Boeing 727-200
Service difficulty reports · 2,835
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Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE aircraft_model_key = '727200' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE aircraft_model_key = '727200' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR FXGA202307122336Unknown · unknownDAMAGE TO FLOOR STRUCTURE F/S 1148 BL RIGHT 45 WL 208. REPAIR OF DAMAGE FLOOR STRUCTURE AT F/S1148 BL RIGHT 45 WL 208. FABRICATE REPLACEMENT PARTS AND INSTALL PER SRM.SDR 2022F00286None · defectiveON 6/28/2022 AT 0610Z, N209TR DEPARTED KTOL FOR KCHA. WHILE CLIMBING THROUGH FL220, "A" SYSTEM HYD LOW LEVEL LIGHT ILLUMINATED AND REMAINED ON. ALSO, THE "A" SYSTEM QTY INDICATOR DROPPED TO 2.2 GALLONS AND STOPPED AT THAT VALUE. CREW PERFORMED MEMORY ITEMS FORSDR K11A2021092200076Seat Track · corrodedSEAT TRACK CORROSION STA 492 TO 500 RBL 50SDR VGCA2019112619003Floorbeam · corrodedFLOOR BEAM CORRODED AT STATION 920 AT LEFT BODY LINE 28SDR 7IWB2019F00137Bleed Air Sys · leakingON 3/2/2019, DEPARTED, APROX 3 MINUTES AFTER TO, THE CREW GOT A NR 1 ENGINE FIRE INDICATION IN THE COCKPIT. THE CREW REDUCED THE POWER SETTING TO IDLE AND THE FIRE INDICATION WENT AWAY. THEY RETURNED TO KMFE SAFELY. AFTER TROUBLESHOOTING BY IJW MECHANICS, IT WSDR 2017FA0000038Access Panel · stuckDURING ROUTINE GEAR SWING AND MANUAL GEAR DEPLOYMENT, THE MAINTENANCE ENGINEER HAD DIFFICULTY IN ACCESSING GEAR DEPLOYMENT PANELS. SCREW DRIVERS AND PRY BARS WERE REQUIRED TO LIFT THE CARPET AND UNDERLAY, DUE TO THE COVERS BEING BONDED TO THE FLOOR. THE AIRCRSDR FOTR20160719002Web · crackedRIGHT WING T/E INBD AILERON OTBD SIDE WEB IS CRACKED.SDR VGCA20160509001Battery · dischargedDURING PREFLIGHT, COCKPIT EMERGENCY LIGHT BATTERY DEAD.SDR I5PA2016022642501Unknown · malfunctionedSHORTLY AFTER TAKEOFF THE CREW CALLED IN THE COMPANY RADIO THAT THEY WERE NOT GETTING A GREEN LIGHT FOR THE NOSE GEAR & THAT THE RED UNSAFE LIGHT STAYED ILLUMINATED. THEY CYCLED THE GEARS & STILL DID NOT GET THE RED NOSE GEAR LIGHT TO EXTINGUISH & THE GREEN LSDR PCSA2015011202Warning Light · illuminatedLEFT GEAR UNSAFE LIGHT.SDR PCSA2015011201Warning Light · illuminatedLEFT MAIN GEAR UNSAFE LIGHT ILLUMINATED.SDR FY4Y20141006003Skin · corrodedDURING CPCP INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950B STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APSDR FY4Y20141006002Skin · corrodedDURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950D STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVASDR FY4Y20141006001Skin · corrodedDURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720E & 720F STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.SDR FY4Y20141003007Skin · corrodedDURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950E+4 STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROSDR FY4Y20141003006Skin · corrodedDURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720B & 720C STRINGER 28L & 28R. