AD Number Subject Effective Docket NumberCitation P

2023-12-15 Navigation 06/21/2023FAA-2023-0923 06/21/2023

2023-10-02 Indicating/Recording System, Navigation 05/26/2023FAA-2022-1647 05/26/2023
2023-02-09 Stabilizers 03/20/2023FAA-2022-1050 02/13/2023
2023-01-13 Wings 03/13/2023FAA-2022-0874 02/06/2023
2022-09-18 Navigation 05/23/2022FAA-2022-0509 05/23/2022
2020-10-10 Wings 06/26/2020FAA-2020-0096 05/22/2020
2018-07-04 Ice and rain protection 09/10/2018FAA-2017-0805 08/06/2018
2018-03-04 Airspeed/Mach Indicator 03/16/2018FAA-2016-6616 02/09/2018
2017-19-05 Smoke Detection 10/31/2017FAA-2017-0099 10/02/2017
2017-17-19 Fuselage 10/04/2017FAA-2017-0503 08/30/2017
2016-25-06 Stabilizers 01/25/2017FAA-2016-8845 12/21/2016
2016-07-28 Wings 04/26/2016FAA-2016-5458 04/11/2016
2016-03-06 Fuel 03/23/2016FAA-2015-0249 02/17/2016
2015-02-05 Navigation 03/05/2015FAA-2014-0624 01/29/2015
2014-21-04 Stabilizers 12/02/2014FAA-2014-0451 10/28/2014
2014-17-02 Communications 09/09/2014FAA-2014-0573 08/25/2014
2014-05-27 Navigation 05/02/2014FAA-2013-0966 03/28/2014
2013-18-09 Communications 10/03/2013FAA-2013-0707 09/18/2013
2013-05-02 Stabilizers 04/15/2013FAA-2011-0909 03/11/2013
2012-21-13 Wings 12/04/2012FAA-2012-0727 10/30/2012
2012-18-05 Fuel 10/11/2012FAA-2011-1229 09/06/2012
2011-21-08 Equipment/Furnishings 11/23/2011FAA-2010-0040 10/19/2011
2011-17-11 Wings 09/26/2011FAA-2009-1213 08/22/2011
2011-15-01 Stabilizers 08/19/2011FAA-2011-0217 07/15/2011
2011-14-03 Stabilizers 08/10/2011FAA-2010-1203 07/06/2011
2011-12-01 Equipment/Furnishings 08/01/2011FAA-2010-0857 06/02/2011
2011-01-16 Fuel 02/16/2011FAA-2010-0549 01/12/2011
2010-25-04 Compliance 01/11/2011FAA-2008-0934 12/07/2010
2009-15-16 R1 Doors 08/05/2010FAA-2010-0702 08/05/2010
2009-21-10 R1 Oxygen 02/04/2010FAA-2010-0029 01/20/2010
2009-21-10 Oxygen 12/17/2009FAA-2009-0915 12/02/2009
2008-22-01 Auxiliary fuel tanks 11/26/2008FAA-2008-0298 10/22/2008
2008-13-29 Overwing frames 08/12/2008FAA-2007-29335 07/08/2008
2008-11-15 Fuel tank systems 07/03/2008FAA-2008-0032 05/29/2008
2008-06-27 Evacuation system's shear-pin 04/28/2008FAA-2007-28370 03/24/2008
2008-03-12 Rudder pedal bracket 03/11/2008FAA-2007-29061 02/05/2008
2007-25-16 Forward passenger doorjamb 01/14/2008FAA-2007-29226 12/10/2007
2007-17-18 Static port heater assemblies 10/02/20072003-NM-198-AD08/28/2007
2007-10-04 Horizontal stabilizer 05/23/2007FAA-2007-28100 05/08/2007
2006-16-02 Refueling Manifold 09/07/2006FAA-2006-24786 08/03/2006
2006-15-15 Wire bundle for the auxiliary hydraulic pump 09/05/20062001-NM-387-AD07/31/2006
2006-10-14 Stop pad support fittings 06/21/2006FAA-2005-22254 05/17/2006
2006-07-11 Aft attach fitting assembly of the spoiler link 05/05/2006FAA-2005-22062 03/31/2006
2006-06-04 Main landing gear (MLG) 04/20/2006FAA-2005-22121 03/16/2006
2006-01-02 Upper lock link assembly of the nose landing ge02/22/20062002-NM-105-AD01/18/2006
2003-17-07 R1 Auxiliary power unit (APU) 09/24/2003FAA-2005-20881 10/03/2005
2005-13-18 Battery terminal screws 08/01/2005FAA-2004-19809 06/27/2005
2005-09-04 Main landing gear (MLG) shock strut pistons 06/02/20052001-NM-293-AD04/28/2005
2005-07-03 Rear spar of the left and right wings 05/04/2005FAA-2004-18774 03/30/2005
2004-25-14 Main landing gear (MLG) 01/20/20052002-NM-333-AD12/16/2004
2004-23-21 Power feeder cables of the auxiliary power unit 01/03/20052000-NM-171-AD11/26/2004
2004-23-05 Ground stud installation of the main battery 12/20/20042000-NM-169-AD11/15/2004
2004-22-01 Cargo restraint strap assemblies 12/01/20042002-NM-91-AD 10/27/2004
2004-15-13 Freeze Protection Ribbon Heaters 09/02/20042002-NM-215-AD07/29/2004
2004-13-23 Seat track locking pins 08/13/20042003-NM-251-AD07/09/2004
2004-11-07 Structural Integrity 07/09/20042000-NM-110-AD06/04/2004
2004-05-25 Seat Locking Pins 04/19/2004FAA-2003-16647,03/15/2004
2004-05-09 Forward cargo compartment 04/07/20042000-NM-170-AD03/03/2004
2004-05-03 Shock strut cylinders 03/15/20042003-NM-122-AD02/27/2004
2004-02-09 Discrepant circuit breakers 03/05/20042002-NM-82-AD 01/30/2004
2003-24-14 Electrical Wiring Installations in Various Areas o01/08/20042000-NM-150-AD12/04/2003
2003-03-15 R1 Airplane Flight Manual (AFM) - oxygen masks 12/22/20032003-NM-91-AD 11/17/2003
2003-09-07 Left and right main landing gear (MLG) 06/05/20032001-NM-170-AD05/01/2003
2002-21-06 Upper wing skin 11/08/20022002-NM-216-AD03/18/2003
2003-03-15 Airplane Flight Manual (AFM) - Oxygen Masks 03/07/20032002-NM-43-AD 01/31/2003
2002-26-20 Panel area above the aft left lavatory 02/18/20032000-NM-166-AD01/13/2003
2002-26-08 Emergency Power Switch Knob on the Overhead02/10/20032002-NM-53-AD 01/06/2003
2002-26-13 Left and right generator power relays 02/06/200399-NM-90-AD 01/02/2003
2002-10-03 Main Landing Gear (MLG) Shock Strut Piston As 06/20/20022001-NM-197-AD05/16/2002
2002-09-06 Support Clamp of Alternating Current (AC) Powe06/06/20022000-NM-165-AD05/02/2002
2002-09-07 Electrical Power Feeder Cables 06/06/20022000-NM-164-AD05/02/2002
2002-04-01 Upper Lock Link Assembly of the Nose Landing 03/28/200297-NM-298-AD 02/21/2002
2002-03-06 Airplane Flight Manual (AFM) to provide the fli 03/21/20022001-NM-114-AD02/14/2002
2002-01-24 Passenger Service Unit Panels of the Overhea 03/06/20022000-NM-362-AD01/30/2002
2001-26-15 Wire Runs in Electrical/Equipment Compartmen02/08/20022000-NM-161-AD01/04/2002
2001-26-16 Interface Connectors of Cabin Fluorescent Lighti02/08/20022000-NM-162-AD01/04/2002
2001-24-27 Rudder Pedal Adjuster Hub Assembly 01/16/20022001-NM-206-AD12/12/2001
2001-24-19 Electrical Wires 01/16/200299-NM-297-AD 12/12/2001
2001-24-17 Light Switch for the Cargo Compartment(s). 01/16/200299-NM-295-AD 12/12/2001
2001-22-17 Auxiliary Hydraulic Pump and Associated Wiring12/18/20012000-NM-260-AD11/13/2001
2001-22-14 Fire Extinguishing System Bottle Cartridges 12/10/200198-CE-113-AD 11/02/2001
2001-20-15 AC Cross-tie Relay 10/26/20012001-NM-264-AD10/11/2001
2001-17-34 Sidewall Fluorescent Lighting 10/04/20012000-NM-163-AD08/30/2001
2001-12-22 Wiring of the Selective Calling (SELCAL) System 07/27/20012000-NM-322-AD06/22/2001
2001-10-10 Static Port Heaters 06/08/20012001-NM-85-AD 05/24/2001
2001-09-18 Main Landing Gear Pistons 06/14/200199-NM-164-AD 05/10/2001
2000-11-01 Insulation Blankets 06/30/200099-NM-161-AD 05/26/2000
2000-08-18 Evacuation Slides 06/13/200097-NM-244-AD 05/09/2000
99-23-22 R2 Transponders 04/20/20002000-NM-81-AD 04/20/2000
2000-04-24 Auxiliary Power Units 05/08/200099-NE-34-AD 03/08/2000
2000-02-23 Engine Ignition Switch 03/09/200098-NM-381-AD 02/03/2000
99-24-04 C1 Hi-Lok Pin Fasteners 12/27/199999-NM-05-AD 12/27/1999
99-22-08 Pneumatic Augmentation Valve 11/30/199998-NM-382-AD 10/26/1999
99-21-06 Slat Drive Mechanism Assembly Brackets 11/12/199998-NM-267-AD 10/07/1999
99-21-07 Main Landing Gear Hydraulic Brake System 11/12/199998-NM-268-AD 10/07/1999
99-13-13 08/02/199998-NM-147-AD 06/28/1999
99-07-14 Vertical-To-Horizontal Stabilizer 05/06/199998-NM-166-AD 04/01/1999
98-13-35 R1 Fatigue Cracks In External Areas Of Fuselage 07/30/199896-NM-203-AD 03/23/1999
99-06-13 Main Landing Gear Shock Strut Cylinder 04/22/199997-NM-292-AD 03/18/1999
99-04-10 Fluorescent Light Ballasts 03/18/199996-NM-163-AD 02/11/1999
98-24-33 Lower Nose Longerons And Attaching Frames 01/07/199997-NM-21-AD 12/03/1998
98-20-21 Sidewall Lighting System 10/27/199896-NM-270-AD 09/22/1998
98-18-17 Tailcone Emergency Evacuation Slide 10/08/199898-NM-10-AD 09/03/1998
98-17-06 Fatigue Cracking of Fuselage Skin Panels 09/18/199897-NM-20-AD 08/14/1998
98-15-15 FIREX Supply Pipe 08/25/199897-NM-105-AD 07/21/1998
98-11-10 Speed Brake Handle Pin 06/26/199897-NM-251-AD 05/22/1998
98-09-19 Non-Regulating Shutoff Valve On Starter 06/03/199896-NM-199-AD 04/29/1998
98-04-07 Upper Fuselage Skin 02/25/199898-NM-12-AD 02/10/1998
96-23-07 R1 Rear Spar Lower Cap Of Wings 09/04/199796-NM-53-AD 08/20/1997
97-08-07 Cabin Sidewall Fluorescent Light Ballasts 05/07/199797-NM-61-AD 04/22/1997
97-04-10 AFM - Autopilot Or Autothrottle Release Button03/28/199796-NM-217-AD 02/21/1997
97-04-04 Auxiliary Power Units 03/24/199796-ANE-15 02/21/1997
97-03-15 Evacuation Slides 03/14/199796-NM-124-AD 02/07/1997
97-03-05 Fuselage Forward Upper Skin 03/10/199796-NM-235-AD 02/03/1997
96-22-10 Lavatory Drainage System 12/11/199695-NM-214-AD 11/06/1996
96-16-04 Ventral Aft Pressure Bulkhead 09/04/199695-NM-186-AD 07/31/1996
74-08-09 R2 Waste Receptacles 07/29/199695-NM-233-AD 06/24/1996
96-11-18 Oxygen Mask Lanyards 07/09/199695-NM-188-AD 06/04/1996
96-11-04 Main Landing Gear Slant Panel Insulation Blanke06/26/199695-NM-185-AD 05/22/1996
96-10-11 Structural Failure 06/20/199694-NM-92-AD 05/16/1996
96-07-15 Wire Bundle In Overhead Switch Panel 05/15/199695-NM-131-AD 04/15/1996
96-05-01 Horizontal Stabilizer Primary Trim Motor 04/03/199695-NM-118-AD 03/04/1996
95-11-12 Emergency Power Switches 07/03/199594-NM-194-AD 06/01/1995
95-08-04 Electrical Plugs 05/18/199594-NM-93-AD 04/18/1995
95-07-03 Auxiliary Power Units 05/03/199594-ANE-17 04/03/1995
95-06-06 Inspect Wire Termination Lugs 04/21/199594-NM-172-AD 03/22/1995
95-02-02 Inspect Tailcone Release Assembly 02/21/199594-NM-100-AD 01/20/1995
94-25-06 Engine Nose Cowl 01/17/199594-NM-87-AD 12/15/1994
94-14-03 Water Heaters and Coffee Makers 08/01/199494-NM-01-AD 06/30/1994
94-09-12 Center And Side Flight Compartment Windshiel 06/09/199493-NM-156-AD 05/10/1994
94-08-04 Anti-Collision Light Cutout 05/23/199493-NM-115-AD 04/21/1994
94-09-02 Generator Power Feeder Cable 05/20/199493-NM-110-AD 04/20/1994
94-02-02 Distance Measuring Equipment 02/21/199492-CE-60-AD 01/18/1994
94-01-06 Traffic Alert and Collision Avoidance System II 02/04/199493-CE-47-AD 01/05/1994
75-16-03 Landing Gear Release System 08/01/1975Unknown
69-26-06 Heat Damage To HF and V.H.F. Coaxial Cable 12/30/1969Unknown
90-14-07 Elevator Control Tab Assembly 07/23/199090-NM-104-AD
85-11-02 R1 Elevator Surface Inspection 08/21/1986Unknown
82-03-06 Tail Cone Lock Housing Modification 03/11/1982Unknown
85-25-06 Power Feeder Cable 01/10/1986Unknown
92-16-06 Aircraft Starters 08/31/199292-CE-05-AD
91-21-07 Trim Relays 11/19/199191-NM-104-AD
82-21-01 Throttle Control Cable 10/21/1982Unknown
91-21-02 Management Control Units 10/23/199191-NM-187-AD
89-25-03 Inspect Window Belt Panels 12/18/198989-NM-228-AD
90-25-04 Engine Mount Cone Bolts 01/02/199190-NM-71-AD
72-17-03 Rudder Pedal Arm Casting 09/16/1972Unknown
90-09-01 Generator Connector 05/29/199089-NM-239-AD
85-01-02 R1 Bulkhead Web And Doublers Inspection 03/31/1986Unknown
93-24-16 Protective Breathing Equipment 02/04/199493-CE-36-AD
78-07-05 Wheelwell Frame Fittings 05/18/1979Unknown
81-04-51 R1 Autothrottle Disengage 12/28/1981Unknown
74-14-07 Passenger Oxygen Masks 08/15/1974Unknown
78-01-11 Emergency Exit Release Handle 02/13/1978Unknown
93-05-16 R1 Inspect Retention Nut 11/18/199393-NM-48-AD
84-21-03 Fitting Assembly (Rod End) Inspection 11/26/1984Unknown
72-09-01 Engine Mount Pylon 03/03/1977Unknown
93-23-01 Water Heaters and Coffee Makers 12/07/199393-NM-181-AD
79-10-13 Door Lock Mechanism 09/13/1979Unknown
80-22-52 Engine And APU Fire Extinguishing System Cartr04/20/1981Unknown
89-13-07 Wheel Assembly 07/24/1989Unknown
84-03-52 R1 MLG Doors, Latches, Shields 06/04/1984Unknown
81-16-51 Cargo Door Latch Hooks and Latch Spool Bolts 09/21/1982Unknown
85-16-07 Fire Prevention - Lavatory Waste Containers 08/26/1985Unknown
74-17-01 Regulator 09/16/1974Unknown
93-14-12 Crewmember Protective Breathing Equipment U09/02/199392-ANE-14
82-18-10 Aircraft Seats 10/04/1982Unknown
94-01-04 Traffic Alert and Collision Avoidance System 02/04/199493-NM-68-AD
69-17-01 Auxiliary Power Unit Unknown
90-23-02 Mid Attendant's Oxygen Mask 12/10/199090-NM-121-AD
83-06-02 Fire Extinguishing Agent 04/04/1983Unknown
86-10-09 Inspect Engine Fire Shutoff Switch Cams 06/09/1986Unknown
70-09-04 Tire Tread Separation 06/02/1970Unknown
87-08-07 Wheel Assembly 05/11/1987Unknown
76-22-07 Flight Attendant's Seat 12/10/1976Unknown
87-17-03 Main Landing Gear Wheel Assembly 09/13/1987Unknown
91-10-11 Flight Controls - Elevator 06/18/199190-NM-288-AD
89-26-02 Inspect Rudder Control 01/13/199089-NM-73-AD
90-23-10 PTU Shut-Off Valve 12/10/199089-NM-215-AD
87-15-08 R1 Cowl Door Latches 04/25/1988Unknown
81-19-05 Thrust Reversers 09/28/1981Unknown
84-03-06 Fuel Tank Pump Conduits 03/19/1984Unknown
81-10-10 R1 Galley Service Doors 04/20/1983Unknown
87-13-09 Tailcone Visual Warning 08/08/1987Unknown
87-08-09 Tire Inflation 06/01/1987Unknown
94-06-01 Ceiling Relief Panels 04/11/199493-NM-161-AD
71-01-05 Emergency Evacuation Slide 02/17/1971Unknown
94-01-08 Aft Pressure Bulkhead 01/28/199493-NM-224-AD
91-24-05 Forward Cabin Attendant Dual Seat 01/07/199291-NM-30-AD
79-19-02 Elevator Spars 09/13/1979Unknown
87-05-08 Evacuation Slide Strap 03/25/1987Unknown
91-22-03 Tailcone Indicating System 01/03/199290-NM-97-AD
91-10-01 Traffic Alert and Collision Avoidance Systems 03/10/199291-CE-42-AD
93-05-07 Inspect Overwing Emergency Exit Door 04/29/199392-NM-162-AD
71-08-01 Aft Evacuation Slide 04/20/1971Unknown
93-23-11 Nose Wheel Assembly 01/05/199493-NM-51-AD
92-20-06 Evacuation Slide 11/20/199292-NM-88-AD
75-08-17 Digital Flight Data Recorders 12/19/1975Unknown
90-09-04 Overhead Stowage Assemblies 05/29/199089-NM-240-AD
92-10-13 R1 AFM Inclusion - Autothrottles 06/13/199695-NM-127-AD
93-09-07 Fire Extinguishers 05/11/199393-NM-37-AD
87-05-51 Floor Proximity Lighting 05/18/1987Unknown
71-15-01 Forward Cabin Attendant's Seat 08/21/1971Unknown
89-08-04 Spoiler Position System 05/04/1989Unknown
88-20-02 Manifold Clamps 10/11/1988Unknown
71-02-06 Evacuation Slide Bar Latch 02/26/1971Unknown
92-02-04 Rudder Actuator 03/27/199291-NM-150-AD
91-11-02 Engine Mount Nuts 06/24/199190-NM-263-AD
87-04-08 AFM Changes-Compressor Blades 03/09/1987Unknown
88-24-04 R1 Placard & AFM Change-APU 03/19/199089-NM-199-AD
80-02-04 Aft Pressure Bulkhead Door 01/21/1980Unknown
90-03-13 Cabin Attendant Oxygen Door 02/15/199089-NM-277-AD
96-02-06 AFM - Limitations - Windshear 02/26/199695-NM-55-AD
87-25-52 Brake/Anti-Skid Control 03/07/1988Unknown
71-24-01 Cabin Ceiling Light Switch 03/24/1972Unknown
91-10-08 Electrical Connectors 06/11/199190-NM-256-AD
82-24-04 De-Icing System 11/23/1982Unknown
92-22-08 R1 Corrosion Prevention And Control 01/12/199393-NM-60-AD
91-13-03 Rudder Control Assembly 06/27/199191-NM-111-AD
85-07-10 Flush Power Motor In Lavatories 05/13/1985Unknown
71-11-08 Instrument Panel Assemblies Unknown
88-12-05 Auto Brake System 07/01/1988Unknown
88-25-51 R1 Horizontal Stabilizer 02/15/1989Unknown
92-09-03 Brake Replacement 05/22/199291-NM-239-AD
88-25-06 Spoiler Control Circuit Breaker 12/16/1988Unknown
89-06-03 Hose Assemblies 03/30/1989Unknown
92-21-05 Auxiliary Power Units 11/24/199292-NM-94-AD
99-08-05 R1 Fuselage Frames And Longerons 05/12/199998-NM-110-AD
85-01-03 Spoiler Drive Link And Fittings 02/14/1985Unknown
82-04-02 Rudder Pedal Arm Assemblies 03/21/1982Unknown
85-06-05 Battery Chargers 05/20/1985Unknown
88-03-09 Digital Flight Guidance Computer 03/11/1988Unknown
