Popular Standards |
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AD 97-02-18 | CORROSION OF THE ANTENNA MOUNTING REINFORCING PLATES AND SURROUNDING SKIN\BRITISH AEROSPC (ENGLAND)\ATP |
AD 97-02-19 | RUNAWAY OF THE AUTOTHROTTLE\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIES\757-300 SERIES\767-200 SERIES\7 |
AD 97-02-21 | CRACKING OF WING RIB-TO-SKIN SUPPORT BRACKETS\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-120 |
AD 97-03-01 | RESULTS OF HEAT GENERATED BY THE ENGINES' RIGHT-HAND EXHAUST STACKS\RAYTHEON AIRCRFT CO\1900D |
AD 97-03-02 | SAILPLANE FLUTTER\GLASFLUGEL\CLUB LIBELLE 205\H 301 LIBELLE\H 301B LIBELLE\KESTREL\STANDARD LIBELLE-201B\STANDARD LIBE |
AD 97-03-06 | APU FIRE DUE TO ECB MALFUNCTION\AUXILIARY POWER INTERNATIONAL CORP\AUXILIARY POWER UNITS |
AD 97-03-08 | FATIGUE CRACKING OF THE DRAG BRACE OF THE LEFT AND RIGHT MLG\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4101 |
AD 97-03-09 | BACKLASH IN THE ELEVATOR CONTROLS AND REDUCED ELEVATOR CONTROL AUTHORITY IN THE MANUAL MODE\FOKKER SVCS\F.28 MARK 0100 |
AD 97-03-11 | FLAME, FUEL, AND VAPOR FROM ENTERING COMPARTMENTS BEHIND FIREZONE COMPARTMENT\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-03-12 | OVERHEATING OF THE ELECTRICAL GROUND POSTS ('EARTH POSTS')\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4101 |
AD 97-03-13 | SETTINGS FOR THE RUDDER PEDALS RESTRICTING MOVEMENT OF THE RUDDER TO ITS MAXIMUM CERTIFIED DEFLECTION\CONSTRUCCIONES A |
AD 97-03-14 | FATIGUE CRACKING OR FRACTURING OF THE PULLEY BRACKETS\BOEING CO\737-300 SERIES |
AD 97-03-16 | FUEL LEAKING FROM THE FUEL PIPE COUPLING\MCDONNELL DOUGLAS CORP\MD-11F\MD-11 |
AD 97-03-18 | LOSS OF BRAKE EFFECTIVENESS\SAAB AIRCRFT AB\SAAB 2000\SAAB 340B\SAAB SF340A |
AD 97-03-19 | FAILURE OF THE ESCAPE SLIDE TO DEPLOY\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B SERIES\747 |
AD 97-04-01 | JAMMING OF THE AILERON CONTROL SYSTEM DURING FLIGHT\BOEING CO\737-100 SERIES\737-200 SERIES\737-200C SERIES\737-300 SE |
AD 97-04-03 | FATIGUE CRACKING AND SUBSEQUENT UNCONTAINED FAILURE OF A FIRST STAGE LPT SEAL PLATE\ALLIEDSIGNAL INC\TFE731-2A\TFE731- |
AD 97-04-04 | TURBINE SHROUD FRAGMENTS EXITING THE APU AND PUNCTURING THE APU COMPARTMENT\ALLIEDSIGNAL INC\GTCP85 SERIES |
AD 97-04-05 | DETACHMENT OF COMPONENT PARTS THAT COULD LODGE IN AND JAM THE ELEVATOR CONTROL\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4 |
AD 97-04-06 | LOOSENING OR LOSS OF THE ATTACHMENT SCREWS\DORNIER LUFTFAHRT GMBH\328-100 |
AD 97-04-07 | DISBONDING\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL B4-600R SERIES\A300 MODEL F4-600R SERIES\A310 MODEL 20 |
AD 97-04-08 | FATIGUE CRACKING IN DRAG STAY UNIT OF THE MLG\FOKKER SVCS\F27 MARK 050\F27 MARK 100\F27 MARK 200\F27 MARK 300\F27 MARK |
AD 97-04-10 | FLIGHT CREW'S ABILITY TO CONTINUE TO CONTROL THE AIRPLANE MANUALLY IF THE AUTOPILOT OR AUTOTHROTTLE FUNCTION FAILS TO |
AD 97-04-11 | FATIGUE FAILURE OF A TAIL LANDING GEAR SPRING\AIR TRACTOR INC\AT-802A\AT-802 |
AD 97-04-13 | INABILITY OF BOTH ENGINES TO UTILIZE THE ENTIRE FUEL SUPPLY\MITSUBISHI HEAVY IND LTD\MU-2B-10\MU-2B-15\MU-2B-20\MU-2B- |
AD 97-04-14 | SELF-ACTIVATION OF THE STICK PUSHER/SHAKER TEST FUNCTION\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE)\AT |
AD 97-04-15 | ELECTRICAL SHORTING OF THE PINS OF THE FIRE EXTINGUISHER BOTTLE CARTRIDGE\PACIFIC SCIENTIFIC CO\FIRE EXTINGUISHER BOTT |
AD 98-07-03 | FATIGUE FAILURE OF THE TAIL ROTOR YOKE (YOKE)\AGUSTA S P A\AB412 EP\AB412\BELL HELICPTR TEXTRON\412CF\412EP\412 |
AD 98-07-04 | CHAFING OF ENGINE CONTROL CABLES\DORNIER LUFTFAHRT GMBH\328-100 |
AD 98-07-05 | COLLAPSE OF THE MAIN LANDING GEAR (MLG) DUE TO FATIGUE CRACKING OF THE MLG TRUNNION FITTINGS\SAAB AIRCRFT AB\SAAB 2000 |
AD 98-07-06 | REDUCED STRUCTURAL INTEGRITY OF THE STABILIZER ATTACHMENT BRACKETS DUE TO CORROSION\BRITISH AEROSPC (ENGLAND)\AVRO 146 |
AD 98-07-07 | HIGH VOLUME FUEL LEAKS AND REPORTED FUEL COLLECTION INSIDE THE ENGINE NACELLE\ROLLS-ROYCE PLC\RB211-535E4-37\RB211-535 |
AD 98-07-08 | OVERHEATING OF THE ELECTRICAL HEATING BLANKETS\ISRAEL AIRCRFT IND LTD\1125 WESTWIND ASTRA\ASTRA SPX |
AD 98-07-09 | FAILURE OF THE STABILIZER BAR DAMPER LINK ASSEMBLY\BELL HELICPTR TEXTRON\47B\47B3\47D\47D1\47G\47G-2\47G-2A\47G-2A-1\4 |
AD 98-07-10 | INCREASED VIBRATION LEVELS, DAMAGE TO THE TAIL ROTOR DRIVE SYSTEM OR TAIL ROTOR ASSEMBLY, AND SUBSEQUENT LOSS OF CONTR |
AD 98-07-11 | FAILURE OF A MAIN ROTOR TIE-BAR (TIE-BAR), LOSS OF A MAIN ROTOR BLADE, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTE |
AD 98-07-12 | STRUCTURAL DAMAGE TO THE HORIZONTAL OR VERTICAL STABILIZER\DORNIER LUFTFAHRT GMBH\328-100 |
