -400 series airplanes, that currently requires repetitive visual inspections to detect cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions, if necessary. That AD also provides an optional terminating action for certain repetitive inspections. This amendment requires repetitive high frequency eddy current (HFEC) inspections, and corrective actions, if necessary. This amendment also mandates accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent fatigue cracking of the corners of the door frame and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane.
AD 2000-07-01 · published Apr 4, 2000, effective May 9, 2000
Empresa Brasileira de Aeronautica, S.A. (EMBRAER), Model EMB-145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Empresa Brasileira de Aeronautica, S.A. (EMBRAER), Model EMB-145 series airplanes, that currently requires repetitive emergency extension (free-fall) functional tests of the nose landing gear (NLG), and lubrication of all NLG hinge points, to ensure that the NLG extends and locks down properly; and corrective action, if necessary. This amendment also requires a terminating modification that includes replacement of the NLG door solenoid valve with an improved valve; replacement of the landing gear (LG) safety pins holder with an improved holder; and replacement of the NLG maneuvering actuator with an improved actuator. This amendment also limits the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the NLG to extend and lock down properly, which could result in damage to the airplane structure, and consequent reduced controllability of the airplane upon landing.
AD 2000-07-02 · published Apr 5, 2000, effective Apr 20, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires deactivation of the map light assemblies; or modification and reidentification of the insulation blankets adjacent to certain map light assemblies, if applicable, a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies, and follow-on actions. This amendment is prompted by incidents in which a broken or cracked light bulb housing of the First Officer map light was found. The actions specified in this AD are intended to detect a broken light bulb housing, which could expose the power contactor. An exposed power contactor could cause the Captain, First Officer, or Right Observer map light to short or overheat, which could result in smoke or fire in the cockpit.
AD 2000-07-05 · published Apr 10, 2000, effective May 15, 2000
Boeing Model 767 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut, and follow-on actions, if necessary. That AD also provides optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by a report that a fractured diagonal brace lug was found during a routine maintenance inspection. The actions specified by this AD are intended to prevent cracking of the diagonal brace of the nacelle strut, which could result in failure of the diagonal brace, and consequent fatigue failure of a strut secondary load path and separation of the engine and strut.
AD 2000-07-09 · published Apr 10, 2000, effective Apr 25, 2000
Boeing Model 737-600, -700, and 800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and 800 series airplanes. This action requires a one-time inspection to detect loose nuts installed on the bolts at each end of the input rods connected to each elevator power control unit (PCU), and corrective action, if necessary. This amendment is prompted by reports of loose nuts on the bolts that connect the lower input crank arm and the vernier adjustment input rod of the elevator PCU. The actions specified in this AD are intended to detect and correct loose nuts on the bolts of the input crank arms of the elevator PCU, which could result in the loss of pivot bolts on the PCU and consequent loss of control of the airplane during takeoff and landing.
AD 2000-07-10 · published Apr 10, 2000, effective Apr 25, 2000
Boeing Model 747-200B, -300, -400, -400D, and -400F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-200B, -300, -400, -400D, and -400F series airplanes. This action requires repetitive inspections to detect cracking of fire extinguisher discharge tubes in certain engine struts, and corrective action, if necessary. For certain airplanes, this action also provides for a modification of the fire extinguisher discharge tubes, which constitutes terminating action for the repetitive inspections. This amendment is prompted by reports that cracked fire extinguisher discharge tubes have been found in the engine struts on certain airplanes. The actions specified in this AD are intended to detect and correct cracked fire extinguishing tubes in the engine struts. In the event of an engine fire, such cracked tubes could reduce the amount of fire extinguishing agent that can be delivered to the engine, and could result in a fire spreading from the engine to the wing of the airplane.
AD 2000-07-04 · published Apr 11, 2000, effective May 16, 2000
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires repetitive tests of the flight idle backup system of the propeller control system; repetitive inspections to determine the level of wear of the pins and bushings of the cam followers on the power lever rods of the engine controls; and follow-on corrective actions, if necessary. This amendment also requires eventual replacement of the power lever and condition lever rods of the engine controls with new, improved parts, which constitutes terminating action for the repetitive tests and 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 failure of the flight idle backup system. In the event of failure of the primary propeller control system, such failure of the flight idle backup system could lead to uncommanded movement of the pitch of the propeller blade to below flight idle and into reverse thrust during flight, and consequent reduced controllability of the airplane.