91-13-06 AFM Changes - Engine Generators 07/15/199191-NM-03-AD
94-22-03 Power Transfer Unit 11/28/199494-NM-78-AD
92-01-03 Tailcone Release System 02/14/199291-NM-137-AD
89-08-10 R1 Fuselage Inspection 06/14/1989Unknown
85-03-08 R1 Fuselage Skin Inspection 04/15/1985Unknown
89-07-08 Aircraft Wiring 04/17/1989Unknown
82-10-04 Longitudinal Trim System 05/18/1982Unknown
79-24-01 R3 Aft Pressure Bulkhead 08/27/1981Unknown
79-18-12 Auxiliary Power Units 10/08/1979Unknown
91-21-03 Electrical Wiring 11/29/199191-NM-74-AD
81-22-01 Slat Control Valve Assembly 11/05/1981Unknown
2000-23-31 Lower Sidewall Lights in Passenger Compartmen12/13/20002000-NM-356-AD
2000-15-17 R1 Hydraulic Pipe Assembly in the Aft Fuselage 09/12/200099-NM-227-AD
71-08-02 Control Of Speed Brake 11/30/1971Unknown
86-22-02 Horizontal Stabilizer Mounting Bolts 11/14/1986Unknown
81-25-03 Windshield Heat Generation 01/04/1982Unknown
97-02-08 R1 Upper Lock Link Assembly Of Nose Landing Gea03/04/199796-NM-99-AD
78-04-03 Aileron Spoiler Mixer Cam 02/21/1978Unknown
92-19-06 Galley Power Feeder Wire Assemblies 11/17/199292-NM-43-AD
93-07-15 Cargo Compartment 05/02/199392-NM-67-AD
90-04-05 Takeoff Warning System 03/08/199089-NM-143-AD
81-02-06 Cargo Door Attach Bolts 04/01/1981Unknown
91-11-03 PSU Oxygen Doors 06/24/199190-NM-287-AD
89-10-10 Evacuation Slide Assemblies 06/12/1989Unknown
86-19-51 Elevator Rod Ends 01/02/1987Unknown
87-16-08 Taxi Speed Indication System 08/20/1987Unknown
90-25-11 In-Flight Spoiler Lockout Mechanism 12/17/199090-NM-228-AD
87-12-01 Main Landing Gear Bolts 06/22/1987Unknown
89-18-04 Engine Starter Shutoff Valve 09/18/198989-NM-16-AD
92-16-15 Oxygen Mask Connectors 09/01/199292-NM-116-AD
89-07-17 AFM Changes-Fuel 05/04/1989Unknown
68-02-05 Nose Gear Shock Strut 02/29/1968Unknown
2000-15-15 Jackscrew Assembly Of Horizontal Stabilizer 08/23/20002000-NM-89-AD
88-24-06 Service Door Assist Handles 12/02/1988Unknown
93-23-03 Evacuation Slides 12/22/199393-NM-39-AD
67-30-05 Battery Charger 12/19/1967Unknown 11/09/1967
67-27-05 Pylon Rear Spar 09/26/1967Unknown 09/26/1967
67-25-05 Thrust Reverser Autothrottle System 09/06/1967Unknown 09/06/1967
67-07-03 Sperry SP-50 Autopilot 03/02/1967Unknown 03/02/1967
67-05-02 Engine Mount 02/10/1967Unknown 02/10/1967
67-05-01 Door Assemblies 02/04/1967Unknown 02/04/1967
Make Product T Product Subtype Summary
The BoeingAircraft Large Airplane The FAA is superseding Airworth
The Boeing Appliance Glider | Large Airplane | Small Airplane | Small/Large Airplane The FAA is superseding Airworth
The BoeingAircraft Large Airplane The FAA is superseding Airworth
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane The FAA is superseding Airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAppliance We are adopting a new airworth
Airbus SAS Appliance We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are superseding Airworthine
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
Airbus | ATAppliance We are superseding Airworthine
Airbus SAS Appliance We are adopting a new airworth
Airbus | ATAppliance We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
ATR - GIE AAppliance We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
Airbus SAS Appliance We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane The FAA is revising an existing a
Airbus | ThAppliance The FAA is revising an existing a
Airbus | ThAppliance We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane We are adopting a new airworth
Airbus | ThAppliance We are adopting a new airworth
The BoeingAircraft Large Airplane The FAA is superseding an existi
The BoeingAircraft Large Airplane We are adopting a new airworth
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane The FAA is superseding an existi
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane The FAA is revising an existing a
The BoeingAircraft Large Airplane The FAA is superseding an existi
The BoeingAircraft Large Airplane This amendment supersedes an
The BoeingAircraft Large Airplane The FAA is adopting a new airwo
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
Airbus | ATAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This amendment revises an exis
The BoeingAircraft Large Airplane This amendment adopts a new a
The BoeingAircraft Large Airplane This document corrects informa
The BoeingAircraft Large Airplane This amendment adopts a new a
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The BoeingAircraft Large Airplane
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The BoeingAircraft Large Airplane This amendment corrects inform
The BoeingAircraft Large Airplane
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The BoeingAircraft Large Airplane This amendment adopts a new a
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The BoeingAircraft Large Airplane This document corrects a typogr
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The BoeingAircraft Large Airplane
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The FAA is superseding Airworthiness Directive (AD) 2022-09- 18, which applied to all The Boeing Company Model 707, 717, and 727 airp
The FAA is superseding Airworthiness Directive (AD) 2021-23- 12, which applied to all transport and commuter category airplanes equipp
The FAA is superseding Airworthiness Directive (AD) 2007-10- 04, which applied to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-
The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC- 9
The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 707, 717, and 727 airplanes; Model DC-8, DC-9
The FAA is superseding Airworthiness Directive (AD) 2016-07- 28, which applied to all The Boeing Company Model DC-9-81 (MD-81), DC-
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
We are adopting a new airworthiness directive (AD) for Rosemount Aerospace Model 851AK pitot probes that were repaired by CSI Aeros
We are adopting a new airworthiness directive (AD) for certain Siemens S.A.S. smoke detectors installed on various transport category air
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD- \n\n((Page 41161)) \n\n81), DC-9-8
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
We are superseding Airworthiness Directive (AD) 2012-18-05 for The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes; Model DC-10-10, DC-10-10F, D
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
We are superseding Airworthiness Directive (AD) 2013-18-09 for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) instal
We are adopting a new airworthiness directive (AD) for certain Rockwell Collins TPR-720 and TPR-900 Mode select (S) transponders that a
We are adopting a new airworthiness directive (AD) for certain Honeywell ASCa Inc. emergency locator transmitters (ELTs) installed on va
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-
We are adopting a new airworthiness directive (AD) for Sicma Aero Seat 88xx, 89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and 96xx series passeng
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking of t
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a detailed inspection to detect distres
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracking of t
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires determining if affected seats and seati
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing fuel level float and pressure
We are adopting a new airworthiness directive (AD) for the McDonnell Douglas Corporation airplanes listed above. This AD requires modi
The FAA is revising an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model DC-9-10 series airplanes, DC-9-
The FAA is revising an existing airworthiness directive (AD), which applies to certain AVOX Systems and B/E Aerospace oxygen cylinder ass
We are adopting a new airworthiness directive (AD) for certain AVOX Systems and B/E Aerospace oxygen cylinder assemblies, as installed
We are adopting a new airworthiness directive (AD) for various transport category airplanes. This AD requires deactivation of PATS Aircra
We are adopting a new airworthiness directive (AD) for all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD- 8
We are adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires revising the FA
We are adopting a new airworthiness directive (AD) for certain Goodrich evacuation systems approved under Technical Standard Orders (
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas airplanes. The existing AD cu
We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplane
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -5
The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 8
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires a one
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an in
The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires a one- time
The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model DC-9-10, -20, - 30, -40
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas transport category airplanes, that re
The FAA is revising an existing airworthiness directive (AD) that applies to various transport category airplanes manufactured by McDonn
The FAA is superseding an existing airworthiness directive (AD), which applies to certain SAFT America Inc. part number (P/N) 021929-000
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), D
The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplan
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires an in
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires reversing th
This amendment adopts a new airworthiness directive (AD), applicable to various transport category airplanes on which cargo restraint st
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-82 (MD-82) and DC-9-83 (MD-
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-8
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires inspe
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplane models, that requires a one
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-8
This amendment revises an existing airworthiness directive (AD), applicable to various Boeing and McDonnell Douglas transport category
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas transport category airplanes listed above
This document corrects information in an existing airworthiness directive (AD) that applies to all McDonnell Douglas Model DC-9-81 (MD-
This amendment adopts a new airworthiness directive (AD), applicable to various Boeing and McDonnell Douglas transport category airpl
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-10, DC-9-20, DC-9-30, DC-9-40
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires replacemen
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (M
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, an
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 se
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 se
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-81, -82, -83, and -87 series airp
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -4
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -5
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -5
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -9-82, -9-83, and -9
This amendment adopts a new airworthiness directive (AD) that applies to certain Overland Aviation Services (OAS) fire extinguishing syst
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 series airplanes a
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, an
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 se
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 and MD-90-30 serie
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, and M
This amendment rescinds Airworthiness Directive (AD) 99-23-22 R1, which is applicable to various transport category airplanes equipped
This amendment adopts a new airworthiness directive (AD), applicable to Honeywell International (formerly AlliedSignal Inc.) 36-300(A), 3
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (milit
This document corrects information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-9-80 s
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80 and C-9 (milita
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-81, -82, -83, and -8
This amendment supersedes two existing airworthiness directives (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, an
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (milit
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, and
This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 an
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment adopts a new airworthiness directive (AD), applicable to any transport category airplane that is equipped with certain Da
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airp
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-80 series airplanes, that requir
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes and Mod
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 series airp
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (milit
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (milita
This amendment revises an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Auxiliary Power Divis
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 ser
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9 series airplanes, that
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas DC-9 and DC-9-80 series airplanes, and M
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and DC-9-80 s
This amendment revises an existing airworthiness directive (AD), applicable to all transport category airplanes, that currently requires ins
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, and
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 ser
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series air
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (milit
This amendment adopts a new airworthiness directive (AD), applicable to certain Model DC-9-80 series airplanes and Model MD-88 airpla
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Aerospace (formerly Garrett Auxiliary Power Divisio
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (milit
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and DC-9-80 series airplanes, M
This amendment adopts a new airworthiness directive (AD), applicable to certain Model DC-9-80 series airplanes and Model MD-88 airpla
This amendment adopts a new airworthiness directive (AD), applicable to certain Nordskog water heaters and coffee makers. This amend
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8, DC-9, and DC-9-80 seri
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airpl
This amendment adopts a new airworthiness directive (AD) that applies to Rockwell International/Air Transport Division (Collins) DME-70
This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell International, Collins Air Transport Division (C
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and