AD 98-07-13 | WIRES IN THE AREA ABOVE THE MAIN PASSENGER DOOR FROM BECOMING WORN OR BREAKING\BOEING CO\767-200 SERIES\767-300 SERIES |
AD 98-07-14 | POWER LEVERS BEING POSITIONED BELOW THE FLIGHT IDLE STOP WHILE THE AIRPLANE IS IN FLIGHT\DORNIER LUFTFAHRT GMBH\328-10 |
AD 98-07-15 | FATIGUE CRACKING IN THE INTERNAL SKIN DOUBLERS\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B S |
AD 98-07-16 | ADVERSELY AFFECTED OPERATION OF THE FUSE\BOEING CO\737-300 SERIES\737-400 SERIES\737-500 SERIES |
AD 98-07-17 | FAILURE OF A FLAP SYSTEM CABLE CAUSED BY FATIGUE\TWIN COMMANDER AIRCRFT CORP\500-A\500-B\500-S\500-U\500\520\560-A\560 |
AD 98-07-18 | IMPROPER OPERATION OF THE PROPELLER DE-ICING CONTROLLER CAUSED BY ELECTROMAGNETIC INTERFERENCE (EMI)\PILATUS AIRCRFT L |
AD 98-07-19 | BUCKLING OF THE TAIL ROTOR CONTROL ROD ASSEMBLY (ROD ASSEMBLY)\MD HELICPTR INC\369FF\369F |
AD 98-07-20 | DAMAGE TO THE TAIL ROTOR BLADES\EUROCOPTER FRANCE\AS332C\AS332L1\AS332L |
AD 98-07-21 | DISPLACEMENT OF THE ENGINE TAILPIPES\LOCKHEED-GEORGIA CORP\1329-23A\1329-23D (JETSTAR)\1329-23E\1329-25 |
AD 98-07-22 | POWER LEVERS BEING POSITIONED BELOW THE FLIGHT IDLE STOP WHILE THE AIRPLANE IS IN FLIGHT\BRITISH AEROSPC (ENGLAND)\HS |
AD 98-07-23 | SIGNIFICANT THRUST LOSS DURING INITIAL CLIMB\AIRBUS INDUSTRIE\A340-211\A340-212\A340-213\A340-311\A340-312\A340-313 |
AD 98-07-24 | FATIGUE CRACKING IN THE VERTICAL SUPPORT BEAM THAT SUPPORTS THE ACTUATOR ATTACHMENT FITTING OF THE CENTER LANDING GEAR |
AD 98-07-25 | INTERFERENCE BETWEEN THE RUDDER HORN AND THE VERTICAL STABILIZER\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROSPAT |
AD 98-07-26 | ARCING BETWEEN EXPOSED CONDUCTORS\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 98-08-02 | REPLACEMENT OR OVERHAUL OF CERTAIN UNIVERSAL JOINTS AND BEARINGS OF THE FLAP TRANSMISSION THAT HAVE REACHED THEIR MAXI |
AD 98-08-03 | STRUCTURAL FAILURE OF THE HORIZONTAL STABILIZER\STEMME GMBH & CO KG\STEMME S10-V\STEMME S10 |
AD 98-08-04 | FAILURE OF THE LANDING GEAR CAUSED BY AN INSUFFICIENT WIRE DIAMETER OF THE ROD SPRINGS\AERMACCHI S P A\S.208A\S.208 |
AD 98-08-05 | MAIN LANDING GEAR (MLG) FAILURE\INDUSTRIE AERONAUTICHE E MECCANICHE\P-180 |
AD 98-08-06 | CRACKED FLIGHT CONTROL CABLES\AERMACCHI S P A\S.205 - 18/F\S.205 - 18/R\S.205 - 20/F\S.205 - 20/R\S.205 - 22/R\S.208A\ |
AD 98-08-08 | FATIGUE CRACKING IN THE SKIN OF THE FUSELAGE\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE)\ATR42-500 |
AD 98-08-10 | POWER LEVERS POSITIONED BELOW THE FLIGHT IDLE STOP WHILE THE AIRPLANE IS IN FLIGHT\SAAB AIRCRFT AB\SAAB 2000 |
AD 98-08-13 | FAILURE OF A SPIDER ARM, LOSS OF CONTROL OF THE TAIL ROTOR BLADE, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\EUR |
AD 98-08-16 | INCREASED BRAKING DISTANCE FOR LANDINGS THAT REQUIRE THE FLIGHT IDLE STOP OVERRIDE\SAAB AIRCRFT AB\SAAB 340B\SAAB SF34 |
AD 98-08-17 | POWER LEVERS BEING POSITIONED BELOW THE FLIGHT IDLE STOP WHILE THE AIRPLANE IS IN FLIGHT\TRACOR FLIGHT SYSTEMS INC\240 |
AD 98-08-18 | FAILURE OF THE ELEVATOR BUNGEE SPRING\PIPER AIRCRFT INC NEW\PA-31-300\PA-31-325\PA-31-350\PA-31P\PA-31 |
AD 98-08-19 | CRACKS AT THE WING TO FUSELAGE ATTACH POINTS\TWIN COMMANDER AIRCRFT CORP\500-A\500-B\500-S\500-U\500\520\560-A\560-E\5 |
AD 98-08-20 | SERVO ACTUATOR ROLL PINS BECOMING LOOSE; FALLING OUT; BECOMING LODGED IN THE OUTPUT SHAFT CLUTCH MECHANISM; AND PREVEN |
AD 98-08-21 | STRUCTURAL FAILURE OF THE WING REAR ATTACHMENT FITTINGS CAUSED BY CRACKS IN THIS AREA\SOCATA - GROUPE AEROSPATIALE\TB |
AD 98-08-22 | FAILURE OF THE ELEVATOR AND RUDDER ATTACHMENT BRACKETS BECAUSE OF CRACKS OR CORROSION DAMAGE\PILATUS AIRCRFT LTD\PC-7 |
AD 98-08-25-R1 | R1 PREVENT THE NOSE LANDING GEAR (NLG) FROM COLLAPSING DUE TO FAILURE OF A DRAG LINK BOLT\TWIN COMMANDER AIRCRFT |
AD 99-12-06 | PREVENT VHF NAVIGATION RECEIVER INTERFERENCE FROM FREQUENCY MODULATION (FM) RADIO STATION BROADCAST FREQUENCIES\ALLIED |
AD 99-12-07 | PREVENT FAILURE OF THE OXYGEN MASK LANYARD PIN TO AUTOMATICALLY PULL AND INITIATE OXYGEN FLOW DURING A LOSS OF AIRPLAN |
AD 99-12-08 | PREVENT OPENING OR LOSS OF THE CARGO DOOR DURING FLIGHT\BOEING CO\737-200C SERIES |
AD 99-12-52 | PREVENT FUEL TANK EXPLOSION RESULTING FROM ARC-THROUGH OF THE FUEL BOOST PUMP WIRING CONDUITS\BOEING CO\727 SERIES\727 |
AD 99-13-01 | PREVENT FAILURE OF THE HIGH PRESSURE TURBINE (HPT) HARDWARE DUE TO IGNITION OF OIL TRAPPED BY THE HPT STAGE 1 INNER RO |
AD 99-13-02 | PREVENT POWER LOSS DUE TO FUEL STARVATION\EUROCOPTER FRANCE\AS332C\AS332L1\AS332L2\AS332L |
AD 99-13-03 | PREVENT USE OF A COLLECTIVE IDLER LINK (LINK) OR COLLECTIVE LEVER (LEVER) BEYOND ITS RETIREMENT LIFE\BELL HELICPTR TEX |
