Popular Standards |
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AD 77-21-04 | CLUTCH AND SHAFT ASSEMBLY\MD HELICPTR INC\369A\369D\369HE\369HM\369HS\369H\369 |
AD 77-21-05 | HIGH PRESSURE TURBINE DISKS\ROLLS-ROYCE PLC\DART 527,528-7E,528D-7E,529-7E,529-7H,529-8E,529-8H,529-8X,529-8Y,529-8Z,5 |
AD 77-21-06 | FUSELAGE STEEL TUBING CLUSTER\PIPER AIRCRFT INC NEW\PA-25\PA-25-235\PA-25-260 |
AD 77-21-07 | WIRING\EUROCOPTER DEUTSCHLAND GMBH (ECD)\BO-105A\BO-105C |
AD 77-21-08 | AUXILIARY FUEL SYSTEM\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 77-21-09 | AILERON/RUDDER JAMMING\LOCKHEED AIRCRFT CORP\188A\188C |
AD 77-22-01 | FUSELAGE STRUCTURE\RAYTHEON AIRCRFT CO\65-80\65-88\65-90\65-A80-8800\65-A80\65-A90\65-B80\65\A65-8200\A65\B90\C90\E90 |
AD 77-22-02 | NOSE LANDING GEAR ENGINE MOUNT\BELLANCA INC\14-19-3A\14-19-3\17-30A\17-30 |
AD 77-22-03 | RING SEGMENT - VHF ANTENNA\LOCKHEED-GEORGIA CORP\1329-23A\1329-23D\1329-23E\1329-25 |
AD 77-22-04 | LANDING GEAR\EUROCOPTER FRANCE\SA341G |
AD 77-22-05 | OPERATING LIMITATIONS\AMERCN CHAMPION AIRCRFT CORP\7ECA\7GCAA\7GCA\7GCBC\7GCB\7GC\7HC\7KCAB |
AD 77-23-02 | PROPELLER FEATHERING SYSTEM\BRITISH AEROSPC (ENGLAND)\HS 748 SERIES 2A |
AD 77-23-03 | ROD END BEARINGS\PIPER AIRCRFT INC NEW\PA-28-140\PA-28-151\PA-28-161\PA-28-180\PA-28-181\PA-28-235\PA-28R-180\PA-28R-2 |
AD 77-23-04 | TOTAL-PRESSURE PROBES\AVIONS MARCEL DASSAULT - BREGUET AVI\FALCON 10 |
AD 77-23-05 | WING OR EMPENNAGE ASSEMBLIES\BRITISH AEROSPC (SCOTLAND)\B.206 SERIES 1\B.206 SERIES 2 |
AD 77-23-08 | CRACKS IN MIAN ROTOR BLADES\SCHWEIZER AIRCRFT CORP\269A-1\269A\269B |
AD 77-23-09 | FUEL FLOW\PIPER AIRCRFT INC NEW\PA-23-250 (NAVY UO-1)\PA-E23-250 |
AD 77-23-10 | SPAR WEB AND BOLTS\SCHWEIZER AIRCRFT CORP\SGS 2-33AK\SGS 2-33A\SGS 2-33 |
AD 77-23-11 | ELT INSTALLATION\CESSNA AIRCRFT CO\182\182A\182B\182C\182D\182E\182F\182G\182H\182J\182K\182L\182M\182N\182P\182Q\182R |
AD 77-24-01 | STABILIZERS AND FINS\PIPER AIRCRFT INC NEW\PA-31-325\PA-31 |
AD 83-02-06 | FUEL FILTER SYSTEM\CONSTRUCCIONES AERONAUTICAS S A\C-212-CB\C-212-CC\C-212-CD\C-212-CE\C-212-CF\C-212-DE\C-212-DF |
AD 83-02-07 | THRUST REVERSER\MCDONNELL DOUGLAS CORP\DC-8-71F\DC-8-71\DC-8-72F\DC-8-72\DC-8-73F\DC-8-73 |
AD 83-02-10 | ICING PREVENTION\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B SERIES\747-200C SERIES\747-200F |
AD 83-02-51 | WALKING BEAM ASSEMBLIES\BELL HELICPTR TEXTRON\222B\222 |
AD 83-03-02 | TURBINE WHEELS\ALLISON ENGINE CO INC\250-B17B\250-B17C\250-B17D\250-B17\250-C20B\250-C20C (T63-A-720)\250-C20F\250-C20 |
AD 83-03-03 | TAIL BOOM SKIN JOINT\HAWKINS & POWERS AVI INC\UH-1B\US HELICPTR INC\UH-1A\UH-1B\UH-1E\UH-1H\UH-1L |
AD 83-03-04 | DAMAGE CHECK OF SHEAR HEADS\BELL HELICPTR TEXTRON\206L-1\206L |
AD 83-03-05 | UNDERCARRIAGE SHOCK ABSORBER\BRITTEN NORMAN (BEMBRIDGE) LTD\BN2A MK. 111-2\BN2A MK. 111-3\BN2A MK. 111 |
AD 83-03-51 | TURBINE ROTORS\ALLIEDSIGNAL INC\ALF502L-2A\ALF502L-2C\ALF502L-2\ALF502L-3\ALF502L\ALF502R-3A\ALF502R-3\ALF502R-4\ALF50 |
AD 83-03-52 | HORIZONTAL STABILIZER HINGE FITTINGS INSPECTION\BOEING CO\767-200 SERIES |
AD 83-04-02 | AILERON CONTROL CABLES\FOKKER SVCS\F.28 MARK 0070\F.28 MARK 0100\F.28 MARK 1000\F.28 MARK 2000\F.28 MARK 3000\F.28 MAR |
AD 83-04-03 | CONTROL WHEEL FAILURE\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-110P1\EMB-110P2 |
AD 83-04-04 | MAIN ROTOR GEARBOXES\ENSTROM HELICPTR CORP\280\F-28A |
AD 83-04-05 | CONTROL COLUMN LOWER ASSY.\BOMBARDIER INC\DHC-3 |
AD 83-04-06 | ENGINE MOUNTING STRUCTURE\BRITISH AEROSPC (SCOTLAND)\BEAGLE B.121 SERIES 1\BEAGLE B.121 SERIES 2\BEAGLE B.121 SERIES 3 |
AD 83-05-02 | TELEFLEX SWIVEL ASSEMBLY INSP.\BRITTEN NORMAN (BEMBRIDGE) LTD\BN2A MK. 111-2\BN2A MK. 111-3\BN2A MK. 111\PILATUS BRITT |
AD 83-05-05 | WINDSHIELD GLAZING FRAME\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 83-05-06 | STRUCTURAL INSPECTION\SUD AVI\CARAVELLE SE 210 MODEL III\CARAVELLE SE 210 MODEL VIR |
AD 83-05-07 | OIL COOLER FITTINGS AND HOSES\PARTENAVIA COSTRUZIONI AERONAUTICAS S P A\P 68B\P 68 |
AD 83-05-08 | FUEL FILTER BLEED PIPE INSPECTION REVISION 1\BRITISH AEROSPC (SCOTLAND)\H.P. 137 JETSTREAM MK. 1\JETSTEAM SERIES 200 |
AD 83-05-09 | WLG JURY STRUT SPINDLES\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B SERIES\747-200C SERIES\7 |
AD 83-06-01 | ICE SHIELDS INSTALLATION\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 83-06-02 | FIRE EXTINGUISHING AGENT\MCDONNELL DOUGLAS CORP\DC-9-81\DC-9-82\DC-9-83\DC-9-87 |
