# N583MD: 1988 Mcdonnell Douglas DC-9-83(MD-83), registration cancelled 2011-10-28

- Type: Cancelled registration (FAA registry, deregistered aircraft)
- Cancelled: October 28, 2011
- Exported to: Mexico
- Status when cancelled: Valid registration
- Airframe: [Mcdonnell Douglas DC-9-83(MD-83)](https://openairdocs.org/model/mcdonnell-douglas-dc-9-83-md-83) (registry code 3022083)
- Engine: [Pratt & Whitney JT8D-1](https://openairdocs.org/engine/pratt-whitney-jt8d-1) (registry code 52044)
- Data sheets: [TCDS A6WE](https://openairdocs.org/tcds/A6WE), [TCDS E2EA](https://openairdocs.org/tcds/E2EA) (OpenAirDocs)
- Serial number: 49659
- Year built: 1988
- Type of aircraft: Fixed wing multi engine
- Engine type: Turbo-jet
- Airworthiness: Standard, transport
- Airworthiness date: September 2, 1997
- Certificate issued: September 11, 1996
- Last registry action: July 10, 2008
- Mode S code: A78224
- Owner when cancelled: [Boeing Capital Corporation](https://openairdocs.org/faa-owner/BOEING%20CAPITAL%20CORPORATION)
- Location: [Seatle, WA](https://openairdocs.org/faa-place/WA/Seatle)
- Physical address: [Renton, WA](https://openairdocs.org/faa-place/WA/Renton)
- Owner type: Corporation
- The mark today: https://openairdocs.org/aircraft/N583MD
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=583MD
- Page: https://openairdocs.org/deregistered/N583MD-2011-10-28

From the FAA registry file of October 29, 2026, cancelled registrations. Owners' street addresses are left out. The Mode S code belongs to the N-number, not the airframe.

ADs and bulletins for the Mcdonnell Douglas DC-9-83(MD-83): https://openairdocs.org/model/mcdonnell-douglas-dc-9-83-md-83.md

## Service difficulty reports (63, newest 50)

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.

- [SDR 2ARF201101005](https://openairdocs.org/sdr/2ARF201101005), Jan 15, 2011: PLATE. BROKEN. CAPTAIN REPORTED THAT DURING CRUISE, ACFT REQUIRED 4 GRADES OF AILERON COMPENSATOR TO MAINTAIN STRAIGHT AND LEVELED FLIGHT. DURING MX REVISION, THE SPIRAL DRIVE
- [SDR 2ARF201101003](https://openairdocs.org/sdr/2ARF201101003), Jan 10, 2011: WATER SEPARATOR. LEAKING. ACFT PERFORMED AN UNSCHEDULED LANDING, DUE TO LOSS OF CABIN PRESSURE AT 36,000 FT. DURING MX REVISION, THE LT WATER SEPARATOR DUCT WAS DETECTED LEAKING; SO THE 
- [SDR 2ARF201012003](https://openairdocs.org/sdr/2ARF201012003), Dec 13, 2010: MOTOR. DAMAGED. ACFT PERFORMED AN UNSCHEDULED LANDING; DURING LANDING THE STAB OUT OF TRIM LIGHT TUNED ON. MX REPLACED THE STABILIZER TRIM MOTOR IAW MM 27-41-71, TESTED CORRECT
- [SDR 2ARF201012002](https://openairdocs.org/sdr/2ARF201012002), Dec 5, 2010: DRIVE UNIT. DAMAGED. CAPTAIN REPORTED THAT DURING CLIMB THE RT UVC AND GENERATOR WERE DISCONNECTED BY HIGH TEMPERATURE; SO THE FLIGHT CREW PERFORMED THE DRIVE GENERATOR MALFUNCTION 
- [SDR 2ARF201010003](https://openairdocs.org/sdr/2ARF201010003), Oct 13, 2010: RADOME. CRACKED. DURING TRANSIT CHECK A BIRD STRIKE WAS DETECTED ON ACFT RADOME. MX PERFORMED A BIRD STRIKE INSP IAW 05-51-18 DETECTING A CRACK OF 21 INCHES LENGTH AND 15 INCHES
- [SDR 2ARF201008001A](https://openairdocs.org/sdr/2ARF201008001A), Aug 14, 2010: PUMP. FAILED. AIRCRAFT RETURNED OF FLIGHT DUE TO DURING CLIMB, THE CENTRAL TANK FUEL PUMP FAILED AND THE BACK PUMP BREAKER THREW OUT. MAINTENANCE PERSONNEL DEFERRED THE REPOR
- [SDR 2ARF201007001](https://openairdocs.org/sdr/2ARF201007001), Jul 10, 2010: TRANSCEIVER. FAULTY. AIRCRAFT RETURNED DUE TO DURING CLIMB, THE RADAR MONITOR IMAGE DISAPPEARED, INDICATING "ANT FAULT". MAINTENANCE PERSONNEL REPLACED AND TESTED THE WEATHER RADAR 
- [SDR 2ARF201006004](https://openairdocs.org/sdr/2ARF201006004), Jun 12, 2010: VALVE. OPEN. DURING FUELING, A FUEL LEAK OCCURRED IN THE LEFT WING WHILE FILLING THE RIGHT TANK DUE TO AIRCRAFT WAS PARKED ON UNEVEN RAMP AND THE SUPPLY VALVE DID NOT CLOSE.
