Popular Standards |
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AD 99-NM-331 | PREVENT FAILURE OF THE SERVOCONTROL PISTON ROD\AIRBUS INDUSTRIE\A319-131\A319-132\A321-100\A321-111\A321-112\A321-13 |
AD 99-NM-334 | PREVENT FAILURE OF THE ENGINE FIRE EXTINGUISHER BOTTLE TO DISCHARGE, OR DISCHARGE OF THE WRONG ENGINE FIRE EXTINGUIS |
AD 99-NM-339 | PREVENT THE INGESTION OF SILL SUPPORT-LOG MATERIAL INTO THE ASPIRATOR OF THE ESCAPE SLIDE\AIRBUS INDUSTRIE\A319-131\ |
AD 99-NM-34 | PREVENT UNDETECTED ACCRETION OF ICE ON THE WINGS\BOMBARDIER INC (FORMERLY CANADAIR LTD)\CL-600-2B19 |
AD 99-NM-343 | PREVENT CRACKING OF THE SLIDING TUBE SUBASSEMBLY OF THE MAIN LANDING GEAR (MLG)\AIRBUS INDUSTRIE\A319-131\A319-132\A |
AD 99-NM-344 | PREVENT FAILURE OF THE ENGINE INTAKE DE-ICING SYSTEM\BRITISH AEROSPC\ATP SERIES |
AD 99-NM-346 | PREVENT FATIGUE CRACKING OF THE UPPER WING SKIN\BOEING\777-200 SERIES\777-300 SERIES |
AD 99-NM-347 | DETECT AND CORRECT CRACKING OR CORROSION OF THE FORWARD ATTACHMENT BOLTS OF THE ENGINE PYLON TO WING INTERFACE\BRITI |
AD 99-NM-348 | PREVENT LOOSENING OF THE LOCKNUT HOLDING THE MLG PISTON TO THE RAMROD\BRITISH AEROSPC\JETSTREAM MODEL 4101 |
AD 99-NM-350 | PREVENT FAILURE OF THE WEU OR MAWEA POWER SUPPLIES\BOEING\747-400 SERIES\747-400F\757-200 SERIES\757-200CB SERIES\75 |
AD 99-NM-351 | PREVENT ERRONEOUS NAVIGATIONAL CALCULATIONS\AIRBUS INDUSTRIE\A319-131\A319-132\A320-111\A320-200\A320-211\A320-212\A |
AD 99-NM-353 | PREVENT FAILURE OF THE RAM AIR TURBINE (RAT) TO DEPLOY IN AN EMERGENCY SITUATION\AIRBUS INDUSTRIE\A319-131\A319-132\ |
AD 99-NM-354 | PREVENT ELECTRICAL ARCING BETWEEN THE FLUORESCENT TUBE PINS AND THE LAMPHOLDERS\SAAB-SCANIA AB\SAAB 340B SERIES\2000 |
AD 99-NM-354-1 | PREVENT ELECTRICAL ARCING BETWEEN THE FLUORESCENT TUBE PINS AND THE LAMPHOLDERS, WHICH COULD BURN THE SURROUNDIN |
AD 99-NM-355 | PREVENT INCREASED LOADS ON THE UPPER WING SKIN DUE TO LOOSENESS OF THE STRINGER FITTINGS AND BOLTS AT RIBS 0 AND 2 O |
AD 99-NM-356 | PREVENT THE LANDING GEAR DOORS FROM BECOMING BLOCKED FROM OPENING DURING APPLICATION OF EMERGENCY PROCEDURES IN THE |
AD 99-NM-358 | PREVENT THE FUEL BOOST PUMP WIRING FROM CHAFING\FOKKER-VFW B V\F.28 MARK 1000\F.28 MARK 2000\F.28 MARK 3000\F.28 MAR |
AD 99-NM-359 | PREVENT THE POSSIBILITY OF A FIRE ON AN AIRPLANE DUE TO CHAFING OF THE ELECTRICAL WIRING OF THE CABIN CEILING LIGHTI |
AD 99-NM-360 | PREVENT ICE ACCUMULATION ON THE AIRPLANE LEADING EDGES\ISRAEL AIRCRFT IND LTD\1125 WESTWIND ASTRA SERIES\ASTRA SPX S |
AD 99-NM-362 | PREVENT ERRATIC OPERATION OF THE WHEEL TACHOMETERS\AIRBUS INDUSTRIE\A300-600 |
AD 99-NM-363 | DETECT AND CORRECT CRACKING OF THE MAIN CARGO DOOR SKIN AND FRAMES\BOEING\707-100 SERIES\707-100B SERIES\707-200 SER |
AD 99-NM-364 | PREVENT AN UNDETECTED DRAGGING PARKING BRAKE, AND CONSEQUENT DECREASED ACCELERATION DURING THE TAKEOFF ROLL, INCREAS |
AD 99-NM-365 | PREVENT FATIGUE CRACKING IN PRIMARY STRUT STRUCTURE AND CONSEQUENT REDUCED STRUCTURAL INTEGRITY OF THE STRUT\BOEING\ |
