N221US, cancelled Jun 14, 2000
Service difficulty reports · 63
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.
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 n_number = 'N221US' AND deregistration_id = 'N221US-2000-06-14' 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 n_number = 'N221US' AND deregistration_id = 'N221US-2000-06-14' 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 98ZZZM494Power Supply · inoperativeFORWARD LEFT (PAX) AND RT SERVICE DOOR EXIT EMERGENCY LIGHTS INOP. REMOVED AND REPLACED FORWARD EMERGENCY LIGHTS POWER SUPPLY PACK, S/N ON 1715, S/N OFF 15002, P/N 60-1321-1, IAW MM 33-51-71. (M)SDR 98ZZZM401Splice · brokenON OVERNIGHT CHECK, FOUND ROW 2 EMERGENCY LIGHT INOP. FOUND BUTT SPLICE BROKEN. REINSTALLED NEW SPLICE, OPS CHECK OK. (M)SDR 98ZZZM80Light · inoperativeFORWARD ENTRY DOOR EMERGENCY EXIT LIGHT INOP, FOUND ON RON MAINTENANCE CHECK. REPLACED LIGHT ASSY, OPS CHECK GOOD. (M)SDR 97ZZZM426Skin · crackedFOUND 5 CRACKS AT FASTENERS STATION 373, 374, 375, 377, STRINGER 15L. REPAIRED PER SRM 53-30-3. (M)SDR 97ZZZM425Skin · crackedFOUND .125 INCH CRACK AT FASTENER HOLE. REPAIRED PER SRM 53-30-1.SDR 97ZZZM424Skin · crackedFOUND TWO .25 INCH LONG CRACKS. REPAIRED PER SRM 53-30-3 FIG 1.SDR 97ZZZM423Skin · crackedFOUND TWO CRACKS AT FASTENER HOLES. REPAIRED PER SRM 53-30-3.SDR 97ZZZM422Frame · crackedFOUND ONE INCH CRACK IN FRAME. REPAIRED PER SRM 51-40-2.SDR 97ZZZM421Frame · crackedLEFT OUTBOARD CHORD ANGLE CRACKED STATION 1156 WL 274, .75 INCH CRACK. REPAIRED PER EO 5391G569.SDR 97ZZZM420Stringer · crackedONE INCH CRACK IN STRINGER. REPAIRED PER SRM 53-10-3.SDR 97ZZZM419Skin · disbondSKIN DISBONDED AT LOWER CORNERS OF EMERGENCY EXIT APERTURE, REPAIRED PER EA 42068.SDR 97ZZZM418Skin · cracked3 INCH BY 5 INCH DELAMINATED AREA AND CRACKS AT SIX FASTENER HOLES. REPAIRED PER EA 42062. (M)SDR 97ZZZM417Bulkhead Fitting · crackedBULKHEAD FITTING CRACKED 3 INCHES. TIME LIMITED REPAIR INSTALLED PER EA 42071 AND DWG 65C 29229. (M)SDR 96ZZZX1484Skin · crackedGSO - .1250 INCH CRACK AT RIVET HOLE FOUND. INSTALLED DOUBLER SRM 53-30-3, FIGURE 6.SDR 96ZZZX1483Skin · crackedGSO - FIVE .25 INCH CRACKS AT RIVET HOLES FOUND. INSTALLED REPAIR PER E.A. 40951.SDR 96ZZZX1482Skin · crackedGSO - 3 CRACKS FORWARD UPPER CORNER, FORWARD SERVICE DOORWAY. INSTALLED DOUBLER PER E.A. 40950.SDR E9WASkin · damagedCLT - INSPECTION VISUALLY FOUND MISSING TRAILING EDGE HONEYCOMB CORE MATERIAL LOCATED AT THE VERTICAL STAB AT RUDDER STATION 218 RIGHT TRAILING EDGE PANEL. COMPOSITE REPAIRED AS PER BOEING SRM 51-40-13. (M)SDR 96ZZZM798Skin · damagedCLT - INSPECTION FOUND 2 PREVIOUSLY INSTALLED DOUBLERS