47 Airworthiness Directives: 28 airplane, 8 rotorcraft, 5 engine, 4 appliance, 2 glider.
AD 2000-05-01 · published Mar 3, 2000, effective Mar 20, 2000
McDonnell Douglas MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas MD-11 series airplanes. This action requires the deactivation of the forward and center cargo control units (CCU). This amendment is 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. The actions specified in this AD are intended to prevent such conditions, which could result in smoke and fire in the cargo compartment.
AD 2000-04-23 · published Mar 7, 2000, effective Mar 22, 2000
Dornier Model 328-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dornier Model 328-100 and -300 series airplanes. This action requires repetitive inspections to detect cracking of the trailing edge of the rudder spring tab, and follow-on actions, if necessary. For certain airplanes, this action provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent cracking of the rudder spring tab, which could result in reduced flutter margin and consequent loss of control of the airplane.
AD 2000-05-09 · published Mar 7, 2000, effective Mar 22, 2000
Boeing Model 757-200, -200PF, and -200CB Series Airplanes Powered by Rolls-Royce RB211-535C/E4/E4B Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200, -200PF, and -200CB series airplanes, that currently requires repetitive inspections of the engine thrust control cable system to detect discrepancies of the wire rope, fittings, and pulleys; and replacement, if necessary. That AD also requires a one-time inspection to determine the part number of certain pulleys, and replacement of existing pulleys with new pulleys, if necessary; and modification of the engine thrust control cable installation. This new action corrects a certain part number. This AD is prompted by reports of failure of certain engine thrust control cables. The actions specified by this AD are intended to prevent failure of certain engine thrust control cables, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane.
AD 2000-05-02 · published Mar 8, 2000, effective Apr 12, 2000
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050, 200, 500, and 600 series airplanes, that requires installation of certain components, and revisions of the Airplane Flight Manual. This action is necessary to prevent undetected failures of the horizontal and vertical stabilizer de-icing system, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-05-04 · published Mar 8, 2000, effective Apr 12, 2000
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive inspections to detect cracking of the fuselage skin in the area of the VHF2 antenna, and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct such cracking, which could result in cabin depressurization of the airplane.
AD 2000-05-05 · published Mar 8, 2000, effective Apr 12, 2000
EADS CASA Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235-100 and CN-235-200 series airplanes, that requires replacement of existing anti-icing distributor valves with new, improved valves. 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 ice accumulation on the wings or tail of the airplane, which could result in reduced controllability of the airplane.
AD 2000-05-06 · published Mar 8, 2000, effective Apr 12, 2000
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that requires a one-time inspection to detect incorrect wiring of the engine fire extinguisher bottle squibs, and corrective action, if necessary. It also requires a modification to the wiring and the addition of wire harness and bottle labeling for future reference. This amendment is prompted by reports of incorrect wiring of the engine fire extinguisher bottle squibs. The actions specified by this AD are intended to prevent failure of the engine fire extinguisher bottle to discharge, or discharge of the wrong engine fire extinguisher bottle.
AD 2000-05-07 · published Mar 8, 2000, effective Apr 12, 2000
Airbus Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that currently requires repetitive inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. That AD also requires modification of Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. This amendment expands the current inspection area for certain airplanes. 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 MLG attachment fittings, which could result in reduced structural integrity of the airplane.
AD 2000-05-08 · published Mar 8, 2000, effective Apr 12, 2000
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A321 series airplanes, that requires replacement of the actuator of the ram air turbine (RAT) with a new actuator. This amendment also requires modification of the actuator wiring. 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 RAT to deploy in an emergency situation, and consequent loss of electrical and hydraulic systems.
AD 2000-05-20 · published Mar 14, 2000, effective Apr 18, 2000
Dassault Aviation Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Fan Jet Falcon series airplanes; Model Mystere-Falcon 20, 50, 200, and 900 series airplanes; and Model Falcon 10, 900EX, and 2000 series airplanes, that requires a functional test of the passenger oxygen masks, determination of the part number of the installed oxygen mask bags; 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 ensure that proper plastic bags of the passenger oxygen masks are installed, and that the masks are functioning properly. Improper plastic bags that have cracks or improperly functioning masks could result in insufficient oxygen to passengers in the event of rapid depressurization of the airplane.