AD 99-NM-368 | PREVENT FAILURE OF THE BACKUP STRUTS IN THE LEFT AND RIGHT NACELLES DUE TO FATIGUE CRACKING\SAAB-SCANIA AB\2000 SERI |
AD 99-NM-369 | ENSURE ADEQUATE ELECTRICAL BONDING BETWEEN THE HORIZONTAL AND VERTICAL STABILIZERS\FOKKER-VFW B V\F.28 MARK 0070\F.2 |
AD 99-NM-371 | PREVENT DAMAGE OF THE UPPER WING LADDER PLATES\BOMBARDIER INC (FORMERLY CANADAIR LTD)\DHC-8-100 SERIES\DHC-8-200\DHC |
AD 99-NM-371-R1 | PREVENT DAMAGE OF THE UPPER WING LADDER PLATES\BOMBARDIER INC (FORMERLY CANADAIR LTD)\DHC-8-100 SERIES\DHC-8-1 |
AD 99-NM-372 | PREVENT DETACHMENT OR BREAKAGE OF WIRES IN THE TEMPERATURE SWITCH ASSEMBLIES OF THE WING ICE PROTECTION SYSTEM\RAYTH |
AD 99-NM-373 | PREVENT CORROSION OF THE AXLE OF THE MAIN LANDING GEAR\BOEING\777-200 SERIES |
AD 99-NM-374 | PREVENT ICE ACCUMULATION ON THE AILERON CONTROL CABLES AND/OR MAIN LANDING GEAR (MLG) DOOR AND DOOR SEAL DURING FLIG |
AD 99-NM-378 | DETECT FATIGUE CRACKING OF CERTAIN STRINGERS, AND AROUND CERTAIN FASTENER HOLES OF THE LOWER SKIN OF THE WINGS\BOEIN |
AD 99-NM-380 | DETECT FATIGUE CRACKING OF THE FORWARD PRESSURE BULKHEAD, WHICH COCOULD RESULT IN RAPID DECOMPRESSION OF THE AIRPLAN |
AD 99-NM-381 | PREVENT CHAFING AND RESULTANT WEAR DAMAGE ON THE INBOARD FLAP DRIVE TRUNNIONS OR ON THE PROTECTIVE HALF-SHELLS\AIRBU |
AD 99-NM-40 | PREVENT FAILURE OF THE FLIGHT IDLE BACKUP SYSTEM\DORNIER-WERKE G M B H\328-100 SERIES |
AD 99-NM-41 | PREVENT IMPROPER LATCHING OF LATCH PINS AND THE MATING LATCH CAM ON THE CARGO DOOR\BOEING\747-100 SERIES\747-100B\747- |
AD 99-NM-46 | DETERIORATION OF CABLE GUARDS IN THE LATERAL CONTROL SYSTEM\BOEING\747-100 SERIES\747-100B\747-200 SERIES\747-200B SER |
AD 99-NM-47 | PREVENT A SHORT CIRCUIT AND OVERHEATING OF THE TRANSIENT SUPPRESSION DIODE\BOEING\737-100 SERIES\737-200 SERIES (T-43) |
AD 99-NM-48 | PREVENT MALFUNCTION OF THE LOW PRESSURE NON-RETURN VALVE IN THE AIRBORNE GROUND CHECK MODULE (AGCM) OF THE RAM AIR TUR |
AD 99-NM-51 | PREVENT CORROSION IN THE INBOARD AND OUTBOARD BEARING HOUSINGS OF THE SUPPORT ASSEMBLY OF THE MAIN LANDING GEAR (MLG)\ |
AD 99-NM-52 | PREVENT FAILURE OF THE ELEVATOR TRIM CABLE DUE TO FATIGUE\SHORT BROTHERS\SD3-60 |
AD 99-NM-53 | PREVENT DEGRADATION OF THE STRUCTURAL CAPABILITIES OF THE AFFECTED AIRPLANES\BOEING\727-100 SERIES\727-100C SERIES\727 |
AD 99-NM-54 | PREVENT CHAFING AS A RESULT OF IMPROPER INSTALLATION OF THE CABLE ASSEMBLY OF THE LOWER BODY ANTI-COLLISION LIGHT\BOEI |
AD 99-NM-55 | PREVENT AN ASYMMETRIC RUDDER FORCE CONDITION\DEHAVILLAND\DHC-8 SERIES |
AD 99-NM-57 | PREVENT CORRODED FUSE PINS\BOEING\757-200 SERIES\757-200PF SERIES |
AD 99-NM-58 | CORROSION AND SUBSEQUENT FRACTURE OF THE FUSE PINS IN THE MAIN LANDING GEAR ATTACHMENT AND SUPPORT FITTINGS\BOEING\777 |
AD 99-NM-62 | PREVENT OVERHEATING, MELTING, AND SUBSEQUENT FAILURE OF THE POWER FEEDER TERMINALS\BOEING\737-600 SERIES\737-700 SERIE |
AD 99-NM-63 | PREVENT JAMMING OF THE FLAP JACKSCREWS\DASSAULT AVI PARIS FRANCE (SEE AVIONS MARCEL DASSAULT A M D )\FALCON 2000\FALCO |