AD 2000-07-06 · published Apr 11, 2000, effective May 16, 2000
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and - 500 series airplanes. This AD requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions, if necessary. This AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which would constitute terminating action for the repetitive inspections. This amendment is prompted by reports indicating that fatigue cracks have been detected in the lower corners of the door frame and cross beam of the forward cargo door. The actions specified by this AD are intended to prevent fatigue cracking of the lower corners of the door frame and cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.
AD 2000-07-07 · published Apr 11, 2000, effective May 16, 2000
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires modification of wing center box angle fittings at frame 47. 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 reduced structural integrity of the wing center box angle fittings at frame 47 due to fatigue cracking.
AD 2000-07-08 · published Apr 11, 2000, effective May 16, 2000
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires replacement of the clevis ends on the tie rods for the center stowage bin supports with improved clevis ends. This amendment is prompted by a report that, under ultimate load conditions, the aluminum clevis ends on the tie rods for the center stowage bin supports can break. The actions specified by this AD are intended to prevent broken tie rods, which could result in the center stowage bins dropping onto the passenger seats below, causing possible injury to the occupants.
AD 2000-07-11 · published Apr 11, 2000, effective May 29, 2000
Industrie Aeronautiche e Meccaniche Model Piaggio P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires repetitively inspecting the brake assembly rods and tubings for wear or damage, and replacing any worn or damaged parts. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent the brake hydraulic fluid from leaking because of the brake assembly rods contacting the brake valve tubing, which could result in the inability to adequately stop the airplane during ground operations.
AD 2000-07-12 · published Apr 11, 2000, effective May 16, 2000
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires repetitive structural inspections of certain aging airplanes, and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This AD relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 727 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
AD 2000-07-13 · published Apr 11, 2000, effective May 16, 2000
Boeing Model 757-200 and -200PF Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -200PF series airplanes, that requires repetitive detailed visual inspections to detect loose fuse pins in the outboard beam attachment and forward trunnion support on the main landing gear (MLG) and to detect corrosion on the structure adjacent to the fuse pin; and corrective actions, if necessary. This amendment also requires eventual replacement of the fuse pins with new corrosion resistant steel (CRES) fuse pins, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of damaged fuse pins caused by corrosion. The actions specified by this AD are intended to prevent corroded fuse pins, which could result in the MLG separating from the wing, and consequent damage to the airplane and possible rupture of the wing fuel tank.
AD 2000-05-03 · published Apr 14, 2000, effective May 19, 2000
Airbus Model A300-600 and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus A300-600 and A310 series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections to detect cracking of the inner flange of fuselage frame FR73A, between beams 5 and 7, 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 detect and correct fatigue cracking of the inner flange of fuselage frame FR73A, which could result in reduced structural integrity of the fuselage.
AD 2000-07-14 · published Apr 14, 2000, effective May 19, 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 a certain passenger seat wire assembly to detect chafed or damaged wires; repair, if necessary; and installation of protective sleeving. This amendment is prompted by a report of arcing emanating from a certain passenger seat wire assembly. The actions specified by this AD are intended to prevent chafing of the passenger seat wire assembly against a bracket at the lower sidewall panel due to insufficient clearance between the bracket and seat wire assembly, which could result in arcing damage to the passenger seat wire assembly and consequent smoke and fire in the main cabin.
AD 2000-07-15 · published Apr 14, 2000, effective May 19, 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 electrical connections to detect corrosion; repair, if necessary; and installation of new circuit breakers and associated wiring. This amendment is prompted by a report that the ratings of certain circuit breakers of a certain video entertainment system exceed the ratings of their associated electrical connector contacts. The actions specified by this AD are intended to prevent a disparity between the ratings of certain circuit breakers and their associated electrical connector contacts, which could damage the electrical connector contacts and cause possible arcing and heat damage to the electrical connector.