AD 2000-05-13 · published Mar 15, 2000, effective Apr 19, 2000
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires a one-time inspection of the main landing gear (MLG) axle flange to detect cracking, and follow-on corrective actions. For certain airplanes, this amendment also requires replacement of the original brake mounting gasket with a more durable aluminum-nickel-bronze gasket, and installation of new shear studs, if necessary. For certain airplanes, this amendment requires modification of the mounting flange holes of the brake torque tube. This amendment is prompted by reports of cracking in the axle flange and by reports of deterioration of the brake mounting gasket. The actions specified by this AD are intended to prevent fracture of the MLG axle and separation of the wheel from the MLG, and consequent reduced controllability of the airplane.
AD 2000-05-18 · published Mar 20, 2000, effective Apr 24, 2000
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracking on the door edge frames of the fuselage bulk cargo compartment, and repair, 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 cracks in the door edge frames of the fuselage bulk cargo compartment, which could result in reduced structural integrity of the airframe.
AD 2000-05-19 · published Mar 20, 2000, effective Apr 24, 2000
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires a one-time detailed visual inspection of the fuselage skin and bonded doubler area above the forward entry doorway to detect fatigue cracking or the existence of certain repairs, and follow-on corrective actions, if necessary. This action also requires a preventive modification or full-sized repair doubler, as applicable. This amendment is prompted by reports of fatigue cracking in the fuselage skin and bonded doublers in the forward and aft corners above the forward entry doorway. The actions specified by this AD are intended to prevent such fatigue cracking of the fuselage skin and bonded doubler, which could result in reduced structural integrity and consequent loss of cabin pressurization.
AD 2000-05-23 · published Mar 20, 2000, effective May 5, 2000
Thrush Aircraft, Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Ayres Corporation (Ayres) S2R series airplanes that are equipped with at least one main landing gear fuselage attach bolt with a grease fitting installed through the shank. This AD requires replacing the main landing gear fuselage attach bolts that are drilled with a grease fitting with undrilled (no grease access) attach bolts. This AD is the result of a report of cracks found in all four main landing gear fuselage attach bolts on one of the affected airplanes. The actions specified by this AD are intended to prevent collapse of the main landing gear caused by cracked main landing gear fuselage attach bolts, which could result in main landing gear collapse with possible wing fuel tank rupture and consequent fire
AD 2000-05-25 · published Mar 20, 2000, effective Apr 24, 2000
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires installation of a placard prescribing special procedures to be followed when operating at certain flight levels with the engine and airframe anti-ice switch ON; modification of the air brake auto-retract function; and a revision to the Airplane Flight Manual (AFM) relative to altitude and operating limitations associated with flight in icing conditions above 26,000 feet. This amendment requires installation/replacement of new placards. This amendment also provides for a terminating modification for the AFM revision and installation/replacement of placards. This amendment is prompted by reports of uncommanded engine thrust reductions (rollback) when operating in certain icing conditions that exist in the vicinity of thunderstorms. The actions specified by this AD are intended to prevent enginepower rollback during flight in icing conditions, a condition that could result in insufficient power to sustain flight.
AD 2000-05-27 · published Mar 20, 2000, effective Apr 24, 2000
BAE Systems (Operations) Limited Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires either a one-time nondestructive test (NDT) inspection or a detailed visual inspection for cracking of the fuselage skin in the vicinity of frame 29 between stringers 12 and 13, and repair, if necessary. This amendment requires that the current thresholds for these inspections be reduced and that repetitive inspections be performed. 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 fuselage skin in the specified area, which could result in reduced structural integrity of the airplane.
AD 2000-05-29 · published Mar 20, 2000, effective Apr 24, 2000
The Boeing Company 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 cracking of various areas of the forward pressure bulkhead, and repair, if necessary. This amendment also provides for certain optional preventive modifications, which, if accomplished, would terminate the repetitive inspections for the affected areas. This amendment is prompted by reports indicating that numerous fatigue cracks were found on critical areas of the forward pressure bulkhead. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in rapid decompression of the airplane fuselage.
