58 Airworthiness Directives: 44 airplane, 8 rotorcraft, 5 engine, 1 glider.
AD 2000-19-05 · published Nov 1, 2000, effective Oct 25, 2000
Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Boeing Model 737- 100, -200, -200C, -300, -400, and -500 series airplanes. That AD supersedes AD 99-05-15, amendment 39-11063, to require a one-time inspection of the attachment nuts at each end attachment of the elevator tab push rods to measure run-on torque values, and corrective actions, if necessary. That AD also requires replacement of all existing bolts and attachment nuts at the forward and aft end attachment of each elevator tab push rod with new bolts and self- locking castellated nuts with cotter pins. This document corrects an inadvertent error regarding the compliance time for certain requirements of that AD. This correction is necessary to provide an adequate compliance time for the replacement of certain parts.
AD 2000-22-04 · published Nov 1, 2000, effective Dec 6, 2000
Learjet Model 45 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 45 series airplanes, that requires repetitive application of grease to the rotating disk assembly of the nose landing gear squat switch mechanism. Application of grease to the squat switch assembly is necessary to prevent moisture contamination and subsequent formation of ice. Such ice formation could result in bending or damaging of the nose landing gear squat switch assembly, which could drive the nose wheel to an uncommanded angle against the force of the steering system. This condition, if not corrected, could result in the airplane departing from the runway at high speeds during landing.
AD 2000-22-08 · published Nov 6, 2000, effective Dec 11, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires inspections of certain components, and corrective action, if necessary. The actions specified by this AD are intended to prevent deterioration and deformation of the mass-balance weights of the aileron, which could affect the surface balance of the aileron and result in loss of aileron control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-22-09 · published Nov 6, 2000, effective Dec 11, 2000
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires inspection of certain components, and corrective action, if necessary. The actions specified by this AD are intended to prevent loosening of the locknut holding the main landing gear (MLG) piston to the ramrod, which could result in detachment of the MLG piston from the ramrod and loss of hydraulic control of the MLG. This action is intended to address the identified unsafe condition.
AD 2000-22-10 · published Nov 7, 2000, effective Nov 22, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires various inspections to detect discrepancies of the elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, and follow-on corrective actions, if necessary. This amendment clarifies certain fiberscopic inspection and replacement procedures, and corrective actions; revises the applicability of the existing AD; and adds an inspection procedure for the servo tab center hinge fittings to detect the presence of washers for both attaching fasteners, and follow-on corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. The actions specified in this AD are intended to prevent the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane.
AD 2000-22-12 · published Nov 7, 2000, effective Dec 12, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires replacement of the existing wire between certain circuit breakers with an improved wire. The actions specified by this AD are intended to prevent overheating of the wire between certain circuit breakers, which could result in smoke emissions in the cockpit. This action is intended to address the identified unsafe condition.
AD 2000-22-15 · published Nov 7, 2000, effective Nov 22, 2000
Boeing Model 747-100, -200B, -200C, -200F, and -300 Series Airplanes Delivered In or Modified Into the Stretched Upper Deck Configuration
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, -200B, -200C, -200F, and -300 series airplanes delivered in or modified into the stretched upper deck configuration. This action requires a one-time inspection to detect chafing between certain engine thrust control cables and certain cable penetration holes, and follow-on actions, if necessary. This action is necessary to prevent chafing and failure of engine thrust control cables, which could result in a severe asymmetric thrust condition during landing, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-22-11 · published Nov 8, 2000, effective Dec 13, 2000
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires modification of the canted pressure deck drain system in the wheel well of the main landing gear (MLG). This amendment is prompted by reports of ice accumulation on the aileron control cables and on the MLG door and door seal during flight, due to fluid entering the canted pressure deck area, leaking into the MLG wheel well, and freezing. The actions specified by this AD are intended to prevent such ice accumulation, which could render one of the aileron control systems and/or the MLG doors inoperative, resulting in reduced controllability of the airplane.
