45 Airworthiness Directives: 34 airplane, 9 rotorcraft, 2 engine.
AD 2000-08-19 · published May 1, 2000, effective Jun 5, 2000
Boeing Model 727 and 727C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and 727C series airplanes, that requires one-time inspections of the exterior body skin located at the forward corners of the mid-galley door hinge cutouts to detect cracking, and corrective actions, if necessary. This AD also requires modification of the body skin of the mid-galley door hinge cutouts. This amendment is prompted by a report indicating that, during fatigue testing on a Boeing Model 727 series airplane, a crack was found in the body skin at the lower forward corners of the mid-galley door hinge cutouts due to cabin pressurization cycles. The actions specified by this AD are intended to prevent such fatigue cracking of the body skin, which could result in reduced structural integrity of the fuselage and consequent loss of cabin pressurization.
AD 2000-08-20 · published May 1, 2000, effective Jun 5, 2000
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that requires modification of the high pressure bleed valve controller of each engine. This amendment is prompted by reports of failure of the bleed air system components such as the thermal compensators and bleed air ducts. The actions specified by this AD are intended to prevent such failures of the bleed air system components, which could result in high temperature air leaking into the cabin and/or cargo areas and could possibly require an emergency landing and evacuation.
AD 2000-08-21 · published May 1, 2000, effective Jun 5, 2000
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracking of the forward and aft inner chords and the splice fitting of the forward inner chord of the station 2598 bulkhead, and repair, if necessary. This amendment is prompted by reports of fatigue cracking found in those areas. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads.
AD 2000-09-02 · published May 2, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger to a cargo-carrying ("freighter") configuration, that requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; an inspection of the door wire bundle; and repair or replacement of discrepant parts. This amendment also requires, among other actions, modification of the hydraulic and indication systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This amendment is prompted by the FAA's determination that certain main deck cargo door systems do not provide an adequate level of safety, and that the means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked is inadequate. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage.
AD 2000-09-01 · published May 3, 2000, effective Jun 7, 2000
McDonnell Douglas Model DC-8 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that currently requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; repetitive inspections of the wire bundle and door latch rollers to detect damage; and repair or replacement of damaged components. This amendment requires, among other actions, modification of the indication and hydraulic systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This amendment is prompted by the FAA's determination that certain main deck cargo door systems do not provide an adequate level of safety; the latching and locking mechanisms are not of adequate design to prevent structural deformation in the event of component jamming; and that there is an absence of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of the door, flight control, or severe structural damage.
AD 2000-09-03 · published May 4, 2000, effective May 19, 2000
Boeing Model 747-400 Series Airplanes Equipped With General Electric CF6-80C2 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently 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 adds an appendix and revises certain actions in the existing AD. This amendment is prompted by a report indicating that completion of the cone brake test of the center drive unit is ineffective for certain airplanes. 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 in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 2000-09-04 · published May 4, 2000, effective May 19, 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 revises certain actions in the existing AD. This amendment is prompted by a report indicating that certain instructions referenced in the existing AD for accomplishment of the cone brake test of the center drive unit are not accurate for certain airplanes. 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 in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
AD 2000-07-51 · published May 5, 2000, effective May 10, 2000
McDonnell Douglas Model 717-200 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-07-51 that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model 717-200 series airplanes by individual notices. This AD requires coiling and stowing of electrical wires between the glareshield control panel and the Integrated Standby Instrument System; and revising the abnormal procedures of the Procedures section of the Airplane Flight Manual to include procedures for identifying and pulling certain circuit breakers if the altimeter Captain's Primary Flight Display (PFD) data become unreliable. This action is prompted by a report of two incidents in which an intermittent loss of altitude data occurred simultaneously on the Captain's PFD, First Officer's PFD, and the Integrated Standby Instrument System (ISIS) altitude display due to a voltage drop in the power distribution control unit. The actions specified by this AD are intended to prevent loss of all altitude information and subsequent essential navigation data for continued safe flight and landing.
