| Doc Number |
Title |
| AD.00.CE.01 |
AD 2000-CE-01 Prevent The Tail-fuselage Hinge Failing |
| AD.00.CE.02 |
AD 2000-CE-02 Prevent Chafing Between the Wing Fuel Quantity Wiring Harness and the Internal Wing Harness Supports at Each Wing Rib Location |
| AD.00.CE.03 |
AD 2000-CE-03 Correct Chafing Damage and Consequent Loss of Engine Oil Caused by Rubbing Pipes |
| AD.00.CE.05 |
AD 2000-CE-05 Prevent Structural Failure Of The Wing Due To Fatigue Cracking (Applicable to MORAVAN a.s. Model Z-242L Airplanes) |
| AD.00.CE.06 |
AD 2000-CE-06 Correct the Misrouted Rudder Control Cable and Consequent Guard Pin Wear or Fraying of the Cables with Loss of Rudder Control |
| AD.00.CE.09 |
AD 2000-CE-09 Detect and Correct Cracks in the Wing Spar Assemblies and Assure the Operational Safety of the Above-Referenced Airplanes |
| AD.00.CE.09.1 |
AD 2000-CE-09 Detect and Correct Cracks in the Wing Spar Assemblies |
| AD.00.CE.10 |
AD 2000-CE-10 Assure That The Copilot's NAV "FLAG" Displays Are Based On The Copilot's Selected NAV Source |
| AD.00.CE.12 |
AD 2000-CE-12 Detect, Correct, And Prevent Further Cracking In The Rudder Quadrant Structure Caused By Incorrectly Installed D-washers |
| AD.00.CE.13 |
AD 2000-CE-13 FMC From Retaining Original Information When An Edit Is Made To A Procedure Or Flight Plan (Applicable to Rockwell Collins, Inc. FMC-4200, FMC-5000, and FMC-6000 Flight Management Computers) |
| AD.00.CE.14 |
AD 2000-CE-14 Unwarranted Display Of The ADC Flag When Switching Static Air Sources (Applicable to Rockwell Collins, Inc. ADC-85, ADC-85A, ADC-850D, and ADC-850F Air Data Computers) |
| AD.00.CE.15 |
AD 2000-CE-15 Correct the Lack of a Firewall Seal and Consequent Progression of Fire and Smoke Through the Firewall Panel Into the Flight Compartment or Cabin in the Event of an Engine Compartment Fire |
| AD.00.CE.16 |
AD 2000-CE-16 Prevent Failure of the Nose Landing Gear (NLG) Upper Strut Caused by Cracking In the Area of the Seeger Retaining Ring Groove |
| AD.00.CE.17 |
AD 2000-CE-17 Fatigue Failure Of Critical Structure Of The Aircraft (Applicable to Short Brothers and Harland Ltd. Models SC-7 Series 2 and SC-7 Series 3 Airplanes) |
| AD.00.CE.20 |
AD 2000-CE-20-AD Information Necessary to Activate the Pneumatic Wing and Tail Deicing Boots at the First Signs of Ice Accumulation is Critical for Flight in Icing Conditions |
| AD.00.CE.22 |
AD 2000-CE-22 Detect and Correct Damaged Rudder Cables Caused by Chafing of the Cable Against the Pulleys |
| AD.00.CE.23 |
AD 2000-CE-23 Detachment Of The Rear Spar Bracket From The Canard Rear Spar (Applicable to Eagle Aircraft (Malaysia) Sdn. Bhd. Model 150B Airplanes) |
| AD.00.CE.24 |
AD 2000-CE-24 Detect, Correct, And Prevent Future Cracks On The Original Design Landing Gear Pivots |
| AD.00.CE.25 |
AD 2000-CE-25 Provide Protection to the Blower Motor Circuit |
| AD.00.CE.26 |
AD 2000-CE-26 Continue to Detect and Correct Any Chafing Between the Map Light Switch and the Bordering Fuel Line |
| AD.00.CE.27 |
AD 2000-CE-27 Eliminate Existing And Prevent Future Fatigue Cracks In The Main Landing Gear (MLG) Hydraulic Actuator End Caps |
| AD.00.CE.28 |
AD 2000-CE-28 Correct Potential Brake Shuttle Valve Problems, Which Could Cause the Brake Assembly to Drag and Overheat |
| AD.00.CE.28.R1 |
AD 2000-CE-28 Correct Potential Brake Shuttle Valve Problems |
| AD.00.CE.29 |
AD 2000-CE-29 Correct Substandard Quality Cockpit Voice Recordings Caused by the Configuration of the Present CVR System, Which Could Affect Air Safety if Important Information that the CVR Provides is Not Available After an Accident |
| AD.00.CE.31 |
AD 2000-CE-31 Correct Damage or Cracks In the Main Landing Gear Lower Side Brace at the Upper Bolt Lug Where the Upper and Lower Side Braces Connect |
| AD.00.CE.32 |
AD 2000-CE-32 Erroneous Altitude Resolutions Causing a Reduction In the Intended Aircraft Collision Avoidance System (ACAS) or Traffic Alert and Collision Avoidance System (TCAS) Change 7 Minimum Separation Margins (Applicable to Rockwell Collins TDR-94 and TDR-94D Mode S Transponders) |
| AD.00.CE.33 |
AD 2000-CE-33 Detect and Correct Corrosion Damage to the Airbrake Levers and Bearings Caused By Collection of Water In the Air Brake Boxes Not Detected During Postflight Checks |
| AD.00.CE.34 |
AD 2000-CE-34 Correct Rudder Clevis And Elevator Control Clevis That Are Too Thin Because Of Abnormal Wear |
| AD.00.CE.36 |
AD 2000-CE-36 Prevent a Dual Engine Flameout On the Affected Airplanes by Providing a System That Automatically Turns On the Engine Igniters When Low Torque Is Sensed |
| AD.00.CE.38 |
AD 2000-CE-38 To Prevent Fuel Flow Interruption (Applicable to Raytheon Aircraft Company 90, 99, 100, 200, and 300 Series Airplanes) |
| AD.00.CE.42 |
AD 2000-CE-42 Correct the Wrong Use of Screws and Consequent Wear In the Pilot/Copilot Pedal Interconnect Tube |
| AD.00.CE.43 |
AD 2000-CE-43 To Detect And Correct Cracks In The Rear Fuselage Bulkhead (Applicable to AeroSpace Technologies of Australia Pty Ltd Airplanes) |
| AD.00.CE.44 |
AD 2000-CE-44 Prevent Structural Failure of the V-tail |
| AD.00.CE.45 |
AD 2000-CE-45 Fuel Boost Pump Wiring From Chafing (Applicable to Fairchild Aircraft, Inc., SA226 Series and SA227 Series) |
| AD.00.CE.46 |
AD 2000-CE-46 Prevent Failure of the Elevator and Rudder Attachment Brackets Because of Cracks or Corrosion Damage |
| AD.00.CE.47 |
AD 2000-CE-47 Loosening of the Throttle Friction Adjustment Beyond Its Normal Limits (Applicable to Pilatus Britten-Norman Ltd. BN-2, BN-2A, BN-2B, BN-2T, BN-2T-4, and BN2A MK. III Series Airplanes) |
| AD.00.CE.48 |
AD 2000-CE-48 Prevent the Rear Canopy Retaining Strap from Not Releasing Properly During the Emergency Egress Procedure Because of the Current Design of the Rear Canopy Emergency Release System |
