Popular Standards |
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AD 00-15-18 | PREVENT POSSIBLE FAILURE OF ONE OR MORE HYDRAULIC SYSTEMS AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE\BOEIN |
AD 00-15-19 | PREVENT LOSS OF A SAND FILTER EJECTION NOZZLE (NOZZLE) IN FLIGHT\EUROCOPTER FRANCE\AS-365N2\AS-365N3\SA-365N\SA-365N1 |
AD 00-15-20 | PREVENT FAILURE OF A MAIN ROTOR BLADE DUE TO CORROSION ON THE INTERNAL SURFACE OF THE SPAR AND SUBSEQUENT LOSS OF CONT |
AD 00-15-51 | PREVENT INTERFERENCE BETWEEN THE AILERON CABLE FAIRLEAD TUBE AND THE AILERON CABLE SECTOR\CESSNA AIRCRFT CO\560XL |
AD 00-15-52 | PREVENT FAILURE OF A MAST OR TRUNNION, SEPARATION OF THE MAIN ROTOR SYSTEM, AND SUBSEQUENT LOSS OF CONTROL OF THE HELI |
AD 00-16-02 | PREVENT FRONT PYLON MOUNT BOLT AND PRIMARY MOUNT THRUST LOAD PATH FAILURE\PRATT & WHITNEY DIV\PW4164\PW4168\PW4168A |
AD 00-16-03 | PREVENT UNUSUAL HANDLING CHARACTERISTICS AND CONSEQUENT REDUCED CONTROLLABILITY DURING GROUND OPERATIONS DUE TO INCORR |
AD 00-16-04 | PREVENT TIP PATH PLANE SEPARATION, INCREASED VIBRATIONS, DAMAGE TO THE MAIN ROTOR SYSTEM, AND SUBSEQUENT LOSS OF CONTR |
AD 00-16-05 | PREVENT FAILURE OF THE SHAFT, LOSS OF THE TAIL ROTOR\SCHWEIZER AIRCRFT CORP\269A\269A-1\269B\269C\269C-1\269D |
AD 00-16-06 | PREVENT A JAMMED FLIGHT CONTROL AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\BELL HELICPTR TEXTRON\430 |
AD 00-16-08 | DETECT AND CORRECT FATIGUE CRACKING OF THE CANTED PRESSURE BULKHEAD AT FUSELAGE STATION (FS) 1212\LOCKHEED AIRCRFT COR |
AD 00-16-09 | PREVENT ELECTRICAL ARCING BETWEEN THE FLUORESCENT TUBE PINS AND THE LAMPHOLDERS\SAAB AIRCRFT AB\SAAB 340B |
AD 00-16-10 | PREVENT IN-FLIGHT LOSS OF INBOARD AND OUTBOARD FLAP ASSEMBLIES DUE TO FAILURE OF H-11 ATTACHING BOLTS\MCDONNELL DOUGLA |
AD 00-16-11 | DETECT AND CORRECT EXCESS BACKLASH OF THE SPHERICAL BEARING OF THE ACTIVE AILERON SERVO-CONTROLS\AIRBUS INDUSTRIE\A330 |
AD 00-16-13 | PREVENT THE INABILITY TO STEER THE AIRPLANE BECAUSE OF EXCESSIVE FREE PLAY IN THE STEERING LINKAGE\BRITISH AEROSPC (SC |
AD 00-16-14 | PREVENT CHAFING AS A RESULT OF IMPROPER INSTALLATION OF THE CABLE ASSEMBLY OF THE LOWER BODY ANTI-COLLISION LIGHT\BOEI |
AD 00-16-15 | PREVENT FAILURE OF THE CARGO BULKHEAD FLOOR ATTACHMENTS\SAAB AIRCRFT AB\SAAB 340B |
AD 00-16-16 | MINIMIZE CONTAMINATION OF THE SWITCH CONTACTS AND CONSEQUENT FAILURE OF THE SWITCHES\BOEING CO\777-200 SERIES |
AD 00-16-51 | PREVENT FAILURE OF THE FRONT TAILPLANE TO FUSELAGE JOINT CONNECTOR\WYTWORNIA SPRZETU KOMUNIKACYJNEGO\PZL-104 WILGA 80 |
AD 00-16-52 | PREVENT IN-FLIGHT LOSS OF A FAIRING HEAT SHIELD, IMPACT WITH TAIL OR MAIN ROTOR BLADES, AND SUBSEQUENT LOSS OF CONTROL |
AD 00-17-01 | PREVENT WHEEL BRAKE SYSTEM MALFUNCTIONS THAT COULD RESULT IN A FIRE IN THE BRAKE AREA\FAIRCHILD AIRCRFT CORP\SA226-AT\ |
AD 00-17-02 | PREVENT INCREASED LOADS ON THE UPPER WING SKIN DUE TO LOOSENESS OF THE STRINGER FITTINGS AND BOLTS AT RIBS 0 AND 2 OF |
AD 00-17-03 | PREVENT CRACKING OF THE NLG MAIN FITTING\FOKKER SVCS\F.28 MARK 0100 |
AD 00-17-04 | DETECT AND CORRECT DISCREPANCIES IN THE UPPER AND LOWER SKINS OF THE FUSELAGE LAP JOINT\BOEING CO\737-100 SERIES\737-2 |
AD 00-17-05 | DETECT AND CORRECT ANY FAILED OR PARTIALLY YIELDED SHEAR RIVETS OF THE ELEVATOR POWER CONTROL ACTUATOR (PCA) BELLCRANK |
AD 00-17-07 | PREVENT IN-FLIGHT LOSS OF A CABIN SLIDING DOOR, IMPACT WITH THE HORIZONTAL STABILIZER, MAIN ROTOR, OR FENESTRON TAIL R |
AD 00-17-08 | PREVENT FATIGUE FAILURE OF A TT STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE), AND SUBSEQUENT LOSS OF CONTROL OF THE HELIC |
AD 00-17-09 | ENSURE CONTINUED STRUCTURAL INTEGRITY OF THESE AIRPLANES (MODEL ATR42-200, ATR42-300, AND ATR42-320 SERIES)\AEROSPATIA |
AD 00-17-10 | PREVENT UNDETECTED FIRES ORIGINATING WITHIN THE HIGH SPEED GEARBOX (HSGB) FROM BREACHING THE HSGB CASE\LOCKHEED AIRCRF |
AD 00-17-11 | DETECT AND CORRECT CRACKS IN MLG DRAG BRACE ASSEMBLIES (CONSISTS OF BOTH BRACE AND LINKS)\FAIRCHILD AIRCRFT CORP\SA226 |
AD 00-17-51 | DETECT AND CORRECT CRACKING OF THE LOWER PORTION OF THE MAIN DECK CARGO DOOR FRAMES\BOEING CO\737-200 SERIES\737-200C |
AD 00-17-52 | PREVENT FAILURE OF THE ROTATING SCISSORS ASSEMBLY AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\AGUSTA S P A\A109E |
AD 00-18-03 | DETECT CRACKS THAT COULD RESULT IN THE FAILURE OF THE COLD STREAM NOZZLE ASSEMBLY\ROLLS-ROYCE PLC\RB211-524D4-19\RB211 |
AD 00-18-04 | PREVENT THE LOSS OF THE STRUCTURAL INTEGRITY OF THE SEAT DUE TO CRACKS IN THE SEAT CENTER CROSSMEMBER\AVIOINTERIORS S |
AD 00-18-06 | PREVENT AN UNCOMMANDED IN-FLIGHT ENGINE SHUTDOWN AND THE POTENTIAL FOR AN IN-FLIGHT DUAL-ENGINE SHUTDOWN\ALLISON ENGIN |
AD 00-18-08 | PREVENT DAMAGE TO THE LONGITUDINAL DRIVE LINK\MD HELICPTR INC\MD-900 |
AD 00-18-09 | PREVENT FAILURE OF A CAP ANGLE, LOSS OF THE TAILBOOM, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\BELL HELICPTR T |