AD 2000-22-14 · published Nov 8, 2000, effective Dec 13, 2000
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes and C-9 (Military) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, that currently requires repetitive radiographic and ultrasonic or eddy current inspections, and modification of the upper cap of the front spar of the left and right engine pylons, if necessary. This amendment requires new, improved x- ray and eddy current inspections to detect cracks of the upper cap of the front spar of the left and right engine pylons, and repetitive inspections or corrective actions, if necessary. This amendment also requires modification of the subject area, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by additional reports of fatigue cracking in the subject area of these airplanes. The actions specified by this AD are intended to prevent failure of the upper cap of the front spar of the engine pylons due to fatigue cracking, and consequent reduced structural integrity of the airplane.
AD 2000-22-16 · published Nov 8, 2000, effective Dec 13, 2000
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires a functional check of the rudder pedals to ensure full and free movement at all rudder pedal positions, and modification of the forward rudder pedal boxes. The actions specified by this AD are intended to prevent restricted movement of the rudder pedals due to structural interference, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-22-17 · published Nov 14, 2000, effective Dec 29, 2000
SOCATA-Groupe AEROSPATIALE Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150T, Rallye 150ST, Rallye 235C, and Rallye 235E Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe AEROSPATIALE (Socata) Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150T, Rallye 150ST, Rallye 235C, and Rallye 235E airplanes. This AD requires you to repetitively inspect, and, if necessary, replace elevator clevis and rudder governor control clevis that are too thin. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to correct rudder and elevator control clevis that are too thin because of abnormal wear, with consequent failure of the rudder and elevator clevis. Such failure could lead to loss of directional or pitch control.
AD 2000-22-20 · published Nov 14, 2000, effective Nov 29, 2000
McDonnell Douglas Model DC-9-10, -9-20, -9-30, -9-40, and -9-50 Series Airplanes and C-9 (Military) Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-10, -9-20, -9-30, -9-40, and -9-50 series airplanes and C-9 (military) airplanes. This action requires, among other actions, measuring the diameter of the hole counterbore of the outboard idler hinge fitting of the left and right wing flap; performing repetitive high frequency eddy current inspections (HFEC) to detect cracks at the flap idler hinge fitting, if necessary; and replacing the flap idler hinge fitting with a new like part, if any crack is detected. This action is necessary to prevent failure of the outboard flap idler hinge fitting due to fatigue cracking, which could result in a deflected flap that may cause an asymmetric lift and consequent reduced controllability and structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-22-22 · published Nov 14, 2000, effective Dec 19, 2000
Raytheon Model Hawker 800XP and Hawker 800 (U-125A) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP and Hawker 800 (U- 125A) series airplanes, that requires inspection of the wire bundle to relay "KT" on panel "JA" for correct routing, adequate clearance from the fuel cross-feed valve operating lever, and the presence of chafing; this amendment also requires corrective action, if necessary. The actions specified by this AD are intended to detect and correct chafing of the wire bundle exiting panel "JA" due to insufficient clearance from the fuel cross-feed valve operating lever. Such chafing of the wire bundle could result in a fire in the area of the fuel system in a confined space. This action is intended to address the identified unsafe condition.
AD 2000-23-02 · published Nov 14, 2000, effective Nov 29, 2000
Bombardier Model CL-600-2B16 (CL-604) Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B16 (CL-604) series airplanes. This action requires, among other actions, a general visual inspection to detect gaps between the vane bracket(s) and the adjacent skin; corrective actions, if necessary; and replacement of the six flap vane actuator beams with new beams. This action is necessary to detect and correct corrosion of the inboard flap actuator beam assembly and gaps between the vane brackets and adjacent skin, which could compromise the structural integrity of the flap systems and reduce the controllability of the airplane in the event that a flap vane actuator or a flap vane bracket fails during flight. This action is intended to address the identified unsafe condition.
AD 2000-23-04 · published Nov 14, 2000, effective Dec 19, 2000
Aerospatiale Model ATR42-500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-500 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a new revision of the "Time Limits" section of the ATR42-400/500 Maintenance Planning Document, which specifies new inspections and compliance times for inspection and replacement actions. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-23-05 · published Nov 14, 2000, effective Dec 19, 2000
British Aerospace Model BAC 1-11 401/AK and 410/AQ Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11 401/AK and 410/AQ airplanes, that requires replacement of certain landing gear brake accumulators with improved accumulators. The actions specified by this AD are intended to prevent loss of hydraulic pressure and possible structural damage to the airplane due to failure of the accumulator. This action is intended to address the identified unsafe condition.