| AD.00.CE.49 |
AD 2000-CE-49 Detect Cracks In The Airbrake Control System And Replace Cracked Parts With Parts Of Improved Design |
| AD.00.CE.50 |
AD 2000-CE-50 Mechanical Failure Of The Valve Stem/Seat Pinned Joint (Applicable to Cameron Balloons Ltd. (Sky Balloons) Mk1 (BR1) & Mk2 (Mistral) Burners) |
| AD.00.CE.54 |
AD 2000-CE-54 Detect And Correct Cracks In The Mlg Radius Rods |
| AD.00.CE.55 |
AD 2000-CE-55 Prevent Loss of Electrical Power to the Windshield Deicing System Due to Operation In the "LIGHT" Mode |
| AD.00.CE.56 |
AD 2000-CE-56 Fatigue Damage In The Wing And Fuselage Areas (Applicable to Twin Commander Aircraft Corporation Models 690D, 695A, and 695B Airplanes) |
| AD.00.CE.57 |
AD 2000-CE-57 Prevent Failure Of The Nose Landing Gear Steering Actuator |
| AD.00.CE.58 |
AD 2000-CE-58 Fatigue Cracking of the Main Landing Gear (MLG) (Applicable to British Aerospace Models HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series 3101 Airplanes) |
| AD.00.CE.59 |
AD 2000-CE-59 Prevent Failure Of The Vertical Fin Front Spar Fittings (Applicable to Air Tractor, Inc. Models AT-300, AT-400, AT-400A, AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-502, and AT-502B Airplanes) |
| AD.00.CE.60 |
AD 2000-CE-60 Minimize The Possibility Of Dirt Or Mud Penetrating The Cockpit (Applicable to Air Tractor, Inc. Models AT-250, AT-300, AT-301, AT-302, AT-400, AT-400A, AT-401, AT-401A, AT-402, AT-402A, AT-501, AT-502, and AT-502A Airplanes) |
| AD.00.CE.61 |
AD 2000-CE-61 Prevent Loose Flap Attachment Screws or the Loss of Flap Attachment Screws |
| AD.00.CE.63 |
AD 2000-CE-63 Failure Of The Steel Fuselage Center-section Tie Bar (Applicable to Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes) |
| AD.00.CE.64 |
AD 2000-CE-64 Failure Of The Tailplane Attachment Brackets (Applicable to Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes) (See Revising NPRM AD 2000-CE-64, April 16, 2003) |
| AD.00.CE.64 |
AD 2000-CE-64 Failure Of The Tailplane Attachment Brackets Caused By Stress Corrosion Cracking (Applicable to Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes) |
| AD.00.CE.66 |
AD 2000-CE-66 Reduced Structural Integrity In The Primary Structure Of The Airplane (Applicable to Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes) |
| AD.00.CE.67 |
AD 2000-CE-67 Detect and Remove Problem Flap Actuators From Service |
| AD.00.CE.69 |
AD 2000-CE-69 Prevent Loss Of Propeller Control Because Of Hardening Or Blocking Of The Control Cable |
| AD.00.CE.70 |
AD 2000-CE-70 Prevent Oil From Entering The Gaseous Oxygen System Service Compartment |
| AD.00.CE.73 |
AD 2000-CE-73 Single Failure Of The Elevator Servo Trim Tab System Causing Severe Elevator Flutter (Applicable to Bombardier Inc. Model Otter DHC-3 Airplanes) |
| AD.00.CE.76 |
AD 2002-CE-76 Wear Of The Rudder Control Cables At The Fairlead (Applicable to Air Tractor, Inc. Model AT-802 and AT-802A Airplanes) |
| AD.00.CE.77 |
AD 2000-CE-77 Allow the Flap Power Drive-unit Circuit Breaker to Close During Flight and Prevent Current Surges In the Flap Control System (Applicable to Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes) |
| AD.00.CE.79 |
AD 2000-CE-79 Failure of the Fuel Line Nipple or the Gascolator (Applicable to Univair Aircraft Corporation Models (ERCO) 415-C, (ERCO) 415-CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A Airplanes) |
| AD.00.CE.79.R1 |
AD 2000-CE-79 R1 Failure Of The Fuel Line Fittings Or The Gascolator (Applicable to Univair Aircraft Corporation Models (ERCO) 415-C, (ERCO) 415-CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A Airplanes) |
| AD.00.CE.80 |
AD 2000-CE-80 Clear And Complete Operating Instructions Are Visible For Opening The Airstair Door And Emergency Exits (Applicable to Raytheon Aircraft Company 65, 90, 99, 100, 200, and 300 Series, and Model 2000 Airplanes) |
| AD.00.NE.03 |
AD 2000-NE-03 Prevent Damage to the Disk Drive Arm Which Could Result in Loss of Stage 1 LP Turbine to Stage 2 LP Turbine Disk Drive, a Turbine Overspeed Condition and Possible Uncontained Disk Failure and Damage to the Airplane |
| AD.00.NE.04 |
AD 2000-NE-04 Prevent Radial Drive Steady Bearing Failure |
| AD.00.NE.08 |
AD 2000-NE-08 Failure Of The Propeller Blade From Fatigue Cracks In The Blade Shank Radius (Applicable to Hartzell Propeller, Inc. Compact Series Propellers) |
| AD.00.NE.08 |
AD 2000-NE-08 To Prevent Failure of the Propeller Blade from Fatigue Cracks in the Blade Shank Radius (Applicable to Hartzell Propeller Inc. Compact Series Propellers) |
| AD.00.NE.09 |
AD 2000-NE-09 To Prevent The Loss Of The Structural Integrity Of The Seat (Applicable to Aviointeriors S.p.A. Series 312 Seats) |
| AD.00.NE.12 |
AD 2000-NE-12 To Prevent Engine Flameout (Applicable To Turbomeca S.A. Arrius Models 2B, 2B1, and 2F Turboshaft Engines) |
| AD.00.NE.12 |
AD 2000-NE-12 Prevent Engine Flameout and the Inability to Maintain the 2.5 Minutes One Engine Inoperative (OEI) Rating Due to Blockage of the Fuel Injection Manifolds (See Revising NPRM AD 2000-NE-12, May 27, 2005) |
| AD.00.NE.13 |
AD 2000-NE-13 Cracks In LPC Fan Blade Roots (Applicable to Rolls-Royce RB211 Series Turbofan Engines) (See Revising NPRM AD 2000-NE-13, February 20, 2003) |
| AD.00.NE.13 |
AD 2000-NE-13 Cracks In LPC Fan Blade Roots (Applicable to Rolls-Royce RB211 Series Turbofan Engines) |
| AD.00.NE.14 |
AD 2000-NE-14 Impeller Failure From Cracks In The Impeller Back Face Area (Applicable to Honeywell International Inc. LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines) |
| AD.00.NE.15 |
AD 2000-NE-15 Prevent Unexpected Power Loss, which could Result in an Uncommanded In-Flight Engine Shutdown, Autorotation, and Forced Landing |