AD 99-NM-69 | PREVENT DETACHMENT OF AN ELEVATOR TAB PUSH ROD DUE TO A DETACHED NUT AT EITHER END ATTACHMENT OF A PUSH ROD\BOEING\737 |
AD 99-NM-70 | PREVENT DAMAGE TO THE FUEL FEED PIPE, WHICH COULD RESULT IN FUEL LEAKS AND AN INCREASED POTENTIAL FOR FIRE ON THE AIRP |
AD 99-NM-71 | PREVENT WIRE CHAFING AND DAMAGE\MCDONNELL DOUGLAS CORP\MD-11 SERIES\MD-11F SERIES |
AD 99-NM-72 | PREVENT CRACKING OF THE DIAGONAL BRACE OF THE NACELLE STRUT\BOEING\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD 99-NM-73 | PREVENT FATIGUE CRACKING OF THE FUSELAGE SKIN AND BONDED DOUBLER AREA ABOVE THE FORWARD ENTRY DOORWAY\BOEING\727-100 S |
AD 99-NM-74 | PREVENT DELAMINATION OF THE COLD-BONDED DOUBLERS\BOEING\727-100 SERIES\727-100C SERIES\727-200 SERIES |
AD 99-NM-75 | PREVENT CRACKING OF THE REAR SPAR WEB\BOEING\727 SERIES |
AD 99-NM-78 | DETECT AND CORRECT CHAFING OF THE DIRECT CURRENT POWERED FLOAT SWITCH WIRING INSULATION IN THE CENTER FUEL TANK AND TH |
AD 99-NM-80 | PREVENT THE TURBINE AIR DISCHARGE DUCT IN THE AIR CONDITIONING SYSTEM FROM DISCONNECTING FROM THE CAU OR WATER SEPARAT |
AD 99-NM-81 | FATIGUE CRACKING OF THE LOWER CORNERS OF THE DOOR FRAME AND CROSS BEAM OF THE FORWARD CARGO DOOR\BOEING\737-100 SERIES |
AD 99-NM-82 | DETECT AND CORRECT FATIGUE CRACKING OF THE INNER FLANGE OF FUSELAGE FRAME FR73A\AIRBUS INDUSTRIE\A300-600\A300-600R\A3 |
AD 99-NM-83 | PREVENT REDUCED STRUCTURAL INTEGRITY OF THE WING FLAP SUPPORT STRUCTURE\EMPRESA BRASILEIRA DE AERONAUTICA S A\EMB-145 |
AD 99-NM-84 | PREVENT FATIGUE CRACKING OF THE CORNERS OF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFT CARGO DOOR\BOEING\737-200 SER |
AD 99-NM-85 | PREVENT IN-FLIGHT SEPARATION OF THE MAIN DECK CARGO DOOR FROM THE AIRPLANE\BOEING\737-200 SERIES (T-43)\737-300 SERIES |
AD 99-NM-88 | FATIGUE CRACKING OF THE UPPER AND LOWER CHORDS OF THE WING FRONT SPAR\BOEING\747-100 SERIES\747-200 SERIES |
AD 99-NM-89 | PREVENT HOLES IN THE INFLATABLE PORTION OF THE SLIDE/RAFT EVACUATION SYSTEM\BOEING\757-200 SERIES\757-300 SERIES |
AD 99-NM-91 | DETECT AND CORRECT FATIGUE CRACKING AND EVENTUAL FAILURE OF THE ATTACHMENT FITTINGS OF THE NUMBER 3 WING SPOILERS\AIRB |
AD 99-NM-92 | PREVENT THE FREEZING OF MOISTURE ENTRAPPED IN THE FIBERGLASS/FOAM INSULATION INSTALLED ON THE FUSELAGE STRUCTURE BETWE |
AD 99-NM-94 | PREVENT REDUCED CONTROLLABILITY OF THE AIRPLANE\AIRBUS INDUSTRIE\A320 SERIES |
AD 99-NM-96 | PREVENT FAILURE OF THE TITANIUM THRUST LINKS DUE TO THE LIFE LIMIT OF THE THRUST LINKS\AIRBUS INDUSTRIE\A319-131\A320- |
AD 99-NM-98 | FAILURE OF THE MANEUVERING ACTUATOR PISTON ROD OF THE MAIN LANDING GEAR (MLG)\EMPRESA BRASILEIRA DE AERONAUTICA S A\EM |
AD 99-NM-98-R1 | R1 PREVENT FAILURE OF THE MANEUVERING ACTUATOR PISTON ROD OF THE MAIN LANDING GEAR (MLG)\EMPRESA BRASILEIRA DE A |
AD 99-SW-04 | PREVENT AN EMERGENCY FLOTATION GEAR NITROGEN CYLINDER FROM EXPLODING WITH RESULTANT HIGH VELOCITY SHRAPNEL\EUROCOPTER |