This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 and C-9 (military)
This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 an

This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and

This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-82 (MD-82) and D
This document corrects a typographical error that appeared in airworthiness directive (AD) 2000-15-17 that was published in the Federal

This document corrects information in an existing airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-

This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9, Model MD-90-30,
 l 707, 717, and 727 airplanes; Model DC-8, DC-9, and DC-10 airplanes; Model MD-10 and MD-11 airplanes; Model DC-9-81 (MD-81), DC-9-
tegory airplanes equipped with a radio (also known as radar) altimeter. AD 2021-23-12 required revising the limitations section of the exis
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 2007-10-04 required repetitive inspecti
DC-9-82 (MD-82), DC- 9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. This AD was prompted by an evaluation
anes; Model DC-8, DC-9, and DC-10 airplanes; Model MD-10 and MD-11 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (M
l 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 2016-07-28 requ
2 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, Model MD-88 airplanes, and Model MD-90- 30 airplanes. This AD was promp
re repaired by CSI Aerospace, Inc. between January 2013 and July 2014 that are installed on airplanes. This AD was prompted by a report
us transport category airplanes. This AD requires inspection and replacement of the affected smoke detectors. This AD was prompted by a
41161)) \n\n81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD was prompted
2 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. This AD was prompted by a report of fatigue cra
2 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD requires repetitive eddy current high fre
DC-9-30, DC-9-40, and DC-9- 50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), MD-8
DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40 and DC-10-40F airplanes; Model MD-10-10F and M
2 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks emanating from the aft-m
ransmitters (ELTs) installed on various transport category airplanes. AD 2013-18-09 required various one-time general visual inspections o
t (S) transponders that are installed on airplanes. This AD was prompted by the identification that the TPR-720 and TPR-900 Mode S trans
ers (ELTs) installed on various transport category airplanes. This AD requires various one-time general visual inspections of the ELT transmi
2 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks of the hinge bearing lugs
-9-82 (MD-82), DC-9-83 (MD- 83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of fatigue cracks found in Stri
-9-30, DC-9-40, and DC-9- 50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), MD-88
and 96xx series passenger seat assemblies, installed on various transport category airplanes. This AD results from mandatory continuing a
pections for cracking of the lower rear spar caps of the wings, and related investigative and corrective actions if necessary. This AD also req
pection to detect distress and existing repairs to the leading edge structure of the vertical stabilizer at the splice at Station Zfs = 52.267; rep
pections for cracking of the left and right upper center skin panels of the horizontal stabilizer, and corrective action if necessary. This AD wa
affected seats and seating systems and their components are compliant with certain FAA regulations, and removing those seats, seating s
level float and pressure switch in-line fuses on the wing forward spars and forward and aft auxiliary fuel tanks, depending on the airplane
e. This AD requires modifying the fuel boost pumps for the center wing, and forward or aft auxiliary fuel tanks. This AD results from fuel sy
0 series airplanes, DC-9-30 series airplanes, DC-9-81 (MD-81) airplanes, DC-9-82 (MD-82) airplanes, DC-9-83 (MD-83) airplanes, DC-9-87 (M
pace oxygen cylinder assemblies, as installed on various transport airplanes. That AD currently requires removing certain oxygen cylinder a
assemblies, as installed on various transport airplanes. This AD requires removing certain oxygen cylinder assemblies from the airplane. T
activation of PATS Aircraft, LLC, auxiliary fuel tanks. This AD results from fuel system reviews conducted by the manufacturer, which identifi
MD-82), DC-9-83 (MD- 83), DC-9-87 (MD-87), and MD-88 airplanes. This AD requires repetitive inspections for cracking of the overwing fra
requires revising the FAA-approved maintenance program, or the Airworthiness Limitations (AWLs) section of the Instructions for Continu
hnical Standard Orders (TSOs) TSO-C69, TSO-C69a, TSO-C69b, and TSO-C69c, installed on certain Boeing, McDonnell Douglas, and Airbus t
anes. The existing AD currently requires an initial general visual or dye penetrant inspection, repetitive dye penetrant inspections, and repl
DC-9-82 (MD-82) airplanes. This AD requires, for certain airplanes, inspecting for cracking of the fuselage skin at the upper corners of the fo
-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD- 83), and -87 (MD-87) airplanes; and Model MD
82 (MD-82), DC-9-83 (MD- 83), DC-9-87 (MD-87), and MD-88 airplanes. This AD requires repetitive inspections to detect cracks in the horiz
C-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD requires installing a clamp, a bonding jumper assembly
dels, that requires a one-time inspection for chafing or signs of arcing of the wire bundle for the auxiliary hydraulic pump, and other speci
es. This AD requires an inspection to determine the part number of the upper and lower stop pad support fittings of all the lower cargo doo
AD requires a one- time inspection of the aft attach fitting assembly of the spoiler link to determine the part number, and further investiga
el DC-9-10, -20, - 30, -40 and -50 series airplanes, and Model DC-9-81 (MD-81), and DC-9- 82 (MD-82) airplanes. That AD currently requires
ategory airplanes, that requires an inspection of the upper lock link assembly of the nose landing gear (NLG) to determine the manufacture
anufactured by McDonnell Douglas. We issued that AD to require a one-time test of the fire extinguishers for the engine and auxiliary pow
umber (P/N) 021929-000 (McDonnell Douglas P/N 43B034LB02) and P/N 021904-000 (McDonnell Douglas P/N 43B034LB03) nickel cadmiu
odel DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes. The existing AD currently re
0, and -50 series airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes. This AD requires repetitive detailed inspections o
dels, that requires an inspection of the retract cylinder support fitting and the cylinder bore of the support fitting of both main landing gea
-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. This amendment requires
hat requires reversing the ground stud installation of the main battery, and installing a new nameplate on the cover of the battery. This acti
which cargo restraint strap assemblies have been installed per STC ST01004NY. This amendment requires revising the airplane flight man
-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and Model MD-88 airplanes, that requires replacement of certain free
D-82) and DC-9-83 (MD-83) airplanes; and Model MD-88 airplanes, that requires inspection of the captain's and first officer's seat track loc
MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, that requires implementation of a program of struct
dels, that requires inspection of the captain's and first officer's seat locking pins for minimum engagement with the detent holes in the se
dels, that requires a one-time inspection for chafing of wiring in the left-hand tunnel area of the forward cargo compartment, repair if nec
l DC-9-81 (MD-81), DC-9- 82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; Model MD-88 airplanes, and Model MD-90-30 air
-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This action requires a one-time visual inspection
MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This action requires one-time inspections to detect d
uglas transport category airplanes, that currently requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen
ry airplanes listed above, that requires a check of the slant pressure panels of the wheel wells of the left and right main landing gear (MLG
las 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. That AD currently requires revisi
transport category airplanes. This AD requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a
-81 (MD-81), DC-9-82 (MD-82), and DC-9-83 (MD-83) airplanes, and Model MD-88 airplanes, that requires an inspection of the disconnect
-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes; and Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87)
hat requires replacement of certain power relays, and subsequent repetitive cleaning, inspecting, repairing, and testing of certain replaced
-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes. This AD requires replacement of cert
-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection to verify proper installation of the s
-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection of the electrical power feeder cable
odel DC-9, DC-9-80, and C-9 series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that currently requires a visual check to
odel DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes, that currently requires a re
-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the dust seals of the passenger service unit (PSU
-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires a detailed visual inspection of certain wires to detect cha
2, -83, and -87 series airplanes, and Model MD-88 airplanes, that requires replacing the interface connectors of the cabin fluorescent lighti
odel DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 airp
-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; and Model MD-88 airplanes, th
-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, and -83 series airplanes. This AD requires modification o
-81, -9-82, -9-83, and -9-87 series airplanes; Model MD-88 airplanes; and Model MD-90-30 series airplanes. This action requires repetitive
S) fire extinguishing system bottle cartridges that were distributed during a certain time period and are installed on aircraft. This AD requir
l DC-9 series airplanes and MD-88 airplanes. This action requires an inspection to determine if a certain AC cross-tie relay is installed; repl
odel DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes, that currently requires an inspection to detect damage, burn
-81, -82, -83, and -87 series airplanes, and MD-88 airplanes, that requires revising the wiring of the selective calling (SELCAL) system. The a
l DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes. This action requires an inspection of the wiring of the primary an
odel DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires a one-time inspection to detect cracking of the main land
-80 and MD-90-30 series airplanes, and Model MD-88 airplanes, that requires a determination be made of whether, and at what locations
series airplanes, and Model MD-88 and MD-90-30 airplanes, that requires replacement of the lanyard assembly pins of the evacuation sli
gory airplanes equipped with Mode "C" transponder(s) with single Gillham code altitude input. That AD requires repetitive tests to detect
dSignal Inc.) 36-300(A), 36-280(B), and 36-280(D) series Auxiliary Power Units (APUs). This amendment requires installation of an external
, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to determine the type of en
Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. That AD currently requires a one-time visual inspection to determine
, DC-9-80 and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires revising the wiring of the air conditioning pneumati
DC-9-81, -82, -83, and -87 series airplanes (MD-81, -82, -83, and -87), and Model MD-88 airplanes, that currently requires visual or eddy cu
Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that currently require installation of hydraulic line re
, DC-9-80, and C-9 (military) series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that requires a one-time inspection of
-80 series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to detect corrosion of the lug bores and the surface
Douglas Model DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires repe
odel DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires inspection(s) to detect fatigue cracking of the shock stru
equipped with certain Day-Ray fluorescent light ballasts installed in the upper and/or lower cabin sidewall, that requires a visual inspection
and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires a one-time visual inspection to det
ies airplanes, that requires an inspection to detect discrepancies of electrical plugs and receptacles of the sidewall lighting system in the p
eries airplanes and Model MD-90-30 and MD-88 airplanes, that requires a one-time inspection of the harness assembly of the tailcone em
-80 series airplanes and Model MD-88 airplanes, that requires repetitive inspections to detect fatigue cracking of certain fuselage skin pan
odel DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that currently requires an inspection to detect chafing
and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires an inspection to determine if the la
, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires modification of certain non-regulating shutoff valv
odel DC-9 and C-9 (military) series airplanes, that currently requires eddy current or dye penetrant inspection for cracks in the upper fusela
DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires visual/dye penetrant and ultrasonic inspections to detect cra
odel DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to determine the type of fluorescent light b
DC-9-80 series airplanes, Model MD-88 airplanes, and Model MD-90 airplanes, that currently requires revising the Airplane Flight Manual (
ett Auxiliary Power Division) GTCP85 Series auxiliary power units (APUs), that currently requires removing the existing turbine wheel shro
and Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires modification of the girt and
-9 series airplanes, that currently requires repetitive visual inspections to detect corrosion and cracking of the fuselage upper skin and fram
0 series airplanes, and Model MD-88 airplanes, that requires repetitive leak checks of the lavatory drain system and repair, if necessary; p
odel DC-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) airplanes, that currently requires repetitive inspections
at currently requires installation of placards prohibiting smoking in the lavatory and disposal of cigarettes in the lavatory waste receptacle
-80 series airplanes, and Model MD-88 and MD-90 airplanes, that requires a one-time measurement of the length of the oxygen mask lan
and Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires modification of the slant pa
-9 and DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that currently requires certain inspections and
odel DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect chafing of or damage to the wire
odel DC-9-80 series airplanes, that currently requires inspection and replacement of certain suspect horizontal stabilizer primary trim moto
, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires repetitive replacement of the emergency power sw
and Model MD-88 airplanes, that requires an inspection to detect damage, burn marks, or discoloration at certain electrical plugs and rece
tt Auxiliary Power Division and Garrett Turbine Engine Co.) GTCP85 series auxiliary power units (APU), that requires modifying the APU to i
, DC-9-80, and C-9 (military) series airplanes and Model MD-88 airplanes, that requires a visual inspection to verify proper installation of th
-9-80 series airplanes, Model MD-88 airplanes, and Model C-9 (military) airplanes, that requires inspection of the tailcone release locking
and Model MD-88 airplanes, that requires modification of the engine nose cowls. This amendment is prompted by several in-flight inciden
ffee makers. This amendment requires an inspection to determine whether certain discrepant pressure relief valves have been installed in
, DC-9, and DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) airplanes; that requires inspection of the center and side w
odel DC-9 and Model DC-9-80 series airplanes, and C-9 (military) airplanes, that currently requires inspections to detect cracking in the skin
odel DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to detect damage of the auxiliary power un
ivision (Collins) DME-700 distance measuring equipment (DME) installed on aircraft. This action requires modifying these DME units to en
Air Transport Division (Collins), Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action r
-80 series airplanes and Model MD-88 airplanes, that requires inspection of the ceiling pressure relief panels in the cargo compartments t

l DC-9 and C-9 (military) series airplanes. This action requires inspections to detect cracking in the ventral aft pressure bulkhead, and repa
 Douglas Model DC-9 and C-9 (military) series airplanes, that currently requires repetitive inspections to detect fatigue cracking of the fuse