AD 2000-23-03 · published Nov 15, 2000, effective Dec 20, 2000
Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time general visual inspection for proper rigging of the liftdumper micro switches installed in the left- and right-hand sides of the pedestal; a functional check of the micro switches; and re-rigging the cam, if necessary. The actions specified by this AD are intended to detect and correct improper rigging of the liftdumper micro switches, which could result in inadvertent extension of the liftdumpers during takeoff roll. This action is intended to address the identified unsafe condition.
AD 2000-23-06 · published Nov 15, 2000, effective Dec 20, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires replacement of defective hydraulic tubing in the left and right wings with new hydraulic tubing. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the loss of hydraulic pressure which could result in reduced controllability of the airplane.
AD 2000-23-07 · published Nov 15, 2000, effective Dec 20, 2000
Airbus Model A300, A300-600, and A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and all Model A300-600 and A310 series airplanes, that currently requires performing a pitch trim system test to detect any continuity defect in the autotrim function, and follow-on corrective actions, if necessary. This amendment requires repetitive inspections of the autotrim function to detect such defects, and corrective actions, if necessary. This amendment also expands the applicability to include additional 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 a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane.
AD 2000-23-08 · published Nov 15, 2000, effective Dec 20, 2000
Airbus Model A310 and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the flight control computers (FCC) with new, improved FCC's having updated software installed. This amendment also requires, for some airplanes, modification of the wiring of the FCC's. The actions specified by this AD are intended to prevent autopilot reversions in certain flight conditions, which could result in misunderstanding by the flight crew and consequent reduced ability to take appropriate action. This action is intended to address the identified unsafe condition.
AD 2000-23-09 · published Nov 15, 2000, effective Dec 20, 2000
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection to detect wear of the hydraulic pump hoses, and corrective action, if necessary. This AD also requires relocation of the clip that secures the left forward hold-open rod of both nacelles. The actions specified by this AD are intended to prevent chafing and consequent rupture of the hydraulic line and loss of hydraulic pressure, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-22-02 R1 · published Nov 16, 2000, effective Nov 13, 2000
Boeing Model 737 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to all Boeing Model 737 series airplanes. That AD supersedes AD 99-05-15, amendment 39-11063, to require revising the FAA-approved Airplane Flight Manual (AFM) procedure in the existing AD to simplify the instructions for correcting a jammed or restricted flight control condition. This document corrects the format for certain AFM material described in that AD. This correction is necessary to ensure that the flightcrew is aware of certain critical recall items in the AFM procedure that are necessary to address a condition involving a jammed or restricted rudder.
AD 2000-23-13 · published Nov 17, 2000, effective Dec 4, 2000
Israel Aircraft Industries, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Israel Aircraft Industries, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes. This action requires a one-time inspection, and corrective action if necessary, to ensure the proper installation of the tie rod through the dust shield and both jackscrew assemblies on the horizontal stabilizer trim actuator. This action is necessary to prevent jamming or disconnection of the horizontal stabilizer trim actuator, which could result in reduced pitch control of the airplane. This action is intended to address the identified unsafe condition.
AD 98-09-16 R1 · published Nov 17, 2000, effective Nov 17, 2000
Aerospatiale Model ATR-42 and ATR-72 Series Airplanes
This amendment rescinds an existing Airworthiness Directive (AD), applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes. That AD currently requires revising the Airplane Flight Manual to add specific flightcrew instructions to be followed in the event of failure of the first generator, which could lead to the loss of main battery power and result in the loss of all electrical power, except the emergency battery supply, during flight. The requirements of that AD were intended to prevent failure of the second of two direct current generators after the failure of the first generator. Since the issuance of that AD, the FAA has received further information indicating that the incident that prompted that AD was an isolated case.