AD 99-13-04 | DETECT AND CORRECT LOOSE AILERON CONTROL BELLCRANK STOP BOLTS\CESSNA AIRCRFT CO\206H\T206H |
AD 99-13-05 | DETECT AND CORRECT FATIGUE CRACKING OF THE OUTBOARD SUPPORT OF THE FLAPERON\BOEING CO\777-200 SERIES\777-300 SERIES |
AD 99-13-07 | DETECT AND CORRECT FATIGUE CRACKING OF THE MLG SHOCK STRUT PISTONS\MCDONNELL DOUGLAS CORP\DC-9-81\DC-9-82\DC-9-83\DC-9 |
AD 99-13-08-R1 | R1 PREVENT FATIGUE CRACKING IN THE WEB OF THE REAR SPAR OF THE WING, WHICH COULD RESULT IN FAILURE OF THE REAR S |
AD 99-13-09 | PREVENT FAILURE OF THE FORK ASSEMBLY, P/N 369D21701-21\MD HELICPTR INC\369D\369E |
AD 99-13-10 | PREVENT INTERMITTENT HYDRAULIC PRESSURE TO THE FLIGHT CONTROLS\BELL HELICPTR TEXTRON\206L-4 |
AD 99-13-11 | PREVENT FUEL LEAKS FROM THE AUXILIARY FUEL TANK SUMP DRAIN\ROBINSON HELICPTR CO\R44 |
AD 99-13-12 | DETECT A CRACK IN THE TAILBOOM SKIN AND TO PREVENT SEPARATION OF THE TAILBOOM FROM THE HELICOPTER\BELL HELICPTR TEXTRO |
AD 99-14-02 | PREVENT STRUCTURAL FAILURE OF THE WING ATTACHMENTS CAUSED BY THE CURRENT DESIGN CONFIGURATION\LET AERONTCL WORKS\L33 S |
AD 99-14-03 | PREVENT DIRECTIONAL DEVIATION ON THE STANDBY MAGNETIC COMPASS CAUSED BY MODIFICATIONS MADE TO THE AIRPLANE SINCE MANUF |
AD 99-14-04 | DETECT AND REPAIR CRACKING OF THE E-42 SATCOM RACK AND ITS SUPPORTING STRUCTURE\BOEING CO\747-300 SERIES\747-400 SERIE |
AD 99-14-05 | PREVENT CORROSION AND POSSIBLE CRACKING OF THE ALUMINUM RIBS AND BRACKETS OF THE TRAILING EDGES ON THE EMPENNAGE\BOEIN |
AD 99-14-06 | PREVENT BLADE ROOT LAG SCREW BREAKAGE\MT-PROPELLER ENTWICKLUNG GMBH\MTV-9-B |
AD 99-14-07 | PREVENT JAMMING OF THE FLAP JACKSCREWS\DASSAULT-AVI\FALCON 2000\FALCON 900EX\MYSTERE-FALCON 900 |
AD 99-14-08 | PREVENT AN UNCONTAINED FAILURE OF THE SIXTH STAGE LOW PRESSURE TURBINE (LPT) INNER AIRSEAL\PRATT & WHITNEY DIV\JT9D-59 |
AD 99-15-01 | UNCONTAINED DISK FAILURE\PRATT & WHITNEY DIV\PW4056\PW4152\PW4156A\PW4164\PW4168\PW4460 |
AD 99-15-02 | CCOC RUPTURE DUE TO CRACKING\PRATT & WHITNEY DIV\JT9D-20J\JT9D-20\JT9D-3A\JT9D-7AH\JT9D-7A\JT9D-7F\JT9D-7H\JT9D-7J\JT9 |
AD 99-15-03 | PREVENT THE WASTEGATE CONTROL FROM MALFUNCTIONING BECAUSE OF HEAT DAMAGE\STEMME GMBH & CO KG\STEMME S10-VT |
AD 99-15-04-R1 | R1 DETECT AND CORRECT IMPROPERLY CALIBRATED TURBINE INLET TEMPERATURE INDICATORS OR DEFECTIVE TURBINE INLET TEMP |
AD 99-15-06 | PREVENT UNCOMMANDED REDUCTION OF ENGINE THRUST AND LOSS OF THRUST CONTROL IN ICING CONDITIONS\ALLIEDSIGNAL INC\ALF502R |
AD 99-15-07 | DETECT AND CORRECT CRACKING OF THE REAR FUSELAGE BULKHEAD AT STATION 228\DE HAVILLAND INC (CANADA)\DHC-2 MK.III\DHC-2 |
AD 99-15-09 | PREVENT LOSS OF CONTROLLABILITY OF THE AIRPLANE DUE TO EXCESSIVE FREEPLAY IN THE ELEVATOR TAB OR A FREE TAB\BOEING CO\ |
AD 99-15-10 | PREVENT FAILURE OF AN ENGINE-DRIVEN PUMP (EDP) SUPPLY SHUTOFF VALVE\BOEING CO\777-200 SERIES\777-300 SERIES |
AD 99-15-11 | PREVENT THE INABILITY TO STEER THE AIRPLANE BECAUSE OF WEAR IN THE NOSE LANDING GEAR STEERING SELECTOR DIFFERENTIAL\BR |
AD 99-15-12 | DETECT LOOSENESS OR GAP OF THE PRESS FIT BUSHING INSTALLATION OF THE ACTUATION FITTINGS OF THE AILERON TRIM TABS\SAAB |
AD 99-15-13 | PREVENT FAILURE OF THE INTERNAL COOLING SYSTEM AIR FAN CAUSED BY A CERTAIN DESIGN CONFIGURATION OF THE IMPELLER\ALEXAN |
AD 99-15-14 | PREVENT FAILURE OF THE PLATE DUE TO FATIGUE CRACKING\BLUE BIRD HELICPTR\CH-54B |
AD 99-16-01 | DETECT AND CORRECT CRACKING OF THE REAR SPAR OF THE WING\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL B4-600R |
AD 99-16-02 | DETECT AND CORRECT FATIGUE CRACKING OF THE AIRPLANE FUSELAGE\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 4 |
AD 99-16-03 | PREVENT UNDETECTED ACCRETION OF ICE ON THE LEADING EDGE OF THE HORIZONTAL STABILIZER\LEARJET INC\23\24A\24B-A\24B\24C\ |
AD 99-16-04 | DETECT AND CORRECT CRACKING IN THE WING TO FUSELAGE FRAME-ANGLES\BOMBARDIER INC\CL-215-1A10\CL-215-6B11 (CL-215T VARIA |
AD 99-16-05 | DETECT AND CORRECT EXCESSIVE WEAR ON THE AILERON CONTROL CABLES, CABLE GUIDES, AND CABLE PULLEYS LOCATED AT THE REAR W |
AD 99-16-06 | PREVENT THE POTENTIAL FOR FAILURE OF THE WING ATTACH FITTINGS CAUSED BY THE UTILIZATION OF SUBSTANDARD MATERIAL\PIPER |
AD 97-04-16 | REDUCTION IN THE TORQUE VALUE OF THE BOLT IN THE WALTER KIDDE NOSE WHEEL STEERING SYSTEM\FOKKER SVCS\F27 MARK 050\F27 |
AD 97-04-17 | LEAKAGE OF HYDRAULIC FLUID FROM THE LOCK JACK ASSEMBLIES OF THE MAIN LANDING GEAR (MLG)\BRITISH AEROSPC (ENGLAND)\AVRO |
AD 97-04-18 | FATIGUE-RELATED CRACKING OF STRINGERS OF THE LOWER SKIN OF THE WINGS\FOKKER SVCS\F27 MARK 100\F27 MARK 200\F27 MARK 30 |