AD 83-06-03 | MLG SUPPORT STRUCTURE\MCDONNELL DOUGLAS CORP\DC-9-31\DC-9-32\DC-9-32 (VC-9C)\DC-9-32F\DC-9-32F (C-9A)\DC-9-32F (C-9B)\ |
AD 83-06-05 | NOSE-GEAR BARREL\AERMACCHI S P A\F.260B\F.260C\F.260 |
AD 83-06-06 | RUDDER CONTROL LEVER ASSY\BRITISH AEROSPC (SCOTLAND)\BEAGLE B.121 SERIES 1\BEAGLE B.121 SERIES 2\BEAGLE B.121 SERIES 3 |
AD 83-06-07 | YAWS AXIS FLIGHT CONTROL\POLSKIE ZAKLADY LOTNIEZE SPOLKA ZO O\PZL M18 |
AD 83-06-08 | MLG BRAKE FLANGE\SHORT BROTHERS PLC\SC-7 SKYVAN SERIES 3 |
AD 83-06-09 | INFLIGHT ENGINE SHUT-DOWN PREVENTION\POLSKIE ZAKLADY LOTNIEZE SPOLKA ZO O\PZL M18 |
AD 83-06-10 | PROP. GOVERNOR RELIEF VALVE\AERMACCHI S P A\F.260B\F.260C\F.260 |
AD 83-07-02 | COUNTERWEIGHTS REINFORCEMENT\POLSKIE ZAKLADY LOTNIEZE SPOLKA ZO O\PZL M18 |
AD 83-07-04 | FLIGHT CONTROL SYSTEM\SHORT BROTHERS PLC\SC-7 SKYVAN SERIES 3 |
AD 83-07-05 | MAIN ROTOR MAST\EUROCOPTER FRANCE\AS-350B1\AS-350B2\AS-350B3\AS-350BA\AS-350B\AS-350C\AS-350D1\AS-350D\AS355E\AS355F1\ |
AD 83-07-06 | SYNCHRONIZING SHAFT\BOEING DEFENSE & SPACE GROUP\107-II\KAWASAKI HEAVY IND LTD\KV107-IIA\KV107-II |
AD 83-07-07 | RUDDER JAMMING\BRITISH AEROSPC (SCOTLAND)\H.P. 137 JETSTREAM MK. 1\JETSTEAM SERIES 200 |
AD 83-07-08 | GROUND/AIR LEVER MECHANISM\SHORT BROTHERS PLC\SC-7 SKYVAN SERIES 3 |
AD 83-07-09 | WIRE OVERHEATING\BOMBARDIER INC\CL-600-1A11 (CL-600)\CL-600-2A12 (CL-601) |
AD 83-07-10 | BUTTERFLY VALVE ATTACHMENT\AERMACCHI S P A\S.205 - 20/F\S.205 - 20/R |
AD 83-07-11 | LEFT AND RIGHT BRAKING LEVERS\POLSKIE ZAKLADY LOTNIEZE SPOLKA ZO O\PZL M18 |
AD 83-07-12 | FUEL TRANSMITTER FLOAT INSP.\PILATUS BRITTEN-NORMAN LTD\BN-2B-20\BN-2B-21\BN-2B-26\BN-2B-27\BN-2\BN-2A\BN-2A-2\BN-2A-2 |
AD 91-18-10 | MLG BRAKING EFFECTIVENESS\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 91-18-13 | PITOT/STATIC HEATERS\SHORT BROTHERS PLC\SD 3-30\SD3-60 |
AD 91-18-14 | PASSENGER AND SERVICE DOORS\BRITISH AEROSPC (ENGLAND)\BAE 146-100A\BAE 146-200A\BAE 146-300A |
AD 91-18-15 | VERTICAL STABILIZER\FOKKER SVCS\F.28 MARK 0100 |
AD 91-18-16 | ELEVATOR TRIM SYSTEM\FOKKER SVCS\F27 MARK 050\F27 MARK 100\F27 MARK 200\F27 MARK 300\F27 MARK 400\F27 MARK 500\F27 MAR |
AD 91-18-17 | PASSENGER DOOR DISARM CABLE\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIES\757-300 SERIES |
AD 91-18-18 | INSPECT FUSELAGE\MCDONNELL DOUGLAS CORP\DC-9-11\DC-9-12\DC-9-13\DC-9-14\DC-9-15\DC-9-15F\DC-9-21\DC-9-31\DC-9-32\DC-9- |
AD 91-18-19 | PILOT SHOULDER HARNESSES\RAYTHEON AIRCRFT CO\58A\58PA\58P\58TCA\58TC\58\95-B55A\95-B55\A36\B36TC\E55A\E55\F33A\V35B |
AD 91-18-20 | MAIN LANDING GEAR\BOMBARDIER INC\DHC-7-100\DHC-7-101\DHC-7-102\DHC-7-103\DHC-7-1 |
AD 91-18-21 | FLAP TRACK SUPPORT FITTINGS\BOMBARDIER INC\DHC-7-100\DHC-7-101\DHC-7-102\DHC-7-103\DHC-7-1 |
AD 91-19-01 | AIR DRIVEN GENERATOR\BOMBARDIER INC\CL-600-1A11 (CL-600)\CL-600-2A12 (CL-601)\CL-600-2B16 (CL-601-3A)\CL-600-2B16 (CL- |
AD 91-19-06 | VERTICAL STABILIZER\INDUSTRIE AERONAUTICHE E MECCANICHE\P-180 |
AD 91-20-04 | STABILIZER TRIM ASSEMBLY\BOEING CO\737-300 SERIES\737-400 SERIES\737-500 SERIES |
AD 91-20-05 | INSPECT SKIN AND CLEATS\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 91-20-06 | ENGINE FIRE EXTINGUISHING SYSTEM\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B SERIES\747-200C |
AD 91-20-08 | FRESH AIR BLOWER HOUSING\RAYTHEON AIRCRFT CO\A36TC\A36\B36TC\F33A\F33C\V35B |
AD 91-20-10 | MAIN ROTOR GRIP\BELL HELICPTR TEXTRON\47G-2A-1\47G-2A\47G-2\47G-3B-1\47G-3B-2A\47G-3B-2\47G-3\47G-4A\47G-4\47G-5A\47G- |
AD 91-20-14 | PILOT'S OPERATING HANDBOOK AND AFM REVISION 1\RAYTHEON AIRCRFT CO\B300C\B300 |
AD 91-21-01 | ENGINE EXHAUST SYSTEM FLANGES, V-BAND COUPLING, AND PIPES\TEXTRON LYCOMING AVCO CORP\TIO-540-S1AD |
AD 91-21-02 | MANAGEMENT CONTROL UNITS\MCDONNELL DOUGLAS CORP\DC-9-81\DC-9-82\DC-9-83\DC-9-87 |
AD 91-21-03 | ELECTRICAL WIRING\MCDONNELL DOUGLAS CORP\DC-9-11\DC-9-12\DC-9-13\DC-9-14\DC-9-15\DC-9-15F\DC-9-21\DC-9-31\DC-9-32\DC-9 |
AD 91-21-04 | INSPECT FOR CRACKS\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 91-21-06 | ENGINE/NOSE COWL\BRITISH AEROSPC (ENGLAND)\BAE 146-100A\BAE 146-200A\BAE 146-300A |
AD 91-21-07 | TRIM RELAYS\MCDONNELL DOUGLAS CORP\DC-9-33F\DC-9-34\DC-9-34F\DC-9-41\DC-9-51\DC-9-81\DC-9-82\DC-9-83\DC-9-87\MD-88\DC- |
AD 91-21-08 | TAILPLANE LOWER SKIN PANEL\BRITISH AEROSPC AIRBUS LTD\BAC 1-11 200 SERIES\BAC 1-11 400 SERIES |
AD 91-21-09 | AIR INDUCTION SYSTEM\PIPER AIRCRFT INC NEW\PA-24-260 |
AD 91-21-10 | LEADING EDGE SLATS\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 91-21-13 | FUEL SHUTOFF CABLE PULLEY BRACKET\BOEING CO\737-300 SERIES\737-400 SERIES\737-500 SERIES |