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATASDR FY4Y20141003005Skin · corrodedDURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING UPPER SKIN FROM WS 611.5 TO WS 613.5. DIMENSIONS OF CORROSION AREA 3 INCHES X 1.25 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.085 INCH, ORIGINAL THICKNESS IS 0.184 INCH, SDR FY4Y20141003004Plate · corrodedDURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 520 TO WS 526. DIMENSIONS OF CORROSION AREA 6 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.141 INCH, ORIGINAL THICKNESS ISSDR FY4Y20141003003Plate · corrodedDURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 701 TO WS 696. DIMENSIONS OF CORROSION AREA 5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.126 INCH, ORIGINAL THICKNESS ISSDR FY4Y20141003002Plate · corrodedDURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 726 TO WS 734. DIMENSIONS OF CORROSION AREA 8 INCHES X 2 INCHES. AFTER THE CORROSION BLEND OUT, THE MIN REMAINING THICKNESS OF 0.031 INCH, ORIGINAL THICKNESS IS SDR FY4Y20141003001Plate · corrodedDURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 738.5 TO WS 742. DIMENSIONS OF CORROSION AREA IS 3.5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.104 INCH, ORIGINAL THICKSDR I5PA201406010002Engine · leakingNUMBER 3 ENG SHUT DOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL, FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENG HAS BEEN R & R. INSTALLED IAW AMM. PERFORMED OPERATIONS CHECK & HIGH POWER ASSURANCESDR I5PA201406010001Engine · leakingNR 3 ENGINE SHUTDOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENGINE HAS BEEN REMOVED & REPLACED. INSTALLED IAW AMM. PERFORMED OPS CHECK & HIGH POWER ASDR FY4Y20121122197Web · corrodedDURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT VERTICAL WEB AT STATION BS 865, LBL 38, 39,WL 165-168 (DIMENSIONS OF CORROSION AREA:2 .3750" × 1.5"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH WAS OVER LIMIT IAW SRM 57-10-01, PAGESDR FY4Y20121116197Skin · corrodedDURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON FUSELAGE LOWER LOBE SKIN PANEL AT STATION BS 1010, WL 148 BETWEEN S-28R AND S-29R. (DIMENSIONS OF CORROSION AREA:5 3/8" × 2"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.019") WAS OVER LIMIT IAW SRM SDR FY4Y201211130001Structure · corrodedDURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT STATION BS 865, LBL 54, WL 169 TO LBL 58 WL 171 ( DIMENSIONS OF CORROSION AREA:3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IASDR FY4Y2012F00244Structure · corrodedPERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT BS 865, LBL 54, WL 169 TO LBL 58, WL 171 (DIMENSIONS OF CORROSION AREA: 3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IAW SRM 53-00-00SDR FDEA201206212293Skin · gougedSKIN GOUGED AND DENTED STA 1087 STR 24R. CUT OUT DAMAGED AREA IAW SRM 51-10-1 AND 53-30-3 FIG 3 FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 53-30-3 FIG 3 AND 53-30-2 FIG 2 INSTALLED REPAIR DOUBLER AND FILLER IAW