-80 series airplanes and Model MD-88 airplanes, that requires modification of the power transfer unit (PTU). This amendment is prompte

l DC-9-82 (MD-82) and DC-9-83 (MD-83) series airplanes, and Model MD-88 airplanes. This action requires deactivating the left and right
published in the Federal Register on August 8, 2000 (65 FR 48368). The typographical error resulted in the omission of an airplane model f

nell Douglas Model DC-9, DC-9-80 and C-9 (military) series airplanes, and Model MD-88 airplanes. The AD currently requires either the in

DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes, that currently requires inspecting the general condition of the jacksc
 DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC- 9-87 (MD-87), and MD-88 airplanes; and Model MD 90-30 airplanes. AD 2022-0
ations section of the existing airplane/ aircraft flight manual (AFM) to incorporate limitations prohibiting certain operations requiring radio
uired repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative and corrective actions if necessary. Since
ompted by an evaluation by the design approval holder (DAH) indicating that certain center wing lower stringers are subject to widespread
82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 (collectively described, in the preamble of this AD, as MD-80) airplanes; and M
nes. AD 2016-07-28 required repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center win
nes. This AD was prompted by a report of loss of airspeed indication due to icing. This AD requires modifying the air data heat (ADH) syste
s prompted by a report that certain pitot probes are indicating the wrong airspeed during flight. This AD requires inspecting the airplane t
s AD was prompted by a report that the affected smoke detectors failed an acceptance test. We are issuing this AD to correct the unsafe c
. This AD was prompted by reports of cracking of various structures in the bulkhead. This AD requires an inspection for cracking in these st
by a report of fatigue cracking in a rear spar lower cap of the horizontal stabilizer. This AD requires repetitive inspections for cracking of th
tive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and corrective actions
DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes; equipped with a center wing fuel tank and Boeing original equipment manufacturer-in
Model MD-10-10F and MD-10-30F airplanes; Model DC-9-81 (MD- 81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes
manating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. This AD requires repetitiv
neral visual inspections of the ELT transmitter units (TUs), and corrective actions if necessary. This new AD corrects the manufacturer's nam
d TPR-900 Mode S transponders respond intermittently to Mode S interrogations from both ground-based and traffic collision avoidance s
ctions of the ELT transmitter units (TUs), and corrective actions if necessary. This AD was prompted by a fire on a parked and unoccupied a
f the hinge bearing lugs of the center section ribs of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (HFE
tigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections fo
DC-9-87 (MD-87), MD-88, and MD-90-30 airplanes; equipped with center wing fuel tank and Boeing original equipment manufacturer- insta
mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an u
cessary. This AD also requires repetitive inspections of certain repaired areas. This AD was prompted by reports of cracking of the wing rea
Station Zfs = 52.267; repetitive inspections for cracking in the front spar cap forward flanges of the vertical stabilizer, and either the aft fla
if necessary. This AD was prompted by a report of a crack found in the upper center skin panel at the aft inboard corner of a right horizon
ng those seats, seating systems, and their components that are shown to be unsafe from the affected fleet. This AD was prompted by a de
pending on the airplane configuration. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this A
s AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent possible sources of ignition in a fu
83) airplanes, DC-9-87 (MD-87) airplanes, MD-88 airplanes, and MD-90-30 airplanes. That AD currently requires modifying the flight deck d
certain oxygen cylinder assemblies from the airplane. This AD removes certain oxygen cylinder part numbers from the applicability. This A
blies from the airplane. This AD was prompted by the reported rupture of a high-pressure gaseous oxygen cylinder, which had insufficient s
nufacturer, which identified unsafe conditions for which the manufacturer has not provided corrective actions. We are issuing this AD to p
cking of the overwing frames from stations 845 to 905 (MD-87 stations 731 to 791), left and right sides, and corrective actions if necessary
Instructions for Continued Airworthiness, as applicable, to incorporate new AWLs for fuel tank systems to satisfy Special Federal Aviation
ell Douglas, and Airbus transport category airplanes. For certain systems, this AD requires replacing the evacuation system's shear-pin rest
ant inspections, and replacement, as necessary, of the rudder pedal bracket. The existing AD also currently requires, for certain airplanes,
e upper corners of the forward passenger doorjamb, installing or replacing doublers as applicable, and doing applicable repairs. This AD re
rplanes; and Model MD-88 airplanes; that requires repetitive inspections and functional tests of the static port heater assemblies, and cor
etect cracks in the horizontal stabilizer, and related investigative/corrective actions if necessary. This AD results from reports of cracks fou
onding jumper assembly, and attaching hardware to the refueling manifold in the right wing refueling station area. This AD results from fu
c pump, and other specified and corrective actions, as applicable. This AD also requires that, for certain airplanes, installation of additional
of all the lower cargo doors, repetitive inspections of all early configuration stop pad support fittings, and corrective action if necessary. Th
ber, and further investigative action and replacement of the assembly with a new or serviceable assembly, if necessary. This AD results fro
hat AD currently requires installing a water drain system for the slant pressure panels in the left and right wheel wells of the main landing g
 ermine the manufacturer, repetitive eddy current inspections for cracking, and modification or replacement if necessary. This AD also pro
ngine and auxiliary power unit (APU), as applicable, to determine the capability of the Firex electrical circuits to fire discharge cartridges, a
B034LB03) nickel cadmium batteries. That AD currently requires replacing all battery terminal screws, verifying that the battery contains de
e existing AD currently requires repetitive inspections to detect cracking of the main landing gear (MLG) shock strut pistons, and replaceme
e detailed inspections of the upper and lower caps of the rear spar of the left and right wings, and corrective action if necessary. This AD a
of both main landing gear (MLG) for corrosion, and corrective action if necessary. This action also requires replacing cadmium-plated retra
his amendment requires a general visual inspection for chafing of the power feeder cables of the auxiliary power unit (APU), and repair if n
r of the battery. This action is necessary to prevent damage to equipment or possible fire in the electrical/electronics equipment compart
g the airplane flight manual to include a procedure for discontinuing the use of certain cargo restraint strap assemblies installed per STC ST
lacement of certain freeze protection ribbon heaters in the lavatory water supply system, and flushing, cleaning, and sterilizing the potabl
st officer's seat track locking pins for insufficient engagement caused by seat track misalignment, and corrective actions if necessary. This
n of a program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airwo
e detent holes in the seat tracks; inspection of the seat lockpins for excessive wear; and corrective actions, if necessary. This action is nece
mpartment, repair if necessary, and coiling and stowing of excess wiring. This action is necessary to prevent wire chafing and subsequent s
and Model MD-90-30 airplanes. This action requires repetitive inspections to detect cracking of the shock strut cylinders of the left and rig
ne-time visual inspection to determine if discrepant circuit breakers are installed, and corrective action if necessary. This action is necessar
e inspections to detect discrepancies of electrical wiring installations in various areas of the airplane, and corrective action if necessary. Th
flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. The actions specified by that A
main landing gear (MLG) for water leakage, and repair of any leak found. This action is necessary to prevent the accumulation of water in
currently requires revisions to the Airplane Flight Manual; installation of inspection aids on the wing upper surfaces; and, among other ac
o don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. This action is necessary to prevent incapa
ection of the disconnect panel area above the aft left lavatory for chafed or damaged wires or unacceptable clearance between the wires
MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This amendment requires replacement of the emergency power switch knob on the overh
sting of certain replaced power relays. This amendment is prompted by reports indicating that the alternating current (AC) cross-tie relay
uires replacement of certain main landing gear (MLG) shock strut piston assemblies with new or serviceable, improved assemblies, which c
oper installation of the support clamp of the alternating current (AC) power relay feeder cables at the aft inboard side of the electrical pow
trical power feeder cables in the aft cargo compartment sidewall for chafing and/or preloading, and corrective actions, if necessary. This ac
equires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive
t currently requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distan
ssenger service unit (PSU) panels of the overhead stowage compartment with new dust seals. The AD provides two options to accomplish
rtain wires to detect chafing and preload; repair, if necessary; and modification of certain wire assemblies. This action is necessary to preve
e cabin fluorescent lighting ballast in the wiring harness of the overhead stowage compartment with new connectors. In lieu of the require
88 airplanes; and C-9 airplanes, that currently requires repetitive inspections to detect cracking of the rudder pedal adjuster hub assembly
odel MD-88 airplanes, that requires an inspection to detect chafing or overheat damage of the electrical wires located at fuselage station Y
D requires modification of the light switch for the cargo compartment(s). This action is necessary to prevent generation of smoke and fire in
ction requires repetitive inspections of the electric motors (or motors) of the auxiliary hydraulic pump for electrical resistance, continuity,
n aircraft. This AD requires you to remove from service any of these fire extinguishing system bottle cartridges. This AD is the result of sev
tie relay is installed; replacement of a certain AC cross-tie relay with a new AC cross-tie relay; and repetitive cleaning, inspection, repair an
to detect damage, burn marks, or discoloration at certain electrical plugs and receptacles of the sidewall lighting in the passenger cabin, an
g (SELCAL) system. The actions specified by this AD are intended to prevent inadvertent very high frequency transmissions and subsequen
wiring of the primary and alternate static port heaters for chafing, loose connections, and evidence of arcing, and to determine what type
cracking of the main landing gear (MLG) pistons, and repair or replacement of the pistons with new or serviceable parts, if necessary. This
er, and at what locations, metallized polyethyleneteraphthalate (MPET) insulation blankets are installed, and replacement of MPET insulati
ins of the evacuation slides with solid corrosion-resistant pins. This amendment is prompted by a report that, due to stress corrosion on t
epetitive tests to detect discrepancies of the Mode "C" transponder(s), air data computer, and certain wiring connections; and corrective a
nstallation of an external load compressor containment shield, or installation of a load compressor impeller with lower stress concentration
etermine the type of engine ignition switch installed in the hinged forward overhead switch panel, and replacement of certain rotary igniti
nspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective action
ir conditioning pneumatic supply control, if applicable, and revising the wiring of the pneumatic augmentation valve. This amendment is p
equires visual or eddy current inspections to detect cracks of the actuator cylinder support brackets of the slat drive mechanism assembly,
ation of hydraulic line restrictors in the main landing gear (MLG), and modification or replacement of the left and right MLG hydraulic dam
one-time inspection of the forward attach pins of the outboard flight spoiler actuators to determine whether the pins are of correct lengt
g bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer; and corrective actions, if necessary. This amendment is
t currently requires repetitive high frequency eddy current inspections of certain areas of the fuselage to detect cracks of the skin and/or l
acking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable p
quires a visual inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall, and the replacement of suspect
visual inspection to detect fatigue cracking of the lower left nose of certain longerons and the attaching frames; repair, if necessary; and i
lighting system in the passenger cabin, and to verify that the ends of all pins and sockets are even and that they are seated and locked int
embly of the tailcone emergency evacuation slide to determine the diameter of the swaged balls; reidentification of the harness assembly
certain fuselage skin panels, and repair, if necessary. For certain airplanes, this amendment also provides for an optional preventative mo
ection to detect chafing on the FIREX pipe assembly of the number one engine; and either repair of chafed pipe assemblies or replacemen
on to determine if the latching lever pin of the speed brake passes an axial force check, and a visual inspection to determine if the staking
n-regulating shutoff valves on the engine starter, or installation of a pressure relief valve in the pneumatic supply line to the starter air shu
racks in the upper fuselage skin in the area of the aft pressure bulkhead tee. This amendment requires new improved repetitive inspectio
nspections to detect cracks in the vertical leg of the rear spar lower cap of the wings, and various follow-on actions. This amendment is pr
ype of fluorescent light ballasts installed in the cabin sidewall; and installation of a protective cover on the ballast, replacement, or remova
Airplane Flight Manual (AFM) to include limitations and procedures to address situations in which the autopilot or autothrottle fails to dis
sting turbine wheel shroud and installing one constructed of Hastelloy "S" material, or installing a containment augmentation ring. This am
dification of the girt and firing lanyard stowage. This amendment is prompted by reports of in-cabin inflation of certain evacuation slides d
elage upper skin and frames in the area of the loop antenna assemblies of the automatic direction finder (ADF), and repair, if necessary. T
nd repair, if necessary; provides for the option of revising the FAA-approved maintenance program to include a schedule of leak checks; re
s repetitive inspections to detect fatigue cracking in the area of the attach tees of the ventral aft pressure bulkhead. This amendment req
vatory waste receptacles; establishment of a procedure to announce to airplane occupants that smoking is prohibited in the lavatories; ins
of the oxygen mask lanyards of the passenger service unit (PSU), and modification of lanyards that are longer than the proper length. Thi
dification of the slant panel insulation blankets on the slant pressure panel of the main landing gear. The amendment also requires a visua
certain inspections and structural modifications. This amendment requires additional inspections and structural modifications. This amen
f or damage to the wire bundle in the overhead switch panel of the cockpit, application of spiral wrap to the wire bundle, and corrective a
bilizer primary trim motors. That AD was prompted by an analysis which revealed that certain incorrectly manufactured motor shafts coul
the emergency power switch in the overhead switch panel with a new switch. This amendment is prompted by a report of heavy smoke i
electrical plugs and receptacles of the sidewall lighting in the passenger cabin, and correction of discrepancies. This amendment would a
s modifying the APU to install an exhaust centerbody. This amendment is prompted by reports of two uncontained APU failures where tu
y proper installation of the wire termination lugs on the ignition selector switch, and removal and correct installation of any improperly ins
tailcone release locking cable fitting assembly, and replacement or modification of the assembly, if necessary. This amendment is prompt
y several in-flight incidents in which the engine nose cowl separated or nearly separated from the airplane. The actions specified by this A
es have been installed in certain galley water heaters and coffee makers; and either replacement of the discrepant valves, or discontinued
of the center and side windshields, and replacement of discrepant windshields. This amendment is prompted by reports that the core ply
etect cracking in the skin and doublers around the upper anticollision light cutout, and repair, if necessary. This amendment expands the
of the auxiliary power unit (APU) power feeder cable installation, repair of damaged cables, and modification of the cable installation. Thi
ng these DME units to ensure they are functioning properly. Several reports of the affected DME units failing to process and update distan
on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic or
e cargo compartments to determine if slotted attach points are present and, if not, modification of the panels. This amendment is prompt

sure bulkhead, and repair, if necessary. This amendment is prompted by reports of cracking found in the ventral aft pressure bulkhead on
tigue cracking of the fuselage frames and longerons 16R and 17R above the forward lower cargo door; repair, if necessary; and modificatio

amendment is prompted by reports of fatigue cracks found in the drain port housings of the PTU's on several airplanes. The actions speci

vating the left and right lower sidewall lights located in the passenger compartment. This action is necessary to prevent arcing and heat d
n of an airplane model from paragraph (c) of the AD. This AD is applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82

tly requires either the installation of external protective doublers between the outboard flight spoiler actuators and the aft spar webs of th