AD 97-04-19 | DISCONNECT UNIT OPENING INADVERTENTLY\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-05-02 | BINDING OF THE AILERON\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-120ER\EMB-120RT\EMB-120 |
AD 97-05-03-R1 | R1 PREVENT DEVIATION FROM AN INTENDED FLIGHT PATH DURING A NON-PRECISION APPROACH TO AN AIRPORT CAUSED BY INACCU |
AD 97-05-04 | LOSS OF THE STANDBY EMERGENCY GENERATION SYSTEM\AIRBUS INDUSTRIE\A320 MODEL -111\A320 MODEL -211\A320 MODEL -212\A320 |
AD 97-05-05 | FAILURE OF THE DIAGONAL BRACES THAT CONNECT THE LEFT AND RIGHT WINGS TO THE FUSELAGE\DORNIER LUFTFAHRT GMBH\328-100 |
AD 97-05-06 | FAILURE OF THE MAIN ROTOR THRUST BEARING (BEARING) AND LOSS OF THE MAIN ROTOR\SCHWEIZER AIRCRFT CORP\269A-1\269A\269B |
AD 97-05-07 | MAINTAINING ADEQUATE THRUST DECAY CHARACTERISTICS IN THE EVENT OF CRITICAL ENGINE FAILURE DURING TAKEOFF\LOCKHEED MART |
AD 97-05-08 | FATIGUE CRACKING\BOEING CO\727 SERIES\727-100 SERIES\727-100C SERIES\727-200 SERIES\727-200F SERIES\727C SERIES |
AD 97-05-09 | PREVENTION OF REDUCED ROLL AND/OR PITCH RATE CONTROL OF THE AILEROND\BOEING CO\737-100 SERIES\737-200 SERIES\737-200C |
AD 97-05-10 | CRACKING AND SEIZING OF THE INTERNAL SUMMING LEVER ASSEMBLY BEARING OF THE MAIN RUDDER POWER CONTROL UNIT (PCU)\BOEING |
AD 97-06-02 | FATIGUE FAILURE OF THE SPIDER\BELL HELICPTR TEXTRON\214B-1\214B\214ST |
AD 97-06-03 | FATIGUE FAILURE OF THE MAST\BELL HELICPTR TEXTRON\214ST |
AD 97-06-04 | FATIGUE CRACKING OF THE LOWER SPAR CHORD\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIES |
AD 97-06-05 | NOSE LANDING GEAR FAILURE\AVIONS PIERRE ROBIN\R2160 |
AD 97-06-06 | INADVERTENT MOVEMENT OF THE PILOT OR COPILOT CHAIR\RAYTHEON AIRCRFT CO\100\1900\1900C\1900D\200\200C\200CT\200T\65-90\ |
AD 97-06-07-R1 | R1 PREVENT FAILURE OF THE ANCHOR POINT FASTENERS ON THE SEAT RESTRAINING SYSTEM, WHICH COULD RESULT IN RELEASE O |
AD 97-06-09 | STICKING CONDITIONS IN THE RUDDER TRIM SWITCH\BOEING CO\737-300 SERIES\737-400 SERIES\737-500 SERIES |
AD 97-06-10 | MLG FAILURE BECAUSE OF A CRACKED 'A' FRAME ASSEMBLY\RAYTHEON AIRCRFT CO\76 |
AD 97-06-11 | FAILURE OF THE RUDDERVATOR DIFFERENTIAL TAIL CONTROL ROD ASSEMBLY\RAYTHEON AIRCRFT CO\H35\J35\K35\M35\N35\P35\S35\V35\ |
AD 97-06-12 | FAILURE OF THE MAIN FITTING\BRITISH AEROSPC (ENGLAND)\AVRO 146-RJ100A\AVRO 146-RJ70A\AVRO 146-RJ85A\BAE 146-100A\BAE 1 |
AD 97-06-13 | LOSS OF OIL\ROLLS-ROYCE PLC\RB211-TRENT 875-17\RB211-TRENT 877-17\RB211-TRENT 884-17\RB211-TRENT 892-17\RB211-TRENT-89 |
AD 97-06-15 | HPC STAGE 1 ROTOR DISK RUPTURE, ENGINE FAILURE, AND DAMAGE TO THE AIRCRAFT\GENERAL ELECTRIC AIRCRFT ENGINES\CF34-1A\CF |
AD 97-06-16 | PROPELLER SEPARATION\MCCAULEY PROPELLER SYSTEMS\1A103/TCM |
AD 97-07-01 | WATER ACCUMULATING IN THE AIR DATA/INERTIAL REFERENCE UNIT (ADIRU) TRAYS OF THE AVIONICS RACKS\AIRBUS INDUSTRIE\A330-3 |
AD 97-07-02 | FATIGUE CRACKING OF THE REAR PRESSURE BULKHEAD\AIRBUS INDUSTRIE\A300 MODEL B2-1A\A300 MODEL B2-1C\A300 MODEL B2-203\A3 |
AD 97-07-03 | FAILURE OF THE NOSE WHEEL\PIPER AIRCRFT INC NEW\PA-31-300\PA-31-325\PA-31-350\PA-31P\PA-31 |
AD 97-07-04 | ENGINE COMBUSTOR LINER DETERIORATION DUE TO THERMAL FATIGUE\ROLLS-ROYCE PLC\RB211-524G2-19\RB211-524G2-T-19\RB211-524G |
AD 97-07-05 | N2 ACCESSORY DRIVE ASSEMBLY DISENGAGEMENT\ALLIEDSIGNAL INC\T5307A\T5309A\T5309B\T5309C\T5311A\T5311B\T5313B\T5317A-1\T |
AD 97-07-06 | FAILURE OF THE STEEL SWASHPLATE SUPPORT ASSEMBLY\BELL HELICPTR TEXTRON\412 |
AD 97-07-08 | FAILURE OF THE FRONT BULKHEAD OF THE AFT MAIN BAGGAGE BAY AND THE DOORS OF THE AFT RIGHT STOWAGE COMPARTMENT\JETSTREAM |
AD 97-07-10-R1 | R1 FAILURE OF THE WING STRUTS\BOMBARDIER INC\DHC-6-1\DHC-6-100\DHC-6-200\DHC-6-300 |
AD 97-07-11 | FAILURE OF THE NLG\BRITISH AEROSPC (SCOTLAND)\H.P. 137 JETSTREAM MK. 1\JETSTEAM SERIES 200\JETSTREAM 3201\JETSTREAM SE |
AD 97-07-12 | WRONG ENGINE-DRIVEN GENERATOR SHUTTING DOWN UNNECESSARILY IN THE EVENT OF AN ENGINE FIRE WARNING\MCDONNELL DOUGLAS COR |
AD 97-07-13 | FATIGUE CAUSING THE CENTER WING ATTACHMENT RODS TO FAIL\CONSTRUCCIONES AERONAUTICAS S A\CN-235-100\CN-235-200\CN-235 |
AD 97-07-14 | FATIGUE CRACKING IN THE RIB FLANGE OF THE FRONT SPAR SIDE OF THE WING CENTER SECTION\AIRBUS INDUSTRIE\A320 MODEL -111\ |
AD 97-08-01 | LOW CYCLE FATIGUE (LCF) FAILURE OF THE FAN DISK\CFM INTNL S A\CFM56-3\CFM56-3B\CFM56-3C |
AD 97-08-02-R1 | R1 CORROSION IN THE ELEVATOR CAUSED BY WATER ENTERING THE ELEVATOR CONTROL ROD\SCHEMPP-HIRTH FLUGZEUGBAU GMGH\DI |
AD 97-08-03 | FAULTY PRESSURE REDUCING VALVE IN THE CARGO FIRE EXTINGUISHING SYSTEM\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 M |