AD 2000-22-21 · published Nov 20, 2000, effective Dec 5, 2000
McDonnell Douglas Model DC-10, Model MD-10, and Model MD-11 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model DC-10, Model MD-10, and Model MD-11 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to ensure that the flight crew is advised of appropriate procedures for disabling certain fuel pump electrical circuits following failure of a fuel pump electrical connector. For certain airplanes, this action also requires revising the AFM to prohibit resetting of tripped fuel pump circuit breakers. This action is necessary to prevent continued arcing following a short circuit of the fuel pump electrical connector, which could damage the conduit that protects the power lead inside the fuel tank, and result in the creation of a potential ignition source in the fuel tank. This action is intended to address the identified unsafe condition.
AD 2000-23-18 · published Nov 21, 2000, effective Dec 26, 2000
Learjet Model 60 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 60 airplanes, that requires inspecting the routing of oxygen tubing to ensure that there is adequate clamping of the tubing and adequate clearance between the tubing and electrical wiring or electrical contacts, and taking corrective action, if necessary. The actions specified by this AD are intended to prevent electrical arcing between the oxygen tubing and an electrical source, which could result in an oxygen fire.
AD 2000-23-20 · published Nov 21, 2000, effective Dec 26, 2000
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires replacement of certain components. The actions specified by this AD are intended to prevent corrosion of the axle of the main landing gear, which could result in cracking and failure of one or more axles, loss of the wheels on the axle, and loss of controllability of the airplane on the ground. This action is intended to address the identified unsafe condition.
AD 2000-23-10 · published Nov 22, 2000, effective Dec 27, 2000
Lockheed Model 188A and 188C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model 188A and 188C series airplanes, that requires a revision of the Airplane Flight Manual (AFM) to add procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated. The actions specified by this AD are intended to prevent incapacitation of the flightcrew as a result of lack of oxygen and consequent loss of control of the airplane due to absence of AFM procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated.
AD 2000-23-15 · published Nov 22, 2000, effective Dec 27, 2000
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires inspecting the connector on the refuel/defuel panel and the electrical connector on the illuminated placard to detect signs of fluid ingression or corrosion, and corrective actions. The actions specified by this AD are intended to prevent electrical shorts or arcing at the illuminated placard connector at the refuel/defuel panel, which could result in a potential ignition source for fuel vapors during fueling procedures. This action is intended to address the identified unsafe condition.
AD 2000-23-17 · published Nov 22, 2000, effective Dec 27, 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 opening the circuit breaker of the pneumatic sense line heater tape, installing an inoperative ring, and coiling and stowing the electrical wire to the circuit breaker of the pneumatic sense line heater tape. That AD also provides for an optional inspection, which, if accomplished, constitutes terminating action for deactivation of the pneumatic sense line heater tape. This amendment requires repetitive inspections of the subject area and corrective actions, if necessary, and provides for an optional terminating modification(s) for the repetitive inspection requirements. This amendment is prompted by the FAA's determination that the one-time optional terminating inspection in the existing AD does not adequately detect chafing, electrical arcing, or inadequate clearance of the subject area. The actions specified by this AD are intended to detect and correct such inadequate clearance, which could result in a hole in the fuel feed pipe caused by electrical arcing, and consequent fuel leakage and possible ignition of the fuel vapors.
AD 2000-23-29 · published Nov 22, 2000, effective Dec 27, 2000
Saab Model SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes, that requires a one-time inspection to detect discrepancies of the flight idle stop override mechanism, 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 prevent increased braking distance for landings that require the flight idle stop override, resulting from the combination of failure of the override mechanism and inability of the power levers to be moved below the flight idle position after touchdown.