AD 2000-08-18 · published May 9, 2000, effective Jun 13, 2000
McDonnell Douglas Model DC-9 Series Airplanes, and Model MD-88 and MD-90-30 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, and Model MD-88 and MD-90-30 airplanes, that requires replacement of the lanyard assembly pins of the evacuation slides with solid corrosion-resistant pins. This amendment is prompted by a report that, due to stress corrosion on the lanyard pins, the arms of the lanyard assembly of the evacuation slide were found to be frozen. The actions specified by this AD are intended to prevent the improper deployment of the evacuation slide due to stress corrosion, which could delay or impede evacuation of passengers during an emergency.
AD 2000-09-06 · published May 9, 2000, effective May 30, 2000
Maule Aerospace Technology, Inc. M-4, M-5, M-6, M-7, MX-7, and MXT-7 Series Airplanes and Models MT-7-235 and M-8-235 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Maule Aerospace Technology, Inc. (Maule) M-4, M-5, M-6, M-7, MX-7, and MXT-7 series airplanes and Models MT-7-235 and M-8- 235 airplanes. This AD requires you to inspect all Nicopress<SUP>TM</SUP> sleeve terminal ends for correct size compression, with adjustment or replacement, as necessary. This AD results from a report of the rudder cable slipping out of the Nicopress<SUP>TM</SUP> sleeve while one of the affected airplanes was landing. The actions specified by this AD are intended to detect and correct improper crimping of the Nicopress<SUP>TM</SUP> sleeve, which could cause a control cable to slip from the sleeve. This could result in loss of rudder, elevator, aileron, or flap control.
AD 2000-09-07 · published May 12, 2000, effective Jun 16, 2000
McDonnell Douglas Model DC-10-10, -15, -30, -30F, and -40 Series Airplanes, and KC-10A (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F, and -40 series airplanes, and KC-10A (military) airplanes, that requires a one-time general visual inspection of circuit breakers to determine the manufacturer of the circuit breakers, and corrective action, if necessary. This amendment is prompted by incidents of smoke and electrical odor in the flight compartment and cabin area as a result of failure of circuit breakers. The actions specified by this AD are intended to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin.
AD 2000-09-08 · published May 12, 2000, effective Jun 16, 2000
Boeing Model 747-100, -200, 747SP, and 747SR Series Airplanes Equipped With Pratt & Whitney JT9D-7, -7A, -7F, and -7J Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, 747SP, and 747SR series airplanes, that requires one-time detailed visual and eddy current inspections to detect cracking of the nose cowl mounting flange; rework of the nose cowl mounting flange; eddy current inspection to detect cracking of the reworked nose cowl mounting flange; and corrective action, if necessary. This amendment is prompted by reports of the nose cowl separating from the engine and departing the airplane following severe engine vibration. The actions specified by this AD are intended to prevent separation of the nose cowl from the engine, which could cause collateral damage to the airplane, and, possibly, reduced controllability of the airplane.
AD 2000-09-09 · published May 12, 2000, effective Jun 16, 2000
EMBRAER Model EMB-145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that currently requires revisions to the Airplane Flight Manual (AFM) to provide the flight crew with updated procedures for prohibiting use of the autopilot below 1,500 feet above ground level, emergency procedures for pitch trim runaway, and abnormal procedures for autopilot trim failure and stabilizer out of trim. That AD also requires installation of certain warning placards. This amendment requires replacement of a certain integrated computer with a new integrated computer; installation of an upgraded integrated computers checklist; and removal of certain placards and certain limitations in the AFM. 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 pitch trim system, which could cause undetected autopilot trim runaway, and consequent reduced controllability of the airplane, uncommanded autopilot disconnect, and excessive altitude loss.
AD 2000-09-10 · published May 12, 2000, effective Jun 16, 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 modification of certain electrical looms of the nose and main landing gear and modification of the rotor shaft attachment of the nose and main landing gear tachometers. 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 erratic operation of the wheel tachometers, which could result in degradation of the braking performance, and possible increased landing roll.
AD 2000-09-11 · published May 12, 2000, effective May 30, 2000
Fokker Model F.28 Mark 0070 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes. This action requires a one-time inspection to detect loose bolts attaching the gustlock counter-bracket to the pulley on the elevator tension regulator assembly, 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 in this AD are intended to prevent restricted elevator movement and consequent reduced controllability of the airplane.