AD 00-18-10 | PREVENT A MALFUNCTIONING TRANSMISSION CLUTCH, LOSS OF DRIVE TO THE MAIN ROTOR SYSTEM, AND SUBSEQUENT LOSS OF CONTROL O |
AD 00-18-11 | PREVENT THE LOSS OF PRIMARY ATTITUDE AND DIRECTIONAL GYROS\ISRAEL AIRCRFT IND LTD\1125 WESTWIND ASTRA |
AD 00-18-12 | DETECT AND CORRECT CRACKS IN THE LUGS, CORROSION IN THE MAIN HOLES, AND OVALIZATION OF THE MAIN HOLES, IN THE CENTERWI |
AD 00-18-13 | PREVENT FATIGUE FAILURE OF A TT STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE), AND SUBSEQUENT LOSS OF CONTROL OF THE HELIC |
AD 00-18-14 | PREVENT FAILURE OF THE SECOND STAGE LOWER PLANETARY PLATE (PLATE), P/N 6435-20229-102\CHET RASPBERRY INC (CRI)\CH-54A\ |
AD 00-18-52 | PREVENT FAILURE OF A MAIN ROTOR BLADE GRIP (GRIP), SEPARATION OF A MAIN ROTOR BLADE, AND SUBSEQUENT LOSS OF CONTROL OF |
AD 00-19-01 | PREVENT WATER FREEZING ON THE BRAKE WHILE THE AIRPLANE IS IN FLIGHT DUE TO WATER, SLUSH, OR SNOW FROM THE RUNWAY ENTER |
AD 00-19-02 | PREVENT FAILURE OF THE ELECTRICAL CONNECTORS OF THE FUEL PUMPS\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-135 |
AD 00-19-04 | PREVENT CHAFING BETWEEN THE WING FUEL QUANTITY WIRING HARNESS AND THE INTERNAL WING HARNESS SUPPORTS AT EACH WING RIB |
AD 00-19-05 | PREVENT DETACHMENT OF AN ELEVATOR TAB PUSH ROD DUE TO A DETACHED NUT AT EITHER END ATTACHMENT OF A PUSH ROD\BOEING CO\ |
AD 00-19-06 | PREVENT CORROSION AND CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE WINGS DUE TO LACK OF COLD EXPANSION OF AN EXISTIN |
AD 00-19-08 | DETECT AND CORRECT CRACKING AND/OR MISSING PIECES OF THE COVESKIN ON THE OUTBOARD LEADING EDGE SLATS ON THE WINGS\BOEI |
AD 00-19-09 | PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE AND CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE STRUT\BOEING CO |
AD 00-19-10 | PREVENT A SUDDEN CHANGE IN PITCH ATTITUDE CAUSED BY AUTOPILOT DISCONNECT\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAE |
AD 00-20-01 | PREVENT GAS GENERATOR REAR BEARING FAILURE\TURBOMECA S A\ARRIEL 1A\ARRIEL 1A1\ARRIEL 1A2\ARRIEL 1B\ARRIEL 1C\ARRIEL 1C |
AD 00-20-03-R1 | R1 PREVENT REDUCED CONTROLLABILITY OF THE AIRPLANE DUE TO AN ACCUMULATION OF WATER, ICE, AND SLUSH ON THE AILERO |
AD 00-20-04 | PREVENT A LOOSE ELECTRICAL GROUND BLOCK OF THE CIRCUIT GROUND WIRES OF THE ELECTRICAL POWER CONTROL UNIT (EPCU)\MCDONN |
AD 00-20-05 | PREVENT THE LANDING GEAR DOORS FROM BECOMING BLOCKED FROM OPENING DURING APPLICATION OF EMERGENCY PROCEDURES IN THE EV |
AD 00-20-07 | CORRECT SUBSTANDARD QUALITY COCKPIT VOICE RECORDINGS CAUSED BY THE CONFIGURATION OF THE PRESENT CVR SYSTEM\RAYTHEON AI |
AD 00-20-09 | PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE AND CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE STRUT\BOEING CO |
AD 00-20-10 | CORRECT IMPROPER DRIVE BELT TENSION AND CONSEQUENT ENGINE CRANKSHAFT OR CONNECTING ROD BEARING DAMAGE\GLASER-DIRKS FLU |
AD 00-20-11 | PREVENT THE TAIL-FUSELAGE HINGE FAILING AND CONSEQUENT LOSS OF CONTROLLED FLIGHT\LET AERONTCL WORKS\BLANIK L-13 |
AD 00-20-12 | PREVENT THE TAIL-FUSELAGE HINGE FAILING AND CONSEQUENT LOSS OF CONTROLLED FLIGHT\AEROTECHNIK S R O\L 13 SEH VIVAT |
AD 00-20-13 | DETECT, CORRECT, AND PREVENT FURTHER CRACKING IN THE RUDDER QUADRANT STRUCTURE CAUSED BY INCORRECTLY INSTALLED D-WASHE |
AD 00-20-14 | CORRECT THE LACK OF A FIREWALL SEAL AND CONSEQUENT PROGRESSION OF FIRE AND SMOKE THROUGH THE FIREWALL PANEL INTO THE F |
AD 00-20-16 | DETECT AND CORRECT DISCREPANCIES OF THE CARGO LOADER SYSTEM IN THE FORWARD AND AFT CARGO COMPARTMENTS\BOEING CO\757-20 |
AD 00-20-17 | PREVENT FAILURE OF THE SPAR TUBE, SEPARATION OF THE HORIZONTAL STABILIZER AND IMPACT WITH THE MAIN OR TAIL ROTOR\EUROC |
AD 00-20-18 | PREVENT A HORIZONTAL STABILIZER SLAT (SLAT) FROM SEPARATING, IMPACT WITH A MAIN OR TAIL ROTOR BLADE\BELL HELICPTR TEXT |
AD 00-20-20 | PREVENT LOSS OF MULTIPLE IRU'S IN FLIGHT, WHICH COULD RESULT IN THE LOSS OF NAVIGATION DATA, AND COMPROMISE THE ABILIT |
AD 00-20-51 | PREVENT FAILURE OF A YOKE, SEPARATION OF A YOKE FROM THE MAIN ROTOR DRIVE SHAFT\ROBINSON HELICPTR CO\R22\R22 ALPHA\R22 |
AD 00-21-01 | PREVENT CORROSION OR FATIGUE CRACKING OF CERTAIN STRUCTURAL ELEMENTS\LOCKHEED AIRCRFT CORP\L-1011-385-1\L-1011-385-1-1 |
AD 00-21-02 | PREVENT DAMAGE TO THE FUEL TRIM TRANSFER SYSTEM\AIRBUS INDUSTRIE\A330-202\A330-223\A330-301\A330-321\A330-322\A330-323 |
AD 00-21-03 | PREVENT THE CONTROL LINK OF THE AILERON AUTOPILOT SERVO FROM BEING DRIVEN OVERCENTER\ISRAEL AIRCRFT IND LTD\1125 WESTW |
AD 00-21-04 | PREVENT DAMAGE TO THE 90-MINUTE AUXILIARY POWER UNIT (APU) STANDBY POWER FEEDER CABLE\BOEING CO\767-200 SERIES\767-300 |
AD 00-21-05 | PREVENT SEPARATION OF THE TOP AND BOTTOM TORQUE LINKS\BRITISH AEROSPC (ENGLAND)\ATP |
AD 00-21-07 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\PRATT & WHITNEY DIV\JT8D-209\JT8D-217\JT8D-217A\JT8D-217C\J |
AD 00-21-09 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\PRATT & WHITNEY DIV\PW2037\PW2037M\PW2040\PW2043\PW2143\PW2 |