AD 2000-06-02 · published Mar 20, 2000, effective May 5, 2000
Dornier Luftfahrt GmbH Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GmbH (Dornier) 228 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of 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 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 2000-06-03 · published Mar 20, 2000, effective May 5, 2000
Viking Air Limited Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Bombardier Inc. (Bombardier) Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of 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 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 2000-06-04 · published Mar 20, 2000, effective May 5, 2000
M7 Aerospace LLC Airplanes
This document adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft Corporation (Fairchild) SA226 and SA227 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of 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 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 2000-05-26 · published Mar 22, 2000, effective Apr 26, 2000
Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, that currently requires inspections to determine the proper installation of rivets in certain key holes and to detect cracks in the area of the key holes where rivets are missing; and correction of discrepancies. This amendment increases the compliance time for the existing requirements and expands the applicability of the existing AD to include additional airplanes. This action also requires various inspections of the subject area for discrepancies, and corrective actions, if necessary; and replacement of certain cargo door hinges with new hinges. For certain airplanes, this action also requires replacement of friction plates, stop fittings, and bolts with new parts. 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 cracks of the cargo door skin, certain frames, and entry door stop fittings and friction plates, which could result in reduced structural integrity of the airplane.
AD 2000-05-28 · published Mar 22, 2000, effective Apr 26, 2000
British Aerospace Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires a one-time inspection to detect cracking or corrosion of the forward attachment bolts of the engine pylon to wing interface, and corrective action, if necessary. It also requires re-installation with re-protected and sealed bolts torqued to a lower level. 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 cracking or corrosion of the forward attachment bolts of the engine pylon to wing interface, which could result in reduced structural integrity of the engine pylon attachment.
AD 2000-06-01 · published Mar 22, 2000, effective May 5, 2000
Cessna Aircraft Company 150, 152, 172, 177, 180, 182, 185, 188, 206, 207, 210, and 337 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 150, 152, 172, 177, 180, 182, 185, 188, 206, 207, 210, and 337 series airplanes. This AD requires measuring the visible length of standpipe (tube) in the top assembly of the fuel strainer assembly for the correct length, and replacing any fuel strainer assembly that does not have the correct length of standpipe. This AD is the result of reports that the fuel strainer assemblies on the affected airplanes were manufactured with the fuel standpipes incorrectly installed in the assembly housing top. The actions specified by this AD are intended to prevent foreign material from entering the fuel system and engine, which could result in loss of engine power or complete engine stoppage during flight.
AD 2000-05-21 · published Mar 23, 2000, effective Apr 27, 2000
Airbus Model A319, A320, A321, A330, and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, A321, A330, and A340 series airplanes, that requires revising the Airplane Flight Manual to provide the flight crew with certain instructions associated with the Global Positioning System (GPS). This amendment also requires modification of the Global Positioning System Signal Unit (GPSSU) of the satellite navigational system. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent position and altitude errors due to bad oscillator warm-up characteristics of the GPSSU, which could result in navigational errors that may exceed 0.5 nautical mile.
AD 2000-06-06 · published Mar 23, 2000
The New Piper Aircraft, Inc. PA-31 Series Airplanes
This document adopts a new airworthiness directive (AD) that applies to all The New Piper Aircraft, Inc. PA-31 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of 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 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 95-19-04 R1 · published Mar 27, 2000
Learjet Model 35, 35A, 36, 36A, 55, 55B, and 55C Airplanes
This amendment rescinds an existing Airworthiness Directive (AD), applicable to certain Learjet Model 35, 35A, 36, 36A, 55, 55B, and 55C airplanes. That AD currently requires installation of a placard on the instrument panel in the cockpit to advise the flightcrew that the Omega navigation system may be inoperative at certain engine speeds. That AD also provides for an optional installation of certain band reject filters, which eliminates the need for the placard. The requirements of that AD were intended to prevent excessive deviation from the intended flight path due to loss of navigation signals, which could result in a potentially low-fuel condition or a traffic conflict. Since the issuance of that AD, use of the Omega navigation system has been permanently discontinued; therefore, the original unsafe condition no longer exists.
AD 95-19-04 R1 RES · published Mar 27, 2000, effective Mar 27, 2000
Learjet Inc. Airplanes
This amendment rescinds an existing Airworthiness Directive (AD), applicable to certain Learjet Model 35, 35A, 36, 36A, 55, 55B, and 55C airplanes. That AD currently requires installation of a placard on the instrument panel in the cockpit to advise the flightcrew that the Omega navigation system may be inoperative at certain engine speeds. That AD also provides for an optional installation of certain band reject filters, which eliminates the need for the placard. The requirements of that AD were intended to prevent excessive deviation from the intended flight path due to loss of navigation signals, which could result in a potentially low-fuel condition or a traffic conflict. Since the issuance of that AD, use of the Omega navigation system has been permanently discontinued; therefore, the original unsafe condition no longer exists.