AD 2000-23-01 · published Nov 27, 2000, effective Dec 21, 2000
Cessna Aircraft Company Model 402C Airplanes
This amendment supersedes Airworthiness Directive (AD) 99-11- 13, which currently requires inspecting (one-time) the forward, aft, and auxiliary wing spars for cracks on certain Cessna Aircraft Company (Cessna) Model 402C airplanes, and repairing any cracks found. AD 99- 11-13 also requires reporting the results of the inspection to the Federal Aviation Administration (FAA) to provide data to help us determine whether the inspection should be repetitive. After re- evaluating the fatigue analysis for the wing spars on the affected airplanes, we have determined that spar cap cracking is not an isolated condition and could continue to develop over the life of the affected airplanes. This AD retains the inspection required in AD 99-11-13, and will make the inspection repetitive. The actions specified by this AD are intended to detect and correct any cracks in the forward, aft, and auxiliary wing spars, which could result in reduced or loss of control of the airplane.
AD 2000-23-19 · published Nov 27, 2000, effective Jan 2, 2001
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires inspections to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38; an inspection to verify that the sizes of the holes of the flap fittings are within specified limits and to ensure that the swaged bushings are not loose; and modification of the flap fittings. This amendment requires repetitive accomplishment of the inspections using improved inspection methods; a one-time visual and repetitive general visual and detailed visual inspections; new repetitive non-destructive test (NDT) inspections; and corrective and follow-on actions, as necessary. This amendment also provides for terminating action for all repetitive inspections and revises the applicability of the existing AD. The actions specified by this AD are intended to prevent high bearing stress on the bushings of the flap fittings, which could result in wear on the bushings, cracking of the flap fittings, and breakage of the lugs; these conditions could result in jamming of the flaps and consequent reduced controllability of the airplane.
AD 2000-23-22 · published Nov 27, 2000, effective Jan 2, 2001
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes, and C-9 (Military) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes and C-9 (military) airplanes, that currently requires a one-time visual inspection to determine if the doorstops and corners of the doorjamb of the forward passenger door have been modified, various follow-on repetitive inspections, and modification, if necessary. This amendment requires a reduction in the inspection threshold and repetitive intervals for a certain doubler configuration and an increase in the grace period for a certain other doubler configuration. This amendment is prompted by a determination that certain inspection compliance times were incorrect. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
AD 2000-23-23 · published Nov 28, 2000, effective Jan 2, 2001
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires modification of the rib 1/wing center spar attachment. This amendment is necessary to prevent fatigue cracking at the rib 1/center spar angle and bottom corner fitting, which could result in reduced structural capability of the wing. This action is intended to address the identified unsafe condition.
AD 2000-23-24 · published Nov 28, 2000, effective Jan 2, 2001
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires an inspection to ensure correct installation of certain self-seal couplings in each nacelle, and corrective action, if necessary. This amendment also requires installation of a new clamp to the self-seal couplings. This action is necessary to prevent separation of the self-seal couplings, which could result in loss of engine oil pressure and a flight- crew-commanded engine shutdown. This action is intended to address the identified unsafe condition.
AD 2000-23-25 · published Nov 28, 2000, effective Dec 13, 2000
Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR Series Airplanes Powered by Pratt & Whitney JT9D-3 and JT9D-7 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR series airplanes powered by Pratt & Whitney JT9D-3 or JT9D-7 series engines. This action requires inspections of the vertical chords of the aft torque bulkhead of the outboard nacelle struts, and corrective action, if necessary. This action also provides optional terminating action for the inspections. This action is necessary to detect and correct cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path. Continued operation with a separated diagonal brace load path increases loads on the upper link, midspar fitting, and dual side links, which could result in separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2000-23-26 · published Nov 28, 2000, effective Jan 2, 2001
Aerospatiale Model ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR72 series airplanes, that requires a revision to the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate inspections to detect fatigue cracking in certain structure, inspection intervals, and life limits for certain components. 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 fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-23-27 · published Nov 28, 2000, effective Jan 2, 2001
Bombardier Model DHC-8-102, -103, and -301 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, and -301 series airplanes, that currently requires a one-time inspection for wear and breakage of wire segments of the individual lighting units of the ceiling and sidewall lights, and replacement of any damaged wiring. The existing AD also requires installation of teflon spiral wrap on the wiring of the ceiling and sidewall lights. This amendment adds a requirement for a one-time inspection to determine if teflon spiral wrap is installed on the wiring of the lavatory lighting system, and installation, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the possibility of a fire on an airplane due to such chafing and consequent short circuiting, overheating, and smoking of the wires on the aircraft structure.