AD 97-08-05 | SWITCHES IN THE CABIN ATTENDANT'S PANEL THAT COULD SHORT CIRCUIT WHEN THEY FAIL\BOEING CO\747-100 SERIES\747-100B SUD |
AD 97-08-06-R1 | R1 QUICK CONNECTORS BECOMING INADVERTENTLY DISCONNECTED\L'HOTELLIER LOUIS\QUICK CONNECTORS |
AD 97-08-07 | FAILURE OF THE FLUORESCENT LIGHT BALLAST AND CONSEQUENT FAILURE OF THE DUST BARRIERS\MCDONNELL DOUGLAS CORP\DC-9-81\DC |
AD 97-08-08 | FATIGUE CRACKING IN THE BOLTS\BOEING CO\777-200 SERIES |
AD 97-08-51 | SEPARATION OF THE OUTBOARD TRAILING EDGE FLAP\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 97-09-02 | THE HIGH PRESSURE TURBINE ROTOR (HPTR) FRONT SHAFT, HPTR FRONT AIR SEAL, HPTR DISK, BOOSTER SPOOL, AND LOW PRESSURE TU |
AD 97-09-03 | CHAFING OF WIRE BUNDLES\AIRBUS INDUSTRIE\A310 MODEL 200 SERIES\A310 MODEL 300 SERIES\A310 MODEL 325 |
AD 97-09-05 | INADEQUATE VENTING OF CABIN PRESSURE\RAYTHEON AIRCRFT CO\BAE.125 SERIES 1000A\HAWKER 1000 |
AD 97-09-06 | CHAFING OF THE TUBES OF THE FIRE EXTINGUISHING AND SMOKE DETECTION SYSTEMS\BOEING CO\757-200 SERIES\757-200CB SERIES\7 |
AD 97-09-07 | CRACKING OF THE SUPPORT BRACKETS\MCDONNELL DOUGLAS CORP\MD-11F\MD-11 |
AD 97-09-08 | FAILURE OF THE PILOT'S AND CO-PILOT'S CONTROL WHEELS\AEROSPC TECHNOLOGIES OF AUSTRALIA PTY LTD\N22B\N22S\N24A |
AD 97-09-09 | STRUCTURAL CRACKING TO THE CABIN CAUSED BY MISSING RIVETS\RAYTHEON AIRCRFT CO\58PA\58P |
AD 97-09-10 | STANDBY ELEVATOR CONTROL SYSTEM\BRITISH AEROSPC (ENGLAND)\ATP |
AD 97-09-11 | INADVERTENT OPENING OF THE PASSENGER/CREW DOOR DURING UNPRESSURIZED FLIGHT\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELL |
AD 97-09-13 | CORROSION AND CONSEQUENT FATIGUE CRACKING OF THE UPPER DECK FLOOR BEAM AT STATION 980\BOEING CO\747-300 SERIES\747-400 |
AD 97-09-15-R1 | R1 PREVENT SUDDEN UNCOMMANDED YAWING OF THE AIRPLANE DUE TO POTENTIAL FAILURES WITHIN THE YAW DAMPER SYSTEM\BOEI |
AD 97-10-01 | FAILURE OF THE FLAP TRANSMISSION SHAFT DUE TO DAMAGED STEADY BEARING ASSEMBLIES\AIRBUS INDUSTRIE\A310 MODEL 200 SERIES |
AD 97-10-02 | CORROSION\BOEING CO\777-200 SERIES\777-300 SERIES |
AD 97-10-03 | CRACKING OF THE ENGINE MOUNTING LUGS\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 97-10-05 | FAILURE OF THE MLG CAUSED BY CRACKS IN THE PINTLE TO CYLINDER INTERFACE AREA\BRITISH AEROSPC (SCOTLAND)\H.P. 137 JETST |
AD 97-10-06 | MOVEMENT OF THE SUPPORT BEAM ATTACHED TO THE FUSELAGE FRAME AT STATION 452.00\ISRAEL AIRCRFT IND LTD\1125 WESTWIND AST |
AD 97-10-07 | IN-FLIGHT UNCOMMANDED ACTIVATION OF THE PROPELLER BRAKE SYSTEM\CONSTRUCCIONES AERONAUTICAS S A\CN-235-100\CN-235-200\C |
AD 97-10-08 | FATIGUE-RELATED CRACKING IN THE GUIDE HOOKS OF THE CARGO DOOR\CONSTRUCCIONES AERONAUTICAS S A\CN-235-100\CN-235-200\CN |
AD 97-10-09 | CRACKING IN FRAME 179 OF THE FUSELAGE\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4101 |
AD 97-10-10 | CRACKING IN THE UPPER FIN AND HORIZONTAL STABILIZER ATTACHMENT FITTINGS\AEROSPC TECHNOLOGIES OF AUSTRALIA PTY LTD\N22B |
AD 97-10-12 | CHAFING OF THE WIRE BUNDLES AND CONSEQUENT INFLIGHT ARCING BEHIND THE AVIONICS CIRCUIT BREAKER\MCDONNELL DOUGLAS CORP\ |
AD 97-10-13 | FAILURE OF THE FLIGHT CONTROL SYSTEM CAUSED BY A CORRODED ELEVATOR TORQUE TUBE\FAIRCHILD AIRCRFT CORP\SA226-AT\SA226-T |
AD 97-10-14 | SEPARATION OF THE STABILONS FROM THE AIRPLANE\RAYTHEON AIRCRFT CO\1900D |
AD 97-10-15 | FAILURE OF THE MAIN GEARBOX SECOND STAGE LOWER PLANETARY PLATE (PLATE) DUE TO FATIGUE CRACKING\ERICKSON AIR-CRANE CO\S |
AD 97-10-16 | SEPARATION OF THE CONTROL ROTOR BLADE ASSEMBLY\HILLER AVI\UH-12A\UH-12B\UH-12C\UH-12D\UH-12\ROGERSON HILLER CORP\UH-12 |
AD 97-11-04 | FATIGUE FAILURE OF THE MAST AND SPLINE PLATE\BELL HELICPTR TEXTRON\412EP\412 |
AD 97-11-05 | CRACKING OF THE FUEL MANIFOLD ASSEMBLY\ALLIEDSIGNAL INC\ALF502L-2A\ALF502L-2C\ALF502L-2\ALF502L-3\ALF502L\ALF502R-3A\A |
AD 97-11-06 | FAN BLADE FAILURE AND SEPARATION AT THE ROOT SECTION\PRATT & WHITNEY DIV\PW4164\PW4168A\PW4168 |
AD 97-11-07 | STRUCTURAL INTEGRITY OF MODEL MD-90-30 AIRPLANES\MCDONNELL DOUGLAS CORP\MD-90-30 |
AD 97-11-08 | LOSS OF AIRPLANE CONTROLLABILITY, OR ENGINE OVERSPEED\BOMBARDIER INC\CL-215-6B11 (CL-415 VARIANT) |
AD 97-11-09 | LOSS OF AIRPLANE CONTROLLABILITY\BOMBARDIER INC\CL-215-6B11 (CL-215T VARIANT) |
AD 97-11-10 | RESTRICTED OXYGEN FLOW\PURITAN-BENNETT AERO SYSTEMS COMPANY\OXYGEN MASKS |
AD 97-11-11 | STRUCTURAL FAILURE OF THE HORIZONTAL STABILIZER CAUSED BY FATIGUE CRACKS\AEROSPC TECHNOLOGIES OF AUSTRALIA PTY LTD\N22 |
AD 97-11-12 | STRUCTURAL FAILURE OF THE FRONT SPAR CAUSED BY CRACKS IN THE STUB WING UPPER FRONT SPAR CAP FLANGES\AEROSPC TECHNOLOGI |
AD 97-11-13 | FAILURE OF BOTH GENERATORS DURING CRITICAL PHASES OF FLIGHT\FAIRCHILD AIRCRFT CORP\SA226-AT\SA226-T(B)\SA226-TC\SA226- |