AD 2000-07-16 · published Apr 14, 2000, effective May 19, 2000
McDonnell Douglas Model MD-11 and MD-11F Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires modification of the external power feeder cable clamping installation. This amendment also requires a detailed visual inspection of the external power feeder cables to detect chafed or damaged wires; and repair, if necessary. This amendment is prompted by reports of damage to the external power feeder cables located under the forward cargo compartment floor, which was caused by excessive cable length and/or maintenance personnel stepping on the cables. The actions specified by this AD are intended to prevent arcing from occurring under the forward cargo compartment floor as a result of damaged external power feeder cables, a situation that could lead to a fire at this location.
AD 2000-07-17 · published Apr 14, 2000, effective May 19, 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 general visual inspection to verify that the circuit breaker panel fully opens, follow-on inspections, and corrective actions, if necessary. This amendment is prompted by an incident of an operator not being able to fully open the observer's upper main circuit breaker panel due to a certain cable being too short. The actions specified by this AD are intended to ensure that the upper main circuit breaker panel opens fully. If the panel does not open fully, maintenance activities may be hindered and cause damage to the circuit breaker panel and wiring, which could result in electrical arcing and consequent smoke and fire in the flight compartment.
AD 2000-07-18 · published Apr 14, 2000, effective May 19, 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 a one-time detailed visual inspection of the generator power feeder wires to detect chafed or damage wires; repair, if necessary; and a modification of the generator power feeder wire installation. This amendment is prompted by reports of generator power feeder wire chafing on the closeout rib of the wing leading edge at a certain station due to insufficient clearance between the generator power feeder wires and the closeout rib. The actions specified by this AD are intended to prevent chafed and burnt generator power feeder wires, which could result in arcing damage to a certain closeout rib of the wing leading edge and fire damage to the wing structure, and consequent reduced structural integrity of the wing.
AD 2000-07-19 · published Apr 14, 2000, effective May 19, 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 detailed visual inspection of the external power feeder cables in the forward cargo compartment between certain stations to detect chafing or damage; repair, if necessary; and installation of spiral wrap. This amendment is prompted by reports of failure of the external power feeder cable due to being chafed during maintenance. The actions specified by this AD are intended to prevent chafing and damage to external ground power feeder cables, which could result in electrical arcing and consequent structural damage and smoke and fire in the forward cargo compartment.
AD 2000-07-20 · published Apr 14, 2000, effective May 19, 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 electrical resistance measurements of the ground studs of the No. 2 generator in the electrical power center of the center accessory compartment for proper electrical bonding and of the ground studs and circuit breaker terminations in the forward cargo compartment to detect looseness and for proper electrical bonding; and corrective actions, if necessary. This amendment is prompted by an incident of charred insulation blankets in the forward cargo compartment in the area of the external ground power receptacle and the galley external power circuit breakers, and another incident of a No. 2 "generator off" alert while the generator was still on line. The actions specified by this AD are intended to prevent arcing and overheating of terminals and consequent smoke and fire in the forward cargo compartment due to improper bonding of ground studs in the forward cargo compartment and in the electrical power center and due to improper installation of circuit breaker terminations.
AD 2000-07-21 · published Apr 14, 2000, effective May 19, 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 general visual inspection of wiring behind the control panel of the auxiliary power unit (APU) located in the cockpit to detect chafing; repair if necessary; and modification of the wiring. This amendment is prompted by an incident of chafing of wire bundles of the control module of the APU. The actions specified by this AD are intended to prevent such chafing and resultant arcing due to insufficient clearance between the wire bundles and the airplane structure, which could result in smoke and fire in the flight deck.
AD 2000-07-22 · published Apr 14, 2000, effective May 19, 2000
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive inspections to detect cracking of the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, 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 detect and correct fatigue cracking in the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box. Such cracking and discrepancies could result in reduced structural integrity of the airplane.
AD 2000-07-23 · published Apr 14, 2000, effective May 19, 2000
Bombardier Model DHC-8-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100 series airplanes, that requires changing the power supply for the thunderstorm lights from the left secondary bus to the left essential bus. 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 failure of the thunderstorm lights in the cockpit after loss of all generated electrical power. This condition could result in the cockpit instruments not being visible to the flight crew during certain emergency procedures, and consequent reduced controllability of the airplane.