AD 2000-23-28 · published Nov 28, 2000, effective Jan 2, 2001
Boeing Model 777 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 777 series airplanes, that currently requires repetitive testing of the engine fire shutoff switch (EFSS) to determine if the override mechanism and the switch handle are operational, and replacement of the EFSS, if necessary. That AD also requires, for certain airplanes, installation of a collar on a specific circuit breaker of the standby power management panel, and installation of placards to advise the flightcrew that the override mechanism must be pushed in order to pull the fire switch. This amendment adds various actions that would terminate the repetitive testing requirements. This amendment is prompted by a report indicating that a solenoid and an override mechanism of the EFSS were not operational due to overheating of the solenoid. The actions specified by this AD are intended to prevent damage to the EFSS solenoid and to the override mechanism, and consequent failure of the EFSS due to overheating of the solenoid; such failure could result in the inability of the flightcrew to discharge the fire extinguishing agent in the event of an engine fire.
AD 2000-23-30 · published Nov 28, 2000, effective Jan 2, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires installation of an additional drain at the fuselage aft section. This action is necessary to prevent mechanical blockage of the elevator control cables due to the freezing of water collected inside the fuselage between the rear pressure bulkhead and the fire wall of the auxiliary power unit. Such cable blockage could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-23-31 · published Nov 28, 2000, effective Dec 13, 2000
McDonnell Douglas Model DC-9-82 (MD-82) and DC-9-83 (MD-83) Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-82 (MD-82) and DC-9-83 (MD-83) series airplanes, and Model MD-88 airplanes. This action requires deactivating the left and right lower sidewall lights located in the passenger compartment. This action is necessary to prevent arcing and heat damage of the Luminator fluorescent lamp holders located outboard of the Passenger Service Unit panel, which could result in smoke and fire in the passenger compartment. This action is intended to address the identified unsafe condition.
AD 2000-23-33 · published Nov 30, 2000, effective Jan 12, 2001
British Aerospace HP137 Mk1 and Jetstream Series 200 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1 and Jetstream series 200 airplanes. This AD requires you to inspect the vertical stabilizer skin for disbonding, corrosion, cracks, and loose rivets, and repair any vertical stabilizer skin where discrepancies are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the vertical stabilizer caused by disbonding, corrosion, cracks, or loose rivets in the stabilizer skin. Such failure could lead to aircraft controllability problems.
AD 2000-24-19 · published Nov 30, 2000, effective Jan 4, 2001
Learjet Model 35, 35A, 36, and 36A Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Learjet Model 35, 35A, 36, and 36A series airplanes, that requires revision of the Airplane Flight Manual (AFM) to add procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated. This amendment is intended to prevent incapacitation of the flightcrew due to lack of oxygen and consequent loss of control of the airplane due to absence of AFM procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated.
AD 2000-23-51 · published Nov 3, 2000
Sikorsky Aircraft Corporation Helicopters
AD 2000-20-51 · published Nov 7, 2000, effective Nov 22, 2000
Robinson Helicopter Company Model R22 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-20-51, which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires checking the yoke half assembly (yoke) for any crack and replacing a cracked yoke assembly before further flight. This AD also requires replacing certain yokes with airworthy yokes before further flight after January 1, 2001. This AD is prompted by the discovery of cracks in the yoke. The actions specified by this AD are intended to detect crack formation and growth, which could result in separation of the yokes from the main rotor drive shaft and subsequent loss of control of the helicopter.
AD 2000-22-13 · published Nov 7, 2000, effective Dec 12, 2000
Bell Helicopter Textron Canada Model 430 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires calibration of the fuel quantity indicating system. This amendment is prompted by an operator report of an inaccurate fuel quantity indicating system. The actions specified by this AD are intended to prevent an inaccurate fuel quantity indicating system reading, engine flameout due to fuel starvation, and a subsequent forced landing.