| AD.00.NE.18 |
AD 2000-NE-18 Failure Of The Hub Due To Loose Hub Through Bolts (Applicable to Dowty Aerospace Propellers, Models R354, R375, R389, and R390 Propellers) |
| AD.00.NE.21 |
AD 2000-NE-21 Restore the Engines to Type Design and to Prevent Possible Low Cycle Fatigue (LCF) Failure of the HPT Stage 1 Disk |
| AD.00.NE.22 |
AD 2000-NE-22 Prevent No. 5 Bearing Rotating Air Seal Failures and Possible Uncontained Engine Failures |
| AD.00.NE.24 |
AD 2000-NE-24 Prevent Premature LPT Disk Failure Due to Cracking of the LPT Disks |
| AD.00.NE.25 |
AD 2000-NE-25 Prevent 2nd Stage HPT Air Seal Assembly Failure |
| AD.00.NE.26 |
AD 2000-NE-26 Detect Wear On The Compressor Bleed Valve Assembly Cover, Guide Pin Shaft, Cotter Pin, And To Detect Particles From Diaphragm Wear |
| AD.00.NE.27 |
AD 2000-NE-27 Detect and Prevent Early Development of Cracks Due to Low Cycle Fatigue of the High Pressure Turbine (HPT) 2nd Stage Wheel In the Aft Bore Face That Can Lead to Wheel Failure Power Loss |
| AD.00.NE.30 |
AD 2000-NE-30 Prevent HPC Air Duct Failures That Could Result In Fan Mid Shaft (FMS) Failures And Uncontained LPT Events |
| AD.00.NE.32 |
AD 2000-NE-32 Prevent Premature Failure Of The Impellers From Being Operated Beyond Their Design Service Life |
| AD.00.NE.34 |
AD 2000-NE-34 Prevent Excessive Vibrations Produced By the Reduction Gearbox Assembly |
| AD.00.NE.35 |
AD 2000-NE-35 Prevent HPT Disk Firtree Fracture |
| AD.00.NE.41 |
AD 2000-NE-41 Prevent HPT 1st to 2nd Stage Turbine Spacer-Failure |
| AD.00.NE.42 |
AD 2000-NE-42 To Prevent Rupture Of The Fan Disk Due To Cracks That Initiate At An Electrical Arc-out (Applicable to General Electric Company CF34 Series Turbofan Engines) |
| AD.00.NE.45 |
AD 2000-NE-45 Fatigue Failure Of Hartzell D-5108-( ) Hubs (Applicable to Hartzell Propeller Inc., Model HD-E6C-3B/E13890K Propellers) |
| AD.00.NE.47 |
AD 2000-NE-47 Engine Takeoff Power Losses Due To HPC Surges (Applicable to Pratt and Whitney PW4000 Series Turbofan Engines) (See Revising NPRM AD2000-NE-47, April 7, 2003) |
| AD.00.NE.47 |
AD 2000-NE-47 Engine Takeoff Power Losses Due To High-pressure-compressor (HPC) Surges (Applicable to Pratt and Whitney PW4000 Series Turbofan Engines) (See Revising NPRM AD 2000-NE-47, July 21, 2003) |
| AD.00.NE.47 |
AD 2000-NE-47 Engine Takeoff Power Losses (Applicable To Pratt & Whitney PW4000 Series Turbofan Engine) |
| AD.00.NE.48 |
AD 2000-NE-48 To Detect And Prevent Cracks In The Fan Disc (Applicable to Rolls-Royce Deutschland Ltd and Co KG (Formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines) |
| AD.00.NE.49 |
AD 2000-NE-49 Failure Of The High Pressure Compressor (HPC) Front Drum Rotor From Cracks (Applicable to Pratt and Whitney PW4000 Series Turbofan Engines) |
| AD.00.NE.50 |
AD 2000-NE-50 Centrifugal Compressor Impeller Failure (Applicable to Honeywell International, Inc., (Formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, And Lycoming) Former Military T53 Series Turboshaft Engines) |
| AD.00.NE.53 |
AD 2000-NE-53 Prevent Failure Of The Fan Disc Due To Fatigue Cracking In The Dovetail Slots |
| AD.00.NE.57 |
AD 2000-NE-57 Failure Of A Hose When Exposed To Fire (Applicable to Titeflex Corporation) |
| AD.00.NE.58 |
AD 2000-NE-58 Fire In The Galley Compartment Due To Inadequate Crimping Of The Electrical Terminal Contact Pins (Applicable to Britax Sell Gmbh & Co. OHG Water Boilers, Coffee Makers, and Beverage Makers) |
| AD.00.NE.60 |
AD 2000-NE-60 Below-limit Flight Idle Propeller Blade Angles (Applicable to Hartzell Propeller Inc. Model HD-E6C-3B/E13890K Propellers) |
| AD.00.NE.61 |
AD 2000-NE-61 Prevent Stage 2 Turbine Aft Cooling Plate Cracking |
| AD.00.NE.62 |
AD 2000-NE-62 Prevent Possible High Pressure (HP) Turbine Disk Failure (See Revising NPRM AD 2000-NE-62, January 30, 2006) |
| AD.00.NE.62 |
AD 2000-NE-62 To Prevent Possible Disc Failure (Applicable to Rolls-Royce plc RB211 Series Turbofan Engines) |
| AD.00.NM.01 |
AD 2000-NM-01 Prevent Opening of the Cargo Door While the Airplane is in Flight |
| AD.00.NM.02 |
AD 2000-NM-02 Prevent Cracking of the NLG Main Fitting, which could Lead to Collapse of the NLG During Takeoff and Landing, and Possible Injury to the Flightcrew and Passengers |
| AD.00.NM.03 |
AD 2000-NM-03 Prevent The Inability To Extend The Nose Landing Gear |
| AD.00.NM.04 |
AD 2000-NM-04 Prevent Failure of the Front Spar Attachment and Upper Cap of the Engine Pylons Due to Fatigue Cracking |
| AD.00.NM.06 |
AD 2000-NM-06 Prevent Failure of the Shoulder Harness |
| AD.00.NM.10 |
AD 2000-NM-10 Prevent the Control Link of the Aileron Autopilot Servo From Being Driven Overcenter |
| AD.00.NM.12 |
AD 2000-NM-12 Prevent the Display of Incorrect Engine Limitations, which could Result in an Overspeed of the Propellers And Potential For Blade Failure |
| AD.00.NM.13 |
AD 2000-NM-13 Prevent Increased Braking Distance for Landings that Require the Flight Idle Stop Override, Resulting from the Combination of Failure of the Override Mechanism and Inability of the Power Levers to be Moved Below the Flight Idle Position After Touchdown |
| AD.00.NM.15 |
AD 2000-NM-15 Prevent the Collapse of the Main Landing Gear Due to Leaks of Hydraulic Oil from the Main Landing Gear Selector Valve |
| AD.00.NM.17 |
AD 2000-NM-17 Prevent Electromagnetic Interference With The Anti-skid Control System |
| AD.00.NM.18 |
AD 2000-NM-18 Prevent Failure of the Bearing Support Fitting of the Forward Trunnion |
| AD.00.NM.19 |
AD 2000-NM-19 Prevent the Potential for Dual Wire Faults from Grounded, Separated, or Shorted Wires (Revised by AD 2000-NM-19 R1) |
| AD.00.NM.19.R1 |
AD 2000-NM-19 Prevent The Potential For Dual Wire Faults From Grounded, Separated, Or Shorted Wires |