AD 2000-07-24 · published Apr 14, 2000, effective May 19, 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 installation of new, improved bonding jumpers on the horizontal stabilizer. 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 ensure adequate electrical bonding between the horizontal and vertical stabilizers. Inadequate electrical bonding, in the event of a lightning strike, could cause electrical arcing, and result in damage to the hydraulic lines and consequent failure of the hydraulic systems.
AD 2000-07-25 · published Apr 14, 2000, effective May 1, 2000
Gulfstream Model G-IV Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires modification of the power feeder cable assemblies of the left and right engine alternators. This amendment is prompted by an incident of an in-flight engine fire on a Model G-IV series airplane due to chafing of the power feeder cable assembly of an engine alternator. The actions specified in this AD are intended to prevent interference and chafing between the alternator power feeder cables and adjacent structure, which could result in an electrical short circuit and consequent fire ignition source in the engine compartment.
AD 2000-07-29 · published Apr 14, 2000, effective May 19, 2000
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that currently requires a one-time operational test of the fire shut-off valves (FSOV) to determine if the FSOV's are functioning correctly, and replacement of failed parts with new or serviceable parts. This amendment requires repetitive performance of the operational test. This amendment also limits the applicability to airplanes installed with certain FSOV's. 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 failure of the FSOV's to close, which could result in failure of the engine fire shut-off system, and consequent inability to extinguish an engine fire.
AD 99-13-08 R1 · published Apr 17, 2000, effective May 22, 2000
Lockheed Model L-1011-385 Series Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing station (IWS) 310 and IWS 343, and of the web area around those fasteners; various follow-on actions; and modification of the web-to-cap fastener holes of the rear spar between IWS 299 and IWS 343, which, when accomplished, defers the initiation of the inspections for a certain period of time. The actions specified by that AD are intended to prevent fatigue cracking in the web of the rear spar of the wing, which could result in failure of the rear spar of the wing and consequent fuel spillage. This amendment, for certain airplanes, extends the compliance time for the modification of the web-to-cap fastener holes, and eliminates references to modification of the outboard spar.
AD 2000-07-26 · published Apr 18, 2000, effective May 23, 2000
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires a one-time detailed visual inspection to detect corrosion on the outer surface of the fuselage skin panel; application of corrosion preventive protection; and corrective action, 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 correct corrosion of the fuselage skin panel, which could result in cracking and consequent reduced structural integrity of the airplane.
AD 2000-07-28 · published Apr 18, 2000, effective Apr 18, 2000
Fokker Model F27 Series Airplanes Equipped With Rolls-Royce 532-7 “Dart 7” (RDa-7) Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with modified operational procedures to ensure continuous operation with the high pressure cock (HPC) levers in the lockout position. This amendment retains the requirements of the existing AD for the Normal and Abnormal Procedures Sections of the AFM, and requires incorporation of amended Limitations and Emergency Procedures Sections into the AFM. This amendment is prompted by a report that certain incorrect instructions had been included in the Emergency Procedures Section of the AFM revision required by the existing AD. The actions specified in this AD are intended to ensure that flightcrews follow correct procedures that will maintain the HPC levers in a permanent lockout position to prevent consequent burnout of the engines during flight.
AD 2000-08-03 · published Apr 20, 2000, effective May 5, 2000
McDonnell Douglas Model MD-11 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires the deactivation of the forward and center cargo control units (CCU). That amendment was prompted by a report of failure of a CCU, which produced overheating of the electrical pins inside the CCU; the subsequent release of hot gases and flames ignited an adjacent insulation blanket. This amendment expands the applicability of the existing AD to include additional airplanes. The actions specified in this AD are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
AD 2000-05-30 · published Apr 24, 2000, effective Apr 24, 2000
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect discrepancies of the cables, fittings, and pulleys of the engine thrust control cable installation, and replacement, if necessary. This AD also requires certain preventative actions on the engine thrust control cable installation for certain airplanes. This amendment is prompted by reports of failure of engine thrust control cables. The actions specified by this AD are intended to prevent such failures, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane.
AD 2000-08-08 · published Apr 24, 2000, effective May 9, 2000
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires a one-time inspection to detect cracking of the rear spar stiffeners in the wing center section; and modification of crack-free stiffeners, or repair of cracked stiffeners. This amendment is prompted by a report of severed rear spar stiffeners of the center wing, which resulted in cracking in the adjacent keel beam structure. The actions specified in this AD are intended to prevent failure of the keel beam structure.