AD 2000-06-08 · published Mar 30, 2000, effective May 4, 2000
Airbus Model A330 and A340 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that currently requires repetitive operational tests of the override mechanism of the trimmable horizontal stabilizer (THS) to determine if the system functions correctly; and corrective action, if necessary. This amendment requires replacement of existing flight control primary computers (FCPC) with improved FCPC's, which would terminate the repetitive operational tests. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent uncommanded movement of the THS, which could result in reduced controllability of the airplane.
AD 2000-04-20 · published Mar 1, 2000, effective Apr 5, 2000
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters, that requires replacing a certain hydraulic relief valve (valve) with a different valve. This amendment is prompted by the discovery of a manufacturing defect in a valve. The actions specified by this AD are intended to prevent intermittent loss of hydraulic pressure to the flight controls and subsequent loss of control of the helicopter.
AD 2000-04-21 · published Mar 1, 2000, effective Apr 5, 2000
MD Helicopters Inc. Model MD600N Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters Inc. (MDHI) Model MD600N helicopters, that requires inspecting each internal fuel hose connection to verify proper installation. This amendment is prompted by the discovery that certain fuel hose connections between the fuel cells and the engine can be incorrectly installed. The actions specified by this AD are intended to prevent fuel starvation of the engine while the fuel gage indicates fuel remaining in the tank, engine flameout, and a subsequent forced landing.
AD 2000-05-11 · published Mar 9, 2000, effective Mar 24, 2000
Airbus Helicopters Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA.315B, SA.316B, SA.316C, SA 318B, SA 318C, SA.319B, SE 313B, SE 3130, SE.3160, and SA 3180 helicopters that have certain tail rotor blades (blades) installed. This action requires reducing the service life of those blades to 400 hours time-in-service (TIS). This amendment is prompted by the discovery that 10 blades were manufactured incorrectly. This condition, if not corrected, could result in failure of a blade and subsequent loss of control of the helicopter.
AD 2000-05-16 · published Mar 15, 2000, effective Mar 30, 2000
Sikorsky Model S-61 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Sikorsky Model S-61 helicopters. This action requires inspecting certain pylon upper and lower hinge web fittings (web fittings) for corrosion or a crack and either repairing certain web fittings or replacing any unairworthy web fittings with airworthy web fittings. The AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment is prompted by the discovery of extensive cracking in the area of the web fittings. The actions specified in this AD are intended to prevent structural failure of the tail boom due to a crack or corrosion of certain web fittings and subsequent loss of control of the helicopter.
AD 2000-05-17 · published Mar 15, 2000, effective Mar 27, 2000
Eurocopter France Model EC 120B Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model EC 120B helicopters, that currently requires, at specified time intervals, inspecting the engine coupling tube for cracks and replacing any cracked engine coupling tube with an airworthy engine coupling tube. This amendment requires, at specified time intervals, visually inspecting and dye-penetrant inspecting the coupling tube for any crack and replacing any cracked coupling tube with a reinforced, airworthy coupling tube. Replacing all coupling tubes and certain engine support fitting components is required on or before March 31, 2000. This amendment is prompted by the discovery of cracks in several coupling tubes. The actions specified by this AD are intended to prevent coupling failure, loss of engine drive, and a subsequent forced landing.
AD 2000-05-15 · published Mar 16, 2000, effective Mar 31, 2000
Eurocopter France Model AS355N Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS355N helicopters. This action requires inspecting the: 4 engine exhaust pipe ejector attachment lugs (lugs) for cracks; starter-generator (S-G) shaft for radial play; S-G attachment flange for cracks; and S-G attachment half- clamps for cracks. This amendment is prompted by 9 reports of S-G damage; 3 reports of the discovery of cracks in the lugs; and 1 report of an in-flight loss of the exhaust pipe ejector. The actions specified in this AD are intended to prevent separation of an engine exhaust pipe ejector from the helicopter, which could result in a tail rotor strike and subsequent loss of control of the helicopter.