WITH BLIND FASTENERS LOCATED AT FUSELGE SKIN, FS 727A AT STRINGER 15R AND 16R. INSTALLED EXTERNAL DOUBLER AS PER BOEING SRM 53-30-3 FIG 6 AND USAIR EA NR 24906. (M)SDR 96ZZZM744Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND MEASURING 12 INCHES BY 2.5 INCHES LOCATED FUSELAGE SKIN AT STATION 927-947 AND STRINGER 14L. INSTALLED FIELD FASTENERS AS PER SRM 53-30-3 FIG 17 DETAIL 1. (M)SDR 96ZZZM743Skin · crackedCLT - INSPECTION VISUALLY FOUND A CRACK THROUGH RIVET .1875 INCH UP AND .125 INCH DOWN LOCATED AT FUSELAGE SKIN AT STATION 251 AND STRINGER 11L. INSTALLED DOUBLER AS PER BOEING SRM 53-30-03 AND USAIR EO NR 22870. (M)SDR 96ZZZM742Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND DISBONDED SKIN AND DOUBLER MEASURING 9 INCHES BY 5 INCHES LOCATED AT THE FUSELAGE SKIN AT STATION 288, STRINGER 14L AND STRINGER 15L. INSTALLED FIELD DOUBLERS AS PER BOEING SRM 53-30-3 DETAIL 1 FIG 17. (M)SDR 96ZZZM741Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND DISBONDED SKIN AND DOUBLER AT THE FUSELAGE SKIN MEASURING 5 INCHES BY 18 INCHES LOCATED AT STATION 920 TO 927 AND STRINGER 9R TO STRINGER 10R. INSTALLED FIELD RIVETS AS PER BOEING SRM 53-30-3. (M)SDR 96ZZZM740Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 3 INCHES BY 4 INCHES AT STATION 967 ABOVE STRINGER 5L. INSTALLED FIELD RIVETS AS PER SRM 53-30-3 FIG 17. (M)SDR 96ZZZM739Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 5 INCHES BY 4 INCHES AT STATION 356, STRINGER 15L AND 16L. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3 DETAIL I AND TABLE III FIG 17. (M)SDR 96ZZZM738Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 14 INCHES BY 2.5 INCHES AT STATION 902 TO 914 AND STRINGER 13R TO STRINGER 14R. INSTALLED FIELD RIVETS AS PER BOEING SRM 53-30-3. (M)SDR 96ZZZM737Skin · crackedCLT - INSPECTION VISUALLY FOUND AND VERIFIED WITH HFEC A 1.25 INCH CRACK LOCATED AT FUSELAGE SKIN FS 1137 AND STRINGER 12L. INSTALLED DOUBLER AS PER BOEING SRM 53-30-3 FIG 30. (M)SDR 96ZZZM736Support Beam · corrosionCLT - INSPECTION VISUALLY FOUND LEVEL I CORROSION AT THE FUSELAGE FLOOR SUPPORT BEAM LOCATED AT LBL 2 TO LBL 6 AND STATION 1014. FABRICATED REPLACEMENT H-CHANNEL AND ATTACH ANGLE AS PER BOEING SRM 51-00-02. (M)SDR 96ZZZM735Skin · gougedCLT - INSPECTION VISUALLY FOUND A 1.5 INCH GOUGE .019 DEEP AT FUSELAGE SKIN LOCATED AT FS 360 1 INCH ABOVE STRINGER 18L. INSTALLED DOUBLER AS PER BOEING SRM 53-30-3, FIG 28. (M)SDR 96ZZZM734Skin · disbondCLT - INSPECTION BY ULTRASONIC FOUND DISBONDED SKIN AND DOUBLER AT THE FUSELAGE SKIN LOCATED AT STATION 927 TO 947 AND STRINGER 21R TO STRINGER 20R. REMOVED AND REPLACED SKIN DOUBLER AS PER BOEING SRM 