- [SDR ASMF201002001](https://openairdocs.org/sdr/ASMF201002001), Jan 28, 2010: DUCT. BROKEN. ACFT RETURNED TO PLATFORM DUE TO AFTER ENGINES START, THE "TAIL COMP TEMP HI" LIGHT TURNED ON. MX REPLACED THE THERMO SWITCHES ON BOTH SIDES IAW MM 36-20-02 AND
- [SDR EE4Y090277](https://openairdocs.org/sdr/EE4Y090277), Sep 21, 2009: SKIN. DELAMINATED. RT WING INBOARD VANE FLAP OUTER AND INNER SKIN DELAMINATED.
- [SDR EE4Y090272](https://openairdocs.org/sdr/EE4Y090272), Sep 17, 2009: STRINGER. CORRODED. RT WING FUEL TANK, AT STR 18R WITH CORROSION FROM XRS 69.000 TO XRS 91.000.
- [SDR EE4Y090298](https://openairdocs.org/sdr/EE4Y090298), Sep 16, 2009: TEE FITTING. CORRODED. LT WING, STA XTE 342, TRAILING EDGE TEE FLANGE CORRODED.
- [SDR EE4Y090271](https://openairdocs.org/sdr/EE4Y090271), Sep 16, 2009: STRINGER. CORRODED. LT WING FUEL TANK INTERNAL STRUCTURE FROM XRS 69.000 TO XRS 137.750, STGR 18L, 19L, 20L, 21L AND 22L, CORRODED.
- [SDR EE4Y090250](https://openairdocs.org/sdr/EE4Y090250), Sep 16, 2009: STRINGER. CORRODED. LT WING FUEL TANK INTERNAL STRUCTURE FROM XRS 69.000 TO XRS 137.750, STGR 18L, 19L, 20L, 21L AND 22L, CORRODED.
- [SDR EE4Y090270](https://openairdocs.org/sdr/EE4Y090270), Sep 14, 2009: FLOOR SUPPORT. CRACKED. LOWER FUSELAGE, STA 332 FWD CARGO COMPARTMENT, FLOOR SUPPORT PN 5936597-535 FLANGE CRACKED.
- [SDR EE4Y090269](https://openairdocs.org/sdr/EE4Y090269), Sep 14, 2009: FITTING. CRACKED. PAX CABIN, STA 1346 PASSENGER AFT ENTRANCE STAIRWELL DOOR, FITTING CRACKED.