AD 2000-06-07 · published Mar 24, 2000
Eurocopter Deutschland GMBH Model MBB-BK 117 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopters, that requires changing the retirement life for the tail rotor (output) drive bevel gear (bevel gear). This amendment is prompted by a fatigue analysis of the bevel gear conducted by the manufacturer due to installation of different tail rotor blades. The actions specified by this AD are intended to prevent fatigue failure of the bevel gear, loss of tail rotor drive, and subsequent loss of control of the helicopter.
AD 2000-06-10 · published Mar 30, 2000, effective Apr 14, 2000
Bell Helicopter Textron Canada Model 407 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This action requires preflight checking and repetitively inspecting the tail boom for a crack and replacing the tail boom if a crack is found. This amendment is prompted by four reports of cracks on the tail boom in the area of the horizontal stabilizer. The actions specified in this AD are intended to prevent separation of the tail boom and subsequent loss of control of the helicopter.
AD 2000-04-22 · published Mar 8, 2000, effective Apr 7, 2000
Rolls-Royce plc Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) RB211-524G2-T-19; RB211-524G3-T-19; RB211-524H2-T-19; RB211 Trent 768-60; and RB211 Trent 772-60 turbofan engines. This AD requires the replacement of the joint bolt assemblies that secure the high-pressure compressor (HPC) to the high-pressure turbine (HPT) of the RB211-524 series and Trent 768 and 772 series turbofan engines. This amendment is prompted by six incidents of bolt failure, one of which resulted in a damaged stage 6 HPC disk following an impact with a separated bolt head. The actions specified in this AD are intended to prevent failure of the HPC-to-HPT joint bolt assemblies, which could result in a cracked stage 6 HPC disk, possible uncontained engine failure, and damage to the airplane.
AD 2000-05-10 · published Mar 9, 2000, effective Apr 7, 2000
General Electric Company Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company GE90-85B series turbofan engines. This action requires removing from service aft mount whiffletrees prior to reaching a new cyclic life limit, and replacing with serviceable parts. This amendment is prompted by a reassessment of the low cycle fatigue capability of the engine mount system due to an increase in engine and propulsion system weight. The actions specified in this AD are intended to prevent aft mount whiffletree failure, which if it occurred with other critical aft mount component failures, could possibly result in an engine mount system failure, and separation of the engine from the aircraft.
AD 2000-05-12 · published Mar 16, 2000, effective Mar 31, 2000
Rolls-Royce plc RB211-524 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Rolls-Royce plc RB211-524 series turbofan engines. This action requires initial and repetitive ultrasonic inspections for cracks in fan blade dovetail roots, and, if necessary, replacement with serviceable parts. This action also provides the options of installing improved design fan blades or reworking current fan blades to the improved configuration as terminating action for the inspections. This amendment is prompted by reports of fan blade failures due to dovetail root cracks. The actions specified in this AD are intended to prevent possible multiple fan blade failures, which could result in an uncontained engine failure and damage to the aircraft.
AD 2000-05-14 · published Mar 23, 2000, effective Apr 27, 2000
AlliedSignal Inc. ALF502 and LF507 Series Turbofan Engines
This amendment supersedes two existing airworthiness directives (AD's), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that require rework or replacement of No. 4 and 5 bearing oil system hardware, initial and repetitive inspections of the oil system, optional installation of an improved oil filter bypass valve, and repetitive inspection of No. 4 and 5 bearing oil inlet tube, to ensure the integrity of the reduction gear system and overspeed protection system. This action would require replacement of the existing power turbine bearing housing assembly with a new, improved power turbine bearing housing assembly, and installation of a reworked or modified fourth turbine rotor disk assembly as a part of a design change to the new No. 4 bearing configuration that eliminates the requirement for repetitive inspections of oil system and No. 4 and 5 bearing oil inlet tube assembly. This amendment is prompted by one report of a contained power turbine rotor shaft separation forward of the Stage 4 low pressure turbine (LPT) rotor on an AlliedSignal Inc. ALF502R-5 engine. The LPT failure was caused by improper inspection of the engine oil system required by AD 97-05-11 R1. The actions specified by this AD are intended to prevent a No. 4 and 5 duplex bearing failure, which can result in a Stage 4 LPT rotor failure, an uncontained engine failure, and damage to the airplane.