AD 99-SW-05 | PREVENT FAILURE OF AN OIL COOLER FAN SPLINED DRIVE SHAFT (SHAFT)\EUROCOPTER DEUTSCHLAND (FORMERLY MESSERSCHMITT-BOLKOW |
AD 99-SW-07 | DETECT FIN ASSEMBLIES WITH REDUCED SKIN THICKNESS WHICH, IF NOT CORRECTED, REDUCE THE STRENGTH OF THE SKIN, AND COULD |
AD 99-SW-08 | PREVENT CONTACT BETWEEN THE WIRE HARNESS AND THE FUEL LINE ASSEMBLY\ROBINSON HELICPTR CO\R-44 |
AD 99-SW-12 | PREVENT USE OF A GRIP ASSEMBLY THAT MAY CRACK\ROBINSON HELICPTR CO\R-44 |
AD 99-SW-13 | PREVENT FAILURE OF THE BOLTS THAT SECURE THE HOIST ARM LOWER FITTING\EUROCOPTER FRANCE (FORMERLY AEROSPATIALE)\AS 332C |
AD 99-SW-14 | PREVENT LOSS OF ELECTRICAL CONTINUITY\EUROCOPTER FRANCE (FORMERLY AEROSPATIALE)\SA366G1 |
AD 99-SW-28 | PREVENT FAILURE OF A MAIN ROTOR PITCH CONTROL LINK ROD-END SPHERICAL BEARING\AGUSTA S P A (FORMERLY SIAI MARCHETTI S P |
AD 99-SW-30 | PREVENT FATIGUE FAILURE OF THE MAST OR TRUNNION\BELL HELICPTR TEXTRON ***(SEE CA DEPT OF FORESTRY CONTNTL COPTERS GARL |
AD 99-SW-34 | PREVENT DAMAGE TO A TAIL ROTOR BLADE (BLADE), LOSS OF TAIL ROTOR CONTROL, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICO |
AD 99-SW-35 | PREVENT FAILURE OF THE SPAR TUBE, SEPARATION OF THE HORIZONTAL STABILIZER AND IMPACT WITH THE MAIN OR TAIL ROTOR, AND |
AD 99-SW-35-1 | PREVENT FAILURE OF THE SPAR TUBE, SEPARATION OF THE HORIZONTAL STABILIZER AND IMPACT WITH THE MAIN OR TAIL ROTOR, |
AD 99-SW-37 | PREVENT OVERHEATING OF THE AIR CONDITIONING SOFT-START CONTROL ASSEMBLY, DAMAGE IN THE LOWER TAILCONE, A FIRE, AND SUB |
AD 99-SW-39 | PREVENT FAILURE OF THE CROSS-BEAM THAT COULD LEAD TO ROTATION OF THE MAIN GEARBOX\EUROCOPTER FRANCE (FORMERLY AEROSPAT |
AD 99-SW-42 | PREVENT TIP PATH PLANE SEPARATION, INCREASED VIBRATIONS, DAMAGE TO THE MAIN ROTOR SYSTEM, AND SUBSEQUENT LOSS OF CONTR |
AD 99-SW-43 | PREVENT THE FRACTURE OF A FLAPPING BEARING TO YOKE ATTACHMENT BOLT (BOLT), FAILURE OF THE BEARING AND YOKE INTERFACE, |
AD 99-SW-45 | DETECT CRACKS THAT COULD LEAD TO DELAMINATION OF THE TAIL ROTOR BLADE KEVLAR TIE-BAR (KEVLAR TIE-BAR)\EUROCOPTER FRANC |
AD 99-SW-54 | PREVENT FUEL STARVATION OF THE ENGINE WHILE THE FUEL GAGE INDICATES FUEL REMAINING IN THE TANK, ENGINE FLAMEOUT, AND A |
AD 99-SW-57 | PREVENT FAILURE OF THE SHAFT, LOSS OF THE TAIL ROTOR, AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\SCHWEIZER AIRCR |
AD 99-SW-65 | PREVENT FATIGUE FAILURE OF A TT STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE), AND SUBSEQUENT LOSS OF CONTROL OF THE HELIC |
AD 99-SW-65-R1 | R1 PREVENT FATIGUE FAILURE OF A TENSION-TORSION (TT) STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE), AND SUBSEQUENT L |
AD 99-SW-67 | PREVENT FATIGUE FAILURE OF A TENSION-TORSION (TT) STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE)\EUROCOPTER DEUTSCHLAND (FO |
AD 99-SW-68 | PREVENT FATIGUE FAILURE OF A TT STRAP, LOSS OF A MAIN ROTOR BLADE (BLADE)\EUROCOPTER CANADA\BO-105LS A-3 |
AD 99-SW-77 | PREVENT FATIGUE FAILURE OF THE TAIL ROTOR (OUTPUT) DRIVE BEVEL GEAR (BEVEL GEAR), LOSS OF TAIL ROTOR DRIVE\EUROCOPTER |