AD 91-22-03 | TAILCONE INDICATING SYSTEM\MCDONNELL DOUGLAS CORP\DC-9-11\DC-9-12\DC-9-13\DC-9-14\DC-9-15\DC-9-15F\DC-9-21\DC-9-31\DC- |
AD 91-22-04 | MAIN CARGO DOOR\BOEING CO\707-100 LONG BODY\707-100B LONG BODY\707-100B SHORT BODY\707-200\707-300 SERIES\707-300B SER |
AD 91-22-05 | STOWAGE BINS\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-200B SERIES\747-200C SERIES\747-200F SER |
AD 91-22-06 | PLACARD OPERATING LIMITATIONS\PARTENAVIA COSTRUZIONI AERONAUTICAS S P A\P 68 OBSERVER\P 68B\P 68C-TC\P 68C\P 68\P68 OB |
AD 91-22-07 | MLG OUTBOARD DOOR\MCDONNELL DOUGLAS CORP\DC-9-11\DC-9-12\DC-9-13\DC-9-14\DC-9-15\DC-9-15F\DC-9-21\DC-9-31\DC-9-32\DC-9 |
AD 91-22-08 | MLG WHEEL WELL PRESSURE FLOOR\BOEING CO\727 SERIES\727-100 SERIES\727-100C SERIES\727-200 SERIES\727-200F SERIES\727C |
AD 91-22-51 | TRAILING EDGE WEDGES\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIES\757-300 SERIES |
AD 91-23-01 | NOSE LANDING GEAR FORK\RAYTHEON AIRCRFT CO\77 |
AD 91-23-02 | CARBURETOR INTAKE BOX\SKY INTNL INC\A-1 |
AD 91-23-03 | FUEL SYSTEM\AVIONS MUDRY ET CIE\CAP 10 B |
AD 91-23-05 | AILERON/RUDDER SERVOMOUNTS\FOKKER SVCS\F.28 MARK 0100 |
AD 91-23-06 | HORIZONTAL STABILIZER ATTACH FITTINGS\FOKKER SVCS\F.28 MARK 0070\F.28 MARK 0100\F.28 MARK 1000\F.28 MARK 2000\F.28 MAR |
AD 00-01-02 | PREVENT THE TURBINE AIR DISCHARGE DUCT IN THE AIR CONDITIONING SYSTEM FROM DISCONNECTING FROM THE CAU OR WATER SEPARAT |
AD 00-01-03 | PREVENT FATIGUE FAILURE OF THE PISTON IN THE RETRACT ACTUATOR OF THE MAIN LANDING GEAR (MLG) AND REDUCED STRUCTURAL IN |
AD 00-01-04 | PREVENT IMPROPER ILLUMINATION OF THE GROUND UNDER THE SERVICE DOOR DUE TO INCORRECT INSTALLATION OF THE AFT EXTERIOR L |
AD 00-01-05 | PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLA |
AD 00-01-06 | ASSURE THAT THE INSTRUMENT PANEL DOES NOT JAM AGAINST THE CANOPY FRAME OF THE EMERGENCY JETTISON SYSTEM\ROLLADEN-SCHNE |
AD 00-01-07 | PREVENT REDUCED STRENGTH CAPABILITY OF THE HORIZONTAL STABILIZER AND CONSEQUENT FAILURE OF THE HORIZONTAL STABILIZER\B |
AD 00-01-08 | PREVENT UNCOMMANDED ENGAGEMENT OF THE RUDDER STANDBY CONTROL SYSTEM (SCS)\BRITISH AEROSPC (ENGLAND)\ATP |
AD 00-01-09 | PREVENT THE USE OF UNAPPROVED PARTS\GENERAL ELECTRIC AIRCRFT ENGINES\CF700-2C\CF700-2D-2\CF700-2D\CJ610-1\CJ610-4\CJ61 |
AD 00-01-10 | PREVENT FATIGUE FAILURE OF THE ELEVATOR AND RUDDER TRIM TAB PIVOT ARMS BECAUSE OF CRACKS\PILATUS AIRCRFT LTD\PC-7 |
AD 00-01-11 | PREVENT MAIN ROTOR BLADE (BLADE) SEPARATION DUE TO FAILURE OF A TENSION-TORSION (TT) STRAP\EUROCOPTER DEUTSCHLAND GMBH |
AD 00-01-12 | DETECT AND CORRECT FATIGUE CRACKING IN THE UNDERFLOOR PRESSURE BULKHEAD OF THE FUSELAGE\BOMBARDIER INC\CL-600-2B19 (RE |
AD 00-01-13 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\PRATT & WHITNEY DIV\JT9D-20J\JT9D-20\JT9D-59A\JT9D-70A\JT9D |
AD 00-01-14 | PREVENT CORROSION AND SUBSEQUENT FRACTURE OF THE FUSE PINS IN THE MAIN LANDING GEAR ATTACHMENT AND SUPPORT FITTINGS\BO |
AD 00-01-15 | PREVENT REDUCED CONTROLLABILITY OF THE AIRPLANE AS A RESULT OF INTERRUPTION OF THE ANTI-SKID SYSTEM FUNCTION, OR INADV |
AD 00-01-16 | DETECT AND CORRECT CRACKS AND CORROSION IN THE EXHAUST SYSTEM\CESSNA AIRCRFT CO\320-1\320A\320B\320C\320D\320E\320F\32 |
AD 00-01-17 | PREVENT FATIGUE CRACKING OF LONGERONS 22 THROUGH 26 AND THE ATTACHING FRAMES\MCDONNELL DOUGLAS CORP\MD-90-30 |
AD 00-01-19 | PREVENT A MAIN ROTOR BLADE EXPANSION BOLT NUT BECOMING LOOSE\EUROCOPTER DEUTSCHLAND GMBH (ECD)\EC135 P1\EC135 T1 |
AD 00-01-51 | PREVENT A FUEL FIRE DUE TO ELECTRICAL SPARKS CONTACTING THE MAINTENANCE LIGHT HOUSING OF THE FUEL SERVICE PANEL\BOMBAR |
AD 00-02-02 | PREVENT THE LOSS OF OXYGEN FROM THE AIRCRAFT OXYGEN SYSTEM\SHORT BROTHERS PLC\SD 3-30\SD3-60 SHERPA\SD3-SHERPA |
AD 00-02-03 | PREVENT FATIGUE CRACKING OF THE ROD ENDS ON THE LEADING EDGE SLAT ACTUATORS\BOEING CO\737-300 SERIES\737-400 SERIES\73 |
AD 00-02-05 | DETECT AND CORRECT FAILURE OF THE TWO DIAPHRAGMS THAT SUPPORT THE UPPER STRUCTURE OF THE FORWARD EQUIPMENT COMPARTMENT |
AD 00-02-06 | PREVENT LOSS OF THE AUTOMATIC OVERSPEED PROTECTION OF THE PROPELLER CONTROL SYSTEM\BOMBARDIER INC\DHC-8-100 SERIES\DHC |
AD 00-02-07 | DETECT AND CORRECT FATIGUE CRACKING IN THE BAGGAGE DOOR FITTINGS AND THE SUPPORT STRUCTURE\BOMBARDIER INC\DHC-7-100\DH |
AD 00-02-08 | PREVENT HYDRAULIC FLUID LEAKAGE DUE TO LOOSE OR BROKEN GLAND ATTACHMENT BOLTS\DORNIER LUFTFAHRT GMBH\328-100 |