AD 2000-05-22 · published Mar 28, 2000, effective May 2, 2000
CFM International CFM56-2, -2A, -2B, -3, -3B, and -3C Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines. This amendment requires a one-time eddy current inspection (ECI) for cracks in the bolt holes of high pressure turbine (HPT) front rotating air seals. This amendment is prompted by reports of machining anomalies in a bolt hole that led to an HPT front rotating air seal failure. The actions specified by this AD are intended to detect cracks in the bolt holes of HPT front rotating air seals, which can lead to an uncontained engine failure and damage to the aircraft.
AD 2000-04-24 · published Mar 8, 2000, effective May 8, 2000
Airbus SAS, The Boeing Company, Honeywell International Inc. Appliances
This amendment adopts a new airworthiness directive (AD), applicable to Honeywell International (formerly AlliedSignal Inc.) 36-300(A), 36-280(B), and 36-280(D) series Auxiliary Power Units (APUs). This amendment requires installation of an external load compressor containment shield, or installation of a load compressor impeller with lower stress concentrations. This amendment is prompted by reports of load compressor impeller failures. The actions specified by this AD are intended to prevent an uncontained APU failure and damage to the airplane.
AD 98-21-21 R1 · published Mar 9, 2000, effective May 1, 2000
Cessna Aircraft Company, Emerald Enterprises Ltd., Mooney Aviation Company Inc, Piper Aircraft Inc., Alexandria Aircraft LLC, Textron Aviation Inc. Appliances
This amendment revises Airworthiness Directive (AD) 98-21-21, which currently requires de-activating the electric door seal inflation system for all aircraft equipped with Bob Fields Aerocessories inflatable door seals. Since issuance of that AD, the manufacturer has developed a modification that would allow these electric door seal inflation systems to remain in service, and the Federal Aviation Administration (FAA) has approved this modification. This AD requires incorporating this modification as a method of complying with the current AD, and will exclude those airplanes with manual door seal inflation systems from the AD requirements of de-activating the system. The actions specified by this AD are intended to prevent smoke and a possible fire in the cockpit caused by overheating of the electric door seal inflation systems, which could result in passenger injury.
AD 2000-05-24 · published Mar 20, 2000, effective Apr 12, 2000
Honeywell International Inc. Appliances
This amendment adopts a new airworthiness directive (AD) that applies to all aircraft equipped with a certain Honeywell International Inc. (Honeywell) KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell. This AD requires that you inspect the autopilot servo actuator for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD is the result of a report of failure of the autopilot servo actuator to disengage when the autopilot power was removed. The actions specified by this AD are intended to detect and correct a loose fastener in the autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.
AD 2000-06-05 · published Mar 24, 2000, effective Apr 10, 2000
Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2 helicopters. This action requires replacing certain tail rotor blades before further flight after April 30, 2000. This amendment is prompted by loss of control of a helicopter due to a lightning strike on a tail rotor blade. This condition, if not corrected, could result in loss of a tail rotor blade and subsequent loss of control of the helicopter.
AD 2000-04-16 · published Mar 1, 2000, effective Mar 20, 2000
Alexander Schleicher Segelflugzeugbau Models ASH 25M and ASH 26E Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models ASH 25M and ASH 26E sailplanes. This AD requires that you accomplish the following: <bullet> Check to see if the sailplane has a muffler marked with an X on the front plate; <bullet> Accomplish pre-flight checks on the carbon reinforced plastic fairing for signs of overheat traces and/or perform boroscope inspections, depending on the number of sailplane hours accumulated; and <bullet> Replace the muffler with an improved design muffler either at a certain time period or immediately if discrepancies are found during any inspection. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent excessive radiation from causing the carbon fiber shroud on the engine muffler to delaminate. The carbon fiber shroud serves the same function as a firewall and delamination could cause a fire to spread throughout the sailplane.
AD 2000-04-26 · published Mar 8, 2000, effective Apr 25, 2000
Alexander Schleicher GmbH & Co. Gliders
This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher GmbH & Co. (Alexander Schleicher) Model ASW-27 sailplanes. This AD requires inspecting the elevator control circuit clearance inside the fuselage tail boom to the fin intersection to assure a clearance of at least 2.5 millimeters (mm) (1/10 inch wide), and adjusting any clearance that does not meet the criteria. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect interference in the elevator control circuit, which, if not corrected, could result in the elevator control jamming with possible loss of control of the sailplane.