AD 97-11-14 | CORROSION OR CRACKING OF MLG A-FRAME FITTINGS\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 97-11-51-R1 | R1 FRACTURE OF THE FIRST STAGE HPT DISK\PRATT & WHITNEY DIV\PW2037M\PW2037\PW2040\PW2043\PW2143\PW2240\PW2337\PW |
AD 97-12-01 | ELECTRICAL ARCING OF THE ALTERNATING CURRENT WIRE AND CONSEQUENT FIRE HAZARD\CESSNA AIRCRFT CO\650 CITATIONS III, CITA |
AD 97-12-02 | PREVENT FAILURE OF THE LINK ASSEMBLY, WHICH COULD RESULT IN LOSS OF CONTROL OF THE HELICOPTER\MD HELICPTR INC\MD-900 |
AD 97-12-04 | INFLIGHT ENGINE POWER LOSS OR SHUTDOWN DUE TO LIBERATED CDP MANIFOLD MATERIAL\GENERAL ELECTRIC AIRCRFT ENGINES\GE90-76 |
AD 97-12-05 | VARIABLE SPEED CONSTANT FREQUENCY (VSCF) GEARSHAFT FLANGE BALL BEARING FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\GE90-7 |
AD 97-12-06 | COWLING RUBBING AGAINST THE GASCOLATOR DRAIN VALVE OR THE TAILPIPE\CESSNA AIRCRFT CO\172 |
AD 97-13-01 | PROPER SWITCHES INSTALLED ON THE FIRE HANDLE PANEL OF THE FIRE HANDLE ASSEMBLY\SAAB AIRCRFT AB\SAAB 2000\SAAB 340B |
AD 97-13-02 | PREVENTING THE PILOT'S SHOE FROM BECOMING JAMMED BETWEEN THE RUDDER PEDAL AND FIREWALL\DIAMOND AIRCRFT IND\DA20-A1 |
AD 97-13-03 | LOSS OF AIRPLANE CONTROLLABILITY OR ENGINE OVERSPEED\FRAKES AVI\G-73 |
AD 97-13-04 | BROKEN OR DEFORMED THRUST REVERSER CONTROL LEVER SPRINGS\AIRBUS INDUSTRIE\A300 MODEL B2-1A\A300 MODEL B2-1C\A300 MODEL |
AD 97-13-05 | FAILURE OF THE LOWER BOLTS THAT JOIN THE DOG-LINKS TO THE PISTON OF THE HORIZONTAL STABILIZER CONTROL UNIT (HSCU)\FOKK |
AD 97-13-07 | PROPELLER BLADE FRACTURE DUE TO A MANUFACTURING DEFECT\HAMILTON STANDARD DIV\54H60 |
AD 97-13-08 | THE SPREAD OF FIRE THROUGH THE ZONES OF EACH NACELLE\BOMBARDIER INC\DHC-8-100 SERIES\DHC-8-300 SERIES |
AD 97-13-10 | OVERSPEED OF THE AFT FAN DISK RESULTING IN AN UNCONTAINED ENGINE FAILURE AND DAMAGE TO THE AIRCRAFT\GENERAL ELECTRIC A |
AD 97-14-01 | FAILURE OF THE LEFT-HAND (LH) RUDDER BAR ASSEMBLY\BRITTEN NORMAN (BEMBRIDGE) LTD\BN2A MK. 111-2\BN2A MK. 111-3\BN2A MK |
AD 97-14-02 | FATIGUE CRACKING OF THE FUSELAGE OUTER SKIN AT FRAMES 28A AND 30A\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL |
AD 97-14-03 | EXCESSIVE RUDDER AUTHORITY\BOEING CO\737-100 SERIES\737-200 SERIES\737-200C SERIES\737-300 SERIES\737-400 SERIES\737-5 |
AD 97-14-04 | UNCOMMANDED MOVEMENTS OF THE RUDDER\BOEING CO\737-100 SERIES\737-200 SERIES\737-200C SERIES\737-300 SERIES\737-400 SER |
AD 97-14-05 | IN-FLIGHT VERTICAL FIN CRACKING\AIR TRACTOR INC\AT-301\AT-302\AT-400A\AT-400\AT-401\AT-402\AT-501\AT-502 |
AD 97-14-07 | POSSIBILITY OF A FIRE IN THE ENGINE HIGH SPEED GEARBOX\LOCKHEED AIRCRFT CORP\L-1011-385-1-14\L-1011-385-1-15\L-1011-38 |
AD 97-14-08 | FAILURE OF THE BRACKETS FOR THE MAIN LANDING GEAR (MLG) UPLOCK BEAM ASSEMBLY\GULFSTREAM AEROSPC CORP\G-159 |
AD 97-14-09 | FAILURE OF THE ELEVATOR TRIM TAB MOUNTING LUGS\GULFSTREAM AEROSPC CORP\G-159 |
AD 97-14-10 | FAILURE OF THE MAIN LANDING GEAR (MLG) RETRACT CYLINDER ATTACHMENT FITTINGS\GULFSTREAM AEROSPC CORP\G-159 |
AD 97-14-13 | EXCESSIVE CHAFE WEAR OF THE ENGINE MOUNT TUBE AND UPPER DIAGONAL TRUSS\GULFSTREAM AEROSPC CORP\G-159 |
AD 97-14-14 | TRIM SYSTEM MALFUNCTION\INDUSTRIE AERONAUTICHE E MECCANICHE\P-180 |
AD 97-15-04 | FATIGUE FAILURE OF THE CARRIER\BELL HELICPTR TEXTRON\214B-1\214B\214ST |
AD 97-15-07 | FAILURE OF THE FORWARD HORIZONTAL STABILIZER BOLT\AEROMOT-INDUSTRIA MECANICO METALURGICA LTDA\AMT-200 (SUPER XIMANGO) |
AD 97-15-08 | FAILURE OF THE TRANSMISSION OUTPUT DRIVE GEAR\MD HELICPTR INC\369D\369E\369FF\369F\500N |
AD 97-15-09 | DETECT AND CORRECT IMPROPERLY INSTALLED/MAINTAINED AUXILIARY POWER UNIT (APU) BATTERY GROUNDS\BOEING CO\757-200 SERIES |
AD 97-15-12 | VIBRATION OF THE RUDDER\BURKHART GROB LUFT-UND\GROB G 109 |
AD 97-15-13-R2 | R2 PREVENT MOISTURE FROM ACCUMULATING AND FREEZING IN THE AIRSTAIR DOOR HANDLE AND LATCH HOUSING\RAYTHEON AIRCRF |
AD 97-15-14 | FATIGUE CRACKS IN THE RUDDER TORQUE TUBE BOTTOM FLANGE ASSEMBLY\INDUSTRIE AERONAUTICHE E MECCANICHE\P-180 |
AD 97-15-15-P | AD 97-15-15 CRACKS IN THE GEAR SHAFT\EUROCOPTER FRANCE\SA-365N1\SA-365N\SA-366G1 |
AD 97-15-17 | LOSS OF THE INTEGRATED HYDRAULIC PACKAGE (IHP) FUNCTION\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-16-02 | FAILURE OF THE SPRAG CLUTCH TO LOCK IN THE DRIVING DIRECTION\ROBINSON HELICPTR CO\R44 |
AD 97-16-03 | AFT-ACTING LANDING GEAR TRUNNION LOADS BEING TRANSFERRED TO THE MAIN LANDING GEAR (MLG) BEAM\BOEING CO\767-200 SERIES\ |
AD 97-16-04 | INCORRECT WIRING OF THE WIRE HARNESS INSTALLATION TO THE FIRE EXTINGUISHER CARTRIDGES IN THE ENGINE NACELLES\SAAB AIRC |