AD 2000-09-12 · published May 12, 2000, effective Jun 16, 2000
Raytheon (Beech) Model 400A and 400T Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that requires replacement of temperature switch assemblies of the wing ice protection system with new, improved parts. This amendment is prompted by reports of electrical continuity problems with solder joints on the temperature switches of the wing ice protection system. The actions specified by this AD are intended to prevent detachment or breakage of wires in the temperature switch assemblies of the wing ice protection system. Such detachment or breakage of wires could result in the flightcrew not being advised of an over-temperature situation on the leading edge of the wing, which could result in structural damage to the wing.
AD 2000-09-13 · published May 15, 2000, effective Jun 23, 2000
British Aerospace Jetstream Model 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to British Aerospace Jetstream Model 3201 airplanes. This AD requires you to inspect the fuel quantity indication system for damage to the insulation of the wiring within the fuel tanks, and repair or replace damaged wiring. Damage is defined as corrosion (indicated by a dark stain), cuts, or nicks. 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 detect damage to the insulation of the wiring within the fuel tanks of the fuel quantity indication system, which could result in a malfunction in the cockpit indicators and/or electrical sparking inside the fuel tank with consequent fire or explosion.
AD 2000-09-15 · published May 15, 2000, effective Jul 24, 2000
Mitsubishi Heavy Industries, Ltd. MU-2B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires modifying the airplanes' operating systems. This AD results from several icing-related incidents and accidents of MU-2B series airplanes, and the Federal Aviation Administration's investigation of the airplane design and pilot's ability to operate in icing conditions. The actions specified by this AD are intended to assist in preventing departure from controlled flight while operating in icing conditions.
AD 2000-10-02 · published May 15, 2000, effective Jun 19, 2000
Airbus Model A319, A320, A321, A330, and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, A321, A330, and A340 series airplanes, that requires repetitive inspections to detect missing and incorrectly installed parts of the footrest actuator assembly, and replacement of discrepant parts with new parts. This AD 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 prevent detachment of the footrest assembly actuator, which could result in partial blockage of the rudder pedals and reduced controllability of the airplane.
AD 2000-10-03 · published May 17, 2000, effective Jun 21, 2000
McDonnell Douglas Model DC-10 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, that requires a one-time detailed visual inspection to determine if wire segments of the wire bundle routed through the feed through on the aft side of the flight engineer's station are damaged or chafed, and corrective actions, if necessary. This amendment is prompted by a report of smoke coming out of the flight engineer's upper right circuit breaker panel, which was followed by circuit breakers popping and the panel lights going out. The actions specified by this AD are intended to prevent chafing of the wire bundle located behind the flight engineer's panel caused by the wire bundle coming in contact with the lower edge of the feed through and consequent electrical arcing, which could result in smoke and fire in the cockpit.
AD 2000-10-04 · published May 22, 2000, effective Jun 6, 2000
Israel Aircraft Industries, Ltd., Model 1124 and 1124A Westwind Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model 1124 and 1124A Westwind airplanes. This action requires a one-time X-ray inspection to detect missing rivets at the rib-to-spar connection of the aileron ribs, and corrective actions, if necessary. This action is necessary to prevent cracking of the aileron skin due to missing rivets, which could result in reduced structural integrity of the aileron and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-10-11 · published May 22, 2000
Gulfstream Model G-159 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-159 series airplanes, that requires an inspection to determine the type of pneumatic deicing boots, and an Airplane Flight Manual (AFM) revision only 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 2000-10-01 · published May 24, 2000, effective Jun 28, 2000
Airbus Model A300 B2, A300-B2K, A300 B4-2C, A300 B4-100, and A300 B4-200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2, A300 B2K, A300 B2-200, A300 B4, A300 B4-100, and A300 B4-200 series airplanes, that currently requires certain structural inspections and modifications. This amendment requires that those inspections be accomplished on additional airplanes. This action also requires new repetitive inspections for airplanes in certain configurations at revised thresholds and intervals. 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 and cracking of the wings and fuselage, which could result in reduced structural integrity of the airplane.
AD 2000-10-12 · published May 24, 2000, effective Jun 8, 2000
Boeing Model 747-400 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747- 400 series airplanes. This action requires repetitive inspections to detect damage or deflection of the crew rest heat exchanger, and follow-on actions, if necessary. This amendment is prompted by reports of cracking and buckling of the front edge of the crew rest heat exchanger on several airplanes. The actions specified in this AD are intended to detect and correct damage or deflection of the crew rest heat exchanger, which could result in jamming of the rudder or elevator control cables, and consequent reduced controllability of the airplane.