SRM 51-30-02SDR CA111025007Detector · failed(CAN) ON CLIMB OUT, CREW EXPERIENCED A "STRUT OVERHEAT" WARNING ON THE NR 3 SIDE. CREW THROTTLED THE ENGINE TO IDLE AND THE WARNING EXTINGUISHED. ACFT RETURNED TO BASE WHERE MX REPLACED A FAULTY FIRE SENSE LOOP.SDR CA111025006Engine · failed(CAN) ON CLIMB OUT, CREW EXPERIENCED A "BANG" AND VIBRATION FROM THE NR 3 ENGINE. CREW SECURED THE ENGINE AND RETURNED TO BASE. MX DISCOVERED THE NR 3 ENGINE HAD EXPERIENCED A CATASTROPHIC INTERNAL FAILURE. THE ENGINE WAS REPLACED AND ACFT RETURNED TO SERVICESDR C8GA2011000007Shaft · shearedDURING CRUISE OPERATION AT FL 300, THE NR 1 ENGINE HYD SYS "A" LOW PSI LIGHT ILLUMINATED. ACFT DIVERTED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED, NOTING THAT THE NR1 ENGINE "A" SYSTEM HYD SYSTEM PUMP WAS AT FAULT. PERFORMED OPS CHECKSDR FDEA201106102374Skin · dentedAFT AIRSTAIRS LT TORQUE BOX EXTERIOR SKIN AT STA 1308, LIGHTING CUT-OUT, SKIN HAS DENT AND CRACK ALONG EDGE. CUTOUT DAMAGED AREA & FABRICATED REPAIR DOUBLER IAW SRM 51-40-2 FIG 1 & 53-10-2 FIG 6, TREATED & PRIMED PARTS IAW SRM 51-10-2, INSTALLED REPAIR DOUBLESDR FY4Y20110317Strap · corrodedHE CORROSION WAS FOUND AT TENSION STRAP OF LT OTBD MID FLAP AT WBL 452 DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE STRAP IS 0.225". AFTER BLEND OUT, THE DIMENSION OF THE CORROSION AREA IS 2.5" (LENGTH) X 2" (WIDTH) AND REMAINDER THICKNESS IS 0.172", IAW SDR FY4Y197M20110315BBeam · corrodedLT HORIZONTAL STAB TRAILING LOWER BEAM LOWER SURFACE STA96 TO 97 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS IS 0.120". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.078" AREA WAS 2.25" X 1.5". IT'S BEYOND LIMIT IAW SRM 55-10-1, PAGE 1, NOTE B. CORRSDR FY4Y197M20110315ASpar · corrodedHEAVY CORROSION ON RT WING INBD MIDFLAP REAR SPAR LOWER CHORD AT WBL142, ORIGINAL THICKNESS 0.121". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.051", AREA WAS 3" X 1". IT'S BEYOND LIMITED IAW SRM 57-50-1, PAGE 8. REPAIR METHOD REF SRM 57-50-2, PAGSDR FY4Y197M20110315Skin · corrodedHEAVY CORROSION ON RT WING INBD MIDFLAP UPPER EXTERNAL SURFACE, AT WBL128, FWD OF FLAP T/E ABOUT 22.5". ORIGINAL THICKNESS IS 0.054" AFTER CORROSION REMOVE, REMAIN THICKNESS IS 0" IAW SRM 57-50-1, PAGE 8, AREA ABOUT 1" X 1.3750". REPAIR METHOD SRM 57-50-4, FSDR FOTR2019813123Hinge · crackedMCD UPPER AFT MOST SEGMENT FUSELAGE SIDE AFT LOBE IS CRACKED. REMOVED MAIN CARGO DOOR AFT SEGMENT HINGE IAW FREIGHTER MM, FIG 5201B, REV F. FABRICATED NEW SECTION FROM MS20001-16-7200 PO 9002399, DIM 18" X 3.75" IAW FREIGHTER MM FIG 5201B REV F. LOCATED ANDSDR FOTR2019813715Frame · misinstalledBS 890 FRAME HAS FASTENER WITH NO ED IN WINDOW AREA, LT SIDE. CUTOUT DAMAGED AREA DIM .75" X .5' ON STA 890 FRAME IAW SRM 53-10-4 FIG 1. FABRICATED 2 EA DOUBLERS FROM 7075-0 .071 DIM. 11" X 3" PO 20198132 IAW SRM 53-10-4 FIG 1. HEAT TREATED PARTS TO 7075T6 SDR FOTR201728764Seat Track · damagedSEAT TRACK STA. 720-740 LBL24 DAMAGED. REPAIRED ON NR 8764 FASI W/O 