| AD.00.NM.22 |
AD 2000-NM-22 Prevent an Inadvertent Increase in Thrust |
| AD.00.NM.23 |
AD 2000-NM-23 Prevent False Smoke Warnings from the Cargo Compartment Smoke Detectors, which could Result in Aborted Takeoffs, Diversions of Flight Routes, and Emergency Evacuation of Flight Crew and Passengers |
| AD.00.NM.24 |
AD 2000-NM-24 Ensure the Integrity of the Fail-Safe Features of the Thrust Reverser System by Preventing Possible Failure Modes, which could Result in Inadvertent Deployment of a Thrust Reverser During Flight |
| AD.00.NM.25 |
AD 2000-NM-25 Prevent False Warning of a Hot Engine Exhaust Tailpipe and Intermittent Signal Failure |
| AD.00.NM.26 |
AD 2000-NM-26 Ensure Continued Structural Integrity of These Airplanes (ATR42-500 series) |
| AD.00.NM.27 |
AD 2000-NM-27 Detect Corrosion of the Lower Surface of the Wing Center Section and the Surrounding Area (Withdrawn by 66 FR 37197, July 17, 2001) |
| AD.00.NM.28 |
AD 2000-NM-28 Prevent Smoke And Fire In The Forward Cargo Compartment |
| AD.00.NM.29 |
AD 2000-NM-29 Prevent Insufficient Clearance And Contact Between The B7-28 Bus And An Adjacent Panel |
| AD.00.NM.31 |
AD 2000-NM-31 Detect Discrepancies That Include But Are Not Limited To Frayed, Chafed, Or Nicked Wires And Wire Insulation |
| AD.00.NM.32 |
AD 2000-NM-32 To Prevent Electrical Shorting Of The Brake Coils Of The Auto Throttle Servo (ATS) (Applicable to McDonnell Douglas Model MD-11 and -11F Airplanes) |
| AD.00.NM.32 |
AD 2000-NM-32 Prevent Electrical Shorting Of The Brake Coils Of The Auto Throttle Servo (ATS) Or Elevator Load Feel (Elf)/Flap Limiter (FL) Duplex Actuator (See Revising NPRM AD 2000-NM-32, July 13, 2004) |
| AD.00.NM.33 |
AD 2000-NM-33-AD Prevent Arcing and Sparking Damage to the Power Feeder Cables, Terminal Strips, and Adjacent Structure |
| AD.00.NM.34 |
AD 2000-NM-34 Prevent Arcing and Heat Damage to the Attachment Points of the Main External and Galley Power Receptacle Ground Wire, Insulation Blankets Outboard and AFT of the Receptacle Area, and Adjacent Power Cables |
| AD.00.NM.35 |
AD 2000-NM-35 Prevent Damaged Electrical Wires or Damaged Door Actuation Cables Due to Chafing by the Cables During Operation of the Forward Passenger Door |
| AD.00.NM.36 |
AD 2000-NM-36 Prevent Electrical Arcing And/Or Heat Damaged Wires Due To Improper Wire Installations During Manufacture And/Or Maintenance Of The Airplane |
| AD.00.NM.37 |
AD 2000-NM-37 Prevent Fire and Smoke in Certain Wire Bundles that are Routed to and From the Main Avionics Compartment or Center Accessory Compartment |
| AD.00.NM.38 |
AD 2000-NM-38 Prevent Overheating Of The Electrical Pins Inside The Cargo Control Units (CCU) |
| AD.00.NM.39 |
AD 2000-NM-39 Detect and Correct Discrepancies of Certain Connectors Which Could Result in Electrical Arcing of the Connectors, Uncommanded Movement of the Engine Fuel Shut-off Valves to the Closed Position, and Consequent In-flight Loss of Thrust or Engine Shutdown From Lack of Fuel |
| AD.00.NM.41 |
AD 2000-NM-41 Prevent Chafing Of The Fuel Level Control Switch Wiring Harness |
| AD.00.NM.44 |
AD 2000-NM-44 Prevent Excessive In-flight Vibrations of the Elevator Tab |
| AD.00.NM.45 |
AD 2000-NM-45 Ensure Continued Structural Integrity Of These Airplanes (Bombardier, Inc.) |
| AD.00.NM.46 |
AD 2000-NM-46 Prevent Chafing Of The Wire Bundle To Relay 'KT' On Panel 'JA' |
| AD.00.NM.47 |
AD 2000-NM-47 Detect and Correct Cracking of the Splice Fitting at Fuselage Frame (Fr) 47, which could Result in Reduced Structural Integrity of the Airplane |
| AD.00.NM.48 |
AD 2000-NM-48 Prevent The Fire Warning From Terminating Prematurely |
| AD.00.NM.50 |
AD 2000-NM-50 Prevent In-flight Loss of Inboard and Outboard Flap Assemblies due to Failure of H-11 Attaching Bolts |
| AD.00.NM.52 |
AD 2000-NM-52 Prevent Electrical Arcing Between the Oxygen Tubing and an Electrical Source Which Could Result in an Oxygen Fire |
| AD.00.NM.53 |
AD 2000-NM-53 Detect and Correct Corrosion of the Retraction Links of the Main Landing Gear (MLG), which could Result in Reduced Structural Integrity and Possible Collapse of the MLG |
| AD.00.NM.54 |
AD 2000-NM-54 Prevent Failure of Multiple TRU's |
| AD.00.NM.55 |
AD 2000-NM-55 Prevent Ignition Sources and Consequent Fire/Explosion in the Fuel Tank |
| AD.00.NM.56 |
AD 2000-NM-56 Prevent Failure of the Overwing Emergency Exits to Open |
| AD.00.NM.57 |
AD 2000-NM-57 Fatigue Cracking Of The Internal Doublers And Frame Structure Of The Fuselage Skin Of The Cockpit Enclosure Window Sill (Applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes) |
| AD.00.NM.60 |
AD 2000-NM-60 Prevent an Asymmetric Braking Condition and a Longer Stopping Distance Due to Sudden Loss of Normal Braking to the Left Wheel |
| AD.00.NM.62 |
AD 2000-NM-62-AD Detect and Correct Excess Backlash of the Spherical Bearing of the Active Aileron Servo-Controls |
| AD.00.NM.63 |
AD 2000-NM-63 Prevent Jamming Of The Roll Control System (Ailerons And Spoilers) |
| AD.00.NM.64 |
AD 2000-NM-64 Detect and Correct Excessive Play of the Eye-end of the Piston Rod of the Elevator Servo-controls |
| AD.00.NM.65 |
AD 2000-NM-65 Prevent Jamming of the Wheel/Tire Assembly (See Revising NPRM AD 2000-NM-65, November 12, 2003) |
| AD.00.NM.65 |
AD 2000-NM-65 Jamming Of The Wheel/Tire Assembly (Applicable to Cessna Model 500, 501, 550, and 551 Airplanes) |
| AD.00.NM.66 |
AD 2000-NM-66 Inadvertent Or Intentional Operation With The Power Levers Below The Flight Idle Stop During Flight For Airplanes That Are Not Certificated For In-flight Operation (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes) |
| AD.00.NM.66.R1 |
AD 2000-NM-66 To Prevent An Inoperative Backup Flight Idle Stop System |