AD 99-15-04 R1 · published May 25, 2000, effective Jul 28, 2000
The New Piper Aircraft, Inc., Models PA-46-310P and PA-46-350P Airplanes
This amendment revises Airworthiness Directive (AD) 99-15-04, which currently requires you to calibrate, inspect, and repair or replace portions of the turbine inlet temperature system on all The New Piper Aircraft, Inc. (New Piper) Models PA-46-310P and PA-46-350P airplanes (different actions for different airplane models). Information reveals that the AD should not apply to airplanes where the factory installed turbine inlet temperature gauge and associated probe have been replaced through supplemental type certificate (STC). This AD retains the actions of AD 99-15-04, and restricts the applicability accordingly. The actions specified by this AD are intended to prevent improper engine operation caused by improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes, which could result in engine damage/failure with consequent loss of control of the airplane.
AD 2000-10-15 · published May 26, 2000, effective Jun 30, 2000
Airbus Model A320 Series Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to certain Airbus Model A320 series airplanes, that currently require modification of the rear spar web of the wing and cold expansion of certain attachment holes for the forward pintle fitting and certain holes at the actuating cylinder anchorage of the main landing gear (MLG). This amendment adds a requirement for repetitive inspections to detect fatigue cracking in certain areas of the rear spar of the wing, and corrective action, if necessary. This amendment also provides for optional terminating action for the requirements of this 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 detect and correct fatigue cracking, which may lead to reduced structural integrity of the wing and the MLG.
AD 2000-10-16 · published May 26, 2000, effective Jun 30, 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 repetitive inspections for discrepancies of the lock bolt for the pintle pin on the main landing gear (MLG), and follow-on corrective actions, if necessary. This amendment requires additional follow-on actions for certain airplanes. This amendment also provides for optional terminating action for the requirements of this 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 detect and correct a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the pintle fitting bearing, and consequent collapse of the MLG during landing.
AD 2000-10-17 · published May 26, 2000, effective Jun 30, 2000
Boeing Model 747 Series Airplanes Equipped With Pratt & Whitney JT9D-70 Series Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections, tests, and certain modifications of the thrust reverser control and indication system and wiring on each engine, and corrective action, if necessary. This amendment also requires installation of a terminating modification, and repetitive functional tests 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 significant reduction in airplane controllability. 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, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
AD 2000-10-18 · published May 26, 2000, effective Jun 30, 2000
Airbus Industrie Model A300, A300-600, and A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that currently requires inspections to detect cracks in the lower spar axis of the pylons between ribs 6 and 7, and repair, if necessary. For certain Model A310 series airplanes, this amendment reduces the currently required inspection thresholds and intervals, and removes an option for a terminating modification. 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 such fatigue cracking, which could result in reduced structural integrity of the engine pylon's lower spar, and possible separation of the engine from the airplane.
AD 2000-10-19 · published May 26, 2000, effective Jun 30, 2000
Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra and Astra SPX Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra and Astra SPX series airplanes, that requires replacement of the existing pneumatic de-icing boot pressure indicator switch with a newly designed switch. This amendment is prompted by an occurrence on a similar airplane model in which the pneumatic de-icing boot indication light may have provided the flightcrew with misleading information as to the proper functioning of the de-icing boots. The actions specified by this AD are intended to prevent ice accumulation on the airplane leading edges, which could result in reduced controllability of the airplane.
AD 2000-10-21 · published May 26, 2000, effective Jun 12, 2000
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires a one-time general visual inspection of the seat locks and seat tracks of the flightcrew seats to ensure that the seats lock in position and to verify that lock nuts and bolts of adequate length are installed on the rear tracklock bracket, and corrective action, if necessary. This action is necessary to prevent uncommanded movement of the flightcrew seats during acceleration and take-off of the airplane, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-10-22 · published May 26, 2000, effective Jun 20, 2000
REVO, Incorporated Models Lake LA-4, Lake LA-4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain REVO, Incorporated (REVO) Models Lake LA-4, Lake LA- 4A, Lake LA-4P, Lake LA-4-200, and Lake Model 250 airplanes. This AD requires you to: inspect the left and right wing upper and lower spar doublers for cracks; replace any cracked parts; and incorporate a modification kit. This AD is the result of a report of a fatigue crack found at the second most inboard wing attachment bolt hole on one of the affected airplanes. Similar fatigue cracking has since been reported on seven more of the affected airplanes, including incidents where the fatigue cracking occurred on airplanes with less than 500 hours time-in-service (TIS). The actions specified by this AD are intended to detect and correct cracks in the wing spars, which could result in the wing separating from the airplane with consequent loss of control.