20172SDR C8GA20100012Valve · stuckDURING CLIMB OPERATION WITH THE LT PACK DEFERRED THE RT PACK WOULD NOT PRESSURIZE ACFT. THE ACFT RETURNED TO TOL WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED AND NOTED THAT THE RT PACK VALVE WOULD ONLY OPEN SLIGHTLY WHEN THE PACK IS TURNEDSDR FDEA201007132504Stringer · corrodedCORROSION ON STRINGER 27L FROM BS 950A TO 1130. REMOVED SECTION OF STRINGER 27L FROM BS 950D PLUS 10 INCHES TO BS 1005, 85 INCHES LONG IAW SRM, REV 103, 53-10-3 FIG 1. FABRICATED STRINGER SECTIONS USING BAC 1498-147, 7075-T6, 19 INCHES LONG, 20 1/2 INCHES LSDR FDEA201001140152Rib · crackedNR 2 SLAT HAS 2 CRACKED RIBS AT FWD MOUNT OF ACTUATOR. REMOVED CRACKED RIBS (2 EA) AT NR 2 SLAT & INSTALLED NEW RIBS INBD/OTBD IAW SRM 51-30-2, SRM 51-30-5, SRM 57-50-2 FIG 2, REV 102.SDR I5PA20090802Spar · corrodedDURING 5C CHECK AND INSPECTION, CORROSION WAS FOUND ON LT WING REAR SPAR LWR SKIN AT WS706 DIMENSION AREA 1.3 INCH X 1.7 INCH. AFTER CORROSION BLENDOUT FOUND MAX BLDOUT DEPT IS BEYOND LIMITATIONS. NO REINFORCEMENT REQUIRED, REMOVE ALL FASTENERS BLEND SMOOSDR FDEA200906172139Skin · crackedLT OTBD FORE FLAP WBL 442, CRACK ON CUTOUT FWD OF ATTACH FITTING. TRIMMED OUT CRACKED AREA, DIM 0.100 INCH LENGTH IAW SRM 51-10-1. FOUND WITHIN LIMITS IAW SRM 57-50-1. FIG 3 TREATED AND PRIMED IAW SRM 51-10-2.SDR FDEA200906172134Shear Tie · damagedFWD PIT- EXTRA HOLE IN SHEAR TIE AT BS 660, BETWEEN STRINGERS 28L AND 27L. REMOVED FASTENERS FOR ACCESS IAW SRM 51-30-2. REMOVED DAMAGED SECTION OF SHEAR TIE IAW SRM 53-10-4 FIG 15. FABRICATED NEW SHEAR TIE IAW SRM 53-10-4 FIG 15. FABRICATED RADIUS FILLER ISDR FDEA200906152115Frame · crackedFWD CARGO AREA, STA 540, STR 21-22L, LWR STUB FRAME EXTENSION, CRACK ON RADIUS. REPAIRED FORWARD CARGO COMPARTMENT LOWER STUB FRAME EXTENSION IAW EA 7-5310-126829.SDR FDEA200906022004Shear Tie · corrodedSHEAR TIE CORRODED STA 950E BETWEEN STR 28L AND 29L. REMOVED SHEAR TIE REPAIR, FABRICATED NEW SHEAR TIE, FABRICATED NEW VERTICAL STIFFENER , HEAT TREATED PARTS TO T6 CONDITION AND INSTALLED IAW SRM 51-30- 2, 53-10-2, 51-10-1, AND 53-10-4.SDR CA090601004Duct · ruptured(CAN) ACFT RETURNED TO YOW AFTER APPROX 30 MINUTES INTO FLIGHT DUE TO FIRE ALARM ON NR 2 ENGINE. ALARM WOULD NOT GO OFF AFTER NORMAL PROCEDURE SO ENGINE SHUTDOWN AND FIRE BOTTLE DISCHARGED. MX FOUND A 4 INCH HOLE IN THE 13TH STAGE BLEED AIR DUCT TO THE NOSE ANSDR FDEA200905141663Bypass Valve · failedON DEPARTURE, FLAP RETRACTION NOT NORMAL, SPLIT FLAPS, OUTBOARD FLAPS IN AGREEMENT W/HANDLE AT FLAPS 5 DEG INBOARD FLAPS STAYED AT 15 DEG. RAN QRH, SOME SLATS EXTENDED. ATTEMPTED FLAP MASTER & RAISE INBD FLAPS, ALT FLAP MOTOR INBD C/B POPPED. RTB. INBD FLASDR FDEA200905121629Vertical Beam · damagedVERTICAL BEAM HAS FASTENERS WITH 0 SPACING BS 1183 LBL 17.8. REPAIRED BS 1183 BULKHEAD VERTICAL BEAM AT LBL 17.8 IAW EA NR 7-5310-127962. "BS 1183 BULKHEAD WITH INSUFFICIENT FASTENER SPACING AT LBL 20 BELOW WL190".
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