| AD.00.NM.68 |
AD 2000-NM-68 R1 Prevent Failure Of The Main Fitting Of The Main Landing Gear (MLG) |
| AD.00.NM.69 |
AD 2000-NM-69 Prevent Unwanted Deployment Of A Thrust Reverser |
| AD.00.NM.70 |
AD 2000-NM-70 Ensure Continued Structural Integrity (See Revising NPRM AD 2000-NM-70, March 11, 2004) |
| AD.00.NM.70 |
AD 2000-NM-70 To Ensure Continued Structural Integrity Of These Airplanes (Applicable to Airbus Model A319, A320, and A321 Series Airplanes) |
| AD.00.NM.72 |
AD 2000-NM-72 Prevent Deflation Of The Escape Slide After Deployment |
| AD.00.NM.73 |
AD 2000-NM-73 Find and Fix Premature Cracking of Certain Fuselage Lap Joint Repairs |
| AD.00.NM.74 |
AD 2000-NM-74 Find And Fix Cracking Of Certain Fuselage Lap Joint Areas |
| AD.00.NM.76 |
AD 2000-NM-76 Prevent High Bearing Stress On The Bushings In The Flap Fittings |
| AD.00.NM.77 |
AD 2000-NM-77 Prevent Fracture of the Lead Screw of the Position 1 Flap Screw Jack |
| AD.00.NM.79 |
AD 2000-NM-79 Prevent Fatigue Cracking At The Rib 1/Center Spar Angle And Bottom Corner Fitting |
| AD.00.NM.80 |
AD 2000-NM-80 Prevent Electrical Sparks From a Grounded Object From Coming Into Contact With the Fuel Port Flood Light Housing of the Fuel Service Panel |
| AD.00.NM.90 |
AD 2000-NM-90 Prevent Unusual Handling Characteristics and Consequent Reduced Controllability During Ground Operations Due to Incorrect Methods of Weighing and Balancing the Airplane |
| AD.00.NM.91 |
AD 2000-NM-91 Prevent Damage To The 90-minute Auxiliary Power Unit (Apu) Standby Power Feeder Cable |
| AD.00.NM.96 |
AD 2000-NM-96 Prevent Chafing of the Wire Harnesses of the High-Level Sensors |
| AD.00.NM.98 |
AD 2000-NM-98 Prevent Contact Between the Precooler Support Link and the Precooler Support Fitting, which could Contribute to an Uncontained Failure of the Diffuser Case and Damage to the Airplane |
| AD.00.NM.100 |
AD 2000-NM-100 Prevent Opening of the Cargo Door While the Airplane is in Flight |
| AD.00.NM.101 |
AD 2000-NM-101 Ensure That the Flight Crew Is Aware That an Electrical System Failure May Have Occurred and That the Main Airplane Batteries Are Powering the Direct Current (DC) Essential Bus |
| AD.00.NM.102 |
AD 2000-NM-102 Prevent Contact Between The Nuts Of The Wiggins Fuel Couplers And The Stiffener On The Access Panel Of The Upper Surface Of The Right Wing |
| AD.00.NM.103 |
AD 2000-NM-103 Prevent Cracking or Breaking of the Door Handle Mounting Hub |
| AD.00.NM.104 |
AD 2000-NM-104 Prevent a Sudden Change in Pitch Due to an Out-of-trim Condition Combined with an Autopilot Disconnect |
| AD.00.NM.105 |
AD 2000-NM-105 Prevent Cracking of the Center Section of the Fuselage |
| AD.00.NM.107 |
AD 2000-NM-107 Prevent a Severe Asymmetric Thrust Condition During Flight which could Result in Loss of Control of the Airplane |
| AD.00.NM.110 |
AD 2000-NM-110 Fatigue Cracking (Applicable to McDonnell Douglas Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87) and MD-88 Airplanes) |
| AD.00.NM.112 |
AD 2000-NM-112 Prevent an Uncommanded Retraction of the Flaps During Takeoff |
| AD.00.NM.113 |
AD 2000-NM-113 Prevent Loss Of Hydraulic Pressure And Possible Structural Damage To The Airplane Due To Failure Of The Landing Gear Brake Accumulator |
| AD.00.NM.114 |
AD 2000-NM-114 Prevent Autopilot Reversions In Certain Flight Conditions, Which Could Result In Misunderstanding By the Flight Crew and Consequent Reduced Ability to Take Appropriate Action |
| AD.00.NM.115 |
AD 2000-NM-115 Prevent Detachment Of The Shoulder Restraint Harness Of The Attendant Or Observer Seat From Its Mounting Bracket During Service |
| AD.00.NM.116 |
AD 2000-NM-116 Ensure that Flight Crew Members Safely Reach the Ground From a Flight Compartment Window In the Event of an Emergency Evacuation |
| AD.00.NM.118 |
AD 2000-NM-118 Prevent The Simultaneous Failure Of Two Air Pressurization Units |
| AD.00.NM.120 |
AD 2000-NM-120 Prevent the Potentiometers That Provide Information On the Positions of the Primary Flight Controls to the Flight Data Recorder (FDR) From Transmitting Noisy Signals or Becoming Imprope (See Revising NPRM AD 2000-NM-120, March 19, 2003) |
| AD.00.NM.120 |
AD 2000-NM-120 Potentiometers That Provide Information On The Positions Of The Primary Flight Controls To The FDR From Transmitting Noisy Signals Or Becoming Improperly Calibrated (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes) (See Revising NPRM AD 2000-NM-120, February 1, 2005) |
| AD.00.NM.120 |
AD 2000-NM-120 To Prevent The Potentiometers That Provide Information On The Positions Of The Primary Flight Controls To The FDR From Transmitting Noisy Signals (Applicable To Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 Series Airplanes) |
| AD.00.NM.121 |
AD 2000-NM-121 Prevent Overheating of the Wire Between Certain Circuit Breakers, Which Could Result in Smoke Emissions in the Cockpit |
| AD.00.NM.122 |
AD 2000-NM-122 Prevent Contact Between One of the Bolts that Attaches the Direct Current (DC) Relay Box on the Left-hand (LH) Side of the Airplane (Hereinafter Referred to as the "LH DC Relay Box") and One of the Power Terminals of Electrical Emergency Contactor 2 (K0519) |
| AD.00.NM.124 |
AD 2000-NM-124 Maintain Airplane Controllability In the Event of an In-Flight Thrust Reverser Deployment (Withdrawn by 69 FR 27865, May 17, 2004) |
| AD.00.NM.125 |
AD 2000-NM-125 Ensure That The Flightcrew Is Able To Recognize The Formation Of Significant Ice Accretion |
| AD.00.NM.127 |
AD 2000-NM-127 Prevent Incapacitation of the Flightcrew and Consequent Loss Of Control of the Airplane Due to Delays in Donning Oxygen Masks in Response to the Activation of the Cabin Altitude Warning Horn |
| AD.00.NM.128 |