- [SDR 2ARF200908001](https://openairdocs.org/sdr/2ARF200908001), Aug 22, 2009: SPOILER SYS. OUT OF ADJUST. ACFT RETURNED TO PLATFORM DUE TO SPOILER DEPLOYED LIGHT TURNED ON AND LEFT SPOILER PARTIALLY EXTENDED. MX ADJUSTED THE RT OTBD SPOILER, DEPLOYED SENSOR IAW MM 2
- [SDR ASMF200803003](https://openairdocs.org/sdr/ASMF200803003), Mar 30, 2008: SWITCH. BURNED. AIRCRAFT RETURNED TO PLATFORM DUE TO SMOKE IN THE CABIN. MAINTENANCE DETECTED A SHORT CIRCUIT IN THE LT ENGINE SYS (A) IGNITION SWITCH, SO BREAKERS K-26 AND L26
- [SDR ASMF200802005](https://openairdocs.org/sdr/ASMF200802005), Feb 13, 2008: UNKNOWN. UNKNOWN. AC RETURNED TO PLATFORM DUE TO IGNITION FAILURE IN LT ENGINE. MAINT REPLACED IGNITION BOX IAW MM 74-10-01, TESTED CORRECT. AC WAS DISPATCHED AND RETURNED TO PLA
- [SDR ASMF200707013](https://openairdocs.org/sdr/ASMF200707013), Jul 16, 2007: VALVE. UNSERVICEABLE. DURING TRANSIT CHECK A FUEL SPILLAGE OCCURRED AT PLATFORM. SPILLAGE STARTED WHEN THE AIRCRAFT WAS BEING REFUELED AND FUEL WAS TRANSFERRED FROM CENTRAL TANK TO L
- [SDR ASMF200707006](https://openairdocs.org/sdr/ASMF200707006), Jul 9, 2007: SPAR CAP. CRACKED. COMPLEMENTING THE REPORT ASMF200707004 DATED ON JULY 5, 2007 WHICH INDICATES THAT (DURING THE INSPECTION OF THE HORIZONTAL STABILIZER REAR SPAR UPPER CAPS), REQ
- [SDR ASMF200707004](https://openairdocs.org/sdr/ASMF200707004), Jul 5, 2007: STABILIZER. CRACKED. DURING THE INSPECTION OF THE HORIZONTAL STABILIZER REAR SPAR UPPER CAPS, REQUIRED BY THE AD 2007-10-04, DETECTED A CRACK OF (2) INCHES LONG AT STATION XH = 6.5.
- [SDR ASMF200704012](https://openairdocs.org/sdr/ASMF200704012), Apr 17, 2007: ENGINE. UNKNOWN. AIRCRAFT REJECTED TAKEOFF DUE TO LT ENGINE DID NOT ACCELERATE. THE PARAMETERS WERE: LT ENGINE WITH EPR 1.40 AND RT ENGINE WITH EPR 1.86 AND T/O FLX TEMP 50. DUR
- [SDR ASMF200612003](https://openairdocs.org/sdr/ASMF200612003), Dec 11, 2006: CADC. FAILED. AIRCRAFT REJECTED TAKEOFF AT 90 KNOTS DUE TO A 15 KTS OF DIFFERENCE BETWEEN SPEED INDICATORS. CADC AND RT AIR SPEED INDICATOR WERE REPLACED IAW MM 34-16-01 AND 
- [SDR ASMF200611008](https://openairdocs.org/sdr/ASMF200611008), Nov 18, 2006: ACTUATOR. FAILED. CAPTAIN REPORTED THAT AFTER TAKEOFF AT GDL THE (AUTO SLATS FAIL) LIGHT TURNED ON IN LOW SPEED (150-230 KIAS) AND FLIGHT CONTROLS WITH VIBRATION. THE STALL COMPU
- [SDR ASMF200610012](https://openairdocs.org/sdr/ASMF200610012), Oct 28, 2006: POWERPLANT. POWER LOSS. AIRCRAFT REJECTED TAKEOFF AT 40 KNOTS DUE TO THE LT ENGINE DID NOT ACCELERATE MORE THAN 1.2 EPR’S. AT PLATFORM, ACCELERATION TEST WAS PERFORMED IAW MM 71-00-00,
- [SDR ASMF200607016](https://openairdocs.org/sdr/ASMF200607016), Jul 22, 2006: UNKNOWN. UNKNOWN. AIRCRAFT RETURNED TO PLATFORM DUE TO AFTER RT ENGINE STARTING SPEED AND F/D FLAGS WERE SHOWN IN ADI AND FLIGHT GUIDANCE COMPUTER WITHOUT INDICATION IN FMA NR 2.