AD 00-02-09 | PREVENT SEPARATION OF THE RESCUE HOIST HOOK ASSEMBLY FROM THE HELICOPTER DUE TO FAILURE OF THE RESCUE HOIST HOOK ASSEM |
AD 00-02-11 | PREVENT FUEL OR FUEL VAPORS FROM ENTERING THE PASSENGER AND CARGO COMPARTMENTS OF THE AIRPLANE IN THE EVENT OF A FAILU |
AD 00-02-12 | PREVENT BEARING FAILURE, LOSS OF TAIL ROTOR DRIVE, AND A SUBSEQUENT FORCED LANDING\BELL HELICPTR TEXTRON\407 |
AD 00-02-13 | PREVENT POSITIONING OF THE POWER LEVERS BELOW THE FLIGHT IDLE STOP DURING FLIGHT\BOMBARDIER INC\DHC-8-100 SERIES\DHC-8 |
AD 00-02-14 | DETECT AND CORRECT DAMAGE TO THE ENGINE EXHAUST MUFFLERS CAUSED BY CRACKING\CESSNA AIRCRFT CO\182S |
AD 00-02-15 | PREVENT ENGINE FAILURE AND THE INABILITY TO FEATHER THE PROPELLER CAUSED BY DISCREPANCIES IN THE ENGINE AND PROPELLER |
AD 00-02-16 | DETECT AND CORRECT MIGRATION OF THE WING ATTACHMENT BUSHES IN THE FUSELAGE FRONT AND REAR SPAR FRAMES\SHORT BROTHERS P |
AD 00-02-17 | PREVENT INTERMEDIATE PRESSURE TURBINE (IPT) AND INTERMEDIATE PRESSURE COMPRESSOR (IPC) SHAFT SPLINE FLANK WEAR\ROLLS-R |
AD 00-02-18 | PREVENT A REDUCED RATE OF MOVEMENT OF THE ELEVATOR, AILERON, OR RUDDER\BOEING CO\737-100 SERIES\737-200 SERIES\737-200 |
AD 00-02-19 | PREVENT FATIGUE CRACKS OF THE FRONT SPAR WEB OF THE CENTER SECTION OF THE WINGS\BOEING CO\727 SERIES\727-100 SERIES\72 |
AD 00-02-21 | PREVENT FATIGUE FAILURE OF THE TOWING BRACKET\JETSTREAM AIRCRFT LTD\JETSTREAM MODEL 4101 |
AD 00-02-22 | PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLA |
AD 00-02-26 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\HARBIN AIRCRFT MFG CORP\Y12 |
AD 00-02-27 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\EMPRESA BRASILEIRA DE AERONA |
AD 00-02-28 | INFORMATION NECESSARY TO ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION IS |
AD 00-02-29 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\SOCATA - GROUPE AEROSPATIALE |
AD 00-02-30 | PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\TWIN COMMANDER AIRCRFT CORP\680-E\680-FL( |
AD 00-02-31 | PREVENT IMPROPER OPERATION OF THE STICK PUSHER SYSTEM CAUSED BY THE EXISTING DESIGN CONFIGURATION\PILATUS AIRCRFT LTD\ |
AD 00-02-32 | PREVENT FATIGUE FAILURE OF THE SPAR TUBE, SEPARATION OF THE HORIZONTAL STABILIZER AND IMPACT WITH THE MAIN OR TAIL ROT |
AD 00-02-34 | PREVENT UNDETECTED ACCRETION OF ICE ON THE WINGS\BOMBARDIER INC\CL-600-2B19 (REGIONAL JET SERIES 100) |
AD 00-03-01 | DETECT AND CORRECT FATIGUE CRACKING OF THE UPPER AND LOWER CHORDS OF THE WING FRONT SPAR\BOEING CO\747-100 SERIES\747- |
AD 00-03-02 | PREVENT FAN MID SHAFT FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\GE90-76B\GE90-85B\GE90-90B |
AD 00-03-03 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\CF34-3A1\CF34-3B1 |
AD 00-03-05 | PREVENT INADEQUATE LIGHTING AND CUEING OF THE EMERGENCY FLOOR PATH LIGHTING SYSTEM\BOEING CO\737-200 SERIES\737-200C S |
AD 00-03-07 | PREVENT BURN THROUGH OF THE COMBUSTOR CASE DUE TO COMBUSTOR LINER CRACKING\ROLLS-ROYCE PLC\RB211-524H-36 |
AD 00-03-08 | DETECT AND CORRECT FATIGUE CRACKING OF MAIN LANDING GEAR (MLG) PISTONS\MCDONNELL DOUGLAS CORP\MD-90-30 |
AD 00-03-09 | PREVENT UNCOMMANDED ROLL OF THE AIRPLANE DURING APPROACH AND LANDING WHEN RESIDUAL ICE IS PRESENT OR CAN BE EXPECTED\C |
AD 00-03-11 | PREVENT BURNT INTERNAL CIRCUIT BOARDS CAUSED BY A SHORT IN EITHER THE ENGINE OR AIRFOIL ANTI-ICE VALVE, OR WINDSHIELD |
AD 00-03-12 | PREVENT LOSS OF THE CHARGING CAPABILITY OF THE AIR DRIVEN GENERATOR (ADG)\MCDONNELL DOUGLAS CORP\MD-11F\MD-11 |
AD 00-03-13 | PREVENT THE WIRE BUNDLE CONTAINED IN THE FEEDTHROUGH FROM CONTACTING THE BOTTOM OF THE FEEDTHROUGH WHICH COULD CAUSE C |
AD 00-03-14 | PREVENT ARCING OF THE BATTERY GROUND STUDS\MCDONNELL DOUGLAS CORP\MD-11F\MD-11 |
AD 00-03-15 | PREVENT ELECTRICAL ARCING CAUSED BY POWER FEEDER CABLE TERMINAL LUGS GROUNDING AGAINST TERMINAL STRIP SUPPORT BRACKETS |
AD 00-03-16 | PREVENT THE THREADED INSERT CONNECTOR FROM PULLING FREE FROM THE CASING OF THE 90 PERCENT BRAKE PEDAL POSITION SWITCH |
AD 00-03-17 | DETECT EXCESSIVE FREEPLAY OR ROD SLIPPAGE IN THE PITCH TRIM ACTUATOR\FAIRCHILD AIRCRFT CORP\SA226-AT\SA226-T(B)\SA226- |
AD 00-03-18 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\PARTENAVIA COSTRUZIONI AERON |
AD 00-03-20 | DETECT AND CORRECT FATIGUE CRACKING ON THE FORWARD FITTINGS IN THE RADIUS OF FRAME 40 ADJACENT TO THE TENSION BOLTS IN |
AD 00-03-21 | PREVENT INTERFERENCE BETWEEN THE LANDING GEAR CONTROL LEVER AND WIRE BUNDLES ADJACENT TO THE LANDING GEAR CONTROL LEVE |