53-30-3 FIG 17. (M)SDR 96ZZZM733Skin · corrosionCLT - INSPECTION VISUALLY FOUND A LEVEL I CORRODED PRODUCTION STRINGER SPLICE 6 INCHES AT THE FUSELAGE SKIN LOCATED AT STATION 908 AND STRINGER 20R. REPLACED AND REPAIR STRINGER PRODUCTION SPLICE AS PER BOEING SRM 51-00-00. (M)SDR 96ZZZM732Skin · disbondedCLT - INSPECTION VISUALLY FOUND 6 INCH DISBONDED FUSELAGE SKIN LOCATED AT STATION 954 BETWEEN STRINGER 24 AND STRINGER 23R. REPLACED SKIN AS PER USAIR EA NR 58009 AND JOB CARD JZ-57-53500 C-1. (M)SDR 96ZZZM731Angle · crackedCLT - INSPECTION VISUALLY FOUND A 1.5 INCH CRACK LOCATED AT THE FUSELAGE RADIUS OF ANGLE AT FS 1085 AND STRINGER 2L. INSTALLED AND MANUFACTURED ANGLE AS PER BOEING SRM 20-30-06. (M)SDR 96ZZZM730Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND TWO 6 INCHES BY 6 INCHES AND 8 INCHES BY 2 INCHES AREAS OF SKIN AND DOUBLER DISBOND LOCATED AT THE FUSELAGE SKIN BETWEEN STATION 277 AND 294.5, STRINGER 5R AND STRINGER 8R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-3SDR 96ZZZM729Skin · disbondedCLT - INSPECTION BY ULTRASONIC, FOUND FUSELAGE SKIN AND DOUBLER DISBOND LOCATED AT STATION 927 TO 947, STRINGER 9L AND STRINGER 10L. INSTALLED FIELD DOUBLERS AS PER BOEING SRM 53-30-3 FIG 17. (M)SDR 96ZZZM728Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND TWO AREAS OF DISBOND, 14 INCHES BY 8 INCHES AND 4 INCHES BY 8 INCHES LOCATED AT THE FUSELAGE SKIN AT STATION 312-344 AND STRINGER 5R AND STRINGER 6R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3 FIG 17 DETAILES I ASDR 96ZZZM727Skin · disbondedCLT - INSPECTION BY ULTRASONIC FOUND FUSELAGE SKIN AND DOUBLER DISBOND LOCATED AT STATION 635, STRINGER 8R AND STRINGER 9R. INSTALLED FIELD RIVETS AS PER BOEING SRM 53-30-3, FIG 17. (M)SDR 96ZZZM726Skin · disbondedCLT - INSPECTION BY ULTRASONIC FOUND FUSELAGE SKIN AND DOUBLER DISBOND 7 INCH BY 2 INCH LOCATED AT STATION 986.5 TO 1016, STRINGER 9R TO STRINGER 10R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3, DETAIL I, FIG 17. (M)SDR 96ZZZM725Chord · crackedCLT - INSPECTION FOUND BY ULTRASONIC AND EDDY CURRENT A CRACK APPROXIMATELY 1 INCH LOCATED AT THE FUSELAGE CHORD, RHS BS 727, OUTBOARD CHORD AT STRINGER 18A. CHORD SECTION REPLACED AS PER EO 5394G068, EO 5394G6075 AND SB 737-53-1088. (M)SDR 96ZZZM724Vertical Fin · dentedCLT - INSPECTION VISUALLY FOUND A DENT LOCATED AT VERTICAL STABILIZER MEASURING 1 INCH BY 2.5 INCH AT FIN STATION 209.90, RIGHT INSPAR. CUT OUT DAMAGE, INSTALLED DOUBLER AS PER USAIR EA NR 40708. (M)SDR 96ZZZM723Chord · crackedCLT - INSPECTION FOUND BY ULTRASONIC AND EDDY CURRENT, A CRACK APPROXIMATELY 1 INCH, LOCATED AT THE FUSELAGE CHORD, RHS BS 727, OUTBOARD