AD 2000-NM-128 Prevent Bottoming Of The Valve Components Before Contact Of The Brake Valve Lever With The Stop |
| AD.00.NM.129 |
AD 2000-NM-129 Prevent The Loss Of Hydraulic Pressure Due To Failed Hydraulic Tubing |
| AD.00.NM.130 |
AD 2000-NM-130 Prevent Deterioration and Deformation of the Mass-Balance Weights of the Aileron |
| AD.00.NM.131 |
AD 2000-NM-131 Prevent Mechanical Blockage Of The Elevator Control Cable Due To The Freezing Of Water Collected Inside The Fuselage Between The Rear Pressure Bulkhead And The Fire Wall Of The Auxiliary Power Unit |
| AD.00.NM.132 |
AD 2000-NM-132 Prevent the Airplane from Departing the Runway at High Speeds During Landing Due to Bending and Damage to the Squat Switch Assembly of the Nose Landing Gear |
| AD.00.NM.133 |
AD 2000-NM-133 Prevent Rupture of the Hydraulic Line and Loss of Hydraulic Pressure Due to Chafing |
| AD.00.NM.134 |
AD 2000-NM-134 Detect And Correct Fatigue Cracking Of The Front Spar Web Of The Wing |
| AD.00.NM.141 |
AD 2000-NM-141 Prevent Failure Of The Mounting Brackets Of The Hydraulic Hand Pump At The Frame Attachment Flanges |
| AD.00.NM.142 |
AD 2000-NM-142 Prevent Premature Failure Of The Shear Pins Of The Elevator Damper |
| AD.00.NM.144 |
AD 2000-NM-144 Prevent The Flight Crew From Being Unaware That An Electrical System Failure Has Occurred And That The Airplane Main Batteries Are Powering The Direct Current (DC) Essential Bus |
| AD.00.NM.145 |
AD 2000-NM-145 Prevent Structural Failure of the Airplane Due to Corrosion |
| AD.00.NM.146 |
AD 2000-NM-146 Prevent Chafing of Wire Bundles in Two Junction Boxes in the Main Wheel Well (Revised by AD 2000-NM-146 R1) |
| AD.00.NM.146.R1 |
AD 2000-NM-146 Prevent Chafing of Wire Bundles In Four Junction Boxes In the Main Wheel Well |
| AD.00.NM.147 |
AD 2000-NM-147 Prevent Stress Corrosion Cracking and Consequent Fracture of the Aft Trunnion of the Outer Cylinder of the MLG |
| AD.00.NM.148 |
AD 2000-NM-148 Prevent Chafing of the Feeder Cables During Removal of the Sump Panels of the Cargo Floor |
| AD.00.NM.149 |
AD 2000-NM-149 Prevent Fire and Smoke In Certain Wire Bundles That Are Routed To and From the Main Avionics Compartment Or Center Accessory Compartment |
| AD.00.NM.150 |
AD 2000-NM-150 Smoke And Fire In Various Areas Of The Airplane Due To Heat Damage And/Or Electrical Arcing (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes) (See Revising NPRM AD 00-NM-150, July 24, 2003) |
| AD.00.NM.150 |
AD 2000-NM-150 Smoke And Fire In Various Areas Of The Airplane Due To Heat Damage (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes) |
| AD.00.NM.152 |
AD 2000-NM-152 Prevent Restricted Movement Of The Rudder Pedals Due To Structural Interference |
| AD.00.NM.154 |
AD 2000-NM-154 Prevent Cross Connection of the Hydraulic Hoses or Pipes that Supply the Main Strut Unlocking Actuator |
| AD.00.NM.156 |
AD 2000-NM-156 Prevent Unrestrained Movement of the Passenger Seats During High Forward Deceleration of the Airplane |
| AD.00.NM.157 |
AD 2000-NM-157 Prevent Fatigue Cracking In Primary Strut Structure and Reduced Structural Integrity of the Strut, Which Could Result In Separation of the Strut and Engine |
| AD.00.NM.158 |
AD 2000-NM-158 Prevent Contact Between the Rotating Paddle Wheel and the Stationary End Plates Within the Center Wing Tank Override/Jettison Fuel Pumps or Horizontal Stabilizer Tank Transfer Pumps Due to Excessive Wear of the Pump Shaft Carbon Thrust Bearing |
| AD.00.NM.159 |
AD 2000-NM-159 Prevent Failure of An Escape Slide to Deploy or Inflate Correctly |
| AD.00.NM.160 |
AD 2000-NM-160 Prevent Excessive Vibrations Generated By the Mounting Configuration of the 15XE Connector |
| AD.00.NM.161 |
AD 2000-NM-161 Prevent Smoke and Fire In the Flight Deck and Main Cabin Due to Insufficient Clearance Between Wire Assemblies and the Ice Protection Airduct and Airstair Door Interlock Rod, Chafing, and Consequent Arcing of Wire Assemblies |
| AD.00.NM.162 |
AD 2000-NM-162 Prevent Electrical Shorting And Arcing Due To The Presence Of Water In The Lighting Ballast Interface Connectors |
| AD.00.NM.163 |
AD 2000-NM-163 Prevent Failures Of The Electrical Connectors |
| AD.00.NM.164 |
AD 2000-NM-164 Possible Arcing Of The Electrical Power Cables In The Aft Cargo Compartment Sidewall (Applicable to McDonnell Douglas Model DC-9-81, -82, and -83 Series Airplanes, and Model MD-88 Airplanes) |
| AD.00.NM.165 |
AD 2000-NM-165 The Alternating Current (AC) Power Relay Feeder Cable From Chafing Against The Aft Inboard Side Of The Electrical Power Center (Applicable to McDonnell Douglas Model DC-9-81, -82, and -83 Series Airplanes, and Model MD-88 Airplanes) |
| AD.00.NM.166 |
AD 2000-NM-166 Chafing Of Wires At The Disconnect Panel Above The Aft Left Lavatory (Applicable to McDonnell Douglas Model DC-9-81, -82, and -83 Series Airplanes, and Model MD-88 Airplanes) |
| AD.00.NM.168 |
AD 2000-NM-168 A Cable From Chafing Against An Edge Of A Lightening Hole (Applicable To McDonnell Douglas Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), And MD-88 Airplanes) (Withdrawn by 70 FR 2066, January 12, 2005) |
| AD.00.NM.169 |
AD 2000-NM-169 Damage To Equipment Or Possible Fire In The Electrical/Electronics Equipment Compartment (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 Airplanes) |
| AD.00.NM.170 |
AD 2000-NM-170 Wire Chafing And Subsequent Shorting To Structure In The Forward Cargo Compartment (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes) |
| AD.00.NM.171 |
AD 2000-NM-171 Chafing Of The Power Feeder Cables Of The Auxiliary Power Unit (APU) (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes and Model MD-88 Airplanes) |
| AD.00.NM.176 |
AD 2000-NM-176 Prevent Fatigue Cracking of the Fuselage Skin |