AD 2000-22-19 · published Nov 14, 2000, effective Dec 19, 2000
Eurocopter France Model SA330F, G, and J Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA330F, G, and J helicopters and requires inspecting the tail rotor blade (blade) skin for cracks and replacing, as necessary, the blade. This amendment requires skin bonding and eddy current inspections of the blade skin for cracks and would reference a more recent service bulletin (SB). This amendment is prompted by improved inspection methods and by the manufacturer revising the SB referenced in the current AD. The actions specified by this AD are intended to prevent fatigue cracking of a blade, failure of a blade, and subsequent loss of control of the helicopter.
AD 2000-18-51 · published Nov 15, 2000, effective Nov 30, 2000
Bell Helicopter Textron, Inc. Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K Helicopters
This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-18-51 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G- 2, 47G2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G- 4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters by individual letters. This AD requires recurring liquid penetrant or eddy current inspections of the main rotor blade grip (grip) threads for a crack. If a crack is detected, this AD requires, before further flight, replacing the cracked grip with an airworthy grip. This AD also establishes a retirement life of 1,200 hours time- in-service (TIS) for each grip. This amendment is prompted by the results of an investigation of an August 1998 accident in which a grip failed on a BHTI Model 47G-2 helicopter due to a fatigue crack. An analysis of the field service data revealed fatigue cracks in 70 percent of the grips inspected. The actions specified by this AD are intended to prevent failure of a grip, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2000-18-52 · published Nov 15, 2000, effective Nov 30, 2000
Bell Helicopter Textron, Inc.-Manufactured Model OH-13E, OH-13H, and OH-13S Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-18-52 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (BHTI)-manufactured Model OH-13E, OH-13H, and OH-13S helicopters by individual letters. This AD requires a liquid penetrant or eddy current inspection of the threads on each main rotor blade grip (grip) for a crack. The inspections must be accomplished within 100 hours time-in-service (TIS) since initial installation on any helicopter or within 10 hours TIS for grips with 100 or more hours TIS and thereafter at intervals not to exceed 200 hours TIS. This AD also establishes a retirement life of 1200 hours TIS for affected grips. This amendment is prompted by the results of an investigation of an August 1998 accident in which a grip failed on a BHTI Model 47G-2 helicopter due to a fatigue crack. The OH-13E, OH-13H, and OH-13S helicopters use the same grips as the Model 47G-2 helicopters. The actions specified by this AD are intended to prevent failure of a grip, loss of a main rotor blade, and subsequent loss of control of the helicopter.
AD 2000-15-21 R1 · published Nov 22, 2000, effective Nov 22, 2000
Overseas Aircraft Support Inc, Rotorcraft Development Corporation, San Joaquin Helicopters, Smith Helicopters, Southwest Florida Aviation International, Arrow Falcon Exporters Inc., AST Inc., Bell Helicopter Textron Inc., Hagglund Helicopters LLC, International Helicopters Inc., Richards Heavylift Helo Inc., Robinson Air Crane Inc., Southern Helicopter Inc., Tamarack Heli
This amendment revises an existing airworthiness directive (AD) that applies to Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P; and Southwest Florida Aviation SW204, SW204HP, SW205, and SW205A-1 helicopters, manufactured by Bell Helicopter Textron Inc. (BHTI) for the Armed Forces of the United States, and requires removing and replacing certain main rotor mast (mast) assemblies. This amendment corrects a part number that was published incorrectly in the existing AD. This amendment is prompted by the discovery of that error. The actions specified by this AD are intended to prevent fatigue failure of the mast and subsequent loss of control of the helicopter
AD 2000-22-07 · published Nov 1, 2000, effective Dec 6, 2000
International Aero Engines AG (IAE) Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain International Aero Engines AG (IAE) V2500-A5 and -D5 series turbofan engines, identified by serial number. This amendment requires the removal of engines assembled with an improper High Pressure Turbine (HPT) module configuration from service prior to accumulating 5,100 or 7,600 cycles in the improper configuration, or at the next shop visit, depending on the type of improper HPT configuration, and restoration to type design. This amendment is prompted by reports of engines that do not conform to the engine type design, which could cause a Low Cycle Fatigue (LCF) life reduction of the HPT stage 1 disk. The actions specified by this AD are intended to restore engines to type design configuration and to prevent possible LCF failure of the HPT stage 1 disk, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-23-12 · published Nov 14, 2000, effective Jan 16, 2001
CFE Company Model CFE738-1-1B Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to CFE Company model CFE738-1-1B turbofan engines, that requires new life limits for certain HPC rotor components in all engines. This amendment is prompted by a reduction in the calculated service life of certain compressor rotor rotating parts to values below currently approved service lives. The actions specified by this AD are intended to prevent failure of certain HPC rotor components, which could result in an uncontained engine failure and damage to the airplane.