AD 00-03-22 | PREVENT LOSS OF THE UNDERWING FITTING LOAD PATH DUE TO MISSING, DAMAGED, OR BROKEN TAPERLOCK BOLTS\BOEING CO\747-100 S |
AD 00-04-01 | PREVENT FAILURE OF THE ENGINE OIL PRESSURE SWITCH DIAPHRAGM, WHICH RESULTS IN LOSS OF ENGINE OIL THROUGH THE VENT HOLE |
AD 00-04-02 | PREVENT FUEL SUCTION FEED OPERATION ON BOTH ENGINES WITHOUT FLIGHT CREW INDICATION\BOEING CO\737-100 SERIES\737-200 SE |
AD 00-04-04 | DETECT AND PREVENT A SHORT CIRCUIT OF A FIRE EXTINGUISHER ELECTRICAL SYSTEM DUE TO A LACK OF SHRINK SLEEVES OR GROMMET |
AD 00-04-05 | PREVENT CRACKS IN THE LOWER SCISSORS FITTING AND FITTING ATTACHMENT BOLTS OF THE HORIZONTAL STABILIZER\ISRAEL AIRCRFT |
AD 00-04-07 | PREVENT FAILURE OF THE ENGINE INTAKE DE-ICING SYSTEM\BRITISH AEROSPC (ENGLAND)\ATP |
AD 00-04-10 | PREVENT PROPELLER MOUNTING BOLT FAILURE\HOFFMANN GMBH & CO KG\HO 27 HM\HO 4/27 ( ) HM\HO 4/27 ( ) |
AD 00-04-12 | PREVENT TITANIUM PROPANE CYLINDERS FROM CRACKING AND RELEASING PROPANE GAS VAPOR WHILE THE BALLOON IS IN SERVICE\CAMER |
AD 00-04-13 | PREVENT FATIGUE CRACKING OF THE FUSELAGE AND THE PASSENGER AND SERVICE DOORS\AEROSPATIALE (SOCIETE NATIONALE INDUSTRIE |
AD 00-04-15 | PREVENT FATIGUE FAILURE OF A DRIVE PIN\BELL HELICPTR TEXTRON\222B\222U\222\230 |
AD 00-04-16 | PREVENT EXCESSIVE RADIATION FROM CAUSING THE CARBON FIBER SHROUD ON THE ENGINE MUFFLER TO DELAMINATE\ALEXANDER SCHLEIC |
AD 00-04-17 | PREVENT FAILURE OF THE UPPER DECK FLOOR BEAMS DUE TO FATIGUE CRACKING AT BS 340, 360, AND 380\BOEING CO\747-100 SERIES |
AD 00-04-18 | PREVENT DAMAGE TO THE FLAP SYSTEM, ADJACENT SYSTEM, OR STRUCTURAL COMPONENTS\BOEING CO\757-200 SERIES\757-200CB SERIES |
AD 00-04-19 | PREVENT IN-FLIGHT SHUTDOWN OF THE ENGINE(S) DUE TO THE FLIGHTCREW USING ERRONEOUS N1 SPEED VALUES DISPLAYED ON THE ENG |
AD 00-04-20 | PREVENT INTERMITTENT LOSS OF HYDRAULIC PRESSURE TO THE FLIGHT CONTROLS AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTE |
AD 00-04-21 | PREVENT FUEL STARVATION OF THE ENGINE WHILE THE FUEL GAGE INDICATES FUEL REMAINING IN THE TANK, ENGINE FLAMEOUT, AND A |
AD 00-04-23 | PREVENT CRACKING OF THE RUDDER SPRING TAB\DORNIER LUFTFAHRT GMBH\328-100\328-300 |
AD 00-04-24 | PREVENT AN UNCONTAINED APU FAILURE AND DAMAGE TO THE AIRPLANE\HONEYWELL INC\36-280(B) SERIES APUS\36-280(D) SERIES APU |
AD 00-04-25 | PREVENT A DOOR LATCH ROD ASSEMBLY FROM DISENGAGING FROM THE DOOR HANDLE AND PREVENTING HELICOPTER OCCUPANTS FROM OPENI |
AD 00-04-26 | DETECT INTERFERENCE IN THE ELEVATOR CONTROL CIRCUIT\ALEXANDER SCHLEICHER GMGH & CO\ASW 27 |
AD 00-05-02 | PREVENT UNDETECTED FAILURES OF THE HORIZONTAL AND VERTICAL STABILIZER DE-ICING SYSTEM, WHICH COULD RESULT IN REDUCED C |
AD 00-05-03 | DETECT AND CORRECT FATIGUE CRACKING OF THE INNER FLANGE OF FUSELAGE FRAME FR73A\AIRBUS INDUSTRIE\A300 MODEL B4-600 SER |
AD 00-05-05 | PREVENT ICE ACCUMULATION ON THE WINGS OR TAIL OF THE AIRPLANE\CONSTRUCCIONES AERONAUTICAS S A\CN-235-100\CN-235-200 |
AD 00-05-06 | PREVENT FAILURE OF THE ENGINE FIRE EXTINGUISHER BOTTLE TO DISCHARGE, OR DISCHARGE OF THE WRONG ENGINE FIRE EXTINGUISHE |
AD 00-05-09 | PREVENT ENGINE THRUST CONTROL CABLE FAILURE\BOEING CO\757-200 SERIES\757-200CB SERIES\757-200PF SERIES |
AD 00-05-10 | PREVENT AFT MOUNT WHIFFLETREE FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\GE90-85B |
AD 00-05-12 | PREVENT POSSIBLE MULTIPLE FAN BLADE FAILURES, WHICH COULD RESULT IN AN UNCONTAINED ENGINE FAILURE AND DAMAGE TO THE AI |
AD 00-05-13 | PREVENT FRACTURE OF THE MAIN LANDING GEAR (MLG) AXLE AND THE SEPARATION OF THE WHEEL FROM THE MLG, AND CONSEQUENT REDU |
AD 00-05-14 | PREVENT A NO. 4 AND 5 DUPLEX BEARING FAILURE\ALLIEDSIGNAL INC\ALF502L-2A\ALF502L-2C\ALF502L-2\ALF502L-3\ALF502L\ALF502 |
AD 00-05-15 | PREVENT SEPARATION OF AN ENGINE EXHAUST PIPE EJECTOR FROM THE HELICOPTER, WHICH COULD RESULT IN A TAIL ROTOR STRIKE AN |
AD 00-05-17 | PREVENT COUPLING FAILURE, LOSS OF ENGINE DRIVE, AND A SUBSEQUENT FORCED LANDING\EUROCOPTER FRANCE\EC120B |
AD 00-05-19 | PREVENT FATIGUE CRACKING OF THE FUSELAGE SKIN AND BONDED DOUBLER AREA ABOVE THE FORWARD ENTRY DOORWAY\BOEING CO\727 SE |
AD 00-05-22 | DETECT CRACKS IN THE BOLT HOLES OF HIGH PRESSURE TURBINE (HPT) FRONT ROTATING AIR SEALS\CFM INTNL S A\CFM56-2\CFM56-2A |
AD 00-05-23 | PREVENT COLLAPSE OF THE MAIN LANDING GEAR CAUSED BY CRACKED MAIN LANDING GEAR FUSELAGE ATTACH BOLTS\AYRES CORP\S-2R\S2 |
AD 00-05-24 | DETECT AND CORRECT A LOOSE FASTENER IN AN AUTOPILOT SERVO ACTUATOR\HONEYWELL INC\KAP 140\KFC 225 |
AD 00-05-25 | PREVENT ENGINE POWER ROLLBACK DURING FLIGHT IN ICING CONDITIONS\BRITISH AEROSPC (ENGLAND)\BAE 146-100A\BAE 146-200A\BA |