AD 99-SW-78 | PREVENT POWER LOSS DUE TO FUEL STARVATION, AN ENGINE FLAMEOUT, AND A SUBSEQUENT FORCED LANDING\EUROCOPTER FRANCE (FORM |
AD 99-SW-80 | DETECT A CRACK IN THE TAILBOOM SKIN AND TO PREVENT SEPARATION OF THE TAILBOOM FROM THE HELICOPTER AND SUBSEQUENT LOSS |
AD 99-SW-81 | PREVENT FAILURE OF THE SECOND STAGE LOWER PLANETARY PLATE (PLATE), P/N 6435-20229-102, DUE TO FATIGUE CRACKING\SIKORSK |
AD 99-SW-82 | PREVENT CRACKING OF THE PLATE SLATS, INCREASED HELICOPTER VIBRATION, LOSS OF TRANSMISSION MOUNTING INTEGRITY, AND SUBS |
AD 99-SW-84 | PREVENT A JAMMED FLIGHT CONTROL AND SUBSEQUENT LOSS OF CONTROL OF THE HELICOPTER\BELL HELICPTR TEXTRON ***(SEE CA DEPT |
AD T83-25-51 | ROTOR HEAD HORIZONTAL HINGE PINS REVISION 1\BOEING DEFENSE & SPACE GROUP\234 |
AD T84-05-51 | COLLECTIVE SLEEVES\BELL HELICPTR TEXTRON\214B-1\214B\214ST |
AD T84-18-51 | MAIN ROTOR SPINDLES\BELL HELICPTR TEXTRON\214ST |
AD T85-21-51 | CRITICAL AIRFRAME SELF-LOCKING NUTS\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD T91-17-51 | THRUST REVERSERS\BOEING CO\767-200 SERIES\767-300 SERIES\767-300F SERIES |
AD T99-06-51 | AD T99-06-51 PREVENT PROPELLER HUB CRACKS\HARTZELL PROPELLER INC\HD-E6C-3 |
AD T99-12-52 | AD T99-12-52 PREVENT FUEL TANK EXPLOSION RESULTING FROM ARC-THROUGH OF THE FUEL BOOST PUMP WIRING CONDUITS\BOEING CO |
FAA 1000.36 | FAA WRITING STANDARDS |
FAA 1050.1 | ENVIRONMENTAL IMPACTS: POLICIES AND PROCEDURES |
FAA 1050.10 | PREVENTION, CONTROL, AND ABATEMENT OF ENVIRONMENTAL POLLUTION AT FAA FACILITIES |
FAA 1050.14 | POLYCHLORINATED BIPHENYLS (PCBS) IN THE NATIONAL AIRSPACE SYSTEM |
FAA 1050.20 | AIRWAY FACILITIES ASBESTOS CONTROL |
FAA 1100.157 | NATIONAL SYSTEMS ENGINEERING DIVISIONS MAINTENANCE PROGRAM PROCEDURES, OPERATIONAL SUPPORT (AOS) |
FAA 1100.87 | ROUTING SYMBOL STANDARDS |
FAA 1110.110 | RESEARCH, ENGINEERING, AND DEVELOPMENT ADVISORY COMMITTEE |
FAA 1110.76 | AIR TRAFFIC PROCEDURES ADVISORY COMMITTEE |
FAA 1200.22 | NAS DATA AND INTERFACE EQUIPMENT USED BY OUTSIDE INTERESTS |
FAA 1280.1 | PROTECTING PRIVACY OF INFORMATION ABOUT INDIVIDUALS |
FAA 1320.36 | DIRECTIVES DISTRIBUTION FOR REGIONAL AIRPORTS DIVISIONS |
FAA 1370.79 | INTERNET POLICY |
FAA 1370.81 | ELECTRONIC MAIL |
FAA 1370.90 | INTERNET ACCESS POINT CONFIGURATION MANAGEMENT |
FAA 1375.2 | STANDARD DATA ELEMENTS AND CODES--GENERAL STANDARDS |
FAA 1375.4 | STANDARD DATA ELEMENTS AND CODES -- FACILITY IDENTIFICATION AND SUPPLEMENTAL STANDARDS |
FAA 1380.26 | CROSS UTILIZATION OF REGIONAL F&E AND OPERATIONS MANPOWER |
FAA 1380.40 | AIRWAY FACILITIES SECTOR LEVEL STAFFING STANDARD SYSTEM |
FAA 1600.2 | SAFEGUARDING CONTROLS AND PROCEDURES FOR CLASSIFIED NATIONAL SECURITY INFORMATION AND SENSITIVE UNCLASSIFIED INFORMATION |
FAA 1600.6 | PHYSICAL SECURITY MANAGEMENT PROGRAM |
FAA 1600.72 | CONTRACTOR AND INDUSTRIAL SECURITY PROGRAM |
FAA 1600.73 | CONTRACTOR AND INDUSTRIAL SECURITY PROGRAM OPERATING PROCEDURES |
FAA 1800.66 | CONFIGURATION MANAGEMENT POLICY |