AD 2000-08-07 · published Apr 26, 2000, effective May 31, 2000
Raytheon Model BAe 125-800A and BAe 125-800B, Model Hawker 800, and Model Hawker 800XP Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A and BAe 125- 800B, Model Hawker 800, and Model Hawker 800XP series airplanes, that currently requires the filling of two tooling holes on the firewalls of the left and right engine pylons with firewall sealant. This amendment requires the sealing of all unused (open) tooling holes on the firewalls of the left and right engine pylons, and expands the applicability to include additional airplanes. This amendment is prompted by reports of additional unused (open) tooling holes, found at locations other than those currently addressed. The actions specified by this AD are intended to prevent an engine fire from moving to the fuselage and to the lines that carry flammable fluid that are located inboard of the firewall.
AD 2000-08-15 · published Apr 26, 2000, effective May 31, 2000
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing 777 series airplanes, that requires a one- time inspection to detect cracking of the fastener holes common to the upper wing skins and trailing edge panels of both wings, and corrective actions, if necessary. This amendment also requires coldwork of the fastener holes and installation of new or serviceable fasteners. This amendment is prompted by a report indicating that fatigue cracks have been found in the upper wing skin of both wings. The actions specified by this AD are intended to prevent fatigue cracking of the upper wing skin, which could result in reduced structural integrity of the wing.
AD 2000-08-17 · published Apr 26, 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 inspections to detect damage of certain taxi light assemblies, and replacement with a new or serviceable part, if necessary. This AD also requires eventual replacement of certain taxi light assemblies with improved parts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that a damaged taxi light detached from an airplane and was ingested into the airplane engines. The actions specified by this AD are intended to prevent damage to the taxi light assembly, which could result in detachment of the taxi light assembly from the airplane, ingestion of taxi light debris into an engine, and consequent loss of thrust from one or both engines.
AD 2000-08-14 · published Apr 27, 2000, effective Jun 1, 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 or checks to detect broken H-11 steel bolts at the wing rear spar side-of-body on the lower chord splice plate and kick fitting; and corrective actions, if necessary. This AD also requires eventual replacement of the existing bolts with new Inconel bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of broken bolts at the wing rear spar side-of-body on the lower chord splice plate. The actions specified by this AD are intended to prevent cracking of the bolts due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure.
AD 2000-08-13 · published Apr 28, 2000, effective May 15, 2000
Learjet Model 45 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with certain instructions associated with an exterior preflight inspection and ground operations. This amendment is prompted by a report indicating the occurrence of an uncommanded brake application condition that was not annunciated in the cockpit. The actions specified in this AD are intended to provide the flight crew with procedures to detect an uncommanded brake application condition during taxi and takeoff. Such a condition could result in a possible wheel/brake fire and/or a high- speed rejected takeoff.
AD 2000-07-03 · published Apr 6, 2000
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters, that requires inspecting the wire harness for contact with the fuel line assembly, removing and replacing the fuel line assembly if chafing has occurred, and installing spiral wrap tubing on the fuel line assembly. This amendment is prompted by four incidents of contact between the wire harness and the fuel line assembly. The actions specified by this AD are intended to prevent contact between the wire harness and the fuel line, which could result in chafing of the wire harness and a potential fire hazard.
AD 2000-08-02 · published Apr 14, 2000, effective May 1, 2000
Agusta Model A109A, A109AII, and A109C Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Agusta Model A109A, A109AII, and A109C helicopters. This action requires inspecting the main transmission to determine if certain Gleason crowns are installed and replacing any unairworthy Gleason crown with an airworthy Gleason crown. This amendment is prompted by the discovery of a cracked Gleason crown during an unscheduled transmission inspection prompted by abnormal noises coming from the transmission during main rotor deceleration. The actions specified in this AD are intended to prevent failure of the main transmission, loss of rotor drive, and subsequent loss of control of the helicopter.