AD 00-05-26 | PREVENT FATIGUE CRACKS OF THE CARGO DOOR SKIN, CERTAIN FRAMES, ENTRY DOOR STOP FITTINGS, OR FRICTION PLATES\AEROSPATIA |
AD 00-05-27 | DETECT AND CORRECT FATIGUE CRACKING OF THE FUSELAGE SKIN IN THE VICINITY OF FRAME 29 BETWEEN STRINGERS 12 AND 13\BRITI |
AD 00-05-28 | DETECT AND CORRECT CRACKING OR CORROSION OF THE FORWARD ATTACHMENT BOLTS OF THE ENGINE PYLON TO WING INTERFACE\BRITISH |
AD 00-05-29 | DETECT FATIGUE CRACKING OF THE FORWARD PRESSURE BULKHEAD, WHICH COULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLANE FU |
AD 00-06-02 | INFORMATION NECESSARY TO ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\DOR |
AD 00-06-03 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION\BOMBARDIER INC\DHC-6-1\DHC-6 |
AD 00-06-04 | INFORMATION NECESSARY TO ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS\FAIRCHILD AIRCRFT CORP\SA226-AT\SA226-T(B) |
AD 00-06-05 | PREVENT FAILURE OF A TAIL ROTOR BLADE DUE TO A LIGHTNING STRIKE AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\EUROC |
AD 00-06-06 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION IS CRITICAL FOR FLIGHT IN IC |
AD 00-06-07 | PREVENT FATIGUE FAILURE OF THE BEVEL GEAR, LOSS OF TAIL ROTOR DRIVE, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\ |
AD 00-08-19 | PREVENT FATIGUE CRACKING OF THE BODY SKIN AT THE FORWARD CORNERS OF THE MID-GALLEY DOOR HINGE CUTOUTS, WHICH COULD RES |
AD 00-08-22 | PREVENT AN ERRONEOUS TOT INDICATION, DAMAGE TO CRITICAL ENGINE COMPONENTS, LOSS OF ENGINE POWER\MD HELICPTR INC\369D\3 |
AD 00-09-05 | PREVENT LOW CYCLE FATIGUE FAILURE OF CONE SHAFTS\ALLISON ENGINE CO INC\AE 3007A1/1\AE 3007A1/2\AE 3007A1/3\AE 3007A1P\ |
AD 00-09-07 | PREVENT INTERNAL OVERHEATING AND ARCING OF CIRCUIT BREAKERS AND AIRPLANE WIRING DUE TO LONG-TERM USE AND BREAKDOWN OF |
AD 00-09-08 | PREVENT SEPARATION OF THE NOSE COWL FROM THE ENGINE\BOEING CO\747-100 SERIES\747-100B SUD SERIES\747-100B SERIES\747-2 |
AD 00-09-09 | PREVENT FAILURE OF THE PITCH TRIM SYSTEM\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMBRAER)\EMB-145ER\EMB-145LR\EMB-145MR |
AD 00-09-10 | PREVENT ERRATIC OPERATION OF THE WHEEL TACHOMETERS\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL B4-600R SERIES |
AD 00-09-11 | PREVENT RESTRICTED ELEVATOR MOVEMENT AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLANE\FOKKER SVCS\F.28 MARK 0070 |
AD 00-09-12 | PREVENT DETACHMENT OR BREAKAGE OF WIRES IN THE TEMPERATURE SWITCH ASSEMBLIES OF THE WING ICE PROTECTION SYSTEM\RAYTHEO |
AD 00-09-13 | DETECT DAMAGE TO THE INSULATION OF THE WIRING WITHIN THE FUEL TANKS OF THE FUEL QUANTITY INDICATION SYSTEM\BRITISH AER |
AD 00-09-14 | PREVENT RADIAL DRIVE STEADY BEARING FAILURE\ROLLS-ROYCE PLC\RB211-535C-37\RB211-535E4-37\RB211-535E4-B-37\RB211-535E4- |
AD 00-09-15-R1 | R1 PREVENTING DEPARTURE FROM CONTROLLED FLIGHT WHILE OPERATING IN ICING CONDITIONS\MITSUBISHI HEAVY IND LTD\MU-2 |
AD 00-10-01 | DETECT AND CORRECT CORROSION AND CRACKING OF THE WINGS AND FUSELAGE\AIRBUS INDUSTRIE\A300 MODEL B2-1A\A300 MODEL B2-1C |
AD 00-10-04 | PREVENT CRACKING OF THE AILERON SKIN DUE TO MISSING RIVETS\ISRAEL AIRCRFT IND LTD\1124A\1124 |
AD 00-10-05 | PREVENT AN EMERGENCY FLOTATION GEAR NITROGEN CYLINDER FROM EXPLODING WITH RESULTANT HIGH VELOCITY SHRAPNEL\EUROCOPTER |
AD 00-10-06 | PREVENT FAILURE OF THE DRIVE SHAFT DUE TO FATIGUE\MD HELICPTR INC\MD-900 |
AD 00-10-07 | PREVENT FAILURE OF AN OIL COOLER FAN SPLINED DRIVE SHAFT (SHAFT), LOSS OF OIL COOLING, AND A SUBSEQUENT ENGINE SHUTDOW |
AD 00-10-08 | PREVENT DAMAGE TO A TAIL ROTOR BLADE (BLADE), LOSS OF TAIL ROTOR CONTROL, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICO |
AD 00-10-10 | PREVENT FAILURE OF THE CROSS-BEAM THAT COULD LEAD TO ROTATION OF THE MAIN GEARBOX\EUROCOPTER FRANCE\AS-350B1\AS-350B2\ |
AD 00-10-11 | ENSURE THAT FLIGHTCREWS ACTIVATE THE WING AND TAIL PNEUMATIC DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION ON T |
AD 00-10-12 | DETECT AND CORRECT DAMAGE OR DEFLECTION OF THE CREW REST HEAT EXCHANGER\BOEING CO\747-400 SERIES\747-400D SERIES\747-4 |
AD 00-10-13 | PREVENT LOSS OF A WINDOW PANEL, IMPACT WITH A MAIN ROTOR BLADE, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\EUROC |
AD 00-10-14 | PREVENT THE FRACTURE OF A FLAPPING BEARING TO YOKE ATTACHMENT BOLT (BOLT), FAILURE OF THE BEARING AND YOKE INTERFACE, |
AD 00-10-15 | DETECT AND CORRECT FATIGUE CRACKING IN CERTAIN AREAS OF THE REAR SPAR OF THE WING\AIRBUS INDUSTRIE\A320 MODEL -111\A32 |