FAA 2100.6 | FLIGHT RESTRICTIONS IN THE PROXIMITY OF THE PRESIDENTIAL AND OTHERPARTIES |
FAA 2150.3 | COMPLIANCE AND ENFORCEMENT PROGRAM |
FAA 3000.22 | AIR TRAFFIC SERVICES TRAINING |
FAA 3300.28 | FEDERAL AVIATION ADMINISTRATION MOBILITY REQUIREMENT |
FAA 3450.32 | QUALITY MANAGEMENT AWARDS PROGRAM |
FAA 3550.10 | PAY ADMINISTRATION (GENERAL) |
FAA 3770.12 | PROCESSING DISCIPLINARY/ADVERSE ACTIONS UNDER THE PASS/FAA AGREEMENT |
FAA 3900.19 | FAA OCCUPATIONAL SAFETY AND HEALTH PROGRAM |
FAA 4100.24 | FAA GENERAL MAINTENANCE MANUAL |
FAA 4400.46 | DISADVANTAGED BUSINESS ENTERPRISE PROGRAM |
FAA 4420.4 | SPACE ACQUISITION |
FAA 4441.16 | ACQUISITION OF TELECOMMUNICATIONS SYSTEMS, EQUIPMENT, AND SERVICES |
FAA 4450.12 | TECHNICAL SUPPORT SERVICES CONTRACT (TSSC-II) MANAGEMENT/ADMINISTRATION HANDBOOK |
FAA 4450.8 | TECHNICAL SUPPORT SERVICE CONTRACT (TSSC) OPERATIONS HANDBOOK |
FAA 4500.3 | PARTICIPATION IN THE FEDERAL CATALOG SYSTEM |
FAA 4600.46 | DISADVANTAGED BUSINESS ENTERPRISE PROGRAM |
FAA 4650.20 | REPORTING AND REPLACEMENT OF ITEMS FAILING UNDER WARRANTY |
FAA 4800.2 | UTILIZATION AND DISPOSAL OF EXCESS AND SURPLUS PERSONAL PROPERTY |
FAA 6000.36 | COMMUNICATIONS DIVERSITY |
FAA 6000.41 | CONTRACTOR-ASSISTED MAINTENANCE FOR THE NATIONAL AIRSPACE SYSTEM |
FAA 6030.20 | ELECTRICAL POWER POLICY |
FAA 6320.10 | ELECTRONIC EQUIPMENT MODIFICATION HANDBOOK WEATHER FIXED MAP UNIT (WFMU) |
FAA 6330.5 | MAINTENANCE OF AIRPORT SURFACE DETECTION EQUIPMENT (ASDE-3) COLLOCATED WITH AIRPORT MOVEMENT AREA SAFETY SYSTEM (AMASS) |
FAA 6350.10 | ELECTRONIC EQUIPMENT MODIFICATION HANDBOOK WEATHER FIXED MAP UNIT (WFMU) |
FAA 6365.3 | MAINTENANCE OF THE MODE SELECT (MODE-S) BEACON SYSTEM |
FAA 6410.17 | ELECTRONIC EQUIPMENT MODIFICATION HANDBOOK DIGITAL BRIGHT RADAR INDICATOR TOWER EQUIPMENT (DBRITE) |
FAA 6430.7 | FAA LONG RANGE RADAR (LRR) EVALUATION PLAN FOR JOINT-USE FACILITIES |
FAA 6480.17 | TERMINAL FACILITY MODERNIZATION/RELOCATION SURVEY AND EVALUATION HANDBOOK |
FAA 6480.21 | MAINTENANCE OF THE CENTER-TERMINAL RADAR APPROACH CONTROL (TRACON)AUTOMATION SYSTEM (CTAS) FOR TRAFFIC MANAGEMENT ADVI |
FAA 6500.13 | IMPLEMENTATION OF 25 KHZ CHANNEL SPACING IN THE VHF BAND (118.0 TO136.0 MHZ) |
FAA 6500.15 | DOWN SCOPE RADIO CONTROL EQUIPMENT (DSRCE) PROJECT IMPLEMENTATION PLAN |
FAA 6530.3 | MAINTENANCE OF DIRECTION FINDER (DF) EQUIPMENT |
FAA 6530.6 | SYSTEM PROGRAM PLAN AND SYSTEM IMPLEMENTATION PLAN VERY HIGH FREQUENCY DIRECTION FINDER TYPE FA-9964 |
FAA 6540.5 | MAINTENANCE OF RADIO COMMUNICATIONS LINK (RCL) SYSTEMS |
FAA 6550.7 | ELECTRONIC EQUIPMENT MODIFICATION HANDBOOK-TOWER DATA LINK SERVICE |
FAA 6560.12 | RUNWAY VISUAL RANGE SYSTEM DRAWINGS |
FAA 6560.23 | RUNWAY VISUAL RANGE (RVR) PROGRAM MANAGEMENT PLAN PROJECT IMPLEMENTATION PLAN |
FAA 6560.29 | NEW GENERATION RUNWAY VISUAL RANGE SYSTEM |
FAA 6600.23 | GENERAL COMMUNICATIONS HANDBOOK |
FAA 6600.25 | PROJECT IMPLEMENTATION PLAN INTEGRATED COMMUNICATIONS SWITCHING SYSTEM (ICSS) |