AD 86-15-10 R2 · published Apr 18, 2000, effective May 23, 2000
Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, F2 and N Helicopters
This amendment revises an existing airworthiness directive (AD), applicable to Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, F2 and N helicopters, that currently requires repetitive inspections of the main rotor head components, the main gearbox (MGB) suspension bars, and the ground resonance prevention system components at intervals not to exceed 400 hours time-in-service (TIS). This amendment requires the same inspections, but at intervals not to exceed 500 hours TIS. This amendment is prompted by reports of confusion and unnecessary costs associated with the difference in the current 400 hours TIS inspection interval and the current manufacturer's master service recommendation of 500 hours TIS inspection interval. The actions specified by this AD are intended to eliminate confusion and unnecessary costs and to prevent ground resonance due to reduced structural stiffness, which could lead to failure of a main rotor head or MGB suspension component and subsequent loss of control of the helicopter.
AD 2000-08-04 · published Apr 19, 2000, effective May 4, 2000
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R44 helicopters. This action requires replacing certain serial number (S/N) sprag clutches with an airworthy sprag clutch as specified in this AD. This amendment is prompted by several reports of sprag clutch failures. The actions specified by this AD are intended to prevent a sprag clutch failure, loss of main rotor RPM during autorotation, and subsequent loss of control of the helicopter.
AD 2000-08-06 · published Apr 19, 2000
Eurocopter France Model SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA-366G1 helicopters, that requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical systems and subsequent loss of control of the helicopter.
AD 2000-08-09 · published Apr 20, 2000, effective May 5, 2000
Robinson Helicopter Company Model R22 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R22 helicopters. This action requires replacing certain serial number sprag clutches with an airworthy sprag clutch as specified in this AD. This amendment is prompted by several reports of clutch assemblies with cracked or fractured sprag ends. The actions specified by this AD are intended to prevent a sprag clutch failure, loss of main rotor RPM during autorotation, and subsequent loss of control of the helicopter.
AD 2000-08-52 · published Apr 21, 2000
Bell Helicopter Textron, Inc. Helicopters
AD 2000-08-05 · published Apr 24, 2000, effective May 30, 2000
Agusta Model A109C and A109K2 Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109C and A109K2 helicopters, that currently requires removing the main rotor pitch control link assemblies, measuring the radial play of each upper and lower spherical rod-end bearing (bearing), and replacing any unairworthy bearing. This amendment requires replacing the pitch control link assembly with an assembly that has increased durability and wear resistance. This amendment is prompted by reports of increased helicopter vibration caused by wear of bearings on certain pitch control link assemblies. The actions specified by this AD are intended to eliminate the need for recurring bearing inspections and to prevent failure of a bearing, increased helicopter vibration, and subsequent reduced controllability of the helicopter.
AD 2000-08-53 · published Apr 26, 2000
AST, Inc, Rotorcraft Development Corporation, San Joaquin Helicopters, International Helicopters, Inc., Robinson Air Crane, Inc., Smith Helicopters, Southern Helicopter, Inc., Southwest Florida Aviation International, Tamarack Helicopters, Inc., US Helicopter, Inc., Richards Heavylift Helo, Inc., Utah State University, Hagglund Helicopters, LLC, Overseas Aircraft Support
AD 2000-08-16 · published Apr 28, 2000, effective Jun 2, 2000
Eurocopter Deutschland GMBH Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 Helicopters
This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters. This AD requires modifying the engine and transmission cowling doors (cowling doors). This amendment is prompted by an emergency landing of an ECD Model MBB-BK 117 helicopter after the No. 1 engine cowling opened, separated from the helicopter, and struck the main and tail rotor blades resulting in a tail rotor imbalance and subsequent departure of the tail rotor gear box from the helicopter. The actions specified by this AD are intended to prevent the cowling doors opening during flight, separating from the helicopter and impacting the main or tail rotor blades, and subsequent loss of control of the helicopter.
AD 2000-06-09 · published Apr 11, 2000, effective Jun 12, 2000
Turbomeca Arrius 1A Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Arrius 1A series turboshaft engines, that requires installation of module TU63, which provides a separate supply of fuel for one of the 10 main injectors of the fuel injection system. This action is prompted by reports of unexpected power loss during test flights. The actions specified by this AD are intended to prevent unexpected power loss, which could result in an uncommanded in-flight engine shutdown, autorotation, and forced landing.