AD 00-21-10 | PREVENT THE STATIC SEAL FROM MOVING FORWARD\CFE CO\CFE738-1-1B |
AD 00-21-12 | PREVENT ELECTROMAGNETIC INTERFERENCE WITH THE ANTI-SKID CONTROL SYSTEM\FOKKER SVCS\F.28 MARK 0100 |
AD 00-21-13 | PREVENT AN UNDETECTED DRAGGING PARKING BRAKE\DORNIER LUFTFAHRT GMBH\328-300 |
AD 00-21-14 | CORRECT CHAFING DAMAGE AND CONSEQUENT LOSS OF ENGINE OIL CAUSED BY RUBBING PIPES\PILATUS AIRCRFT LTD\PC-12\PC-12/45 |
AD 00-22-01 | PREVENT A MULTIPLE-ENGINE POWER LOSS DUE TO HPC SURGES\PRATT & WHITNEY DIV\PW4050\PW4052\PW4056\PW4060\PW4060A\PW4060C |
AD 00-22-04 | PREVENT THE AIRPLANE FROM DEPARTING THE RUNWAY AT HIGH SPEEDS DURING LANDING DUE TO BENDING AND DAMAGE TO THE SQUAT SW |
AD 00-22-05 | PREVENT BREAKAGE OF THE POWER CONTROL CABLE ASSEMBLIES DUE TO THE INFLEXIBLE CONSTRUCTION OF THE CABLE, WHICH COULD RE |
AD 00-22-07 | RESTORE THE ENGINES TO TYPE DESIGN AND TO PREVENT POSSIBLE LOW CYCLE FATIGUE (LCF) FAILURE OF THE HPT STAGE 1 DISK\INT |
AD 00-22-08 | PREVENT DETERIORATION AND DEFORMATION OF THE MASS-BALANCE WEIGHTS OF THE AILERON\EMPRESA BRASILEIRA DE AERONAUTICA S A |
AD 00-22-09 | PREVENT LOOSENING OF THE LOCKNUT HOLDING THE MLG PISTON TO THE RAMROD\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4101 |
AD 00-22-10 | PREVENT DISCONNECTION OF THE ELEVATOR SPRING TAB OR SERVO TAB HINGE FROM THEIR ATTACHMENTS\EMPRESA BRASILEIRA DE AERON |
AD 00-22-11 | PREVENT ICE ACCUMULATION ON THE AILERON CONTROL CABLES AND/OR MAIN LANDING GEAR (MLG) DOOR AND DOOR SEAL DURING FLIGHT |
AD 00-22-12 | PREVENT OVERHEATING OF THE WIRE BETWEEN CERTAIN CIRCUIT BREAKERS, WHICH COULD RESULT IN SMOKE EMISSIONS IN THE COCKPIT |
AD 00-22-13 | PREVENT AN INACCURATE FUEL QUANTITY INDICATING SYSTEM READING, ENGINE FLAMEOUT DUE TO FUEL STARVATION, AND A SUBSEQUEN |
AD 00-22-15 | PREVENT CHAFING AND FAILURE OF ENGINE THRUST CONTROL CABLES\BOEING CO\747-100 SERIES\747-100B SERIES\747-100B SUD SERI |
AD 00-22-16 | PREVENT RESTRICTED MOVEMENT OF THE RUDDER PEDALS DUE TO STRUCTURAL INTERFERENCE\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL |
AD 00-22-17 | CORRECT RUDDER CLEVIS AND ELEVATOR CONTROL CLEVIS THAT ARE TOO THIN BECAUSE OF ABNORMAL WEAR\SOCATA - GROUPE AEROSPATI |
AD 00-22-18 | CORRECT THE WRONG USE OF SCREWS AND CONSEQUENT WEAR IN THE PILOT/COPILOT PEDAL INTERCONNECT TUBE\RAYTHEON AIRCRFT CO\5 |
AD 00-22-19 | PREVENT FATIGUE CRACKING OF A BLADE, FAILURE OF A BLADE\EUROCOPTER FRANCE\SA330F\SA330G\SA330J |
AD 00-22-21 | PREVENT CONTINUED ARCING FOLLOWING A SHORT CIRCUIT OF THE FUEL PUMP ELECTRICAL CONNECTOR\MCDONNELL DOUGLAS CORP\DC-10- |
AD 00-22-22 | DETECT AND CORRECT CHAFING OF THE WIRE BUNDLE EXITING PANEL "JA" DUE TO INSUFFICIENT CLEARANCE FROM THE FUEL CROSS-FEE |
AD 00-23-01 | DETECT AND CORRECT ANY CRACKS IN THE FORWARD, AFT, AND AUXILIARY WING SPARS\CESSNA AIRCRFT CO\402C |
AD 00-23-02 | DETECT AND CORRECT CORROSION OF THE INBOARD FLAP ACTUATOR BEAM ASSEMBLY AND GAPS BETWEEN THE VANE BRACKETS AND ADJACEN |
AD 00-23-03 | DETECT AND CORRECT IMPROPER RIGGING OF THE LIFTDUMPER MICRO SWITCHES\FOKKER SVCS\F.28 MARK 1000\F.28 MARK 2000\F.28 MA |
AD 00-23-04 | ENSURE CONTINUED STRUCTURAL INTEGRITY OF THESE AIRPLANES (MODEL ATR42-500 SERIES)\AEROSPATIALE (SOCIETE NATIONALE INDU |
AD 00-23-05 | PREVENT LOSS OF HYDRAULIC PRESSURE AND POSSIBLE STRUCTURAL DAMAGE TO THE AIRPLANE DUE TO FAILURE OF THE LANDING GEAR B |
AD 00-23-06 | PREVENT THE LOSS OF HYDRAULIC PRESSURE DUE TO FAILED HYDRAULIC TUBING\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\ |
AD 00-23-08 | PREVENT AUTOPILOT REVERSIONS IN CERTAIN FLIGHT CONDITIONS\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL B4-600R |
AD 00-23-09 | PREVENT RUPTURE OF THE HYDRAULIC LINE AND LOSS OF HYDRAULIC PRESSURE DUE TO CHAFING\EMPRESA BRASILEIRA DE AERONAUTICA |
AD 00-23-10 | PREVENT INCAPACITATION OF THE FLIGHTCREW AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE DUE TO DELAYS IN DONNING OXYGE |
AD 00-23-11 | PREVENT DAMAGE TO THE DISK DRIVE ARM WHICH COULD RESULT IN LOSS OF STAGE 1 LP TURBINE-TO-STAGE 2 LP TURBINE DISK DRIVE |
AD 00-23-12 | PREVENT FAILURE OF CERTAIN HIGH PRESSURE COMPRESSOR (HPC) ROTOR COMPONENTS\CFE CO\CFE738-1-1B |
AD 00-23-13 | PREVENT JAMMING OR DISCONNECTION OF THE HORIZONTAL STABILIZER TRIM ACTUATOR\ISRAEL AIRCRFT IND LTD\1121\1121A\1121B\11 |
AD 00-23-14 | PREVENT OIL FIRES IN AND AROUND THE NO. 4 BEARING AREA\PRATT & WHITNEY DIV\JT9D-20\JT9D-20J\JT9D-3A\JT9D-59A\JT9D-7\JT |
AD 00-23-15 | PREVENT ELECTRICAL SHORTS OR ARCING AT THE ILLUMINATED PANEL CONNECTOR AT THE REFUEL/DEFUEL PANEL\SAAB AIRCRFT AB\SAAB |
AD 00-23-17 | DETECT AND CORRECT INADEQUATE CLEARANCE BETWEEN THE FUEL FEED PIPE OF THE NUMBER 2 ENGINE AND THE PNEUMATIC SENSE LINE |
AD 00-23-18 | PREVENT ELECTRICAL ARCING BETWEEN THE OXYGEN TUBING AND AN ELECTRICAL SOURCE\LEARJET INC\60 |
AD 00-23-19 | PREVENT HIGH BEARING STRESS ON THE BUSHINGS IN THE FLAP FITTINGS\SAAB AIRCRFT AB\SAAB 340B\SAAB SF340A |