| AD.00.NM.178 |
AD 2000-NM-178 To Prevent Fuel Leakage And Reduced Structural Integrity Of The Wings Due To Fatigue Cracking |
| AD.00.NM.179.R1 |
AD 2000-NM-179 R1 Prevent Corrosion From Developing On the Underside of the Top Skin of the Center Wing |
| AD.00.NM.181 |
AD 2000-NM-181 Prevent The Collapse Of The Main Landing Gear Due To Leaks Of Hydraulic Oil From The Main Landing Gear Selector Valve |
| AD.00.NM.184 |
AD 2000-NM-184 Detect and Correct Fatigue Cracking of the Lower Spar Chord, Which Could Result In Reduced Structural Integrity of the Engine Strut |
| AD.00.NM.185 |
AD 2000-NM-185 Prevent Chafing And Damage To Electrical Wires Of The Cockpit And Consequent Electrical Arcing Due To Wires That Were Routed Improperly During Production Of The Airplane |
| AD.00.NM.186 |
AD 2000-NM-186 Prevent Possible Overheating Of Cargo Control Unit (CCU) Components |
| AD.00.NM.187 |
AD 2000-NM-187 Protect Against Electrical Failures In the Cargo Control Units (CCU) |
| AD.00.NM.188 |
AD 2000-NM-188 Prevent Chafing and Arcing of the Parallel Feeder Cables of the Number 2 Integrated Drive Generator (IDG) |
| AD.00.NM.189 |
AD 2000-NM-189 Prevent Chafing In the Upper Avionics Circuit Breaker Panel of the Main Observer's Station |
| AD.00.NM.190 |
AD 2000-NM-190 Detect Riding or Chafing of the Wire Bundles Adjacent to the Disconnect Panel Bracket Assembly |
| AD.00.NM.191 |
AD 2000-NM-191 Prevent Arcing Damage to the Terminal Strips and Damage to the Adjacent Structure of the Wheel Well Area of the Right Main Landing Gear (MLG) |
| AD.00.NM.192 |
AD 2000-NM-192 Prevent Arcing Damage to the Terminal Strips and Damage to the Adjacent Structure In the Wing Areas Inboard of the Pylons 1 and 3 and the No. 2 Engine (Withdrawn by 68 FR 52864, September 8, 2003) |
| AD.00.NM.193 |
AD 2000-NM-193 Prevent Loss of the Charging Capability of the Air Driven Generator (ADG) |
| AD.00.NM.195 |
AD 2000-NM-195 Moisture From Entering The Strake Feed-Thru And Internal Electrical Connectors (Applicable to McDonnell Douglas MD-90-30 Series Airplanes) |
| AD.00.NM.196 |
AD 2000-NM-196 Chafing Of The Wiring In The Left-Hand Tunnel Area Of The Forward Cargo Compartment (Applicable to McDonnell Douglas Model MD-90-30 Series Airplanes) |
| AD.00.NM.197 |
AD 2000-NM-197 Damage To The Galley Power Feeder Cable (Applicable to McDonnell Douglas Model MD-90-30 Airplanes) |
| AD.00.NM.198 |
AD 2000-NM-198 Ground Stud Nut From Being Inadequately Tightened Or Becoming Loose (Applicable to McDonnell Douglas Model MD-90-30 Series Airplanes) |
| AD.00.NM.201 |
AD 2000-NM-201 Prevent Fatigue Failure Of Certain Existing Fasteners In The Aft Pickup Fittings Of The Horizontal Stabilizer (Withdrawn by 66 FR 20409) |
| AD.00.NM.202 |
AD 2000-NM-202 Prevent Breakage of the Power Control Cable Assemblies Due to the Inflexible Construction of the Cable |
| AD.00.NM.203 |
AD 2000-NM-203 Prevent a Mechanical Failure of the Uplock Box Mechanisms |
| AD.00.NM.205 |
AD 2000-NM-205 Prevent Fatigue Cracking of the Corners of the Doorframe and the Cross Beams of the Aft Cargo Door, Which Could Result In Rapid Depressurization of the Airplane |
| AD.00.NM.207 |
AD 2000-NM-207 Detect Improper Grounding of a Water Heater |
| AD.00.NM.211 |
AD 2000-NM-211 Prevent Failure of the Passenger Service Units (PSUs) to Deliver Oxygen to the Passengers In the Event of Decompression of the Airplane |
| AD.00.NM.212.R1 |
AD 2000-NM-212 R1 Prevent The Turbine Air Discharge Duct Or Water Separator Outlet Duct From Disconnecting From The Cold Air Unit Turbine Or From The Water Separator |
| AD.00.NM.213 |
AD 2000-NM-213 Prevent Electrical Shorts Or Arcing At The Illuminated Panel Connector At The Refuel/Defuel Panel |
| AD.00.NM.214 |
AD 2000-NM-214 Prevent Reduced Structural Integrity of the Airplane Due to Fatigue Damage and Consequent Cracking of the Pick-Up Angles at Frame 40 |
| AD.00.NM.215 |
AD 2000-NM-215 To Detect and Correct Cracking or Breaking of the Rod Ends and Connecting Fittings (Applicable to Empresa Brasileira de Aeronautica S.A. EMBRAER Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.00.NM.217 |
AD 2000-NM-217 Prevent Potential Ignition Of The Moisture Barrier Cover Of The Drip Shield |
| AD.00.NM.220 |
AD 2000-NM-220 Detect And Correct Fatigue Cracking Of Certain Areas Of The Fuselage Skin |
| AD.00.NM.221 |
AD 2000-NM-221 Prevent Separation of the Self-Seal Couplings, Which Could Result In Loss of Engine Oil Pressure and a Flight-Crew-Commanded Engine Shutdown |
| AD.00.NM.222 |
AD 2000-NM-222 Prevent Loss of the Nose Wheel Steering and Reduced Controllability of the Airplane On the Ground |
| AD.00.NM.223 |
AD 2000-NM-223 Detect and Correct Fatigue Cracking of Fuselage Frame 07 In the Upper Frame Section Assembly of the Lateral Cockpit Windows |
| AD.00.NM.224 |
AD 2000-NM-224 Prevent The Elevator Cable Tension Regulators From Becoming Detached From The Splined Shaft Of The Assembly |
| AD.00.NM.226 |
AD 2000-NM-226 Prevent Potential Ignition of Fiberglass Insulation in the Environmental Control System (ECS) Ducts |
| AD.00.NM.227 |
AD 2000-NM-227 Prevent Electrical Arcing of the Fuel Boost Pump Wire |
| AD.00.NM.228 |
AD 2000-NM-228 Prevent The Inability Of The Flight Crew To Remove Power From The Telephone System When Necessary |
| AD.00.NM.229 |
AD 2000-NM-229 Prevent the Inability of the Flight Crew to Remove Power From the In-Flight Entertainment (IFE) System When Necessary |
| AD.00.NM.230 |
AD 2000-NM-230 Prevent the Attachment Pin From Fully Migrating From the Brake Torque Rod and the Collar From Detaching From the Main Landing Gear (MLG) |
| AD.00.NM.231 |
AD 2000-NM-231 Prevent the Inability of Flight Crew to Remove Power From the In-Flight Entertainment (IFE) System When Necessary |