FAA 6600.28 | SMALL TOWER VOICE SWITCH PROJECT IMPLEMENTATION PLAN |
FAA 6620.4 | PROJECT IMPLEMENTATION PLAN MULTICHANNEL VOICE RECORDER SYSTEM |
FAA 6650.11 | RADIO SIGNALING EQUIPMENT (RSE) PROJECT IMPLEMENTATION PLAN |
FAA 6650.7 | AIRPORT COMMUNICATIONS MEDIA/EQUIPMENT SELECTION CRITERIA |
FAA 6670.11 | PROJECT IMPLEMENTATION PLAN MULTICHANNEL VOICE RECORDER PROJECT HIGH CAPACITY VOICE RECORDERS |
FAA 6740.3 | SUPPORT DRAWINGS FOR NONDIRECTIONAL BEACON INSTALLATION |
FAA 6740.4 | NONDIRECTIONAL BEACON (NDB) INSTALLATION STANDARDS HANDBOOK |
FAA 6750.19 | INSTRUMENT LANDING SYSTEM INSTALLATION DRAWINGS |
FAA 6750.36 | SITE SURVEY, SELECTION, AND ENGINEERING DOCUMENTATION FOR ILS AND ANCILLARY AIDS |
FAA 6750.47 | END-FIRE GLIDE ANTENNA INSTALLATION DRAWINGS |
FAA 6750.48 | INSTRUMENT LANDING SYSTEMS EIGHT-ELEMENT V-RING LOCALIZER ANTENNA INSTALLATION DRAWINGS |
FAA 6750.5 | MAINTENANCE OF RADIO COMMUNICATIONS LINK (RCL) SYSTEMS |
FAA 6780.5 | DME INSTALLATION STANDARDS HANDBOOK TYPE FA-9639 |
FAA 6790.12 | DOUBLE SIDEBAND DOPPLER VOR INSTALLATIONS STANDARDS HANDBOOK |
FAA 6810.2 | VERY HIGH FREQUENCY (VHF) OMNIRANGE TEST (VOT) SITING CRITERIA |
FAA 6820.10 | VOR, VOR/DME AND VORTAC SITING CRITERIA |
FAA 6820.12 | PROJECT IMPLEMENTATION PLAN FOR VHF OMNIDIRECTIONAL RANGE (VOR) AND DISTANCE MEASURING EQUIPMENT (DME) |
FAA 6820.13 | PROJECT IMPLEMENTATION PLAN FOR LOW POWER TACAN ANTENNA |
FAA 6820.9 | VOR, VOR/DME, VORTAC INSTALLATION STANDARD DRAWINGS |
FAA 6830.5 | CRITERIA FOR SITING MICROWAVE LANDING SYSTEMS (MLS) |
FAA 6850.15 | VISUAL GUIDANCE LIGHTING SYSTEMS STANDARD DRAWINGS |
FAA 6850.16 | LAMP, PAR 64 BULB, MOGUL END PRONG |
FAA 6850.17 | MEDIUM-INTENSITY APPROACH LIGHTING SYSTEM WITH RUNWAY ALIGNMENT INDICATOR LIGHTS (MALSR) |
FAA 6850.21 | OMNIDIRECTIONAL APPROACH LIGHTING SYSTEM (ODALS) |
FAA 6850.23 | MEDIUM INTENSITY APPROACH LIGHTING SYSTEM WITH RUNWAY ALIGNMENT INDICATOR LIGHTS AND RUNWAY END IDENTIFIER LIGHTS |
FAA 6850.24 | RUNWAY END IDENTIFIER LIGHTING SYSTEM |
FAA 6850.29 | MEDIUM INTENSITY APPROACH LIGHTING SYSTEM WITH RUNWAY ALIGNMENT INDICATOR LIGHTS WITH REMOTE MONITORING SUBSYSTEM (MAL |
FAA 6850.31 | REMOTE RADIO CONTROL SYSTEM FA-10266 PROJECT IMPLEMENTATION PLAN |
FAA 6850.32 | PRECISION APPROACH PATH INDICATOR WITH REMOTE MONITORING SUBSYSTEM(PAPI WITH RMS) FA-10265 PROJECT IMPLEMENTATION PLAN |
FAA 6850.34 | STANDARD DRAWINGS FOR RUNWAY END IDENTIFIER LIGHTING SYSTEM TYPE FA-10264 WITH REMOTE MONITORING SUBSYSTEM |
FAA 6850.36 | PRECISION APPROACH PATH INDICATOR (PAPI) WITH REMOTE MONITORING SUBSYSTEM (RMS) |
FAA 6850.7 | VISUAL GUIDANCE LIGHTING SYSTEMS STANDARD DRAWINGS |
FAA 6950.19 | PRACTICES AND PROCEDURES FOR LIGHTNING PROTECTION, GROUNDING, BONDING, AND SHIELDING IMPLEMENTATION |
FAA 6950.2 | ELECTRICAL POWER POLICY IMPLEMENTATION AT NATIONAL AIRSPACE SYSTEM FACILITIES |
FAA 6950.20 | FUNDAMENTAL CONSIDERATIONS OF LIGHTNING PROTECTION, GROUNDING, BONDING, AND SHIELDING |