AD 00-23-20 | PREVENT CORROSION OF THE AXLE OF THE MAIN LANDING GEAR\BOEING CO\777-200 SERIES |
AD 00-23-23 | PREVENT FATIGUE CRACKING AT THE RIB 1/CENTER SPAR ANGLE AND BOTTOM CORNER FITTING\AIRBUS INDUSTRIE\A330-321\A330-322\A |
AD 00-23-24 | PREVENT SEPARATION OF THE SELF-SEAL COUPLINGS\SAAB AIRCRFT AB\SAAB 2000 |
AD 00-23-25 | DETECT AND CORRECT CRACKING OF THE VERTICAL CHORDS ADJACENT TO THE LOWER SPAR FITTING\BOEING CO\747-100 SERIES\747-100 |
AD 00-23-26 | ENSURE CONTINUED STRUCTURAL INTEGRITY\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROS\ATR72 SERIES\ATR72-101\ATR72- |
AD 00-23-27 | PREVENT THE POSSIBILITY OF A FIRE ON AN AIRPLANE DUE TO CHAFING OF THE ELECTRICAL WIRING OF THE CABIN CEILING LIGHTING |
AD 00-23-28 | PREVENT DAMAGE TO THE ENGINE FIRE SHUTOFF SWITCH (EFSS) SOLENOID AND TO THE OVERRIDE MECHANISM\BOEING CO\777-200 SERIE |
AD 00-23-29 | PREVENT INCREASED BRAKING DISTANCE FOR LANDINGS THAT REQUIRE THE FLIGHT IDLE STOP OVERRIDE\SAAB AIRCRFT AB\SAAB 340B |
AD 00-23-31 | PREVENT ARCING AND HEAT DAMAGE OF THE LUMINATOR FLUORESCENT LAMP HOLDERS LOCATED OUTBOARD OF THE PASSENGER SERVICE UNI |
AD 00-23-32 | DETECT AND CORRECT IMPROPER MOVEMENT IN THE ELEVATOR CONTROL SYSTEM AND TO INCREASE THE STIFFNESS OF THE ELEVATOR CONT |
AD 00-23-33 | PREVENT FAILURE OF THE VERTICAL STABILIZER CAUSED BY DISBONDING, CORROSION, CRACKS, OR LOOSE RIVETS IN THE STABILIZER |
AD 00-23-34 | PREVENT A SEVERE ASYMMETRIC THRUST CONDITION DURING FLIGHT\BOEING CO\737-300 SERIES\737-400 SERIES\737-500 SERIES |
AD 00-23-52-E | LETTER AD 2000-23-52 PREVENT FAILURE OF THE SHAFT AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\SIKORSKY AIRCRF |
AD 00-24-03 | PREVENT AN UNCOMMANDED RETRACTION OF THE FLAPS DURING TAKEOFF\DORNIER LUFTFAHRT GMBH\328-100 |
AD 00-24-04 | CORRECT THE MISROUTED RUDDER CONTROL CABLE AND CONSEQUENT GUARD PIN WEAR OR FRAYING OF THE CABLES WITH LOSS OF RUDDER |
AD 00-24-05 | PREVENT FAILURE OF THE NOSE LANDING GEAR (NLG) UPPER STRUT CAUSED BY CRACKING IN THE AREA OF THE SEEGER RETAINING RING |
AD 00-24-06 | DETECT AND CORRECT CRACKING OF THE MAIN CARGO DOOR SKIN AND FRAMES\BOEING CO\707-100 LONG BODY\707-100 LONG BODY\707-1 |
AD 00-24-09 | PREVENT SMOKE AND FIRE IN THE FORWARD CARGO COMPARTMENT DUE TO BURN DAMAGE TO THE INSULATION BLANKETS IN THE AREA SURR |
AD 00-24-10 | PREVENT INSUFFICIENT CLEARANCE AND CONTACT BETWEEN THE B7-28 BUS AND AN ADJACENT PANEL, WHICH COULD RESULT IN ARCING D |
AD 00-24-11 | PREVENT CHAFING OF ELECTRICAL WIRE ASSEMBLIES ABOVE THE FORWARD PASSENGER DOORS, WHICH COULD RESULT IN AN ELECTRICAL F |
AD 00-24-12 | PREVENT ARCING AND SPARKING DAMAGE TO THE POWER FEEDER CABLES, TERMINAL STRIPS, AND ADJACENT STRUCTURE, AND CONSEQUENT |
AD 00-24-14 | PREVENT DAMAGED ELECTRICAL WIRES OR DAMAGED DOOR ACTUATION CABLES DUE TO CHAFING BY THE CABLES DURING OPERATION OF THE |
AD 00-24-15 | PREVENT ELECTRICAL ARCING AND/OR HEAT DAMAGED WIRES DUE TO IMPROPER WIRE INSTALLATIONS DURING MANUFACTURE AND/OR MAINT |
AD 00-24-16 | PREVENT FIRE AND SMOKE IN CERTAIN WIRE BUNDLES THAT ARE ROUTED TO AND FROM THE MAIN AVIONICS COMPARTMENT OR CENTER ACC |
AD 00-24-17 | PREVENT OVERHEATING OF THE ELECTRICAL PINS INSIDE THE CARGO CONTROL UNITS (CCU) AND SUBSEQUENT RELEASE OF HOT GASES AN |
AD 00-24-19 | PREVENT INCAPACITATION OF THE FLIGHTCREW AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE DUE TO DELAYS IN DONNING OXYGE |
AD 00-24-21 | PREVENT SEPARATION OF THE CONTROL SYSTEM ATTACHMENTS AT PIVOTING POINTS\HILLER AVI\UH-12\UH-12A\UH-12B\UH-12C\UH-12D\U |
AD 00-24-22 | PREVENT THE REAR CANOPY RETAINING STRAP FROM NOT RELEASING PROPERLY DURING THE EMERGENCY EGRESS PROCEDURE BECAUSE OF T |
AD 00-24-23 | DETECT CRACKS IN THE AIRBRAKE CONTROL SYSTEM AND REPLACE CRACKED PARTS WITH PARTS OF IMPROVED DESIGN\CENTRAIR\101\101A |
AD 00-24-24 | DETECT CRACKING, LOOSE RIVETS, AND MISSING RIVETS ON COMMON NOZZLE ASSEMBLY P/N FK16544 OR FK16558\ROLLS-ROYCE PLC\RB2 |
AD 00-24-25 | PREVENT THE INABILITY TO EXTEND THE NOSE LANDING GEAR DUE TO EXCESSIVE CLEARANCE OF THE ROLLER IN THE DRAG STAY RIGGIN |
AD 00-24-26 | PREVENT FAN BLADE FAILURE\ROLLS-ROYCE PLC\RB211-TRENT 875-17\RB211-TRENT 877-17\RB211-TRENT 884-17\RB211-TRENT 892-17\ |
AD 00-25-01 | \PIPER AIRCRFT INC NEW\PA-31\PA-31-300\PA-31-325\PA-31-350\PA-31P\PA-31P-350\PA-31T\PA-31T1\PA-31T2\PA-31T3 |
AD 00-25-02 | DETECT AND REPAIR OR REPLACE DAMAGED WOOD WING SPARS\AMERCN CHAMPION AIRCRFT CORP\11AC\11BC\11CC\7AC\7ACA\7BCM (ARMY L |
AD 00-25-03 | PREVENT AN ACTUATOR PISTON FROM UNTHREADING FROM ITS ROD END, LOSS OF CONTROL OF THE MAIN ROTOR, AND SUBSEQUENT LOSS O |
AD 00-25-04 | PREVENT AN ASYMMETRIC BRAKING CONDITION AND A LONGER STOPPING DISTANCE DUE TO SUDDEN LOSS OF NORMAL BRAKING TO THE LEF |
AD 00-25-05 | PREVENT FAILURE OF THE RIVETS ATTACHING THE GAMAH COUPLING HINGE TO THE FUEL SYSTEM TUBING AND CONSEQUENT SEPARATION O |