AD 97-16-05 | CORROSION IN THE LOWER SKINS OF THE WING CENTER SECTION\GULFSTREAM AEROSPC CORP\G-159 |
AD 97-16-06 | FATIGUE CRACKING ON THE FORWARD FITTING OF FRAME 47 AT THE LEVEL OF THE LAST FASTENER OF THE EXTERNAL ANGLE FITTING\AI |
AD 97-16-07 | FALSE FIRE WARNING INPUTS OF THE ENGINES AND AUXILIARY POWER UNIT (APU)\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-16-08 | FATIGUE CRACKING OF THE HINGES\FOKKER SVCS\F.28 MARK 0100 |
AD 97-16-09 | UNCOMMANDED APPLICATION OF THE BRAKES DURING LANDING\BRITISH AEROSPC (ENGLAND)\ATP |
AD 97-16-10 | FAILURE OF THE FLIGHT INSTRUMENTS DURING FLIGHT\RAPCO INC\FILTERS |
AD 97-17-02 | LOOSE BUSHING RETAINER NUTS OF THE PIVOT PINS IN THE HORIZONTAL STABILIZER HINGE ASSEMBLY\BOEING CO\777-200 SERIES |
AD 97-17-04 | FAN HUB FAILURE DUE TO TIEROD\PRATT & WHITNEY DIV\JT8D-209\JT8D-217C\JT8D-217\JT8D-219 |
AD 97-17-05 | FLUID LEAKING FROM THE GAS GENERATOR CASE DRAIN PORTS\PRATT & WHITNEY CANADA INC\PW118A\PW118B\PW118\PW119B\PW119C\PW1 |
AD 97-17-06 | SELF-ACTIVATION OF THE VALVES\BELL HELICPTR TEXTRON\214ST |
AD 97-17-07 | POSSIBLE IN-FLIGHT SEPARATION OF THE WING FROM THE AIRPLANE\SKY INTNL INC\S-1S\S-1T\S-2A\S-2B\S-2S\S-2 |
AD 97-17-08 | FATIGUE CRACKING AND FAILURE OF THE PROPELLER MOUNTING BOLTS\RAYTHEON AIRCRFT CO\1900D |
AD 97-18-03 | FAILURE OF THE ULTRASONIC WELD ON THE CONE AND SEAL ASSEMBLY OF THE OXYGEN MASK\PURITAN-BENNETT AERO SYSTEMS COMPANY\O |
AD 97-18-04 | DETECT AND CORRECT FATIGUE CRACKING OF THE MIDSPAR FUSE PINS\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIE |
AD 97-18-05 | DETECT AND CORRECT FATIGUE CRACKING OF THE MIDSPAR FUSE PINS\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIE |
AD 97-18-06 | PREVENT CORROSION IN THE BEARINGS, CABLES, ELECTRICAL CONNECTORS, OR OTHER EQUIPMENT IN THE MAIN WHEEL WELL\BOEING CO\ |
AD 97-18-07 | PREVENT OVERBIAS OR OVERBALANCE OF THE RUDDER\RAYTHEON AIRCRFT CO\BAE.125 SERIES 800A\HAWKER 800XP\HAWKER 800 |
AD 97-18-08 | REDUCE STRUCTURAL INTEGRITY AND POTENTIAL COLLAPSE OF THE MAIN LANDING GEAR DUE TO LOOSE SPHERICAL BEARINGS OF THE DRA |
AD 97-18-10 | PREVENT THE DIRECT CURRENT (DC) POWER DISTRIBUTION SYSTEM FROM SHORT CIRCUITING\BOMBARDIER INC\CL-600-2B19 (REGIONAL J |
AD 97-18-11 | PREVENT IN-FLIGHT FAILURE OF THE TAILBOOM VERTICAL FIN SPAR (VERTICAL FIN SPAR) AND SUBSEQUENT LOSS OF CONTROL OF THE |
AD 97-19-01 | PREVENT DAMAGE TO THE HYDRAULIC TUBES AND ELECTRICAL HARNESSES\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-19-03 | PREVENT THE CAPTAIN AND FIRST OFFICER CREW SEATS FROM SLIDING FREELY ON THE TRACK\BOEING CO\737-100 SERIES\737-200 SER |
AD 97-19-04 | PREVENT CRACKING IN THE FIREWALL OF THE AUXILIARY POWER UNIT\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-145ER |
AD 97-19-05 | TO PREVENT AUXILIARY POWER UNIT (APU) FAILURE\SAAB AIRCRFT AB\SAAB 2000 |
AD 97-19-06 | PREVENT DISBONDING AND SEPARATION OF PORTIONS OF THE BLADE\CARSON HELICPTRS INC\S-61L\SIKORSKY AIRCRFT CORP\S-61A\S-61 |
AD 97-19-07 | TO PREVENT AN ENGINE FLAME-OUT DURING A RAPID THROTTLE REDUCTION\DASSAULT-AVI\FALCON 2000 |
AD 97-19-09 | PREVENT FATIGUE FAILURE OF THE BEARING BOLTS\BELL HELICPTR TEXTRON\214ST |
AD 97-19-10 | FAILURE OF THE PLATE DUE TO FATIGUE CRACKING\ERICKSON AIR-CRANE CO\S-64E |
AD 97-19-11 | DAMAGE TO THE AILERON HINGE FITTINGS DUE TO FAILURE OF THE SHEAR PINS\BOMBARDIER INC\CL-600-2B19 (REGIONAL JET SERIES |
AD 97-19-13 | PREVENT FRACTURE OF THE HIGH PRESSURE TURBINE (HPT) SHAFT\PRATT & WHITNEY DIV\JT8D-209\JT8D-217A\JT8D-217C\JT8D-217\JT |
AD 97-19-15 | GENERATION OF SPARKS AND A POTENTIAL IGNITION SOURCE INSIDE THE FUEL TANK\BOEING CO\767-200 SERIES\767-300 SERIES\767- |
AD 97-19-16-P | AD 97-19-16 UNCONTAINED FAILURE OF THE ENGINE FAN BLADES\FOKKER SVCS\F.28 MARK 0100 |
AD 97-19-17 | PREVENT FATIGUE CRACKING ON SPECIFIC CRITICAL ROTATING PARTS, WHICH COULD RESULT IN FAILURE OF THE PART, CAUSING AN UN |
AD 97-19-18 | PREVENT FIRST STAGE LPC DISK RIM SEPARATION DUE TO LOW CYCLE FATIGUE\ALLIEDSIGNAL INC\TSCP700-4B\TSCP700-5 |
AD 97-20-02 | PREVENT LOSS OF AIRPLANE CONTROLLABILITY OR ENGINE OVERSPEED WITH CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER |
AD 97-20-03 | PREVENT LOSS OF AIRPLANE CONTROLLABILITY, OR ENGINE OVERSPEED AND CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER |
AD 97-20-04 | PREVENT AN ELECTRICAL OVERLOAD AND A FAILURE OF THE VOLTAGE REGULATOR AND OVER-VOLTAGE RELAY, THAT COULD RESULT IN AN |
AD 97-20-05 | PREVENT JAMMING OR RESTRICTING OF THE AILERON CABLE\BRITISH AEROSPC (ENGLAND)\HS 748 SERIES 2A\HS 748 SERIES 2B |