- [SDR ASMF200606015](https://openairdocs.org/sdr/ASMF200606015), Jun 25, 2006: COWLING. DAMAGED. DURING TRANSIT CHECK, A LOSE OF MATERIAL IN THE LT ENGINE NOISE SUPPRESSOR WAS DETECTED. AN INSPECTION WAS PERFORMED AND DAMAGE WAS OUT OF LIMITS, THEREFORE, TH
- [SDR ASMF200606012](https://openairdocs.org/sdr/ASMF200606012), Jun 20, 2006: ANNUNCIATOR. MALFUNCTIONED. AIRCRAFT RETURNED TO PLATFORM, FMA FAILURE WITH RT SPD FLAGS AND FD IN RT ADI WERE SHOWED. THE FLT GUIDE SYSTEM WAS RESEATED AND AUTO LAND IN BOTH SYSTEM WERE P
- [SDR ASMF200603007](https://openairdocs.org/sdr/ASMF200603007), Mar 16, 2006: WINDOW. BROKEN. CAPTAIN REPORTED THAT DURING FLIGHT AT 320 FEET, WITH 7.7 OF CABIN DIFFERENTIAL PRESSURE A STRONG NOISE WAS HEARD IN THE PASSENGERS CABIN DUE TO THE 32 WINDOW W
- [SDR ASMF200603003](https://openairdocs.org/sdr/ASMF200603003), Mar 8, 2006: TARGET. FAILED. CAPTAIN REPORTED THAT AFTER MAIN LANDING GEAR EXTENSION, THE GEAR DOOR OPEN LIGHT TURNED ON. ABNORMAL PROCEDURE WAS PERFORMED BUT THE LIGHT CONTINUED ON, SO THE
- [SDR ASMF200512008](https://openairdocs.org/sdr/ASMF200512008), Dec 8, 2005: BUNGEE CYLINDER. LEAKING. DURING TRANSIT CHECK, TECHNICAL PERSONNEL DETECTED A HYDRAULIC LIQUID LEAK IN THE RT MAIN LANDING GEAR. BUNGEE CYLINDER WAS REPLACED IAW MM 32-32-02, TESTED COR
- [SDR ASMF200508005](https://openairdocs.org/sdr/ASMF200508005), Aug 10, 2005: CSD. MALFUNCTIONED. AIRCRAFT PERFORMED AN UNSCHEDULED LANDING AT HMO AS CONSEQUENCE OF OVERTEMPERATURE ON LEFT CONSTANT SPEED DRIVE (CSD). LEFT CHIP DETECTORS WERE CHECKED, ALL COR
- [SDR ASMF200507019](https://openairdocs.org/sdr/ASMF200507019), Jul 25, 2005: ENGINE. FAILED. CAPTAIN REPORTED THAT DURING LEFT ENGINE STARTING AND SHUT OFF, VIBRATION WAS FELT IN THE HOLE AIRCRAFT. THE LEFT ENGINE VIBRATION ABSORBERS, BARS AND ACCESSORI
- [SDR ASMF200506022](https://openairdocs.org/sdr/ASMF200506022), Jun 19, 2005: TRANSMITTER. INOPERATIVE. CAPTAIN REPORTED RT HYDRAULIC BRAKE PRESS INDICATION SYSTEM INOPERATIVE. WIRING SYSTEM CHECK DETECTED ELECTRICAL LINE DAMAGED ON RT BRAKE PRESS TRANSMITTER CONN
- [SDR ASMF200506005](https://openairdocs.org/sdr/ASMF200506005), Jun 3, 2005: COMPUTER. FAILED. AIRCRAFT RETURNED OF FLIGHT, AFTER ROTATION, THE DISAGREE IN SLAT PANEL, AUTO SLAT FAIL AND STALL INDICATION FAILURE IN ANNUNCIATOR PANEL LIGHTS COME ON. BOTH C
- [SDR ASMF200505007](https://openairdocs.org/sdr/ASMF200505007), May 5, 2005: CONNECTOR. FAILED. AIRCRAFT ARRIVED WITH CAPTAIN REPORT OF VOR NR 2 WITH OSCILLATIONS OF 30 RADIALS AND RIGHT EHSI WITH OFF FLAG IN LEFT RMI. AIRCRAFT WAS SENT TO THE HANGAR AND R
- [SDR ASMF200501008](https://openairdocs.org/sdr/ASMF200501008), Jan 15, 2005: DUCT. DAMAGED. DURING ENGINES STARTING, RT ENGINE DID NOT STARTED BECAUSE N1 WAS OUT OF SERVICE. DURING MAINTENANCE REVISION WAS DETECTED 8TH STAGE DUCT BROKEN. DUCT WAS REPLA
- [SDR ASMF200410015](https://openairdocs.org/sdr/ASMF200410015), Oct 19, 2004: SHUTOFF VALVE. FAILED. CAPTAIN REPORTED LOSS OF HYDRAULIC FLUID OF THE RT SYSTEM AND LANDING GEAR DOORS DID NOT OPEN IN A NORMAL WAY, OPENING THEM MANUALLY. AIRCRAFT WAS SENT TO THE H