AD 00-25-06 | REDUCE STRESSES THAT COULD LEAD TO FATIGUE CRACKING OF THE LPT 4TH STAGE AIR SEAL\PRATT & WHITNEY DIV\PW4052\PW4056\PW |
AD 00-25-07 | DETECT AND CORRECT DAMAGE OF THE AFT END OF EACH INBOARD FLAP TRACK OF THE WING OUTBOARD FLAP\BOEING CO\737-100 SERIES |
AD 00-25-51-E | LETTER AD 2000-25-51 PREVENT AN UNCONTAINED FAILURE OF THE HPT STAGE 1 OR STAGE 2 DISK DUE TO EXCEEDED LIFE-CYCLE |
AD 00-25-54-E | LETTER AD 2000-25-54 PREVENT FAILURE OF A BLADE AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\AGUSTA S P A\A109 |
AD 00-26-01 | PREVENT FATIGUE FAILURE OF A TENSION-TORSION (TT) STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE), AND SUBSEQUENT LOSS OF CO |
AD 00-26-02 | PREVENT FAILURE OF THE STATOR BLADES OF THE FENESTRON TAIL ROTOR\EUROCOPTER DEUTSCHLAND GMBH (ECD)\EC135 P1\EC135 T1 |
AD 00-26-16 | INSTALL MISSING RIVETS IN THE RIGHT HAND FUSELAGE PANEL ASSEMBLY IN THE AREA ABOVE THE RIGHT WING AND BELOW THE CABIN |
AD 00-26-17 | PREVENT LOSS OF ELECTRICAL POWER TO THE WINDSHIELD DEICING SYSTEM DUE TO OPERATION IN THE "LIGHT" MODE\PILATUS AIRCRFT |
AD 00-26-18 | PREVENT AERODYNAMIC FLUTTER OF THE UPPER AIRBRAKE CAUSED BY THE CURRENT DESIGN AIRBRAKE EYEBOLTS\WESTLAND HELICPTRS LT |
AD 00-26-19 | PREVENT IN-FLIGHT DAMAGE TO THE WING SKINS CAUSED BY ABNORMAL VENTING CONDITIONS OF THE WING FUEL TANK\SOCATA - GROUPE |
AD 00-26-20 | PREVENT THE FLIGHT CREW FROM BEING UNAWARE THAT AN ELECTRICAL SYSTEM FAILURE HAS OCCURRED AND THAT THE AIRPLANE MAIN B |
AD 00-CE-01 | PREVENT THE TAIL-FUSELAGE HINGE FAILING\AEROTECHNIK S R O\L 13 SEH VIVAT |
AD 00-CE-02 | PREVENT CHAFING BETWEEN THE WING FUEL QUANTITY WIRING HARNESS AND THE INTERNAL WING HARNESS SUPPORTS AT EACH WING RIB |
AD 00-CE-03 | CORRECT CHAFING DAMAGE AND CONSEQUENT LOSS OF ENGINE OIL CAUSED BY RUBBING PIPES\PILATUS AIRCRFT LTD\PC-12\PC-12/45 |
AD 00-CE-06 | CORRECT THE MISROUTED RUDDER CONTROL CABLE AND CONSEQUENT GUARD PIN WEAR OR FRAYING OF THE CABLES WITH LOSS OF RUDDER |
AD 00-CE-09 | DETECT AND CORRECT CRACKS IN THE WING SPAR ASSEMBLIES AND ASSURE THE OPERATIONAL SAFETY OF THE ABOVE-REFERENCED AIRPLA |
AD 00-CE-09-1 | DETECT AND CORRECT CRACKS IN THE WING SPAR ASSEMBLIES\RAYTHEON\45 (YT-34)\A45 (T34A, B45)\D45 (T-34B) |
AD 00-CE-10 | ASSURE THAT THE COPILOT'S NAV "FLAG" DISPLAYS ARE BASED ON THE COPILOT'S SELECTED NAV SOURCE\RAYTHEON\1900D |
AD 00-CE-12 | DETECT, CORRECT, AND PREVENT FURTHER CRACKING IN THE RUDDER QUADRANT STRUCTURE CAUSED BY INCORRECTLY INSTALLED D-WASHE |
AD 00-CE-15 | CORRECT THE LACK OF A FIREWALL SEAL AND CONSEQUENT PROGRESSION OF FIRE AND SMOKE THROUGH THE FIREWALL PANEL INTO THE F |
AD 00-CE-16 | PREVENT FAILURE OF THE NOSE LANDING GEAR (NLG) UPPER STRUT CAUSED BY CRACKING IN THE AREA OF THE SEEGER RETAINING RING |
AD 00-CE-20 | INFORMATION NECESSARY TO ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION IS |
AD 00-CE-22 | DETECT AND CORRECT DAMAGED RUDDER CABLES CAUSED BY CHAFING OF THE CABLE AGAINST THE PULLEYS\EAGLE AIRCRFT PTY LTD\150B |
AD 00-CE-24 | DETECT, CORRECT, AND PREVENT FUTURE CRACKS ON THE ORIGINAL DESIGN LANDING GEAR PIVOTS\CESSNA AIRCRFT CO\172RG |
AD 00-CE-26 | CONTINUE TO DETECT AND CORRECT ANY CHAFING BETWEEN THE MAP LIGHT SWITCH AND THE BORDERING FUEL LINE\CESSNA\172K\172N\1 |
AD 00-CE-27 | ELIMINATE EXISTING AND PREVENT FUTURE FATIGUE CRACKS IN THE MAIN LANDING GEAR (MLG) HYDRAULIC ACTUATOR END CAPS\RAYTHE |
AD 00-CE-28 | CORRECT POTENTIAL BRAKE SHUTTLE VALVE PROBLEMS, WHICH COULD CAUSE THE BRAKE ASSEMBLY TO DRAG AND OVERHEAT\FAIRCHILD AI |
AD 00-CE-28-R1 | CORRECT POTENTIAL BRAKE SHUTTLE VALVE PROBLEMS\FAIRCHILD AIRCRFT CORP\SA226-AT\SA226-T(A)\SA226-T(B)\SA226-TC\SA |
AD 00-CE-29 | CORRECT SUBSTANDARD QUALITY COCKPIT VOICE RECORDINGS CAUSED BY THE CONFIGURATION OF THE PRESENT CVR SYSTEM, WHICH COUL |
AD 00-CE-42 | CORRECT THE WRONG USE OF SCREWS AND CONSEQUENT WEAR IN THE PILOT/COPILOT PEDAL INTERCONNECT TUBE\RAYTHEON\58 |
AD 00-CE-46 | PREVENT FAILURE OF THE ELEVATOR AND RUDDER ATTACHMENT BRACKETS BECAUSE OF CRACKS OR CORROSION DAMAGE\PILATUS AIRCRFT L |
AD 00-CE-48 | PREVENT THE REAR CANOPY RETAINING STRAP FROM NOT RELEASING PROPERLY DURING THE EMERGENCY EGRESS PROCEDURE BECAUSE OF T |
AD 00-CE-49 | DETECT CRACKS IN THE AIRBRAKE CONTROL SYSTEM AND REPLACE CRACKED PARTS WITH PARTS OF IMPROVED DESIGN\S N CENTRAIR\101\ |
AD 00-CE-54 | DETECT AND CORRECT CRACKS IN THE MLG RADIUS RODS\BRITISH AEROSPC\JETSTREAM SERIES 200\HP 137 MK.1\JETSTREAM MODEL 3101 |
AD 00-CE-55 | PREVENT LOSS OF ELECTRICAL POWER TO THE WINDSHIELD DEICING SYSTEM DUE TO OPERATION IN THE "LIGHT" MODE\PILATUS AIRCRFT |
AD 00-CE-57 | PREVENT FAILURE OF THE NOSE LANDING GEAR STEERING ACTUATOR\JETSTREAM AIRCRFT LTD (FORMERLY BRITISH AEROSPC )\JETSTREAM |
AD 00-CE-61 | PREVENT LOOSE FLAP ATTACHMENT SCREWS OR THE LOSS OF FLAP ATTACHMENT SCREWS\SOCATA--GROUPE AEROSPATIALE (SEE MORANE-SAU |
AD 00-CE-67 | DETECT AND REMOVE PROBLEM FLAP ACTUATORS FROM SERVICE\PIAGGIO & C (SEE INDUSTRIE AERONAUTICHE E MECCANICHE)\P-180 |