al condition of the jackscrew assembly and the area around the jackscrew assembly to detect the presence of metal shavings and flakes. Th
 -30 airplanes. AD 2022-09-18 required revising the limitations and operating procedures sections of the existing airplane flight manual (AF
perations requiring radio altimeter data when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs)
tions if necessary. Since the FAA issued AD 2007-10-04, it has been determined that certain compliance times and repetitive intervals mus
re subject to widespread fatigue damage (WFD). WFD analysis found that fatigue cracks could grow to a critical length after the structural
MD-80) airplanes; and Model MD-90-30 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied on to
and right side center wing lower skin, and repair if any crack was found. This AD continues to require repetitive ETHF inspections for any c
air data heat (ADH) system. We are issuing this AD to address the unsafe condition on these products.
nspecting the airplane to determine the number of affected pitot probes installed and replacing the affected pitot probes. We are issuing
D to correct the unsafe condition on these products.
n for cracking in these structures, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these prod
ctions for cracking of the rear spar lower caps of the horizontal stabilizer, post-modification and post-repair inspections, and corrective ac
n, and corrective actions if necessary. This AD was prompted by reports of cracking at certain stringers, associated end fittings, and skins in
uipment manufacturer-installed auxiliary fuel tanks. AD 2012-18-05 required adding design features to detect electrical faults and to detec
-9-87 (MD-87) airplanes; Model MD-88 airplanes; and Model MD-90-30 airplanes. This AD was prompted by reports of latent air data tran
This AD requires repetitive high frequency eddy current (ETHF) inspections for cracks in the areas around the two aft-most barrel nut holes
the manufacturer's name in the AD applicability and adds a source of approval for an installation. AD 2013-18-09 was prompted by a fire
ffic collision avoidance system (TCAS-) equipped airplanes. This AD requires testing and calibration of the alignment of the transponders. W
arked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. We are issuing this AD to detect a
uency eddy current (HFEC) inspections for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the ho
repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessa
ment manufacturer- installed auxiliary fuel tanks. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD re
identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: \n\n\n\tCracks have been fo
cracking of the wing rear spar lower cap at the outboard flap and inboard drive hinge at station Xrs=164.000; the cracking is due to mater
zer, and either the aft flanges or side skins; repetitive inspections for loose and missing fasteners; and related investigative and corrective a
corner of a right horizontal stabilizer. We are issuing this AD to detect and correct cracks in the horizontal stabilizer upper center skin pane
D was prompted by a determination that the affected seats and seating systems may not meet certain flammability, static strength, and d
rer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors
sources of ignition in a fuel tank caused by an electrical fault in the fuel boost pumps. An ignition source in the fuel tank could result in a fi
odifying the flight deck door. This AD revises the applicability by removing certain airplanes. This AD was prompted by a report indicating t
the applicability. This AD was prompted by the reported rupture of a high- pressure gaseous oxygen cylinder, which had insufficient stren
, which had insufficient strength characteristics due to improper heat treatment. We are issuing this AD to prevent an oxygen cylinder from
e are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could
tive actions if necessary. This AD results from reports of cracked overwing frames. We are issuing this AD to detect and correct such crack
Special Federal Aviation Regulation No. 88 requirements. This AD results from a design review of the fuel tank systems. We are issuing this
n system's shear-pin restraints with new ones. For certain other systems, this AD requires an inspection for manufacturing lot numbers; an
es, for certain airplanes, replacing the rudder pedal bracket assemblies with new, improved parts, which would terminate the repetitive ins
cable repairs. This AD results from reports of fatigue cracking in the fuselage skin at the upper corners of the forward passenger doorjamb
ater assemblies, and corrective actions if necessary. The actions specified by this AD are intended to prevent an electrical short of the stati
om reports of cracks found in the horizontal stabilizer--in the upper and lower aft skin panels at the aft inboard corner at station XH = 8.2,
a. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing on the in-tank side of
installation of additional protective sleeving on the upper portion of the auxiliary hydraulic pump wire assembly. This AD results from repo
e action if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from a report of cr
sary. This AD results from a determination that the holes of certain aft attach fitting assemblies of the spoiler link were not cold-worked d
ells of the main landing gear (MLG). This new AD also requires inspecting the seal assemblies of the overwing emergency exit doors for def
 essary. This AD also provides for optional terminating action for the repetitive inspections. The actions specified by this AD are intended to
re discharge cartridges, and troubleshooting actions if necessary. This new AD removes certain transport category airplanes from the appli
t the battery contains design specification cells, and replacing the cells if the battery contains non-design specification cells. This new AD re
t pistons, and replacement of a cracked piston with a new or serviceable part. This amendment removes certain airplanes but requires tha
on if necessary. This AD also provides an optional modification that would end the repetitive inspections. This AD is prompted by reports o
g cadmium-plated retract cylinder support bushings and bearings of both MLG. This action is necessary to detect and correct corrosion to
nit (APU), and repair if necessary. This amendment also requires replacement of a support bracket located on the left side of the lower car
nics equipment compartment due to electrical arcing between the ground stud of the main battery and adjacent structure. This action is in
blies installed per STC ST01004NY, if used as the only cargo restraint. This amendment also requires revising the airplane weight and balan
and sterilizing the potable water system; disconnecting, coiling, and stowing the wiring of the freeze protection ribbon heater; or removal
ctions if necessary. This action is necessary to prevent uncommanded movement of the captain's and first officer's seats during takeoff an
ure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This action is nec
ssary. This action is necessary to prevent uncommanded seat movement during takeoff and/or landing, which could result in interference
hafing and subsequent shorting to structure in the forward cargo compartment, which could result in smoke or fire in the airplane. This ac
inders of the left and right main landing gears (MLG), and replacement of any cracked shock strut cylinder. This action is necessary to prev
y. This action is necessary to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and brea
e action if necessary. The actions specified by this AD are intended to prevent smoke and fire in various areas of the airplane due to heat d
ctions specified by that AD are intended to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of cont
ccumulation of water in the wheel wells of the MLG during flight, which could freeze on the lateral control mixer and control cables, resulti
es; and, among other actions, installation of an overwing heater blanket system or primary upper wing ice detection system, and installati
essary to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This action is
ance between the wires and adjacent structure, and corrective actions, if necessary. The actions specified by this AD are intended to preve
witch knob on the overhead switch panel in the flight compartment with a new, improved knob made of non-conductive material. The acti
rent (AC) cross-tie relay shorted out internally, which caused severe smoke and burn damage to the relay, aircraft wiring, and adjacent pan
ved assemblies, which constitutes terminating action for the requirements of certain other ADs. This action is necessary to prevent fatigue
side of the electrical power center, and corrective actions, if necessary. This action is necessary to prevent the AC power relay feeder cable
ons, if necessary. This action is necessary to prevent possible arcing of the electrical power cables in the aft cargo compartment sidewall a
g gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. The existi
ppropriate landing distance and flap positions, if applicable, for wet or icy runways. That AD also provides for an optional terminating actio
o options to accomplish this. Operators can either replace the seals all at once or remove the seals and repetitively clean and inspect the a
tion is necessary to prevent insufficient clearance between wire assemblies and the ice protection airduct and airstair door interlock rod; c
ors. In lieu of the required replacement, this AD requires adding interface seals to the existing interface connectors of the cabin fluorescen
l adjuster hub assembly, and replacement of the assembly, if necessary. That AD also provides for an optional terminating action for the re
ated at fuselage station Y=110.000 bulkhead of the lower nose left tunnel; and corrective actions, if necessary. This AD also requires replac
ation of smoke and fire in a cargo compartment due to an illuminated light with a missing cover contacting cargo contents for an extended
l resistance, continuity, mechanical rotation, and associated wiring resistance/voltage; and corrective actions, if necessary. The actions sp
is AD is the result of several incidents where the fire extinguishing system bottle cartridges activated with excessive energetic force. In one
ng, inspection, repair and testing of a certain AC cross-tie relay. This action is necessary to prevent AC cross-tie relay failures, which could r
n the passenger cabin, and correction of discrepancies. That AD also requires modification of the electrical connectors, which terminates th
missions and subsequent loss of radio communications for airplane and/or airport operations; and to prevent inadvertent high frequency
to determine what type of insulation blanket is installed in the area of the static port heaters; and corrective actions, if necessary. This acti
parts, if necessary. This amendment requires, among other actions, repetitive dye penetrant and magnetic particle inspections to detect c
cement of MPET insulation blankets with new insulation blankets. This amendment is prompted by reports of in- flight and ground fires o
e to stress corrosion on the lanyard pins, the arms of the lanyard assembly of the evacuation slide were found to be frozen. The actions sp
ections; and corrective actions, if necessary. The requirements of that AD were intended to prevent false advisories that direct the flightc
 wer stress concentrations. This amendment is prompted by reports of load compressor impeller failures. The actions specified by this AD
nt of certain rotary ignition switches with new design rotary ignition switches. This amendment is prompted by reports of smoke in the fli
ee; and corrective actions, if necessary. This document corrects a typographical error in a service bulletin reference. This correction is nece
ve. This amendment is prompted by a report indicating that the pneumatic augmentation valve may go fully open when an engine fails du
ve mechanism assembly, and replacement of any cracked brackets. This amendment continues to require repetitive eddy current inspecti
right MLG hydraulic damper assemblies. This amendment requires an additional modification of the MLG hydraulic damper assemblies, or
pins are of correct length, and follow-on corrective actions. This amendment is prompted by a report that forward attach pins of incorrec
ary. This amendment is prompted by reports of corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal
acks of the skin and/or longeron, and various follow-on actions. That AD also requires installation of a preventative modification, which te
nder with a serviceable part. That AD also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if a
replacement of suspect ballasts with new or serviceable ballasts. This amendment is prompted by reports of smoke, fumes, and/or electr
epair, if necessary; and installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of ce
re seated and locked into place. This amendment also requires replacement of any discrepant part with a new part, and modification of t
of the harness assembly; and reinstallation or replacement of the assembly with a new assembly, if necessary. This amendment is prompt
ptional preventative modification, which, if accomplished, would terminate the repetitive inspections. This amendment is prompted by re
semblies or replacement of the chafed pipe assemblies with new pipe assemblies; and modification of the FIREX and the pneumatic sense
determine if the staking of the latching lever pin is acceptable; and follow-on corrective action, if necessary. This amendment is prompted
ine to the starter air shutoff valve on engines 1 and 2. This amendment is prompted by reports of uncontained failures of engine starters
oved repetitive inspections and follow-on actions, and expands the applicability of the existing AD to include additional airplanes. This ame
s. This amendment is prompted by the necessity to provide the current address of the FAA office that receives the results of reporting req
replacement, or removal/disconnection of the ballast, if necessary. That action also requires, for some airplanes, removal of the dust bar
r autothrottle fails to disengage. That AD was prompted by incidents in which the flightcrew was unable to disconnect the autopilot or aut
gmentation ring. This amendment deletes the option of installing a turbine shroud constructed of Hastelloy "S" material. This amendment
rtain evacuation slides due to the impingement of the galley service cart on the slide girt and firing lanyard. The actions specified by this A
d repair, if necessary. This amendment adds a requirement to perform a visual and an eddy current inspection of the fuselage forward up
hedule of leak checks; requires the installation of a cap on the flush/fill line; and requires replacement or modification of the vent system p
d. This amendment requires revised inspection and repair procedures, and provides for terminating action. It also deletes Model MD-88
ited in the lavatories; installation of ashtrays at certain locations; and repetitive inspections to ensure that lavatory waste receptacle door
n the proper length. This amendment is prompted by a report that the length of the oxygen mask lanyards of the PSU were found to be to
ent also requires a visual inspection to detect discrepancies of the left and right seal assemblies of the overwing emergency exit door, and
modifications. This amendment is prompted by an evaluation conducted by the Airworthiness Assurance Working Group, which identified
bundle, and corrective actions, if necessary. That AD was prompted by reports of chafed and shorted wires that resulted in smoke emana
ctured motor shafts could fail prematurely and, in turn, cause the primary trim motor to fail. The actions specified in that AD are intended
report of heavy smoke in the cockpit coming from the overhead switch panel on a Model DC-9-81 series airplane. The actions specified by
his amendment would also require modification of the electrical connectors, which, when accomplished, would terminate the inspection r
d APU failures where turbine wheel fragments exited the APU exhaust axially and damaged the aircraft. The actions specified by this AD a
on of any improperly installed wire termination lugs. This amendment also requires application of sealant to the wire termination lugs and
s amendment is prompted by reports of the inability of the tailcone to deploy because the swaged ball on the cable had jammed after pas
ctions specified by this AD are intended to prevent separation of the engine nose cowl from the airplane during severe vibration of the eng
t valves, or discontinued use of the water heaters or coffee makers and installation of placards indicating that these units are not to be use
reports that the core ply of certain windshields was incorrectly tempered during the manufacturing process. The actions specified by this
mendment expands the applicability to include additional Model DC-9-80 series airplanes and Model MD-88 airplanes, and requires the pe
e cable installation. This amendment requires an inspection of previously modified airplanes to determine whether a spacer or "stand off
ocess and update distance outputs, and reports of these units establishing a continuous restart mode upon power application prompted t
dated computer logic or reprogramming certain processors while they are still on board the aircraft. The development of candidate enha
is amendment is prompted by a report that certain panels were manufactured without the appropriate slotted attach points. The actions

aft pressure bulkhead on several airplanes. The actions specified in this AD are intended to prevent the propagation of cracks in the ventra
cessary; and modification of the fuselage frames and longerons, if necessary, and follow-on repetitive inspections to detect fatigue crackin

lanes. The actions specified by this AD are intended to prevent failure of the PTU housing due to fatigue cracking, which could result in th

event arcing and heat damage of the Luminator fluorescent lamp holders located outboard of the Passenger Service Unit panel, which cou
C-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87); Model MD-88 airplanes; and Model MD-90-30 series airplanes

d the aft spar webs of the wings, or replacement of the pistons of the outboard flight spoiler actuators with improved pistons. This action

al shavings and flakes. This amendment also requires inspecting for metallic particles in the lubrication for the jackscrew assembly of the h
 rplane flight manual (AFM) to incorporate specific operating procedures for, depending on the airplane model, instrument landing system
o Air Missions (NOTAMs). Since the FAA issued AD 2021-23-12, the FAA determined that additional limitations are needed due to the conti
repetitive intervals must be reduced to address the unsafe condition. This AD continues to require the actions specified in AD 2007-10-04
ngth after the structural modification point (SMP) for these center wing lower stringers. This AD requires replacing certain left and right sid
s cannot be relied on to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.
HF inspections for any cracking in the left and right side center wing lower skin, and repair if any crack is found. This AD also requires expa

probes. We are issuing this AD to address the unsafe condition on these products.

condition on these products.