- [SDR ASMF200406032](https://openairdocs.org/sdr/ASMF200406032), Jun 27, 2004: CADC. FAILED. CAPTAIN REPORTED THAT DURING CRUISE AT 35,000 FEET, VERTICAL VELOCIMETER BAR FD TRI WAS OUT OF SERVICE AND CADC ABNORMAL PROCEDURE WAS PERFORMED. DURING TRANSIT
- [SDR ASMF200406030](https://openairdocs.org/sdr/ASMF200406030), Jun 26, 2004: SELECTOR SWITCH. FAILED. AIRCRAFT RETURNED TO PLATFORM, APU OUT OF SERVICE AND ENGINE GENERATORS WITHOUT INDICATION OF VOLTAGE AND FREQUENCY. CIRCUIT BREAKERS B1-204, B1-205 AND B1-206 
- [SDR ASMF200403011](https://openairdocs.org/sdr/ASMF200403011), Mar 20, 2004: PRESSURE SWITCH. MALFUNCTIONED. DURING TRANSIT CHECK THE LEFT OIL LOW PRESSURE LIGHT TURNED ON. THE SWITCH WAS DEFERRED IAW MEL 79-2. DURING OVERNIGHT SERVICE THE LOW PRESSURE SWITCH WAS REPLA
- [SDR MEX2003440](https://openairdocs.org/sdr/MEX2003440), Sep 21, 2003: PUMP. FAILED. DURING CRUISE AT 33,000 FT, THE RUDDER TRAVEL UNRESTRICTED LIGHT TURNS 'ON'. AFTER LANDING THE HYDRAULIC PRESSURE INDICATES 2500 PSI. THE ELECTRIC MOTOR DRIVEN 
- [SDR MEX2003271](https://openairdocs.org/sdr/MEX2003271), Jul 7, 2003: SUPPRESSOR. DAMAGED. AIRCRAFT AIR TURN BACK DUE TO ENGINE 2 FAILURE DURING INITIAL CLIMB, REACHING 660 DEGREE C OF EGT EMERGENCY PROCEDURE WAS PERFORMED. DURING REVISION THE EXHAUST
- [SDR MEX2003285](https://openairdocs.org/sdr/MEX2003285), Jul 3, 2003: AMPLIFIER. FAULTY. DURING TRANSIT CHECK DETECTED THAT DURING TEST ENGINE FIRE ALARM SYSTEM NR 2 NOT CANCELL AURA WARNING. DURING REVISION BREAKER AND AMPLIFIER A2-6 WERE WITH DAMA
- [SDR MEX2003263](https://openairdocs.org/sdr/MEX2003263), Apr 7, 2003: PROXIMITY SWITCH. FAILED. AIRCRAFT ARRIVED WITH CAPTAIN REPORT THAT DURING FINAL APPROACH THE NOSE LANDING GEAR LIGHT TURNED RED AND NOSE LANDING GEAR ALARM CAME ON. AFTER MISSED APPROAC
- [SDR MEX2002307](https://openairdocs.org/sdr/MEX2002307), Sep 22, 2002: PUMP. FAILED. AIRCRAFT RETURNED FROM FLIGHT AS CONSEQUENCE OF THE LIGHT (RT HYD PRESS LOW) AT PLATFORM, TECH SUPPLIED 14 QTS OF HYDRAULIC FLUID. RIGHT ENGINE WAS STARTED BUT 
- [SDR MEX2002305](https://openairdocs.org/sdr/MEX2002305), Sep 18, 2002: SWITCH. FAILED. AIRCRAFT RETURNED OF FLIGHT AS CONSEQUENCE OF PRESSURIZATION FAILURE. AT PLATFORM TECH DETECTED THAT THE LIGHT (FLOW) TURNED ON IN PRESSURIZATION SELECTOR AND T
- [SDR 971355015](https://openairdocs.org/sdr/971355015), Aug 28, 1997: SKIN. CORRODED. PREVIOUSLY EXISTING BLENDOUT REPAIRS OF WING LOWER SKINS REQUIRE MAPPING AND DISPOSITION. MAPPED BLENDOUTS AND REPORTED TO DACO -- MOST ACCEPTABLE AS IS, FOUR A
- [SDR IH971355014](https://openairdocs.org/sdr/IH971355014), Aug 12, 1997: DOME. CRACKED. NR 2 ENGINE FRONT BULLET IS CRACKED AROUND RIVETS, 2 CRACKS WERE FOUND IN THE 5930646-25 DOME SKIN. CRACKS WERE COMMON TO THIS SKIN ONLY. THE INNER DETAILS OF T

All 63: https://openairdocs.org/deregistered/N583MD-2011-10-28/reports.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.