AD 00-CE-69 | PREVENT LOSS OF PROPELLER CONTROL BECAUSE OF HARDENING OR BLOCKING OF THE CONTROL CABLE\SOCATA--GROUPE AEROSPATIALE (S |
AD 00-CE-70 | PREVENT OIL FROM ENTERING THE GASEOUS OXYGEN SYSTEM SERVICE COMPARTMENT\SOCATA--GROUPE AEROSPATIALE (SEE MORANE-SAULNI |
AD 00-NE-04 | PREVENT RADIAL DRIVE STEADY BEARING FAILURE\ROLLS-ROYCE LTD\RB-211-535C\RB-211-535E4\RB-211-535E4B\BOEING\757-200 SERI |
AD 00-NE-24 | PREVENT PREMATURE LPT DISK FAILURE DUE TO CRACKING OF THE LPT DISKS\PRATT & WHITNEY\PW305\PW305A\BRITISH AEROSPC\BAE 1 |
AD 00-NE-25 | PREVENT 2ND STAGE HPT AIR SEAL ASSEMBLY FAILURE\PRATT & WHITNEY\PW4074\PW4077\PW4077D\PW4090 |
AD 00-NE-26 | DETECT WEAR ON THE COMPRESSOR BLEED VALVE ASSEMBLY COVER, GUIDE PIN SHAFT, COTTER PIN, AND TO DETECT PARTICLES FROM DI |
AD 00-NE-30 | PREVENT HPC AIR DUCT FAILURES THAT COULD RESULT IN FAN MID SHAFT (FMS) FAILURES AND UNCONTAINED LPT EVENTS\GENERAL ELE |
AD 00-NM-01 | PREVENT OPENING OF THE CARGO DOOR WHILE THE AIRPLANE IS IN FLIGHT\MCDONNELL DOUGLAS CORP\DC-8-61F\DC-8-62F\DC-8-63F\DC |
AD 00-NM-02 | PREVENT CRACKING OF THE NLG MAIN FITTING, WHICH COULD LEAD TO COLLAPSE OF THE NLG DURING TAKEOFF AND LANDING, AND POSS |
AD 00-NM-03 | PREVENT THE INABILITY TO EXTEND THE NOSE LANDING GEAR\RAYTHEON\HAWKER 800XP SERIES\HAWKER 800A (U-125A) |
AD 00-NM-04 | PREVENT FAILURE OF THE FRONT SPAR ATTACHMENT AND UPPER CAP OF THE ENGINE PYLONS DUE TO FATIGUE CRACKING\MCDONNELL DOUG |
AD 00-NM-06 | PREVENT FAILURE OF THE SHOULDER HARNESS\FOKKER-VFW B V\F.27 MARK 050\F.27 MARK 100\F.27 MARK 200\F.27 MARK 300\F.27 MA |
AD 00-NM-07 | PREVENT CRACKING OF THE HYDRAULIC LINES\DORNIER-WERKE G M B H\328-300 SERIES |
AD 00-NM-10 | PREVENT THE CONTROL LINK OF THE AILERON AUTOPILOT SERVO FROM BEING DRIVEN OVERCENTER\ISRAEL AIRCRFT IND LTD\ASTRA SPX |
AD 00-NM-100 | PREVENT OPENING OF THE CARGO DOOR WHILE THE AIRPLANE IS IN FLIGHT\MCDONNELL DOUGLAS CORP\DC-8-63F\DC-8-62F\DC-8-71F\ |
AD 00-NM-101 | ENSURE THAT THE FLIGHT CREW IS AWARE THAT AN ELECTRICAL SYSTEM FAILURE MAY HAVE OCCURRED AND THAT THE MAIN AIRPLANE |
AD 00-NM-103 | PREVENT CRACKING OR BREAKING OF THE DOOR HANDLE MOUNTING HUB\BOEING\737-200 SERIES\737-300 SERIES\737-400 SERIES\737 |
AD 00-NM-104 | PREVENT A SUDDEN CHANGE IN PITCH DUE TO AN OUT-OF-TRIM CONDITION COMBINED WITH AN AUTOPILOT DISCONNECT\AIRBUS INDUST |
AD 00-NM-105 | PREVENT CRACKING OF THE CENTER SECTION OF THE FUSELAGE\AIRBUS INDUSTRIE\A300-600\A300-600R |
AD 00-NM-107 | PREVENT A SEVERE ASYMMETRIC THRUST CONDITION DURING FLIGHT WHICH COULD RESULT IN LOSS OF CONTROL OF THE AIRPLANE\BOE |
AD 00-NM-112 | PREVENT AN UNCOMMANDED RETRACTION OF THE FLAPS DURING TAKEOFF\DORNIER-WERKE G M B H\328-100 SERIES |
AD 00-NM-113 | PREVENT LOSS OF HYDRAULIC PRESSURE AND POSSIBLE STRUCTURAL DAMAGE TO THE AIRPLANE DUE TO FAILURE OF THE LANDING GEAR |
AD 00-NM-114 | PREVENT AUTOPILOT REVERSIONS IN CERTAIN FLIGHT CONDITIONS, WHICH COULD RESULT IN MISUNDERSTANDING BY THE FLIGHT CREW |
AD 00-NM-118 | PREVENT THE SIMULTANEOUS FAILURE OF TWO AIR PRESSURIZATION UNITS\AIRBUS INDUSTRIE\A330-301 SERIES\A330-321 SERIES\A3 |
AD 00-NM-12 | PREVENT THE DISPLAY OF INCORRECT ENGINE LIMITATIONS, WHICH COULD RESULT IN AN OVERSPEED OF THE PROPELLERS AND POTENTIA |
AD 00-NM-121 | PREVENT OVERHEATING OF THE WIRE BETWEEN CERTAIN CIRCUIT BREAKERS, WHICH COULD RESULT IN SMOKE EMISSIONS IN THE COCKP |
AD 00-NM-125 | ENSURE THAT THE FLIGHTCREW IS ABLE TO RECOGNIZE THE FORMATION OF SIGNIFICANT ICE ACCRETION\EMPRESA BRASILEIRA DE AER |
AD 00-NM-127 | PREVENT INCAPACITATION OF THE FLIGHTCREW AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE DUE TO DELAYS IN DONNING OXY |
AD 00-NM-129 | PREVENT THE LOSS OF HYDRAULIC PRESSURE DUE TO FAILED HYDRAULIC TUBING\EMPRESA BRASILEIRA DE AERONAUTICA S A\EMB-145 |
AD 00-NM-130 | PREVENT DETERIORATION AND DEFORMATION OF THE MASS-BALANCE WEIGHTS OF THE AILERON\EMPRESA BRASILEIRA DE AERONAUTICA S |
AD 00-NM-131 | PREVENT MECHANICAL BLOCKAGE OF THE ELEVATOR CONTROL CABLE DUE TO THE FREEZING OF WATER COLLECTED INSIDE THE FUSELAGE |
AD 00-NM-132 | PREVENT THE AIRPLANE FROM DEPARTING THE RUNWAY AT HIGH SPEEDS DURING LANDING DUE TO BENDING AND DAMAGE TO THE SQUAT |
AD 00-NM-133 | PREVENT RUPTURE OF THE HYDRAULIC LINE AND LOSS OF HYDRAULIC PRESSURE DUE TO CHAFING\EMPRESA BRASILEIRA DE AERONAUTIC |
AD 00-NM-134 | DETECT AND CORRECT FATIGUE CRACKING OF THE FRONT SPAR WEB OF THE WING\BOEING\747-100 SERIES\747-100B\747-100B SUD\74 |
AD 00-NM-141 | PREVENT FAILURE OF THE MOUNTING BRACKETS OF THE HYDRAULIC HAND PUMP AT THE FRAME ATTACHMENT FLANGES\BRITISH AEROSPC\ |
AD 00-NM-142 | PREVENT PREMATURE FAILURE OF THE SHEAR PINS OF THE ELEVATOR DAMPER\BOMBARDIER INC (FORMERLY CANADAIR LTD)\CL-600-2B1 |
AD 00-NM-144 | PREVENT THE FLIGHT CREW FROM BEING UNAWARE THAT AN ELECTRICAL SYSTEM FAILURE HAS OCCURRED AND THAT THE AIRPLANE MAIN |