AD 2000-23-11 · published Nov 15, 2000, effective Dec 20, 2000
Rolls-Royce Spey 555-15, -15H, -15N, and -15P Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce (RR) plc. Spey 555-15, -15H, -15N, and -15P turbofan engines, that requires modification of the low pressure (LP) turbine stage 2 nozzle guide vane (NGV) support ring seal assembly. This amendment is prompted by two instances of disk drive arm damage. In both cases, heavy damage to the stage 1 LP turbine-to-stage 2 LP turbine disk drive arm occurred as a result of an out-of-balance condition following the failure of a stage 2 LP turbine blade. The actions specified by this AD are intended to prevent damage to the disk drive arm which could result in loss of stage 1 LP turbine-to-stage 2 LP turbine disk drive, a turbine overspeed condition, and possible uncontained disk failure and damage to the airplane.
AD 2000-23-14 · published Nov 20, 2000, effective Jan 19, 2001
Pratt & Whitney JT9D Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney JT9D series turbofan engines. This AD will require installation of an improved No. 4 bearing internal oil pressure tube, initial and repetitive inspections of the No. 4 bearing oil pressure tube for turbine exhaust case (TEC) strut clearance and alignment, and, if necessary, replacement with serviceable parts. This amendment is prompted by loss of integrity in the oil system that allows oil to migrate into high temperature metal cavities in the turbine exhaust case and cause oil fires. The actions specified by this AD are intended to prevent oil fires in and around the No. 4 bearing area that could cause excessive thermal growth of the sixth stage low pressure turbine (LPT) disk, liberation of the sixth stage LPT disk, uncontained engine failure, and damage to the airplane.
AD 2000-23-21 · published Nov 27, 2000, effective Dec 12, 2000
Teledyne Continental Motors IO-360, TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550, and TSIOL-550 Series Reciprocating Engines
This amendment supersedes emergency airworthiness directive (AD) 2000-08-51. Emergency AD 2000-08-51 was sent to all known U.S. owners and operators of Teledyne Continental Motors (TCM) IO-360, TSIO- 360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550, and TSIOL-550 series reciprocating engines by individual letters. This amendment requires removing a core sample of material from the propeller mounting flange of certain crankshafts, and sending the core sample to TCM for evaluation. This amendment is prompted by reports of crankshaft failures, and by the addition of additional crankshaft serial numbers (SN) that have been added to the suspect population. The actions specified by this AD are intended to prevent fracture of the crankshaft connecting rod journal, which could result in total engine power loss, in-flight engine failure and possible forced landing.
AD 2000-23-32 · published Nov 30, 2000, effective Jan 13, 2001
DG Flugzeugbau GmbH Models DG-500 Elan Series, DG-500M, and DG-500MB Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain DG Flugzeugbau GmbH (DG Flugzeugbau) Models DG-500 Elan Series, DG-500M, and DG-500MB sailplanes. This AD requires you to visually inspect the elevator control system for proper movement, obtain and incorporate a repair scheme if improper movement is found, and modify and install resin thickened cottonflock reinforcements to the elevator control system as a way to increase the stiffness of the elevator control support stand. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Federal Republic of Germany. The actions specified by this AD are intended to detect and correct improper movement in the elevator control system and to increase the stiffness of the elevator control support stand. Without accomplishing these actions, the pilot's capability to use full elevator control deflection could be limited, which could require increased force in moving the elevator control with a consequent potentially uncontrolled flight condition.