AT STRINGER 18A. CHORD SECTION REPLACED AS PER EO 5394G068, EO 5394G6075 AND SB 737-53-1088. (M)SDR 96ZZZM722Angle · crackedCLT - INSPECTION VISUALLY FOUND A 1.5 INCH CRACK LOCATED AT THE FUSELAGE RADIUS OF ANGLE AT FS 1085 AND STRINGER 2L. INSTALLED AND MANUFACTURED ANGLE AS PER BOEING SRM 20-30-06. (M)SDR 96ZZZM721Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND TWO 6 INCH BY 6 INCH AND 8 INCH BY 2 INCH AREAS OF SKIN AND DOUBLER DISBOND LOCATED AT THE FUSELAGE SKIN BETWEEN STATION 277 AND 294.5, STRINGER 5R AND STRINGER 8R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3 FIG SDR 96ZZZM720Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND FUSELAGE SKIN AND DOUBLER DISBOND LOCATED AT STATION 927 TO 947, STRINGER 9L AND STRINGER 10L. INSTALLED FIELD DOUBLERS AS PER BOEING SRM 53-30-3 FIG 17. (M)SDR 96ZZZM719Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND TWO AREAS OF DISBOND, 14 INCHES BY 8 INCHES AND 4 INCHES BY 8 INCHES LOCATED AT THE FUSELAGE SKIN AT STATION 312-344 AND STRINGER 5R AND STRINGER 6R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3 FIG 17, DETAILS I ASDR 96ZZZM718Skin · disbondCLT - INSPECTION BY ULTRASONIC FOUND FUSELAGE SKIN AND DOUBLER DISBOND LOCATED AT STATION 635, STRINGER 8R AND STRINGER 9R. INSTALLED FIELD RIVETS AS PER BOEING SRM 53-30-3, FIG 17. (M)SDR 96ZZZM717Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND FUSELAGE SKIN AND DOUBLER DISBOND 7 INCHES BY 2 INCHES LOCATED AT STATION 986.5 TO 1016, STRINGER 9R TO STRINGER 10R. INSTALLED FIELD FASTENERS AS PER BOEING SRM 53-30-3, DETAIL I, FIG 17. (M)SDR 96ZZZM716Skin · disbondCLT - INSPECTION BY ULTRASONIC, FOUND FUSELAGE SKIN AND DOUBLER DISBOND, 13 INCHES BY 13 INCHES LOCATED AT STATION 986.5 TO 1016 AND STRINGER 12R TO STRINGER 13R. INSTALLED FIELD RIVETS AS PER BOEING SRM 53-30-3 FIG 17 DETAIL I. (M)SDR 96ZZZM715Skin · disbondedCLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND MEASURING 12 INCHES BY 2.5 INCHES LOCATED FUSELAGE SKIN AT STATION 927-947 AND STRINGER 14L. INSTALLED FIELD FASTENERS AS EPR SRM 53-30-3 FIG 17, DETAIL 1. (M)SDR 96ZZZM714Skin · crackedCLT - INSPECTION VISUALLY FOUND A CRACK THROUGH RIVET .1875 INCH UP AND .125 INCH DOWN LOCATED AT FUSELAGE SKIN AT STATION 251 AND STRINGER 11L. INSTALLED DOUBLER AS PER BOEING SRM 53-30-03 AND USAIR EO NR 22870. (M)SDR 96ZZZM713Skin · disbondedCLT - INSPECTION BY ULTRASONIC FOUND DISBONDED SKIN AND DOUBLER MEASURING 9 INCHES BY 5 INCHES LOCATED AT THE FUSELAGE SKIN AT STATION 288, STRINGER 14L AND STRINGER 15L. INSTALLED FIELD DOUBLERS AS PER BOEING SRM 53-30-3 DETAIL 1 FIG 17. (M)
Back to N221US, cancelled Jun 14, 2000