AD 2000-11-01 · published May 26, 2000, effective Jun 30, 2000
McDonnell Douglas Model DC-9-80 and MD-90-30 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 and MD-90-30 series airplanes, and Model MD-88 airplanes, that requires a determination be made of whether, and at what locations, metallized polyethyleneteraphthalate (MPET) insulation blankets are installed, and replacement of MPET insulation blankets with new insulation blankets. This amendment is prompted by reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets covered with MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead to a much larger fire.
AD 2000-11-02 · published May 26, 2000, effective Jun 30, 2000
McDonnell Douglas Model DC-10-10F, DC-10-15, DC-10-30, DC-10-30F, and DC-10-40 Series Airplanes, and Model MD-11 and -11F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10F, DC-10-15, DC- 10-30, DC-10-30F, and DC-10-40 series airplanes, and Model MD-11 and - 11F series airplanes, that requires a determination be made of whether, and at what locations, metallized polyethyleneteraphthalate (MPET) insulation blankets are installed, and replacement of MPET insulation blankets with new insulation blankets. This amendment is prompted by reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets covered with MPET, which may contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and could lead to a much larger fire.
AD 2000-08-22 · published May 5, 2000, effective May 22, 2000
MD Helicopters Inc. Model 369D, 369E, 500N, and 600N Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to MD Helicopters Inc. (MDHI) Model 369D, 369E, 500N, and 600N helicopters with certain analog/digital turbine outlet temperature (TOT) indicators installed. This action requires repetitive calibration testing of the TOT indicating system and corrective actions if necessary. This amendment is prompted by seven reports of erroneous TOT readings and two reports of incorrect wiring harness terminal lugs on the thermocouple wiring. The actions specified in this AD are intended to prevent an erroneous TOT indication, damage to critical engine components, loss of engine power, and a subsequent forced landing.
AD 2000-10-06 · published May 17, 2000, effective Jun 1, 2000
MD Helicopters Inc. Model MD900 Helicopters
This amendment adopts a new airworthiness directive (AD) for MD Helicopters Inc. (MDHI) Model MD900 helicopters. This action requires visually inspecting the drive shaft to determine the assembly part number (P/N) and marking the drive shaft assembly P/N and serial number (S/N) on any unmarked drive shaft. This AD also requires creating a component history card or equivalent record for certain drive shaft assemblies and replacing any drive shaft assembly that has reached its life limit. This amendment is prompted by the discovery of several drive shafts with no assembly P/N marked on the part, which could result in a drive shaft remaining in service past its life limit. The actions specified in this AD are intended to prevent failure of the drive shaft due to fatigue, which could result in total loss of drive to the main rotor hub and subsequent loss of control of the helicopter.
AD 2000-10-07 · published May 17, 2000
Eurocopter Deutschland GmbH (Eurocopter) Model EC 135 Helicopters
This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter Model EC 135 helicopters. This AD requires replacing a certain oil cooler fan splined drive shaft (shaft) with a different airworthy shaft and re-identifying the part numbers on the oil cooler fans. This amendment is prompted by two incidents in which the shaft broke. The actions specified by this AD are intended to prevent failure of the shaft, loss of oil cooling, and a subsequent engine shutdown during flight.
AD 2000-10-08 · published May 17, 2000
Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and requires conducting inspections of each tail rotor blade for bonding separation, measuring the clearance between the tip of each tail rotor blade and the circumference of the air duct, and replacing the blade if necessary. This amendment is prompted by an inflight incident in which the tail rotor blades were significantly damaged due to bonding separation. The actions specified by this AD are intended to prevent damage to a tail rotor blade, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 2000-10-09 · published May 22, 2000, effective Jun 26, 2000
Eurocopter France Model AS350B, BA, B1, B2, B3, D, and AS355E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model AS350B, BA, B1, B2, B3, D, and AS355E, F, F1, F2, and N helicopters that requires replacing certain circuit breakers. This amendment is prompted by the discovery of the loss of electrical continuity between the terminals of an installed circuit breaker. The actions specified by this AD are intended to prevent loss of electrical power to the emergency flotation gear or other optional installations and subsequent loss of the helicopter emergency flotation capability.