AD 00-NM-146 | PREVENT CHAFING OF WIRE BUNDLES IN TWO JUNCTION BOXES IN THE MAIN WHEEL WELL\BOEING\737-100 SERIES\737-200 SERIES\73 |
AD 00-NM-147 | PREVENT STRESS CORROSION CRACKING AND CONSEQUENT FRACTURE OF THE AFT TRUNNION OF THE OUTER CYLINDER OF THE MLG\BOEIN |
AD 00-NM-148 | PREVENT CHAFING OF THE FEEDER CABLES DURING REMOVAL OF THE SUMP PANELS OF THE CARGO FLOOR\MCDONNELL DOUGLAS CORP\DC- |
AD 00-NM-149 | PREVENT FIRE AND SMOKE IN CERTAIN WIRE BUNDLES THAT ARE ROUTED TO AND FROM THE MAIN AVIONICS COMPARTMENT OR CENTER A |
AD 00-NM-152 | PREVENT RESTRICTED MOVEMENT OF THE RUDDER PEDALS DUE TO STRUCTURAL INTERFERENCE\BRITISH AEROSPC\JETSTREAM MODEL 4101 |
AD 00-NM-157 | PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE AND REDUCED STRUCTURAL INTEGRITY OF THE STRUT, WHICH COULD RESUL |
AD 00-NM-17 | PREVENT ELECTROMAGNETIC INTERFERENCE WITH THE ANTI-SKID CONTROL SYSTEM\FOKKER-VFW B V\F.28 MARK 0100 |
AD 00-NM-179 | PREVENT CORROSION FROM DEVELOPING ON THE UNDERSIDE OF THE TOP SKIN OF THE CENTER WING\BRITISH AEROSPC\BAE 146 SERIES |
AD 00-NM-18 | PREVENT FAILURE OF THE BEARING SUPPORT FITTING OF THE FORWARD TRUNNION\BOEING\727-100 SERIES\727-100C SERIES\727-200 S |
AD 00-NM-181 | PREVENT THE COLLAPSE OF THE MAIN LANDING GEAR DUE TO LEAKS OF HYDRAULIC OIL FROM THE MAIN LANDING GEAR SELECTOR VALV |
AD 00-NM-184 | DETECT AND CORRECT FATIGUE CRACKING OF THE LOWER SPAR CHORD, WHICH COULD RESULT IN REDUCED STRUCTURAL INTEGRITY OF T |
AD 00-NM-19 | PREVENT THE POTENTIAL FOR DUAL WIRE FAULTS FROM GROUNDED, SEPARATED, OR SHORTED WIRES\BOEING\767-200 SERIES\767-200ER |
AD 00-NM-201 | PREVENT FATIGUE FAILURE OF CERTAIN EXISTING FASTENERS IN THE AFT PICKUP FITTINGS OF THE HORIZONTAL STABILIZER, WHICH |
AD 00-NM-202 | PREVENT BREAKAGE OF THE POWER CONTROL CABLE ASSEMBLIES DUE TO THE INFLEXIBLE CONSTRUCTION OF THE CABLE\SHORT BROTHER |
AD 00-NM-205 | PREVENT FATIGUE CRACKING OF THE CORNERS OF THE DOORFRAME AND THE CROSS BEAMS OF THE AFT CARGO DOOR, WHICH COULD RESU |
AD 00-NM-212 | PREVENT THE TURBINE AIR DISCHARGE DUCT OR WATER SEPARATOR OUTLET DUCT FROM DISCONNECTING FROM THE COLD AIR UNIT TURB |
AD 00-NM-213 | PREVENT ELECTRICAL SHORTS OR ARCING AT THE ILLUMINATED PANEL CONNECTOR AT THE REFUEL/DEFUEL PANEL\SAAB-SCANIA AB\SF- |
AD 00-NM-214 | PREVENT REDUCED STRUCTURAL INTEGRITY OF THE AIRPLANE DUE TO FATIGUE DAMAGE AND CONSEQUENT CRACKING OF THE PICK-UP AN |
AD 00-NM-22 | PREVENT AN INADVERTENT INCREASE IN THRUST\AIRBUS INDUSTRIE\A320-232\A320-233 |
AD 00-NM-221 | PREVENT SEPARATION OF THE SELF-SEAL COUPLINGS, WHICH COULD RESULT IN LOSS OF ENGINE OIL PRESSURE AND A FLIGHT-CREW-C |
AD 00-NM-222 | PREVENT LOSS OF THE NOSE WHEEL STEERING AND REDUCED CONTROLLABILITY OF THE AIRPLANE ON THE GROUND\SAAB-SCANIA AB\SF- |
AD 00-NM-223 | DETECT AND CORRECT FATIGUE CRACKING OF FUSELAGE FRAME 07 IN THE UPPER FRAME SECTION ASSEMBLY OF THE LATERAL COCKPIT |
AD 00-NM-224 | PREVENT THE ELEVATOR CABLE TENSION REGULATORS FROM BECOMING DETACHED FROM THE SPLINED SHAFT OF THE ASSEMBLY\BRITISH |
AD 00-NM-227 | PREVENT ELECTRICAL ARCING OF THE FUEL BOOST PUMP WIRE\AIRBUS INDUSTRIE\A319-131\A319-132\A320-111\A320-200\A320-211\ |
AD 00-NM-23 | PREVENT FALSE SMOKE WARNINGS FROM THE CARGO COMPARTMENT SMOKE DETECTORS, WHICH COULD RESULT IN ABORTED TAKEOFFS, DIVER |
AD 00-NM-25 | PREVENT FALSE WARNING OF A HOT ENGINE EXHAUST TAILPIPE AND INTERMITTENT SIGNAL FAILURE\SAAB-SCANIA AB\SF-340A\SAAB 340 |
AD 00-NM-253 | DETECT AND CORRECT FATIGUE CRACKING OF THE INNER SIDESTAYS OF THE MAIN LANDING GEAR (MLG), WHICH COULD RESULT IN FAI |
AD 00-NM-256 | PREVENT THE SPRING TAB OR THE SERVO TAB FROM BECOMING DISCONNECTED, RESULTING IN STRUCTURAL FAILURE, AND TO PREVENT |
AD 00-NM-26 | ENSURE CONTINUED STRUCTURAL INTEGRITY OF THESE AIRPLANES (ATR42-500 SERIES)\AEROSPATIALE\ATR42-500 |
AD 00-NM-260 | PREVENT VARIOUS FAILURES OF ELECTRIC MOTORS OF THE AUXILIARY HYDRAULIC PUMP AND ASSOCIATED WIRING\MCDONNELL DOUGLAS |
AD 00-NM-264 | PREVENT FATIGUE CRACKING IN THE ZONE OF THE FITTINGS CONNECTING THE FUSELAGE TO STIFFENER RODS LOCATED IN FRAMES 33, |
AD 00-NM-265 | PREVENT INCAPACITATION OF THE FLIGHTCREW AND CONSEQUENT LOSS OF CONTROL OF THE AIRPLANE DUE TO DELAYS IN DONNING OXY |
AD 00-NM-269 | PREVENT VARIOUS FAILURES OF ELECTRIC MOTORS OF THE AUXILIARY HYDRAULIC PUMP AND ASSOCIATED WIRING\MCDONNELL DOUGLAS |
AD 00-NM-27 | DETECT CORROSION OF THE LOWER SURFACE OF THE WING CENTER SECTION AND THE SURROUNDING AREA\BOEING\727-100 SERIES |
AD 00-NM-275 | PREVENT FAILURE OF THE CORE COWL LATCHES DURING AN ENGINE FIRE\BOEING\747-400 SERIES\767-200 SERIES\767-200ER SERIES |
AD 00-NM-279 | PREVENT CRACKING OF THE UPPER SKIN OF THE WING\BOEING\707-100 SERIES\707-100B SERIES\707-200 SERIES\707-300 SERIES\7 |
AD 00-NM-28 | PREVENT SMOKE AND FIRE IN THE FORWARD CARGO COMPARTMENT\MCDONNELL DOUGLAS CORP\MD-11 SERIES |
AD 00-NM-280 | PREVENT OPENING OF THE CARGO DOOR WHILE THE AIRPLANE IS IN FLIGHT OR COLLAPSE OF THE MAIN DECK CARGO FLOOR\MCDONNELL |