| AD.00.NM.232 |
AD 2000-NM-232 Prevent The Inability Of Flight Crew To Remove Power From The In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.233 |
AD 2000-NM-233 Prevent the Inability of Flight Crew to Remove Power From the In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.234 |
AD 2000-NM-234 Ensure That the Flight Crew Is Able to Remove Electrical Power From the In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.235 |
AD 2000-NM-235 Prevent The Inability Of Flight Crew To Remove Power From The In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.236 |
AD 2000-NM-236 Ensure That the Flight Crew Is Able to Remove Electrical Power From the In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.237 |
AD 2000-NM-237 Ensure That The Flight Crew Is Able To Remove Electrical Power From The In-flight Entertainment (IFE) System When Necessary And Is Advised Of Appropriate Procedures For Such Action |
| AD.00.NM.238 |
AD 2000-NM-238 Prevent The Inability Of The Flight Crew To Remove Power From The In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.239 |
AD 2000-NM-239 Ensure That the Flight Crew and Cabin Crew are Able to Remove Electrical Power From the In-flight Entertainment (IFE) System When Necessary |
| AD.00.NM.240 |
AD 2000-NM-240 Ensure That the Flight Crew Is Able to Remove Power From the In-Flight Entertainment (IFE) System When Necessary |
| AD.00.NM.241 |
AD 2000-NM-241 Ensure That the Flight Crew Is Able to Remove Electrical Power From the In-Flight Entertainment (IFE) System When Necessary |
| AD.00.NM.242 |
AD 2000-NM-242 Ensure That the Flight Crew Is Able to Remove Electrical Power From the Passenger Entertainment System (PES) When Necessary |
| AD.00.NM.243 |
AD 2000-NM-243 Ensure That the Flight Crew Is Able to Remove Electrical Power From the Entire Passenger Entertainment System (PES) When Necessary |
| AD.00.NM.244 |
AD 2000-NM-244 Ensure That the Flight Crew Is Able to Remove Electrical Power From the Passenger Entertainment System (PES) When Necessary |
| AD.00.NM.245 |
AD 2000-NM-245 Ensure That The Flight Crew Is Able To Remove Electrical Power From The Entire Passenger Entertainment System (PES) When Necessary And Is Advised Of Appropriate Procedures For Such Action |
| AD.00.NM.246 |
AD 2000-NM-246 Ensure That The Flight Crew Is Able To Remove Electrical Power From The Entire Passenger Entertainment System (PES) When Necessary And Is Advised Of Appropriate Procedures For Such Action |
| AD.00.NM.247 |
AD 2000-NM-247 Fatigue Cracking Of Certain Repairs Of The Fuselage Between Frame 10 And Frame 80 (Applicable to Airbus Model A300 B2 And B4 Series Airplanes) |
| AD.00.NM.250 |
AD 2000-NM-250 Prevent Loss Of The Underwing Fitting Load Path Due To Missing Or Damaged Taperlock Fasteners |
| AD.00.NM.251 |
AD 2000-NM-251 Find and Fix Fatigue Cracking In the Bulkhead Frame Support At Body Station (BS) 2598 Under the Hinge Support Fittings of the Horizontal Stabilizer |
| AD.00.NM.253 |
AD 2000-NM-253 Detect And Correct Fatigue Cracking Of The Inner Sidestays Of The Main Landing Gear (MLG), Which Could Result In Failure Of The MLG |
| AD.00.NM.256 |
AD 2000-NM-256 Prevent the Spring Tab or the Servo Tab from Becoming Disconnected, Resulting In Structural Failure, and to Prevent Damage to the Leading Edge of the Spring Tab |
| AD.00.NM.257 |
AD 2000-NM-257 Prevent Failure Of The Bleed-air Check Valve On The Bleed Low-pressure Line Of The Engine |
| AD.00.NM.260 |
AD 2000-NM-260 Prevent Various Failures of Electric Motors of the Auxiliary Hydraulic Pump and Associated Wiring |
| AD.00.NM.261 |
AD 2000-NM-261 Prevent the Ejection Jack on the Ram Air Turbine (RAT) From Failing When the RAT Is Deployed At High Airspeeds |
| AD.00.NM.262 |
AD 2000-NM-262 Prevent Fatigue Of The Engine Control System Cables |
| AD.00.NM.263 |
AD 2000-NM-263 Prevent the Loss of Electrical Power, Other Than that Provided By the Emergency System, In the Event of Disconnection of the Single Electrical Connector Within the Electrical Master Central Unit |
| AD.00.NM.264 |
AD 2000-NM-264 Prevent Fatigue Cracking In The Zone Of The Fittings Connecting The Fuselage To Stiffener Rods Located In Frames 33, 34, And 35 |
| AD.00.NM.265 |
AD 2000-NM-265 Prevent Incapacitation of the Flightcrew and Consequent Loss of Control of the Airplane Due to Delays in Donning Oxygen Masks in Response to the Activation of the Cabin Altitude Warning Horn |
| AD.00.NM.266 |
AD 2000-NM-266 Fatigue Cracking of the Oleo Strut of the Nose Landing Gear (NLG) (Applicable to BAE Systems (Operations) Limited Model BAe 146 Series Airplanes and Model Avro 146-RJ Series Airplanes) |
| AD.00.NM.267 |
AD 2000-NM-267 Prevent Failure Of The Alternate Braking System |
| AD.00.NM.268 |
AD 2000-NM-268 Prevent Damage to the Wires In Certain Wire Bundles Due to Contact Between the Bundles and the Adjacent Ceiling Support Bracket |
| AD.00.NM.269 |
AD 2000-NM-269 Prevent Various Failures Of Electric Motors Of The Auxiliary Hydraulic Pump And Associated Wiring |
| AD.00.NM.271 |
AD 2000-NM-271 Detect And Correct Bushing Migration, Corrosion, Or Cracking Of The Lugs On The Bulkhead Fitting Of The Rear Engine Mount |
| AD.00.NM.272 |
AD 2000-NM-272 Prevent Blockage of Pressure Hoses to the Ground Spoiler Actuators |
| AD.00.NM.273 |
AD 2000-NM-273 Prevent Fatigue Cracking of the Fuselage |
| AD.00.NM.274 |
AD 2000-NM-274 Prevent A Main Landing Gear (MLG) Gear-up Landing And Possible Injury To Passengers And Crew |
| AD.00.NM.275 |
AD 2000-NM-275 Prevent Failure Of The Core Cowl Latches During An Engine Fire |
| AD.00.NM.276 |
AD 2000-NM-276 Detect and Correct Fatigue Cracking of Nose Wheel Well (NWW) Vertical Beams and Frames |