ctions, and corrective actions if necessary. This AD also provides an optional terminating fatigue life enhancement modification. We are iss
end fittings, and skins in the center wing fuel tank where the stringers meet the end fittings. We are issuing this AD to detect and correct
trical faults and to detect a pump running in an empty fuel tank. Since we issued AD 2012-18-05, we have determined that it is necessary t
ts of latent air data transducer degradation. This AD requires revising the maintenance or inspection program, as applicable, to incorporat
aft-most barrel nut holes of the upper rear spar caps, and corrective actions if necessary; and repetitive ETHF inspections for cracks in the a
was prompted by a fire on a parked and unoccupied airplane; preliminary information indicated combustion in the area of the ELT TU. Thi
nt of the transponders. We are issuing this AD to correct the unsafe condition on these products.
suing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an electrical short a
center section of the horizontal stabilizer; measuring crack length and blending out cracks; and replacing the horizontal stabilizer center se
ons, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not suppor
manufacturer. This AD requires adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. We a
\n\tCracks have been found on seats (with) backrest links P/N (part number) 90-000200-104-1 and 90-000200-104-2. These cracks can sig
cracking is due to material fatigue from normal flap operating loads. We are issuing this AD to detect and correct such fatigue cracking, wh
stigative and corrective actions if necessary. This AD was prompted by reports of cracked vertical stabilizer skin, a severed front spar cap, e
r upper center skin panel. Uncorrected cracks might ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
ty, static strength, and dynamic strength criteria. Failure to meet static and dynamic strength criteria could result in injuries to the flightcre
h flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
l tank could result in a fire or an explosion and consequent loss of the airplane.
d by a report indicating that certain equipment of the flight deck door is defective. We are issuing this AD to prevent failure of this equipm
ch had insufficient strength characteristics due to improper heat treatment. We are issuing this AD to prevent an oxygen cylinder from rup
t an oxygen cylinder from rupturing, which, depending on the location, could result in structural damage and rapid decompression of the a
mable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
t and correct such cracking, which could sever the frame, increase the loading of adjacent frames, and result in damage to adjacent struct
tems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or
acturing lot numbers; and a general visual inspection of the shear-pin restraint for discrepancies, and corrective actions if necessary. This A
minate the repetitive inspections. For certain airplanes, this new AD requires initial inspection at a reduced threshold, removes an inspecti
ard passenger doorjamb. We are issuing this AD to prevent cracking of the fuselage skin at the upper corners of the forward passenger doo
ectrical short of the static port heater from sparking and igniting the insulation blanket adjacent to the static port heater, which could resu
rner at station XH = 8.2, and in the rear spar upper caps adjacent to the aft skin panel at station XH = 10.0. We are issuing this AD to detect
ng on the in-tank side of the fueling valve during a lightning strike, which could result in an ignition source that could ignite fuel vapor and
his AD results from reports of shorted wires and evidence of arcing on the power cables of the auxiliary hydraulic pump, as well a fuel syst
esults from a report of cracks found in the area of the upper and lower stop pad support fittings of the cargo door pan on numerous airpla
were not cold-worked during production. We are issuing this AD to prevent fatigue cracking of the aft attach fitting of the spoiler link and c
rgency exit doors for defects and constant gap; replacing defective door seals; performing repetitive operational checks of the water drain
 y this AD are intended to prevent fracture of the upper lock link assembly of the NLG, which could result in failure of the NLG to extend fo
airplanes from the applicability of the existing AD. This AD results from reports indicating that fire extinguishers for the engine and auxilia
tion cells. This new AD requires an inspection for certain nickel cadmium batteries and, if necessary, replacing battery terminal screws with
irplanes but requires that the existing inspections, and corrective actions if necessary, be accomplished on additional MLG shock strut pist
s prompted by reports of fatigue cracks in the upper and lower caps of the wing spar. We are issuing this AD to detect and correct fatigue c
and correct corrosion to the retract cylinder support fitting of the MLG and the cylinder bore in the support fitting, which could result in co
left side of the lower cargo compartment with a new "U" shaped bracket. This action is necessary to prevent chafing of the power feeder
tructure. This action is intended to address the identified unsafe condition.
rplane weight and balance manual to include the same procedure described previously. The actions specified by this AD are intended to p
bon heater; or removal of freeze protection heaters. This action is necessary to prevent failure of freeze protection ribbon heaters, which
s seats during takeoff and landing, which could result in interference with the operation of the airplane and consequent temporary loss of
e goal. This action is necessary to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes. Thi
ld result in interference with the operation of the airplane and consequent temporary loss of control of the airplane. This action is intende
e in the airplane. This action is intended to address the identified unsafe condition.
tion is necessary to prevent failure of the shock strut cylinders of the MLGs due to cracking, which could result in collapse of the MLGs and
long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartm
he airplane due to heat damage and/or electrical arcing of improperly installed wiring. This action is intended to address the identified uns
ould result in loss of control of the airplane. This amendment removes certain requirements for certain airplanes and revises the direction
nd control cables, resulting in restricted lateral control and consequent reduced controllability of the airplane. This action is intended to a
on system, and installation of a heater protection panel or an equipment protection device on certain overwing heater blanket systems. Th
e airplane. This action is intended to address the identified unsafe condition.
D are intended to prevent chafing of wires at the disconnect panel above the aft left lavatory, which could result in electrical arcing, and c
uctive material. The actions specified by this AD are intended to prevent the knob from conducting electricity, which could result in delive
wiring, and adjacent panels. The actions specified by this AD are intended to prevent internal arcing of the left and right generator power
essary to prevent fatigue cracking of the MLG shock strut pistons, which could result in failure of the MLG shock strut pistons during landin
power relay feeder cables from chafing against the aft inboard side of the electrical power center due to improper installation, which coul
compartment sidewall and consequent damage to equipment and the adjacent structure, which could result in smoke and/or fire in the c
on of the NLG. The existing AD also provides for terminating action for the repetitive inspections. This amendment requires, among other
ptional terminating action for the applicable AFM revision. For certain airplanes, this action requires accomplishment of the previously opti
y clean and inspect the area to defer the installation for an interim period. The actions specified by this AD are intended to ensure replace
tair door interlock rod; chafing; and consequent arcing of wire assemblies. Such arcing could result in damage to electronic equipment and
s of the cabin fluorescent lighting ballast between certain stations and reidentifying the connector assemblies. This action is necessary to p
minating action for the repetitive inspections. This amendment requires accomplishment of a new terminating action for the repetitive ins
s AD also requires replacing the external power ground stud with a new ground stud using new attaching parts, torquing new attachments
ontents for an extended period of time. This action is intended to address the identified unsafe condition.
ecessary. The actions specified by this AD are intended to prevent various failures of the electric motor(s) of the auxiliary hydraulic pump a
e energetic force. In one instance, the discharge valve outlet screen fractured and the screen material went through the distribution mani
ay failures, which could result in internal arcing of the relay and smoke and/or fire in the cockpit and cabin. This action is intended to addre
ors, which terminates the inspection requirement. That action was prompted by reports of failures of the electrical connectors in the side
vertent high frequency transmissions and subsequent electrical shock to ground service personnel and/or damage to the airplane during f
ns, if necessary. This action is necessary to ensure that insulation blankets constructed of metallized MylarTM are removed or protected f
e inspections to detect cracks of the MLG pistons; repair and replacement of discrepant parts; and installation of a preventative modificati
flight and ground fires on certain airplanes manufactured with insulation blankets covered with MPET, which may contribute to the spread
e frozen. The actions specified by this AD are intended to prevent the improper deployment of the evacuation slide due to stress corrosio
es that direct the flightcrew to change course and either climb or descend, which could result in the flightcrew deviating the airplane from
 ons specified by this AD are intended to prevent an uncontained APU failure and damage to the airplane.
eports of smoke in the flight compartment during engine ignition selection. The actions specified by this AD are intended to prevent an int
e. This correction is necessary to ensure that the appropriate service information is used to accomplish the AD. \n\n\tThe incorporation by
when an engine fails during initial climb prior to deactivation of the second segment climb switch. The actions specified by this AD are int
ve eddy current inspection, adds an inspection requirement, and expands the area of inspection. This amendment also provides terminati
c damper assemblies, or replacement of the MLG hydraulic damper assemblies with modified and reidentified hydraulic damper assemblie
d attach pins of incorrect length were found to be installed in the flight spoiler actuators on several in-service and in-production airplanes.
he vertical-to-horizontal stabilizer, apparently due to the improper brushing of cadmium on the hinge plates during manufacture. The acti
ve modification, which terminates the repetitive inspections. The actions specified in that AD are intended to prevent fatigue cracks, whic
rake systems, which, if accomplished, terminates the repetitive inspections. This amendment requires that the subject inspection be acco
ke, fumes, and/or electrical fire emitting from the baggage bin of the aft passenger compartment due to the failure of the fluorescent ligh
of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cr
rt, and modification of the electrical wiring and connectors of the sidewall lighting system in the passenger cabin. This amendment is prom
s amendment is prompted by a failed deployment of the tailcone emergency evacuation slide during a system test conducted by the man
dment is prompted by reports of fatigue cracking of certain fuselage skin panels. The actions specified by this AD are intended to prevent s
nd the pneumatic sense pipe assembly clamp marriage. This amendment revises the applicability of the existing AD to include additional
amendment is prompted by reports that the speed brake handle jammed in the ground spoiler position. The actions specified by this AD a
lures of engine starters during flight and maintenance, which resulted from the application of excessive pressure on the engine starter tha
onal airplanes. This amendment is prompted by additional reports of fatigue cracking and improperly seated attachments in the upper fus
e results of reporting requirements of this AD. The actions specified in this AD are intended to prevent fatigue cracking in the vertical leg o
removal of the dust barriers from the outboard ceiling panels, and installation of modified outboard ceiling panels. This amendment wou
nect the autopilot or autothrottle function from the engaged position, due to a discrepancy in a microswitch that is associated with the op
aterial. This amendment is prompted by a report of insufficient APU containment capability with the Hastelloy "S" shroud alone installed.
ctions specified by this AD are intended to prevent inadvertent inflation of the evacuation slides inside the cabin, which could contribute t
the fuselage forward upper skin under the antennas, followed by the reinstallation of the ADF antennas using an improved procedure. Th
tion of the vent system piping. This amendment is prompted by continuing reports of damage to engines and airframes, separation of eng
o deletes Model MD-88 airplanes from the applicability of the rule. This amendment is prompted by reports of fatigue cracking found in th
y waste receptacle doors operate correctly. That AD was prompted by fires occurring in lavatories, which were caused by, among other th
PSU were found to be too long, apparently due to improper installation during production. The actions specified by this AD are intended t
mergency exit door, and replacement of any discrepant door seal. This amendment is prompted by a report that the flaps and landing gea
Group, which identified additional inspections and structural modifications for mandatory action. The actions specified by this AD are inte
esulted in smoke emanating from the overhead switch panel of the cockpit. This amendment expands the applicability of the rule to inclu
in that AD are intended to prevent such failures of the primary trim motor, which could ultimately result in reduced controllability of the a
The actions specified by this AD are intended to ensure replacement of the emergency power switch when it has reached its maximum lif
rminate the inspection requirement. This amendment is prompted by reports of failures of the electrical connectors in the sidewall fluore
ns specified by this AD are intended to prevent an axially uncontained APU failure and damage to the aircraft.
wire termination lugs and the attachment screws. This amendment is prompted by a report that, during the manufacturer's production flig
e had jammed after passing into the release handle hole. The actions specified by this AD are intended to prevent the inability of the tailc
vere vibration of the engine.
e units are not to be used. This amendment is prompted by reports of injuries to cabin crew members that resulted from explosions of ga
actions specified by this AD are intended to prevent failure of the windshield.
nes, and requires the performance of stress coining procedures on the plate nut clearance holes or installation of shims and an external do
er a spacer or "stand off" has been installed, and installation of those items, if necessary. This amendment is prompted by reports of gene
application prompted this AD. The actions specified by this AD are intended to prevent improper operation of this equipment, which cou
ment of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the p
ach points. The actions specified by this AD are intended to ensure that the action of the cargo compartment pressure relief panels will en

on of cracks in the ventral aft pressure bulkhead, which could lead to failure of the bulkhead and subsequent rapid decompression of the a
to detect fatigue cracking of the skin adjacent to the modification. That AD was prompted by numerous instances of fatigue cracking of th

which could result in the loss of both hydraulic systems (until the PTU is shut off).\n\n\tThe incorporation by reference of certain publicati

ce Unit panel, which could result in smoke and fire in the passenger compartment. This action is intended to address the identified unsafe
D-90-30 series airplanes. This AD requires installation of a pipe support and clamps on the hydraulic lines in the aft fuselage; replacement

ved pistons. This action corrects a part number specified for flight spoiler actuator assembly that is acceptable for installation on these air

screw assembly of the horizontal stabilizer and surrounding area to detect any discrepancy; follow-on actions; and corrective actions, if ne
strument landing system (ILS) approaches, non-precision approaches, ground spoiler deployment, and go-around and missed approaches,
needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United S
ecified in AD 2007-10-04 with revised compliance times for certain actions. The FAA is issuing this AD to address the unsafe condition on th
certain left and right side center wing lower stringers. The FAA is issuing this AD to address the unsafe condition on these products.
operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that during approach, landings, and go- arounds,
is AD also requires expanding the inspection area to include adjacent stringers with similar stress levels and to perform repetitive inspecti

modification. We are issuing this AD to address the unsafe condition on these products.
D to detect and correct cracking in the center wing lower skin. Such cracking could cause structural failure of the wings.
ned that it is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. This new AD allows certain action
applicable, to incorporate special compliance items (SCIs). We are issuing this AD to prevent erroneous air data information, which could l
ections for cracks in the areas around the two aft- most barrel nut holes of any repaired or replaced upper rear spar cap, and corrective acti
e area of the ELT TU. This new AD was prompted by the identification of an error in the applicability of AD 2013-18-09. We are issuing this

t in an electrical short and possible ignition source.

ontal stabilizer center section rib, if necessary. We are issuing this AD to detect and correct cracking in the hinge bearing lugs of the horizo
ing structure not supporting the limit load condition, which could lead to loss of structural integrity of the wing.
an empty fuel tank. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flamma
4-2. These cracks can significantly affect the structural integrity of seat backrests. \n\nFailure of the backrest links could result in injury to
such fatigue cracking, which could result in fuel leaks, damage to the wing skin or other structure, and consequent reduced structural integ
severed front spar cap, elongated fastener holes at the leading edge of the vertical stabilizer, and a cracked front spar web and front spar
e horizontal stabilizer.
n injuries to the flightcrew and passengers during emergency landing conditions. In the event of an in-flight or post- emergency landing fir

nt failure of this equipment, which could jeopardize flight safety. \n\nDATES: This AD is effective August 5, 2010, to all persons except thos
oxygen cylinder from rupturing, which, depending on the location, could result in structural damage and rapid decompression of the airpla
decompression of the airplane, damage to adjacent essential flight equipment, deprivation of the necessary oxygen supply for the flightc

mage to adjacent structure and loss of overall structural integrity of the airplane.
s, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and
tions if necessary. This AD results from several reports of corroded shear-pin restraints that prevented Goodrich evacuation systems from
old, removes an inspection option, and lengthens the repetitive inspection intervals. This AD results from reports of failures of the captain
e forward passenger doorjamb, which could lead to loss of overall structural integrity of the airplane.
heater, which could result in smoke and/or fire in the cabin area. This action is intended to address the identified unsafe condition.
issuing this AD to detect and correct cracks in the upper and lower aft skin panels and rear spar upper caps, which, if not corrected, could
uld ignite fuel vapor and cause a fuel tank explosion.
pump, as well a fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent shorted wires or arcing at the auxi
pan on numerous airplanes. We are issuing this AD to prevent cracks in the cargo door pan, which could result in the inability to fully press
g of the spoiler link and consequent failure of the fitting. Failure of the fitting could result in an asymmetrical lift condition and consequent
hecks of the water drain system auto drain valve and corrective actions if necessary; and, for certain airplanes, modifying the insulation bla
of the NLG to extend following a gear-down selection, and consequent gear-up landing, structural damage, and possible injury to passeng
r the engine and auxiliary power unit had failed to discharge when commanded. We are issuing this AD to prevent failure of the fire exting
ery terminal screws with new hex head bolts and adding shims. This AD is prompted by a report of battery screws shearing off while unde
nal MLG shock strut pistons. This amendment also requires replacing the MLG shock strut pistons with new improved parts, which would t
ect and correct fatigue cracking in the upper and lower caps of the rear spar of the left and right wings, which could result in structural fai
which could result in compromised integrity of the retract cylinder support fitting of the MLG and possible damage to the hydraulic system
ng of the power feeder cables of the APU, which could result in electrical arcing to adjacent structure and consequent fire in the airplane.