AD 2000-06-11 · published Apr 11, 2000, effective Jun 12, 2000
Turbomeca Makila 1 Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Makila 1 series turboshaft engines, that requires a one-time visual inspection of the scavenge and lubrication systems for obstruction due to coke deposits, then reconditioning of the engine oil system prior to return to service. This amendment is prompted by a report of an in-flight engine shutdown due to roller bearings contaminated by certain types of detergent oil. The actions specified by the proposed AD are intended to prevent in-flight engine shutdown due to roller bearing failure following oil contamination.
AD 2000-06-12 · published Apr 11, 2000, effective Jun 12, 2000
Turbomeca Artouste III Series Turboshaft Engines
This amendment adopts a new airworthiness directive (AD), applicable to Turbomeca Artouste III series turboshaft engines, that requires smoke emissions checks after every ground engine shutdown. If smoke is detected, this AD would require inspecting for fuel flow. If fuel flow is not detected, the engine may have injection wheel cracks, which would require removing the engine from service for repair. If fuel flow is detected, the engine may have a malfunctioning electric fuel cock, which would require removing the electric fuel cock from service and replacing it with a serviceable part. This action is prompted by reports of cracked injection wheels. The actions specified by this AD are intended to prevent injection wheel cracks, which could result in an in-flight engine shutdown.
AD 2000-08-01 · published Apr 18, 2000, effective Jun 19, 2000
Rolls-Royce plc Tay 650-15 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc Tay 650-15 series turbofan engines. This AD requires the establishment of cyclic life limits for stage 1 high pressure turbine (HPT) and stage 1 low pressure turbine (LPT) disks operating under new flight plan profiles. This amendment is prompted by reports that, on some engines, cracks in the stage 1 HPT and stage 1 LPT disks could initiate and propagate at a faster rate than forecast under the flight plan profiles originally published at the time the engine design was certified. The actions specified by this AD are intended to prevent crack initiation and propagation leading to turbine disk failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 2000-08-10 · published Apr 24, 2000, effective Oct 23, 2000
General Electric Company GE90 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company GE90 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 2000-08-11 · published Apr 24, 2000, effective Oct 23, 2000
General Electric Company CF6-6, CF6-45, and CF6-50 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6-6, CF6-45, and CF6-50 series turbofan engines, that requires revisions to the Time Limits Section 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 would add additional eddy current inspections (ECI) for the high pressure turbine rotor (HPTR) Stage 1 and 2 disks. This action is prompted by additional focused inspection procedures 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 2000-08-12 · published Apr 24, 2000, effective Oct 23, 2000
General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 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 eddy current inspections (ECI) for the high pressure turbine rotor (HPTR) Stage 1 and 2 disks for all affected engine models, and would add fan forward shaft inspections for the CF6-80C2 engine model only. This amendment is prompted by additional focused inspection procedures for 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 2000-08-51 · published Apr 28, 2000
Teledyne Continental Motors Engines
AD 2000-07-27 · published Apr 18, 2000, effective May 3, 2000
Various Transport Category Airplanes Equipped With Certain Honeywell Air Data Inertial Reference Units
This amendment adopts a new airworthiness directive (AD) that is applicable to various transport category airplanes equipped with certain Honeywell air data inertial reference units (ADIRU). This action requires inspection of a failed ADIRU to determine its modification status, and replacement of an unmodified failed ADIRU with a serviceable ADIRU. This action also provides for optional terminating action for the requirements of the AD. This amendment is prompted by reports of dual critical failures of inertial reference units on ADIRU's during flight. The actions specified in this AD are intended to prevent loss of the main sources of attitude data, consequent high pilot workload, and a significant increase in the likelihood of pilot error.
AD 99-23-22 R2 · published Apr 20, 2000
Various Transport Category Airplanes Equipped with Mode “C” Transponder(s) with Single Gillham Code Altitude Input
This amendment rescinds Airworthiness Directive (AD) 99-23-22 R1, which is applicable to various transport category airplanes equipped with Mode "C" transponder(s) with single Gillham code altitude input. That AD requires repetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective actions, if necessary. The requirements of that AD were intended to prevent false advisories that direct the flightcrew to change course and either climb or descend, which could result in the flightcrew deviating the airplane from its assigned flight path, and a possible mid-air collision. Since the issuance of that AD, test data have been collected that demonstrate that the repetitive tests are unnecessary.