AD 00-10-17 | PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT\BOEING CO\747-100 SERIES\747-100B SERIES\747-100B SU |
AD 00-10-19 | PREVENT ICE ACCUMULATION ON THE AIRPLANE LEADING EDGES\ISRAEL AIRCRFT IND LTD\1125 WESTWIND ASTRA\ASTRA SPX |
AD 00-10-20 | DETECT AND CORRECT CRACKING OF THE FUSELAGE SKIN\LOCKHEED AIRCRFT CORP\L-1011-385-1\L-1011-385-1-14\L-1011-385-1-15\L- |
AD 00-10-21 | PREVENT UNCOMMANDED MOVEMENT OF THE FLIGHTCREW SEATS DURING ACCELERATION AND TAKE-OFF OF THE AIRPLANE\BOEING CO\737-30 |
AD 00-10-22 | TO DETECT AND CORRECT CRACKS IN THE WING SPARS, WHICH COULD RESULT IN LOSS OF THE WING WITH CONSEQUENT LOSS OF CONTROL |
AD 00-10-23 | DETECT AND CORRECT FATIGUE CRACKING OF THE LONGERON SPLICE FITTINGS AT STRINGER 11\BOEING CO\747-100 SERIES\747-100B S |
AD 00-10-51 | DETECT AND CORRECT CRACKING OR FRACTURING OF THE TENSION BOLTS ON THE SIDE LOAD UNDERWING FITTINGS ON THE STRUT\BOEING |
AD 00-11-01 | ENSURE THAT INSULATION BLANKETS CONSTRUCTED OF METALLIZED POLYETHYLENETERAPHTHALATE (MPET) ARE REMOVED FROM THE FUSELA |
AD 00-11-02 | ENSURE THAT INSULATION BLANKETS CONSTRUCTED OF METALLIZED POLYETHYLENETERAPHTHALATE (MPET) ARE REMOVED FROM THE FUSELA |
AD 00-11-04 | PREVENT THE EXHAUST STACK FROM DETACHING FROM THE TURBOCHARGER DUE TO FAILURE OF THE V-BAND EXHAUST CLAMP\COMMANDER AI |
AD 00-11-05 | DETECT AND CORRECT CRACKS IN THE SPAR PLATES\AIR TRACTOR INC\AT-301\AT-401\AT-401A\AT-401B\AT-501 |
AD 00-11-06 | PREVENT EXPOSURE OF ELECTRICAL CONDUCTOR, WHICH COULD PERMIT ARCING FROM THE WIRE TO THE CONDUIT AND CREATE A POTENTIA |
AD 00-11-07 | PREVENT THE LEAKAGE OF FUEL INTO THE FORWARD CARGO BAY\BOEING CO\747-200B SERIES\747-200C SERIES\747-200F SERIES\747-3 |
AD 00-11-11 | PREVENT FATIGUE CRACKING OF THE AFT WHEEL WELL BULKHEAD\BOEING CO\777-200 SERIES |
AD 00-11-12 | PREVENT A STAGE 14 HIGH PRESSURE COMPRESSOR (HPC) DISK FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\CF6-45A\CF6-45A2\CF6-5 |
AD 00-11-13 | PREVENT THE FUEL BOOST PUMP WIRING FROM CHAFING\FOKKER SVCS\F.28 MARK 1000\F.28 MARK 2000\F.28 MARK 3000\F.28 MARK 400 |
AD 00-11-14 | TO ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION IS CRITICAL FOR FLIGHT IN |
AD 00-11-15 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\ALLIEDSIGNAL INC\ALF502R-3\ALF502R-3A\ALF502R-4\ALF502R-5\A |
AD 00-11-16 | DETECT AND CORRECT FATIGUE CRACKING OF THE LOWER SPAR CAPS\AYRES CORP\S2R-G5\S2RHG-T65\S2R-R1820\S2R-T15\S2R-T34\S2R-T |
AD 00-11-17 | DETECT CRACKS THAT COULD LEAD TO DELAMINATION OF THE TAIL ROTOR BLADE KEVLAR TIE-BAR (KEVLAR TIE-BAR), LOSS OF TAIL RO |
AD 00-11-19 | PREVENT NON-DEPLOYMENT OF AN ESCAPE SLIDE DURING AN EMERGENCY EVACUATION, TO DETECT DAMAGED DISCONNECT HOUSINGS IN THE |
AD 00-11-20 | PREVENT DAMAGE TO BONDED SKIN PANELS TO GO UNDETECTED, WHICH COULD RESULT IN FAILURE OF THE BONDED SKIN PANELS\BOMBARD |
AD 00-11-22 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\ALLISON ENGINE CO INC\AE 3007A\AE 3007A1\AE 3007A1/1\AE 300 |
AD 00-11-24 | DETECT AND CORRECT DAMAGE OF THE NOSE LANDING GEAR (NLG) DOWNLOCK SUPPORT\BRITISH AEROSPC (ENGLAND)\ATP |
AD 00-11-25 | PREVENT AN INADVERTENT INCREASE IN THRUST\AIRBUS INDUSTRIE\A320 MODEL -232\A320 MODEL -233 |
AD 00-11-29 | PREVENT FAILURE OF THE SHOULDER HARNESS\FOKKER SVCS\F.28 MARK 0070\F.28 MARK 0100\F.28 MARK 1000\F.28 MARK 2000\F.28 M |
AD 00-11-52 | PREVENT MAIN ROTOR BLADE ROOT END POCKET SEPARATION, IMPACT WITH MAIN ROTOR OR TAIL ROTOR BLADES\SIKORSKY AIRCRFT CORP |
AD 00-11-52-E | LETTER AD 2000-11-52 PREVENT MAIN ROTOR BLADE ROOT END POCKET SEPARATION, IMPACT WITH MAIN ROTOR OR TAIL ROTOR BLA |
AD 00-12-03 | PREVENT CRACKING OF THE PLATE SLATS, INCREASED HELICOPTER VIBRATION, LOSS OF TRANSMISSION MOUNTING INTEGRITY, AND SUBS |
AD 00-12-05 | PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE\INTNL AERO ENGINES AG (IAE)\V2500-A1\V2522-A5\V2524-A5\V252 |
AD 00-12-07 | PREVENT CORROSION IN THE INBOARD AND OUTBOARD BEARING HOUSINGS OF THE SUPPORT ASSEMBLY OF THE MAIN LANDING GEAR (MLG)\ |
AD 00-12-08 | PREVENT AFT ENGINE MOUNT LINK FAILURE\GENERAL ELECTRIC AIRCRFT ENGINES\CF6-80C2A8\CF6-80C2D1F\CF6-80C2A1\CF6-80C2A2\CF |
AD 00-12-09 | PREVENT OVERHEATING OF THE AIR CONDITIONING SOFT-START CONTROL ASSEMBLY, DAMAGE IN THE LOWER TAILCONE\SIKORSKY AIRCRFT |
AD 00-12-11 | PREVENT FATIGUE CRACKS IN THE BOLT HOLES OF THE WING SPARS\AIRBUS INDUSTRIE\A300 MODEL B4-600 SERIES\A300 MODEL B4-600 |