his AD are intended to prevent shifting or unrestrained cargo in the cargo compartment, which could cause an unexpected change in the a
n ribbon heaters, which could result in the charring, scorching, smoking, and shorting out of freeze protection ribbon heaters in the lavato
quent temporary loss of control of the airplane. This action is intended to address the identified unsafe condition.
y of these airplanes. This action is intended to address the identified unsafe condition.
ne. This action is intended to address the identified unsafe condition.

collapse of the MLGs and consequent reduced controllability during landing. This action is intended to address the identified unsafe conditi
e in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
ddress the identified unsafe condition.
nd revises the direction to the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning occurs, rathe
s action is intended to address the identified unsafe condition.
ater blanket systems. That AD also requires disabling the anti-ice systems for the upper wing surface on certain airplanes. This document

n electrical arcing, and consequent fire in the cabin. This action is intended to address the identified unsafe condition.
ich could result in delivery of an electrical shock and consequent injury to flightcrew or maintenance personnel. This action is intended to
d right generator power relays, auxiliary power relays, and external power relays, and consequent smoke and/or fire in the cockpit and cab
rut pistons during landing or jacking of the airplane, and consequent damage to the airplane structure and injury to the passengers, flightc
installation, which could result in electrical arcing and damage to adjacent structures, and consequent smoke and/or fire in the electrical
moke and/or fire in the cargo compartment. This action is intended to address the identified unsafe condition.
requires, among other actions, expanding the applicability of the existing AD, revising compliance times; and adding new inspection requ
ent of the previously optional terminating action. The actions specified by this AD are intended to prevent the flightcrew from performing a
ended to ensure replacement of dust seals of the lower PSU panel that may contribute to the spread of a fire when ignition occurs from el
ectronic equipment and adjacent structures, or cause the insulation blankets to ignite, which could result in smoke and fire in the flight de
s action is necessary to prevent electrical shorting and arcing due to the presence of water in the lighting ballast interface connectors, whi
on for the repetitive inspections. This amendment is prompted by that FAA's determination that further rulemaking is necessary. The actio
quing new attachments, and installing a nameplate. This action is necessary to prevent loose external power ground wires, which could ca

uxiliary hydraulic pump and associated wiring, which could result in fire at the auxiliary hydraulic pump and consequent damage to the adj
gh the distribution manifold. The actions specified by this AD are intended to prevent damage to fire extinguishing system components ca
tion is intended to address the identified unsafe condition.
al connectors in the sidewall fluorescent lighting, which resulted in smoke or lighting interruption in the passenger cabin. This amendment
e to the airplane during fueling operations or fuel tank maintenance. This action is intended to address the identified unsafe condition.
removed or protected from the area of the static port heater. Such insulation blankets could propagate a small fire that is the result of an
preventative modification; as applicable. This amendment also provides for an optional terminating action for certain MLG pistons. This a
contribute to the spread of a fire when ignition occurs from small ignition sources such as electrical arcing or sparking. The actions specifi
de due to stress corrosion, which could delay or impede evacuation of passengers during an emergency.
viating the airplane from its assigned flight path, and a possible mid-air collision. Since the issuance of that AD, test data have been collect
tended to prevent an internal electrical short in the engine ignition switch, which could result in smoke in the flight compartment.
n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal
ecified by this AD are intended to prevent opening of the pneumatic augmentation valve, which could result in significant loss of thrust fro
t also provides terminating action for the repetitive inspections. This amendment is prompted by reports indicating that additional crackin
draulic damper assemblies. This amendment is prompted by reports indicating that MLG hydraulic damper assemblies removed for overha
in-production airplanes. The actions specified by this AD are intended to prevent failure of the piston of the flight spoiler actuator and con
g manufacture. The actions specified by this AD are intended to detect and correct corrosion of the lug bores and the surface of the hinge
ent fatigue cracks, which could result in loss of the structural integrity of the fuselage and, consequently, lead to rapid depressurization of
bject inspection be accomplished repetitively following installation of brake line hydraulic restrictors. This amendment is prompted by an
e of the fluorescent light ballasts. The actions specified by this AD are intended to prevent fire in the passenger compartment resulting fr
o prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of
This amendment is prompted by reports of failures of the electrical connectors in the sidewall fluorescent lighting, which resulted in smok
t conducted by the manufacturer. The actions specified by this AD are intended to prevent failure of the tailcone emergency evacuation s
re intended to prevent such fatigue cracking, which could result in reduced structural integrity of the airplane, and consequent loss of pre
AD to include additional airplanes and remove others. This amendment is prompted by reports of incidents in which the pneumatic sense
ns specified by this AD are intended to prevent a jammed speed brake handle pin, which could result in retraction of the spoilers and full a
on the engine starter that was associated with the installation of non-regulating shutoff valves on the starter. The actions specified by this
hments in the upper fuselage skin in the area of the aft pressure bulkhead tee. The actions specified in this AD are intended to detect and
cking in the vertical leg of the rear spar lower cap of the wing, which, if not detected and corrected in a timely manner, could result in loss
s. This amendment would add a requirement to replace certain ballasts on which a protective cover is installed with other ballasts, or rem
s associated with the operation of those functions. This amendment requires an inspection of the autopilot and autothrottle engage switc
shroud alone installed. The actions specified by this AD are intended to prevent turbine shroud fragments from exiting the APU and punc
which could contribute to injury of passengers and/or flightcrew in the passenger cabin.
mproved procedure. This amendment is prompted by the development of a modification of the ADF antenna installation that constitutes
ames, separation of engines from airplanes, and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory
tigue cracking found in the subject area. The actions specified by this AD are intended to prevent the propagation of fatigue cracking, whic
used by, among other things, the improper disposal of smoking materials in lavatory waste receptacles. The actions specified by that AD a
by this AD are intended to ensure that the length of these oxygen mask lanyards is correct, so that the oxygen canister will be properly acti
the flaps and landing gear did not extend or retract properly due to water accumulation in the slant pressure panel area. The actions spec
cified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes.
bility of the rule to include certain Model DC-9 and MD-90-30 series airplanes, and C-9 (military) series airplanes. This amendment also ad
ed controllability of the airplane. This amendment expands the applicability of the existing AD to include additional affected airplanes.
reached its maximum life limit; an emergency power switch that is not replaced could fail and lead to a short in the electrical circuit, whic
ors in the sidewall fluorescent lighting, which resulted in smoke or lighting interruption in the passenger cabin. The actions specified by th

facturer's production flight testing, an abnormal engine start valve open annunciation for engine No. 2 occurred and resulted in an uncont
t the inability of the tailcone to deploy, which could impede the egress of passengers from the airplane during an emergency evacuation.

ed from explosions of galley water heaters. The actions specified by this AD are intended to prevent explosions of galley water heaters an

shims and an external doubler. This amendment is prompted by a report that stress coining procedures were not performed on the plate
mpted by reports of generator power feeder cables electrically shorting to the airplane structure due to chafing. The actions specified by t
is equipment, which could result in navigational errors.
eptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incom
ssure relief panels will enable the airplane to withstand a rapid decompression caused by a hole below the compartment floor.

decompression of the airplane.

 of fatigue cracking of the fuselage frames and longerons. The actions specified by that AD are intended to prevent fatigue cracking of the

rence of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 28, 1994.

ess the identified unsafe condition.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by th
ft fuselage; replacement of the hydraulic pipe assembly in the aft fuselage with a new pipe assembly; and installation of drain tube assemb

r installation on these airplanes. This action is necessary to ensure that operators who previously have installed assemblies with this part n

d corrective actions, if necessary. This amendment is prompted by numerous reports from operators that indicate instances of metallic sha
and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G
the contiguous United States at transmission frequencies between 3.7-3.98 GHz. For certain airplanes, this AD requires revising the limita
he unsafe condition on these products.
n these products.
ndings, and go- arounds, as a result of this interference, certain airplane systems may not properly function, resulting in increased flightcre
form repetitive inspections with increased sensitivity for crack detection. This AD was prompted by a report of a crack at a certain stringer

AD allows certain actions as optional methods of compliance. This AD was prompted by our determination that it is necessary to clarify th
ormation, which could lead to a mid- air collision within reduced vertical separation minimum (RVSM) airspace.
r cap, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could prop
8-09. We are issuing this AD to detect and correct discrepancies of the battery wiring installation inside the TU, which could result in an ele

earing lugs of the horizontal stabilizer center section ribs, which could result in failure of the lugs, and consequent inability of the horizont

ombination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
could result in injury to an occupant during emergency landing conditions. We are issuing this AD to require actions to correct the unsafe
reduced structural integrity of the wing.
par web and front spar cap bolt holes in the vertical stabilizer. We are issuing this AD to detect and correct such cracking damage, which c

t- emergency landing fire, failure to meet flammability criteria could result in an accelerated fire. We are issuing this AD to prevent accele

o all persons except those persons to whom it was made immediately effective by AD 2009-15-16, issued July 15, 2009, which contained th
ompression of the airplane, damage to adjacent essential flight equipment, deprivation of the necessary oxygen supply for the flightcrew,
en supply for the flightcrew, and injury to cabin occupants or maintenance or other support personnel.

fuel tank explosion and consequent loss of the airplane.

vacuation systems from deploying properly. We are issuing this AD to prevent failure of an evacuation system, which could impede an em
of failures of the captain's rudder pedal brackets before reaching the initial inspection threshold identified in the existing AD. We are issuin

unsafe condition.
, if not corrected, could lead to the loss of overall structural integrity of the horizontal stabilizer.

res or arcing at the auxiliary hydraulic pump, which could result in loss of auxiliary hydraulic power, or a fire in the wheel well of the airpla
he inability to fully pressurize an airplane, possible pressure loss, or possible rapid decompression of the airplane.
ndition and consequent reduced controllability of the airplane.
difying the insulation blankets on the slant pressure panels in the left and right MLG wheel wells. This AD results from reports of water run
ossible injury to passengers and crew. This action is intended to address the identified unsafe condition.
t failure of the fire extinguishers to fire discharge cartridges, which could result in the inability to put out a fire in an engine or in the APU.
shearing off while under normal torque loads. We are issuing this AD to prevent internal shorting, arcing, and loss of emergency battery p
ved parts, which would terminate the repetitive inspections. The actions specified by this AD are intended to prevent fatigue cracking of th
ld result in structural failure of the wings.
e to the hydraulic system. This action is intended to address the identified unsafe condition.
uent fire in the airplane. This action is intended to address the identified unsafe condition.

expected change in the airplane's center of gravity, damage to the airplane structure and/or flight control system, a hazard to the flightcre
on heaters in the lavatory water supply system. This condition, if not corrected, could also result in electrical arcing of freeze protection ri

identified unsafe condition.

de warning occurs, rather than "when the cabin altitude warning horn sounds." This action is intended to address the identified unsafe con

rplanes. This document corrects a reference to an incorrect paragraph. This correction is necessary to provide the correct paragraph refer

his action is intended to address the identified unsafe condition.

re in the cockpit and cabin.
o the passengers, flightcrew, or ground personnel. This action is intended to address the identified unsafe condition.
d/or fire in the electrical power center area. This action is intended to address the identified unsafe condition.

ng new inspection requirements. This amendment is prompted by a report indicating that an NLG upper lock link fractured prior to landin
tcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lo
n ignition occurs from electrical arcing of a failed light holder assembly, which could cause damage to adjacent structure and smoke emitti
e and fire in the flight deck and main cabin. This action is intended to address the identified unsafe condition.
nterface connectors, which could result in smoke in the main cabin. This action is intended to address the identified unsafe condition.
ng is necessary. The actions specified by this AD are intended to \nprevent loss of rudder pedal control and reduction of braking capability
nd wires, which could cause arcing and overheated wire insulation and consequent smoke/fire in the cockpit. This action is intended to ad

quent damage to the adjacent electrical equipment and/or structure. This action is intended to address the identified unsafe condition. \n
g system components caused by a fire extinguishing system bottle cartridge activating with excessive energetic force, which could result in

cabin. This amendment expands the applicability of the existing AD to include additional airplanes. This amendment is intended to preven
ed unsafe condition.
e that is the result of an electrical short of the static port heater and could lead to a much larger fire and smoke in the cabin. This action is
rtain MLG pistons. This amendment is prompted by additional reports of failure of the MLG pistons during towing of the airplanes. The acti
king. The actions specified by this AD are intended to ensure that insulation blankets constructed of MPET are removed from the fuselage

t data have been collected that demonstrate that the repetitive tests are unnecessary.
 t compartment.
Director of the Federal Register as of December 27, 1999. (64 FR 63187, November 19, 1999).
nificant loss of thrust from the remaining engine and consequent inadequate initial climb performance of the airplane.
g that additional cracking was found outside the original inspection area. The actions specified by this AD are intended to prevent inadve
blies removed for overhaul had failed or damaged spring retainers, due to insufficient material thickness of the spring retainers. The actio
spoiler actuator and consequent puncturing of the aft spar web, which could result in fuel leakage and reduced structural integrity of the
the surface of the hinge plates of the vertical-to-horizontal stabilizer, which could result in reduced structural integrity of the airplane.
apid depressurization of the airplane. This amendment corrects the requirements of the current AD by indicating the specific area in whic
ment is prompted by an additional report of fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG. The action
ompartment resulting from failure of the fluorescent light ballast of the cabin sidewall.
oss of pressurization of the airplane.
g, which resulted in smoke or lighting interruption in the passenger cabin. The actions specified by this AD are intended to prevent failures
emergency evacuation slide to deploy automatically due to incorrect diameter of the swaged balls on the wire rope of the harness assemb
d consequent loss of pressurization.
ch the pneumatic sense pipe chafed against the FIREX supply pipe of the number one engine. The actions specified by this AD are intende
of the spoilers and full advancement of the left throttle during a go- around.
actions specified by this AD are intended to prevent such uncontained failures of the engine starters, which could create a fire hazard in t
e intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced
nner, could result in loss of the spar cap, and consequent damage to the spar cap web and adjacent wing skin structure; this condition cou
th other ballasts, or removal/disconnection of the ballast. This amendment is prompted by additional reports of heavy smoke and fumes e
utothrottle engage switches located in the flight guidance control panel, and installation of improved switches. Accomplishment of these
xiting the APU and puncturing the APU compartment, which could result in reduced fire extinguishing capability in the APU compartment.