AD 97-20-10-R1 | R1 PREVENT SIMULTANEOUS POWER LOSS TO BOTH ATTITUDE AND HEADING REFERENCE SYSTEMS (AHRS)\BOMBARDIER INC\DHC-8-10 |
AD 97-20-11 | PREVENT THE MLG FROM FAILING TO EXTEND BECAUSE OF CORRODED MLG INBOARD LOCKING HINGES\SOCATA - GROUPE AEROSPATIALE\TBM |
AD 97-20-12 | POSSIBLE HEAT ACCUMULATION\MD HELICPTR INC\MD-900 |
AD 97-20-14 | CHANCE OF ICING-RELATED INCIDENTS OR ACCIDENTS OF THE AFFECTED AIRPLANES DUE TO PILOT ERROR\MITSUBISHI HEAVY IND LTD\M |
AD 97-20-15 | PREVENT CRACKS IN THE HEAD AREA OF THE OUTBOARD TENSION-TORSION (T-T) BAR PIN\HILLER AVI\UH-12A\UH-12B\UH-12C\UH-12D\R |
AD 97-21-01-R1 | R1 PREVENT PROPELLER HUB CRACKS\MT-PROPELLER ENTWICKLUNG GMBH\MTV-3 |
AD 97-21-03 | HEAT DAMAGE TO THE FUEL FEED HOSE ASSEMBLIES OF THE AUXILIARY POWER UNIT (APU)\RAYTHEON AIRCRFT CO\BAE.125 SERIES 800A |
AD 97-21-06 | PREVENT LOSS OF CONTROL OF THE ELEVATOR AND/OR RUDDER, DUE TO FAILURE OF THE ELEVATOR AND/OR RUDDER ASSEMBLIES AS A RE |
AD 97-21-07-R1 | R1 PREVENT ACCESSORY DRIVE CARRIER ASSEMBLY FAILURE\ALLIEDSIGNAL INC\T5313B\T5317A |
AD 97-21-08 | PREVENT COOLING PLATE FRACTURE, WHICH COULD RESULT IN A CONTAINED ENGINE FAILURE AND AN INFLIGHT ENGINE SHUTDOWN\GENER |
AD 97-21-11 | PREVENT STRUCTURAL DAMAGE AND/OR LOSS OF THE RUDDER OR ELEVATORS IF THE AIRPLANE IS OPERATED UNDER ULTIMATE LOAD CONDI |
AD 97-21-12 | PREVENT FATIGUE CRACKING IN THE AREA OF THE CENTER WING-TO-FUSELAGE ATTACHMENT FITTING, WHICH CONSEQUENTLY COULD REDUC |
AD 97-21-13 | PREVENT LOSS OF AIRPLANE CONTROLLABILITY, OR ENGINE OVERSPEED WITH CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER |
AD 97-21-15 | PREVENT POSSIBLE OVERHEATING OF THE ELECTRICAL GENERATOR FEEDER CABLES AND CONSEQUENT DAMAGE, WHICH COULD LEAD TO POSS |
AD 97-22-03 | PREVENT LOSS OF DIRECTIONAL CONTROL CAUSED BY SEAT BELT INTERFERENCE WITH THE REAR RUDDER PEDAL CONTROLS\EXTRA FLUGZEU |
AD 97-22-07 | PREVENT SUDDEN DECOMPRESSION OF THE AIRPLANE\BOEING CO\737-100 SERIES\737-200 SERIES\737-200C SERIES\737-300 SERIES\73 |
AD 97-22-08 | PREVENT LOSS OF AIRPLANE CONTROL OR ENGINE OVERSPEED WITH CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER LEVERS B |
AD 97-22-11 | PREVENT LOSS OF AIRPLANE CONTROL OR ENGINE OVERSPEED WITH CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER LEVERS B |
AD 97-22-12 | PREVENT LOSS OF AIRPLANE CONTROL OR ENGINE OVERSPEED WITH CONSEQUENT LOSS OF ENGINE POWER CAUSED BY THE POWER LEVERS B |
AD 97-22-16 | PREVENT THE VENT BLOWER ASSEMBLY BEARINGS FROM SEIZING, WHICH COULD RESULT IN SMOKE EMANATING FROM THE INSULATING MATE |
AD 97-23-02 | PREVENT UNCONTAINED FAILURE OF ENGINE FAN BLADES DUE TO HIGH CYCLE FATIGUE CRACKING, WHICH COULD RESULT IN LOSS OF THR |
AD 97-23-03 | PREVENT FAILURE OF THE BEARING CAP ATTACHMENT BOLTS, WHICH COULD RESULT IN DETACHMENT OF THE BEARING CAPS AND CONSEQUE |
AD 97-23-05 | PREVENT THE PITCH CONTROL CABLES ON THE CONTROL COLUMN FROM BECOMING JAMMED DUE TO FAILURE OF THE ATTACHMENT BOLT, WHI |
AD 97-23-06 | PREVENT FAILURE OF THE RING GEAR, LOSS OF DRIVE TO THE MAIN ROTOR GEARBOX, AND A SUBSEQUENT FORCED LANDING\SCHWEIZER A |
AD 97-23-07 | PREVENT FAILURE OF THE CLUTCH, LOSS OF POWER TO THE MAIN ROTOR AND A SUBSEQUENT FORCED LANDING OF THE HELICOPTER\EUROC |
AD 97-23-08 | RUDDER CONTROL BECOMING JAMMED BECAUSE OF THE YAW DAMPER CONTROL CABLES SLIPPING OUT OF THE GROOVE ON THE TENSION ADJU |
AD 97-23-09 | PREVENT FAILURE OF THE FUSELAGE BECAUSE OF CRACKS IN THE FUSELAGE SIDE FRAMES, WHICH, IF NOT DETECTED AND CORRECTED, C |
AD 97-23-10 | PREVENT FAILURE OF THE CABLE TENSION REGULATOR ON BOTH THE LEFT AND RIGHT ELEVATORS, AND CONSEQUENT REDUCED CONTROLLAB |
AD 97-23-11 | PREVENT THE ACCUMULATION OF SLUSH IN THE MAIN LANDING GEAR (MLG) BAY AREAS THAT COULD FREEZE AND INTERFERE WITH THE LA |
AD 97-23-12 | PREVENT REDUCED STRUCTURAL INTEGRITY AND POTENTIAL COLLAPSE OF THE MAIN LANDING GEAR\FOKKER SVCS\F.28 MARK 0070\F.28 M |
AD 97-23-14 | LOSS OF AIRPLANE CONTROLLABILITY\MARYLAND AIR IND INC\FH-227B\FH-227C\FH-227D\FH-227E\FH-227 |
AD 97-23-15 | LOSS OF AIRPLANE CONTROLLABILITY\MARYLAND AIR IND INC\F-27\F-27A\F-27B\F-27F\F-27G\F-27J\F-27M\FH-227\FH-227B\FH-227C\ |
AD 97-24-01 | PREVENT FAILURE OF THE BUSHINGS OF THE MAIN LANDING GEAR (MLG) TRAILING ARM, WHICH COULD RESULT IN COLLAPSE OF THE MLG |
AD 97-24-03 | PREVENT INJURY TO PASSENGERS AS A RESULT OF INADEQUATE BREAKING STRENGTH OF THE BAGGAGE NET\DASSAULT-AVI\FALCON 2000 |
AD 97-24-05 | PREVENT CONTAMINATION IN THE AFT WING BREAK CONNECTORS, WHICH COULD RESULT IN UNCOMMANDED FLAP EXTENSIONS AND INCORREC |
AD 97-24-06 | TO PREVENT CRACKS IN THE AILERON OPERATING LEVER'S ACTUATING SHAFT WELDED SEAMS\GLASFLUGEL\STANDARD LIBELLE-201B\STAND |