AD 00-12-14 | PREVENT FALSE WARNING OF A HOT ENGINE EXHAUST TAILPIPE AND INTERMITTENT SIGNAL FAILURE\SAAB AIRCRFT AB\SAAB 340B\SAAB |
AD 00-12-17 | DETECT FATIGUE CRACKS IN THE PITCH LOAD FITTINGS OF THE WING FRONT SPAR\BOEING CO\767-200 SERIES\767-300 SERIES\767-30 |
AD 00-12-20 | PREVENT FRACTURE OF THE LEAD SCREW OF THE POSITION 1 FLAP SCREW JACK\AIRBUS INDUSTRIE\A310 MODEL 200 SERIES\A310 MODEL |
AD 00-12-21 | PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT AND CONSEQUENT REDUCED CONTROLLABILITY OF THE AIRPLA |
AD 00-13-01 | PREVENT AN UNCONTAINED TURBINE WHEEL FAILURE\ALLISON ENGINE CO INC\AE 3007A\AE 3007A1\AE 3007A1/1\AE 3007A1/2\AE 3007A |
AD 00-13-02 | PREVENT INCORRECT OPERATION OF THE PRECOOLER DIFFERENTIAL PRESSURE SWITCHES\EMPRESA BRASILEIRA DE AERONAUTICA S A (EMB |
AD 00-13-04 | PROHIBIT DISPATCH OF AN AIRPLANE WITH AN ENGINE-MOUNTED BACKUP GENERATOR HAVING A SHEARED SHAFT; AND TO DETECT AND COR |
AD 00-13-05 | PREVENT POSSIBLE MULTIPLE FAN BLADE FAILURES\ROLLS-ROYCE PLC\RB211 TRENT 768-60\RB211 TRENT 772-60\RB211 TRENT 772B-60 |
AD 00-13-06 | PREVENT STRUCTURAL FAILURE DUE TO A CRACK OR CORROSION OF PYLON UPPER AND LOWER HINGE WEB FITTINGS (WEB FITTINGS)\SIKO |
AD 00-13-08 | PREVENT LOSS OF DRIVE TO THE TAIL ROTOR AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\EUROCOPTER DEUTSCHLAND GMBH ( |
AD 00-13-09 | PREVENT FAILURE OF THE BACKUP STRUTS IN THE LEFT AND RIGHT NACELLES DUE TO FATIGUE CRACKING\SAAB AIRCRFT AB\SAAB 2000 |
AD 00-13-51-E | LETTER AD 2000-13-51 DETECT AND CORRECT CRACKING OF THE LOWER PORTION OF THE MAIN DECK CARGO DOOR FRAMES\BOEING CO |
AD 00-14-02 | PREVENT LOSS OF COMMUNICATION BETWEEN THE FLIGHT CREW AND AIR TRAFFIC CONTROL (ATC)\BOEING CO\737-600 SERIES\737-700 S |
AD 00-14-03 | PREVENT FALSE SMOKE WARNINGS FROM THE CARGO COMPARTMENT SMOKE DETECTORS\SAAB AIRCRFT AB\SAAB 340B\SAAB SF340A |
AD 00-14-05 | ENSURE ADEQUATE ELECTRICAL BONDING BETWEEN THE WING SPAR CONNECTORS OF THE FUEL QUANTITY INDICATING SYSTEM (FQIS) AND |
AD 00-14-07 | PREVENT CRACKING OF THE REAR SPAR WEB\BOEING CO\727 SERIES\727-100 SERIES\727-100C SERIES\727-200 SERIES\727-200F SERI |
AD 00-14-08 | ACTIVATE THE PNEUMATIC WING AND TAIL DEICING BOOTS AT THE FIRST SIGNS OF ICE ACCUMULATION IS CRITICAL FOR FLIGHT IN IC |
AD 00-14-09 | PREVENT THE DISPLAY OF INCORRECT ENGINE LIMITATIONS\SHORT BROTHERS PLC\SD3-60 |
AD 00-14-10 | PREVENT CRACKING OF THE ATTACHMENT FASTENERS OF THE VERTICAL STABILIZER\MCDONNELL DOUGLAS CORP\DC-10-10\DC-10-10F\DC-1 |
AD 00-14-12 | PREVENT A POSSIBLE FLAMMABLE CONDITION, WHICH COULD RESULT IN SMOKE AND FIRE IN THE FORWARD CREW REST AREA\MCDONNELL D |
AD 00-14-13 | PREVENT CRACKING OR BREAKING OF THE DOOR HANDLE MOUNTING HUB\BOEING CO\737-200 SERIES\737-200C SERIES\737-300 SERIES\7 |
AD 00-14-14 | DETECT AND CORRECT THERMAL OXIDATION OF THE MAIN BRAKE ASSEMBLIES\BFGOODRICH AVIONICS SYSTEMS INC\MAIN BRAKE ASSEMBLIE |
AD 00-14-16 | PREVENT THE TAIL ROTOR BLADES FROM STRIKING THE TAILBOOM, SEPARATION OF THE AFT SECTION OF THE TAILBOOM WITH THE TAIL |
AD 00-14-17 | PREVENT UNCOMMANDED CHANGES IN THE SETTINGS ON THE PILOT'S AND CO-PILOT'S INSTRUMENT DISPLAYS\BOMBARDIER INC\CL-600-2B |
AD 00-14-18 | ENSURE THAT THE POWERED ROLLER PANS ARE POSITIONED PROPERLY\MCDONNELL DOUGLAS CORP\MD-11\MD-11F |
AD 00-14-51 | DETECT AND CORRECT FATIGUE CRACKS IN THE WING LOWER SPAR CAP\AIR TRACTOR INC\AT-501\AT-502\AT-502A |
AD 00-15-02 | PREVENT DAMAGE OF CERTAIN WIRE BUNDLES ROUTED TO THE FUEL TANK TRANSFER PUMPS IN THE HORIZONTAL STABILIZER, WHICH COUL |
AD 00-15-03 | PREVENT CERTAIN PROPELLER BLADE SUSPENSION FORKS FROM CRACKING, WHICH COULD RESULT IN THE LOSS OF A PROPELLER BLADE DU |
AD 00-15-06 | PREVENT ARCING OF THE POWER FEEDER CABLES AGAINST THE FUSELAGE STRUCTURE\MCDONNELL DOUGLAS CORP\DC-10-10\DC-10-15\DC-1 |
AD 00-15-08 | DETECT AND CORRECT FATIGUE CRACKING OF THE BULKHEAD WEB\BOEING CO\747-100 SERIES\747-100B SERIES\747-100B SUD SERIES\7 |
AD 00-15-10 | PREVENT FAILURE OF THE PROPELLER BLADE\MCCAULEY PROPELLER SYSTEMS\4HFR34C |
AD 00-15-12 | DETECT AND CORRECT STRESS CORROSION CRACKING IN THE FRONT SPAR OF THE CENTER SECTION OF THE HORIZONTAL STABILIZER\BOEI |
AD 00-15-13 | PREVENT SMOKE AND POSSIBLE FIRE IN THE OVERHEAD SWITCH PANEL LIGHTING CIRCUITRY DUE TO AN OVERLOAD CONDITION\MCDONNELL |
AD 00-15-14 | PREVENT PROPAGATION OF SMOKE AND FUMES IN THE COCKPIT AND PASSENGER CABIN\MCDONNELL DOUGLAS CORP\MD-11\MD-11F |
AD 00-15-17 | PREVENT HYDRAULIC FLUID LEAKAGE INTO THE AUXILIARY POWER UNIT (APU) INLET DUE TO FATIGUE VIBRATION AND CRACKING IN THE |