AD 00-NM-282 | PREVENT OPENING OF THE CARGO DOOR WHILE THE AIRPLANE IS IN FLIGHT OR COLLAPSE OF THE MAIN DECK CARGO FLOOR\MCDONNELL |
AD 00-NM-285 | PREVENT LOOSE OR MISSING NUTS ON THE CLEVIS ASSEMBLIES THAT SUPPORT THE AUXILIARY TRACKS OF THE INBOARD LEADING EDGE |
AD 00-NM-29 | PREVENT INSUFFICIENT CLEARANCE AND CONTACT BETWEEN THE B7-28 BUS AND AN ADJACENT PANEL\MCDONNELL DOUGLAS CORP\MD-11 SE |
AD 00-NM-293 | DETECT AND CORRECT IMPROPER RIGGING OF THE LIFTDUMPER MICRO SWITCHES, WHICH COULD RESULT IN INADVERTENT EXTENSION OF |
AD 00-NM-295 | DETECT AND CORRECT CRACKING OF THE LOWER PORTION OF THE MAIN DECK CARGO DOOR FRAMES\BOEING\737-200 SERIES\737-300 SE |
AD 00-NM-296 | PREVENT FRACTURE OF A CLAMSHELL COUPLING ON THE POTABLE WATER FILL LINE\BOEING\767-200 SERIES\767-300 SERIES |
AD 00-NM-306 | DETECT AND CORRECT FATIGUE CRACKING ON THE FORWARD FITTINGS IN THE RADIUS OF FRAME 40 ADJACENT TO THE TENSION BOLTS |
AD 00-NM-308 | PREVENT INABILITY TO SHUT OFF THE FLOW OF FUEL TO AN ENGINE AFTER AN UNCONTAINED ENGINE FAILURE\BOEING\737-300 SERIE |
AD 00-NM-309 | FIND AND FIX DISCREPANCIES (BONDING, LOOSE FITTINGS, CRACKING) OF THE BONDING JUMPER ASSEMBLIES\BOEING\767-200 SERIE |
AD 00-NM-31 | DETECT DISCREPANCIES THAT INCLUDE BUT ARE NOT LIMITED TO FRAYED, CHAFED, OR NICKED WIRES AND WIRE INSULATION\MCDONNELL |
AD 00-NM-313 | DETECT AND CORRECT CHAFING AND TO PREVENT ELECTRICAL CONTACT BETWEEN THE FUEL QUANTITY INDICATING SYSTEM (FQIS) WIRI |
AD 00-NM-319 | PREVENT UNCOMMANDED APPLICATION OF 50 PERCENT BRAKING IN ONE PAIR OF WHEELS, WHICH COULD RESULT IN THE AIRPLANE SKID |
AD 00-NM-32 | PREVENT ELECTRICAL SHORTING OF THE BRAKE COILS OF THE AUTO THROTTLE SERVO (ATS) OR ELEVATOR LOAD FEEL (ELF)/FLAP LIMIT |
AD 00-NM-321 | PREVENT REJECTED TAKEOFFS DUE TO EXCEEDING ENGINE OIL PRESSURE LIMITS\EMPRESA BRASILEIRA DE AERONAUTICA S A\EMB-135 |
AD 00-NM-33 | PREVENT ARCING AND SPARKING DAMAGE TO THE POWER FEEDER CABLES, TERMINAL STRIPS, AND ADJACENT STRUCTURE\MCDONNELL DOUGL |
AD 00-NM-34 | PREVENT ARCING AND HEAT DAMAGE TO THE ATTACHMENT POINTS OF THE MAIN EXTERNAL AND GALLEY POWER RECEPTACLE GROUND WIRE, |
AD 00-NM-35 | PREVENT DAMAGED ELECTRICAL WIRES OR DAMAGED DOOR ACTUATION CABLES DUE TO CHAFING BY THE CABLES DURING OPERATION OF THE |
AD 00-NM-354 | PREVENT CRACKING OF THE VERTICAL CHORDS ADJACENT TO THE LOWER SPAR FITTING\BOEING\747-100 SERIES\747-200 SERIES\747S |
AD 00-NM-36 | PREVENT ELECTRICAL ARCING AND/OR HEAT DAMAGED WIRES DUE TO IMPROPER WIRE INSTALLATIONS DURING MANUFACTURE AND/OR MAINT |
AD 00-NM-37 | PREVENT FIRE AND SMOKE IN CERTAIN WIRE BUNDLES THAT ARE ROUTED TO AND FROM THE MAIN AVIONICS COMPARTMENT OR CENTER ACC |
AD 00-NM-38 | PREVENT OVERHEATING OF THE ELECTRICAL PINS INSIDE THE CARGO CONTROL UNITS (CCU)\MCDONNELL DOUGLAS CORP\MD-11 SERIES |
AD 00-NM-41 | PREVENT CHAFING OF THE FUEL LEVEL CONTROL SWITCH WIRING HARNESS\LOCKHEED AIRCRFT CORP LOCKHEED-GEORGIA CO & LOCKHEED-C |
AD 00-NM-46 | PREVENT CHAFING OF THE WIRE BUNDLE TO RELAY 'KT' ON PANEL 'JA'\RAYTHEON\HAWKER 800XP SERIES |
AD 00-NM-48 | PREVENT THE FIRE WARNING FROM TERMINATING PREMATURELY\AIRBUS INDUSTRIE\A310-200\A310-200ADV\A310-221\A310-222\A310-300 |
AD 00-NM-49 | PREVENT OPENING OF THE CARGO DOOR WHILE THE AIRPLANE IS IN FLIGHT\MCDONNELL DOUGLAS CORP |
AD 00-NM-50 | PREVENT IN-FLIGHT LOSS OF INBOARD AND OUTBOARD FLAP ASSEMBLIES DUE TO FAILURE OF H-11 ATTACHING BOLTS\MCDONNELL DOUGLA |
AD 00-NM-52 | PREVENT ELECTRICAL ARCING BETWEEN THE OXYGEN TUBING AND AN ELECTRICAL SOURCE WHICH COULD RESULT IN AN OXYGEN FIRE\LEAR |
AD 00-NM-55 | PREVENT IGNITION SOURCES AND CONSEQUENT FIRE/EXPLOSION IN THE FUEL TANK\AIRBUS INDUSTRIE\A319-131\A319-132\A320-111\A3 |
AD 00-NM-56 | PREVENT FAILURE OF THE OVERWING EMERGENCY EXITS TO OPEN\DASSAULT AVI PARIS FRANCE (SEE AVIONS MARCEL DASSAULT A M D )\ |
AD 00-NM-57 | PREVENT FATIGUE CRACKING OF THE INTERNAL DOUBLERS AND FRAME STRUCTURE OF THE FUSELAGE SKIN OF THE COCKPIT ENCLOSURE WI |
AD 00-NM-60 | PREVENT AN ASYMMETRIC BRAKING CONDITION AND A LONGER STOPPING DISTANCE DUE TO SUDDEN LOSS OF NORMAL BRAKING TO THE LEF |
AD 00-NM-62 | DETECT AND CORRECT EXCESS BACKLASH OF THE SPHERICAL BEARING OF THE ACTIVE AILERON SERVO-CONTROLS\AIRBUS INDUSTRIE\A330 |
AD 00-NM-63 | PREVENT JAMMING OF THE ROLL CONTROL SYSTEM (AILERONS AND SPOILERS)\CESSNA\750 |
AD 00-NM-64 | DETECT AND CORRECT EXCESSIVE PLAY OF THE EYE-END OF THE PISTON ROD OF THE ELEVATOR SERVO-CONTROLS\AIRBUS INDUSTRIE\A33 |
AD 00-NM-65 | PREVENT JAMMING OF THE WHEEL/TIRE ASSEMBLY\CESSNA\500\501\550\551 |
AD 00-NM-66 | PREVENT AN INOPERATIVE BACKUP FLIGHT IDLE STOP SYSTEM\EMPRESA BRASILEIRA DE AERONAUTICA S A\EMB-120 SERIES |
AD 00-NM-68 | PREVENT FAILURE OF THE MAIN FITTING OF THE MAIN LANDING GEAR (MLG)\BOMBARDIER INC (FORMERLY CANADAIR LTD)\CL-600-2B19 |
AD 00-NM-69 | PREVENT UNWANTED DEPLOYMENT OF A THRUST REVERSER\MCDONNELL DOUGLAS CORP\DC-10-10F\DC-10-10\DC-10-15\DC-10-30F (KC-10A) |