allation that constitutes terminating action for the required repetitive visual inspections. The actions specified by this AD are intended to
ms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The action
of fatigue cracking, which could lead to structural failure of the ventral aft pressure bulkhead and subsequent rapid depressurization of th
ns specified by that AD are intended to prevent such fires. This amendment revises the existing AD to allow dispatch relief in the event a l
ster will be properly activated when needed during an emergency.
l area. The actions specified by this AD are intended to prevent such water accumulation, which could result in the failure of the flaps or l

This amendment also adds a requirement to reroute the wire bundle to preclude chafing and damage. The actions specified by this AD ar
al affected airplanes.
e electrical circuit, which could result in a fire in the overhead switch panel and smoke in the cockpit.
e actions specified by this AD are intended to prevent failures of the electrical connectors, which could result in poor socket/pin contact, e

nd resulted in an uncontained failure of the engine starter. The actions specified by this AD are intended to prevent damage to the engine
emergency evacuation.

galley water heaters and coffee makers, and subsequent injuries to passengers or cabin crew members.

performed on the plate nut clearance holes of the upper anticollision light doublers during production of certain airplanes. The actions sp
he actions specified by this AD are intended to prevent the APU power feeder cable from chafing against adjacent structures, which could

r misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
nt fatigue cracking of the fuselage frames and longerons 16R and 17R, which could result in reduced structural integrity of the airplane. Th

ember 28, 1994.

ations is approved by the Director of the Federal Register as of December 13, 2000.\n\n\tComments for inclusion in the Rules Docket mus
on of drain tube assemblies and diverter assemblies in the area of the auxiliary power unit inlet; as applicable.

semblies with this part number will be given proper credit for that installation, and will not be required to perform additional, unnecessar

instances of metallic shavings in the vicinity of the jackscrew assembly and gimbal nut of the horizontal stabilizer. The actions specified in
 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-09-18, the FAA determ
quires revising the limitations section of the existing AFM to incorporate limitations prohibiting certain operations requiring radio altimete

ng in increased flightcrew workload while on approach with the flight director, autothrottle, or autopilot engaged. This AD requires revisin
rack at a certain stringer not addressed by AD 2016-07-28, and cracks at certain other \n\n((Page 31047)) \n\nstringers and associated en

is necessary to clarify the actions for airplanes on which the auxiliary fuel tanks are removed. We are issuing this AD to reduce the potenti

bilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin p
ich could result in an electrical short and possible ignition source.

inability of the horizontal stabilizer to sustain the required limit loads and loss of control of the airplane.

ns to correct the unsafe condition on these products.

racking damage, which could result in the structure being unable to support limit load, and could lead to the loss of the vertical stabilizer.

his AD to prevent accelerated fires and injuries to the flightcrew and passengers.

2009, which contained the requirements of this amendment. \n\tThe Director of the Federal Register approved the incorporation by refer
upply for the flightcrew, and injury to cabin occupants or maintenance or other support personnel.

ich could impede an emergency evacuation and increase the chance of injury to passengers and flightcrew during the evacuation. \n\nDA
xisting AD. We are issuing this AD to prevent failure of the rudder pedal bracket assembly, which could result in the loss of rudder and bra

e wheel well of the airplane. The actions specified by this AD are also intended to reduce the potential of an ignition source adjacent to the

rom reports of water runoff from the slant pressure panels in the left and right MLG wheel wells, which subsequently froze on the lateral c
n engine or in the APU. \n\nDATES: The effective date of this AD is September 24, 2003. \n\n\tOn September 24, 2003 (68 FR 50058, Augu
of emergency battery power due to failed battery screws, which could result in loss of emergency power to electrical flight components o
ent fatigue cracking of the MLG pistons, which could result in failure of the pistons and consequent damage to the airplane structure or inj

a hazard to the flightcrew, and/or possible loss of controllability of the airplane. This action is intended to address the identified unsafe co
g of freeze protection ribbon heaters, leading to fire and damage to water lines and components under the lavatory sink. This action is int

the identified unsafe condition.

correct paragraph reference. \n\nDATES: Effective November 8, 2002.\n\n\tThe incorporation by reference of certain publications listed i

fractured prior to landing and jammed against the NLG shock strut, restricting the NLG from fully extending. The actions specified by this A
ght-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane o
ucture and smoke emitting from the PSU panel into the passenger cabin. This action is intended to address the identified unsafe condition

d unsafe condition.
tion of braking capability.
action is intended to address the identified unsafe condition.\n\n\nDATES: Effective January 16 2002. The incorporation by reference of

fied unsafe condition. \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD80-29A067, dated October 21,
ce, which could result in the fire extinguishing system operating improperly.

ent is intended to prevent failures of the electrical connectors, which could result in poor socket/pin contact, excessive heat, electrical arci

the cabin. This action is intended to address the identified unsafe condition.
of the airplanes. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure
moved from the fuselage. Such insulation blankets could propagate a small fire that is the result of an otherwise harmless electrical arc and
 nded to prevent inadvertent slat retraction in flight.
ing retainers. The actions specified by this AD are intended to prevent failure of the hydraulic damper assemblies of the MLG, which could
ructural integrity of the wings.
grity of the airplane.
the specific area in which the subject inspection must be conducted. This amendment is prompted by communication received from the
r of the MLG. The actions specified by this AD are intended to prevent collapse of the MLG due to fracturing of the shock strut cylinder.

nded to prevent failures of the electrical connectors, which could result in poor socket/pin contact, excessive heat, electrical arcing, and c
e of the harness assembly.

d by this AD are intended to prevent chafing of the FIREX supply pipe, which could result in a hole in the pipe and consequently prevent th

create a fire hazard in the engine nacelle.

and consequent reduced structural integrity of the airplane.
cture; this condition could lead to reduced structural integrity of the wing.
eavy smoke and fumes emitting from the ceiling panels in the forward passenger cabin due to the failure of the fluorescent light ballasts. T
complishment of these actions will terminate the previous requirement for the AFM revision. The actions specified by this AD are intende
the APU compartment.

this AD are intended to prevent rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural in
ane fuselage. The actions specified by this AD are intended to prevent such damage associated with the problems of "blue ice."
id depressurization of the airplane.
ch relief in the event a lavatory door ashtray is missing.

e failure of the flaps or landing gear to properly extend or retract.

s specified by this AD are intended to prevent the potential for fire and uncontrolled smoke throughout the cockpit as a result of chafing a

oor socket/pin contact, excessive heat, electrical arcing, and subsequently, connector burn through and smoke in the passenger cabin.

nt damage to the engine cowling, damage to adjacent engine components, and possible fire in the cowling, due to an uncontained failure

irplanes. The actions specified by this AD are intended to prevent crack growth in the doublers, which could result in damage to the adjac
structures, which could result in electrical shorting and arcing, and a fire below the cabin floor.
 grity of the airplane. This amendment corrects an erroneous reference to a certain volume of the Supplemental Inspection Document. \n

in the Rules Docket must be received on or before January 29, 2001.

m additional, unnecessary work to comply with the requirements of the AD.

The actions specified in this AD are intended to prevent loss of pitch trim capability due to excessive wear of the jackscrew assembly of th
-09-18, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose sig
requiring radio altimeter data, due to the presence of 5G C-Band interference. This AD also requires modifying certain airplanes to allow s

. This AD requires revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate sp
ngers and associated end fittings, and skins in the center wing fuel tank wherethe stringers meet the end fittings addressed by AD 2016-07

AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank

pper center or aft skin panel and adversely affect the structural integrityof the airplane.

of the vertical stabilizer.

e incorporation by reference of a certain publication listed in the AD as of August 5,2010. \n\tOn July 6, 2010 (75 FR 38017, July 1, 2010), t

the evacuation. \n\nDATES: This AD is effective April 28, 2008. \n\tThe Director of the Federal Register approved the incorporation by ref
e loss of rudder and braking control at either the captain's or first officer's position.

n source adjacent to the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequen

ntly froze on the lateral control mixer and control cable assemblies. We areissuing this AD to prevent ice from forming on the lateral contro
2003 (68 FR 50058, August 20, 2003), the Director of the Federal Register approved the incorporation by reference of certain service bulle
ical flight components or other emergency power systems required in the event of loss of the aircraft primary power source.
airplane structure or injury to airplane occupants. This action is intended to address the identified unsafe condition. \n\n\nDATES: Effecti

the identified unsafe condition.

ry sink. This action is intended to address the identified unsafe condition.

tain publications listed in the regulations was approved previously by the Director of the Federal Register as of November 8, 2002 (67 FR 6

ctions specified by this AD are intended to prevent the upper lock link assembly fromfracturing due to fatigue cracking, and the NLG conse
d result in the airplane overrunning the end of the runway during landing on awet or icy runway.
ntified unsafe condition.

oration by reference of certain publications listed in the regulations is approved bythe Director of the Federal Register as of January 16, 20

A067, dated October 21, 1999; and McDonnell Douglas Alert Service Bulletin MD90-29A018, dated October 21, 1999; as listed in the regula

ssive heat, electrical arcing, and subsequently, connector burn-through andsmoke and/or fire in the passenger cabin.

ch could result in failure of the pistons and subsequent damage to the airplane structure or injury to airplane occupants.
armless electrical arc and could lead to a much larger fire.
 of the MLG, which could result in vibration damage and collapse of the MLG.

ation received from the manufacturer that the current requirements of the ADare different than the service information referenced as the
shock strut cylinder.

t, electrical arcing, and consequently, connector burnthrough and smoke in the passenger cabin.

consequently prevent the proper distribution of the fire extinguishing agent within the nacelle in the event of a fire.

uorescent light ballasts. The actions specified in this AD are intended to prevent a fire in the passenger compartment, which could result fr
d by this AD are intended to ensure that the autopilot and autothrottle disengage when commanded to do so by the flightcrew.

ent reduced structural integrity of the airplane, due to problems associated with corrosion and fatigue cracking in the subject area.
of "blue ice."

it as a result of chafing and shorting in the electrical wire bundles.

he passenger cabin.

an uncontained failure of the engine starter.

t in damage to the adjacent structure, and subsequent loss of cabin structural integrity.
nspection Document. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997, w

ackscrew assembly of the horizontal stabilizer, which could result in reduced controllability of the airplane.\n\n\tThe incorporation by refe
 -Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GH
tain airplanes to allow safe operations in the U.S. 5G C-Band radio frequency environment. The FAA is issuing this AD to address the unsaf

(AFM) to incorporate specific operating procedures for, depending on the airplane model, instrument landing system (ILS) approaches, no
ddressed by AD 2016-07-28. The FAA is issuing this AD to address the unsafe condition on these products.

could result in fuel tank explosions and consequent loss of the airplane.

FR 38017, July 1, 2010), the Director of the Federal Register approved the incorporation by reference of a certain other publication listed in

the incorporation by reference of a certain publication listed in this AD as of April 28, 2008. \n\tThe Director of the Federal Register appro

explosion and consequent loss of the airplane.

ming on the lateral control mixer and control cable assemblies, which could reduce controllability of the airplane.
e of certain service bulletins listed in the AD.
wer source.
on. \n\n\nDATES: Effective June 2, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin MD80-32A308, Revision 04,

vember 8, 2002 (67 FR 65298, October 24, 2002).\n\n\tThe incorporation by reference of certain publications, as listed in the regulations,

king, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to th

ister as of January 16, 2002.

99; as listed in the regulations, is approved by the Director of the Federal Register as of December 18, 2001.
mation referenced as the appropriate service information in the current AD.

nt, which could result from failure of the fluorescent light ballast of the upper and lower cabin sidewall, and consequent failure of the dus
he flightcrew.

the subject area.

ted October 20, 1997, was approved previously by the Director of the Federal Register as of May 12, 1999 (64 FR 16805, April 7, 1999).

he incorporation by reference of Boeing Alert Service Bulletin DC9-27A362, Revision 02, dated March 30, 2000; Boeing Alert Service Bulleti
ies between 3.7-3.98 GHz. This AD requires revising the limitations and operating procedures sections of the AFM to incorporate specific o
AD to address the unsafe condition on these products.

em (ILS) approaches, non- precision approaches, ground spoiler deployment, and go-around and missed approaches, when in the presenc

ther publication listed in the AD. \n\tWe must receive any comments on this AD by September 20, 2010.

e Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 11, 2008 (73 FR 658
80-32A308, Revision 04, dated June 12, 2001, as listed in the regulations, is approved by the Director of the Federal Register as of June 2, 2

isted in the regulations, was approved previously by the Director of the Federal Register as January 17, 1992 (57 FR 2014, January 17, 199

crew, and damage to the airplane.

equent failure of the dust barriers of the outboard ceiling panel.
16805, April 7, 1999).

oeing Alert Service Bulletin MD90-27A034, Revision 02, dated March 30, 2000; and Boeing Alert Service Bulletin 717-27A0002, Revision 02,
to incorporate specific operating procedures for, depending on the airplane model, ILS approaches, non-precision approaches, ground sp

es, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to addre

rch 11, 2008 (73 FR 6586, February 5, 2008).

al Register as of June 2, 2005. \n\n\tThe incorporation by reference of Boeing Service Bulletin MD80-32- 309, Revision 01, dated April 25, 2

R 2014, January 17, 1992).\n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved pr
7-27A0002, Revision 02, dated March 30, 2000; as listed in the regulations; is approved by the Director of the Federal Register as of Augus
n approaches, ground spoiler deployment, and go-around and missed approaches, due to the presence of 5G C-Band interference. The FAA

issuing this AD to address the unsafe condition on these products.

sion 01, dated April 25, 2001, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 20, 20

lations, was approved previously by the Director of the Federal Register as of May 7, 2001 (66 FR 17499, April 2, 2001).
eral Register as of August 23, 2000.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin DC9-27A362, dated February 11,
nd interference. The FAA is issuing this AD to address the unsafe condition on these products.
egister as of June 20, 2002 (67 FR 34823, May 16, 2002). \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin
362, dated February 11, 2000; Boeing Alert Service Bulletin MD90-27A034, dated February 11, 2000; and Boeing Alert Service Bulletin 717-
las Alert Service Bulletin MD80-32A308, dated March 5, 1998; and McDonnell Douglas Alert Service Bulletin MD80-32A308, Revision 01, d
lert Service Bulletin 717-27A0002, dated February 11, 2000; as listed in the regulations; was approved previously by the Director of the Fe
0-32A308, Revision 01, dated May 12, 1998; as listed in the regulations; was approved previously by the Director of the Federal Register as
by the Director of the Federal Register as of March 6, 2000 (65 FR 10379, February 28, 2000).\n\n\tComments for inclusion in the Rules Do
f the Federal Register as of as of July 28, 1999 (64 FR 33392, June 23, 1999).
nclusion in the Rules Docket must be received on or before October 10, 2000.