FAA 6950.25 | POWER CONDITIONING DEVICES AT FAA FACILITIES |
FAA 6970.1 | TEMPERATURE/HUMIDITY CONTROL OF FAA FACILITIES |
FAA 7210.3 | FACILITY OPERATION AND ADMINISTRATION |
FAA 8040.4 | SAFETY RISK MANAGEMENT |
FAA 8110.20 | FAR 25.1203: IN-FLIGHT MONITORING OF FIRE DETECTION SYSTEMS |
FAA 8110.54 | INSTRUCTIONS FOR CONTINUED AIRWORTHINESS RESPONSIBILITIES, REQUIREMENTS, AND CONTENTS |
FAA 8260.38 | CIVIL UTILIZATION OF GLOBAL POSITIONING SYSTEM (GPS) |
FAA 8260.50 | UNITED STATES STANDARD FOR WIDE AREA AUGMENTATION SYSTEM (WAAS) |
FAA AC 120-72 | MAINTENANCE RESOURCE MANAGEMENT TRAINING |
FAA AC 140-7 | FAA CERTIFIED REPAIR STATIONS DIRECTORY |
FAA AC 20-12 | USE OF SOCIETY OF AUTOMOTIVE ENGINEERS (SAE) CLASS H11 BOLTS |
FAA AC 20-152 | RTCA, INC, DOCUMENT RTCA/DO-254, DESIGN ASSURANCE GUIDANCE FOR AIRBORNE ELECTRONIC HARDWARE |
FAA AC 20-153 | ACCEPTANCE OF DATA PROCESSES AND ASSOCIATED NAVIGATION DATABASES |
FAA AC 23-19 | AIRFRAME GUIDE FOR CERTIFICAITON OF PART 23 AIRPLANES |
FAA AC 25.613-1 | MATERIAL STRENGTH PROPERTIES AND MATERIAL DESIGN VALUES |
FAA AC 25.856-1 | THERMAL/ACOUSTIC INSULATION FLAME PROPAGATION TEST METHOD DETAILS |
FAA AC 39-8 | CONTINUED AIRWORTHINESS ASSESSMENTS OF POWERPLANT AND AUXILIARY POWER UNIT INSTALLATIONS OF TRANSPORT CATEGORY AIRPLAN |
FAA AC 90-23 | AIRCRAFT WAKE TRUBULENCE |
FAA N 8200.73 | CATEGORY I THRESHOLD CROSSING HEIGHTS |
FAA ORDER 1375.1 | DATA MANAGEMENT |
FAA ORDER 7210.33 | DIGITAL TERRAIN MAP VERIFICATION PROCEDURES |
FAA RD 75-110 | ANALYSIS OF AIRFIELD RUNWAY ROUGHNESS CRITERIA |
FAA-C-2309 | CONSTRUCTION AND INSTALLATION OF RUNWAY VISUAL RANGE SYSTEMS AT AIRPORTS DESIGNATED FOR CAT I AND CAT II OPERATIONS |
FAA-C-2626 | CONSTRUCTION OF A MEDIUM INTENSITY APPROACH LIGHTING SYSTEM WITH RUNWAY ALIGNMENT INDICATOR LIGHTS (MALSR) AND OF A RUNW |
FAA-C-2637 | CONSTRUCTION OF VOR, VOR/DME, OR VORTAC FACILITY WITH 21-FOOT OR 32-FOOT DIAMETER COUNTERPOISE AND EQUIPMENT BUILDING |
FAA-D-2494 | TECHNICAL INSTRUCTION BOOK MANUSCRIPT: ELECTRONIC, ELECTRICAL, AND MECHANICAL EQUIPMENT, REQUIREMENTS FOR PREPARATION OF |
FAA-E-2204 | DIESEL ENGINE GENERATOR SETS IOKW TO 750KW |
FAA-E-2470 | TRANSPARENT PLASTIC WINDOW SHADES |
FAA-E-2492/2 | CATEGORY I INSTRUMENT LANDING SYSTEM EQUIPMENT REQUIREMENTS |
FAA-E-2660 | ATCRBS OPEN ARRAY ANTENNA (FIVE-FOOT) |
FAA-E-2678/6 | VOR/VORTAC EQUIPMENT REPLACEMENT AND FACILITY MODERNIZATION PART 6 - DME/TACAN TRANSPONDER EQUIPMENT |
FAA-E-2697 | LOW-LEVEL WIND SHEAR ALERT SYSTEM |
FAA-E-2756 | FOUR-BOX PRECISION APPROACH PATH INDICATOR |
FAA-E-2790 | AIRPORT SURVEILLANCE RADAR TRANSMISSION SYSTEM, VIDEO, FIBER OPTIC |
FAA-E-982 | PAR-56 LAMPHOLDER |
FAA-STD-008 | SITING AND INSTALLATION STANDARDS FOR RUNWAY VISUAL RANGE EQUIPMENT FOR CATEGORY I AND II OPERATION |
FAA-STD-029 | SELECTION AND IMPLEMENTATION OF TELECOMMUNICATIONS STANDARDS |
FAA-STD-049 | FIBER OPTIC TELECOMMUNICATION SYSTEMS AND EQUIPMENT |
TSO CIMA | TSO-C IMA, INTERGRATED MODULAR AVIONICS HARDWARE ELEMENTS |