AD 2000-10-10 · published May 22, 2000, effective Jun 26, 2000
Eurocopter France Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N helicopters and requires inspecting the main gearbox suspension bi-directional cross-beam (cross-beam) for cracks, and replacing the cross-beam if a crack is found. This amendment requires the same inspections as the existing AD, but adds the time intervals for performing repetitive dye-penetrant inspections on cross-beams with 5,000 or more hours time-in-service (TIS). This amendment is prompted by the discovery that time intervals for performing the required dye-penetrant inspections are not included in the existing AD. The actions specified by this AD are intended to prevent failure of the cross-beam that could lead to rotation of the main gearbox, resulting in severe vibrations and a subsequent forced landing.
AD 2000-10-13 · published May 22, 2000, effective Jun 6, 2000
Eurocopter France Model SA-365N, SA-365N1, AS-365N2 and AS-365N3 Helicopters
This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA-365N, SA-365N1, AS-365N2 and AS-365N3 helicopters. This action requires inspecting the installation of each window panel on the enlarged sliding door (door). If any window panel is installed on the outside of the door, this AD requires installing and sealing the window panel on the inside. This amendment is prompted by the loss of a window panel in flight that was incorrectly sealed with the window installed on the outside of the door. This condition, if not corrected, could result in loss of a window panel in flight. The actions specified in this AD are intended to prevent loss of a window panel, impact with a main rotor blade, and subsequent loss of control of the helicopter.
AD 2000-10-14 · published May 22, 2000
Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 Helicopters
This amendment adopts a new airworthiness directive (AD) for BHTC Model 222, 222B, 222U, and 230 helicopters that requires inspecting each flapping bearing to yoke attachment bolt (bolt) and replacing each bolt that shows thread damage, shank wear, or corrosion pitting with an airworthy bolt. This amendment is prompted by the discovery of a fractured bolt during a post-flight inspection. The actions specified by this AD are intended to prevent a fracture of a bolt, failure of the bearing and yoke interface, and subsequent loss of control of the helicopter.
AD 2000-10-05 · published May 25, 2000, effective Jun 29, 2000
Eurocopter France Model SE.3160, SA.316B, SA.316C, SA.319B, SA330F, SA330G, SA330J, SA341G, and SA342J Helicopters
This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SE.3160, SA.316B, SA.316C, SA.319B, SA330F, SA330G, SA330J, SA341G, and SA342J helicopters. This AD requires inspecting each inflation head and union nut on certain emergency flotation gear nitrogen cylinders and replacing each cracked inflation head with an airworthy inflation head. This amendment is prompted by the discovery of cracked inflation heads during routine maintenance inspections of emergency flotation systems. The actions specified by this AD are intended to prevent an emergency flotation gear nitrogen cylinder from exploding with resultant high velocity shrapnel, which could cause airframe damage or personal injury and subsequent loss of control of the helicopter.
AD 2000-09-05 · published May 5, 2000, effective Jul 5, 2000
Allison Engine Company AE 3007 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Allison Engine Company AE 3007 series turbofan engines. This AD would require removal of certain cone shafts from service before exceeding new cyclic life limits and replacement with serviceable parts. This amendment is prompted by additional testing and low cycle fatigue (LCF) life analysis that substantiate lower cyclic lives than originally determined. The actions specified by this AD are intended to prevent LCF failure of cone shafts, which could result in an uncontained engine failure and damage to the aircraft.
AD 2000-09-14 · published May 12, 2000, effective Jul 11, 2000
Rolls-Royce plc RB211-535 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211-535 series turbofan engines. This AD will require removal from service of suspect radial drive steady bearings with certain serial number prefixes and replacement with serviceable parts. This amendment was prompted by reports of a number of radial drive steady bearing failures from distinct batches of parts. The actions specified by this AD are intended to prevent radial drive steady bearing failure, which could result in an in-flight engine shutdown and smoke and fumes in the cabin.
