N522MC, cancelled Apr 11, 2012
Service difficulty reports · 157
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 = 'N522MC' AND deregistration_id = 'N522MC-2012-04-11' 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 = 'N522MC' AND deregistration_id = 'N522MC-2012-04-11' 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 UIEA2011122800737Jackscrew · damagedDURING WALKAROUND, MX FOUND THE NR 2 LT THRUST REVERSER HALF DAMAGE AND NOTICED A BROKEN JACK SCREW ON THE UPPER ANGLE GEARBOX/BALL SCREW ACTUATOR, BROKEN CASCADE VANES AND SHEARED FLEX CABLES. (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBSDR UIEA2011122700736Jackscrew · brokenDURING WALKAROUND, MX FOUND THE NR 2 LT T/R HALF DAMAGE AND NOTICED A BROKEN JACK SCREW ON THE UPPER ANGLE GEARBOX/BALL SCREW ACTUATOR, BROKEN CASCADE VANES AND SHEARED FLEX CABLES. (REF FIG 1). PERFORMED A TIME LIMITED REPAIR.SDR UIEA2011121200714Nozzle · crackedDURING WALK AROUND CHECK, MX FOUND CRACK APPROX 1 INCH IN LENGTH, ON THE OUTER SLEEVE OF THE LONG FIXED CORE EXHAUST NOZZLE ON THE NR 4 ENGINE AT THE 8 O`CLOCK POSITION (REF FIG 1). (DISPOSITION WAS MADE TO REMOVE ANY BURRS AND WELD REPAIR THE CRACK USING EM 7SDR UIEA2011111800665Skin · damagedDURING INSPECTION MX FOUND THE NR 2 ENGINE RT THRUST REVERSER CORE COWL INNER SKIN DAMAGED/DELAMINATED. AT APPROX 4 O'CLOCK POSITION WITH SIZE 7.0" X 11.0" AND ALSO AT 5 O'CLOCK POSITION WITH SIZE 4.0" X 11.0". REF FIG 1. REPAIRED DAMAGE IAW MM EM 78-32-03,SDR UIEA2011091900514Skin · damagedDURING VOR ANTENNA REPLACEMENT, DISCOVERED THE VERTICAL STABILIZER - FIN WL339.5 SUSTAINED LIGHTNING STRIKE CAUSING DAMAGE TO THE VOR ANTENNA AND TO THE RT SIDE OF THE VERTICAL STABILIZER EXTERNAL SKIN CONSISTING OF A HOLE/PUNCTURE MEASURING 1.3 INCHES DIAM. (SDR UIEA2011101900597Lamp · inoperativeUPPER DECK AFT NR 1 AND NR 2 CEILING EMERGENCY LIGHTS INOPERATIVE. RELAMPED AND TESTED OK IAW MM 33-51-00 AND MM 33-51-07.SDR UIEA2011061400320Power Supply · inoperativeRIGHT SIDE U/D DR SLIDE EMERGENCY LIGHT INOP. EMERGENCY LT POWER PACK REPLACED.SDR UIEA2011061100296Intercostal · crackedFOUND A CRACK DURING A C4/A12-CHECK. (PART 1, TIME-LIMITED REPAIR WAS ACCOMPLISHED AT BY TRIMMING THE FRAME WEB, REPLACING THE INTERCOSTAL WEB AND SPLICING IN NEW SEGMENTS OF FRAME INNER CHORDS. THE PART 2 PERMANENT OR INTERIM REPAIR IS REQUIRED W/N 1,000FC ORSDR UIEA2011061000312Skin · crackedCRACK DAMAGE IN SKIN ASSY 65B04116-2 AT BS 955 - 987, S37R - 39R IN THE DRAG SPLICE FITTING AREA. THE CRACK DAMAGE WAS DETECTED DURING C04 PLUS A12 CHECK AND WHILE COMPLYING WITH SB 747-53A2444 REV 2. (NRC 501750 WAS USED TO DOCUMENT THE FINDING OF THE CRACKSDR UIEA2011061000299Structure · crackedL3 PASSENGER DOOR (ASSY PN 65B01842-287, SN TLS 13762) AFT UPPER CORNER WITH CRACK REPAIR AT INTERNAL SURFACE. THE CRACK WHICH MEASURES APPROX 1.5 INCHES LONG (REPAIRED WITH STOP DRILL AT BOTH ENDS. IN ADDITION, A REPAIR ANGLE WAS FOUND AT THE AFT EDGE AS SHSDR UIEA2011060700310Skin · crackedCRACKS WERE FOUND AT MAIN ENTRY DOOR 1R LOWER FWD CORNER OF DOOR CUTOUT IN OUTER SKIN, DOUBLER, CHORD AND STRAPS.( DOCUMENTATION OF REPAIR AT MAIN ENTRY DOOR 1R AT LOWER FWD CORNER OF DOOR CUTOUT. DAMAGE WAS CRACKS IN OUTER SKIN, DOUBLER, STRAPS AND CHORD. DASDR UIEA2011060700300Bulkhead Web · crackedDURING C-CHECK, A CRACK WAS FOUND IN THE PRESSURE WEB. THE CRACK WAS LOCATED AT THE 11 O'CLOCK POSITION, EXTENDING THROUGH TWO (2) FASTENER HOLES OTBD OF THE RT 2ND INTERMEDIATE STIFFENER FROM THE TOP. THE CRACK EXTENDED 0.1875 IN INBD AND 0.125 IN OTBD AS SSDR UIEA2011060300315Tension Tie · damagedDAMAGE WAS DISCOVERED DURING INSPECTION IAW EO 4753B328 - SB 747-53A2502 (ASSOCIATED WITH AD 2006-01-07) AT THE C4 CHECK. IN ADDITION TO THE SHORT EDGE MARGIN ON THE TENSION TIE, THE FRAME AND FRAME DOUBLER FASTENER HOLES HAVE BEEN PREVIOUSLY OVERSIZED IAW SB SDR UIEA2011060200298Stiffener · damagedNOSE WHEEL WELL - STIFFENER, BS 280/LBL 10 - FILLER REPAIR. EO 4753B355. (EO RS NR:R-53-00-37098, REV A, FABRICATION AND INSTALLATION OF THE TWO (2) STRUCTURAL FILLERS TO ELIMINATE INTERFERENCE DURING THE INSTALLATION OF REPLACEMENT STIFFENER 141U5190-219, WASDR UIEA2011060200286Fairing · crackedDURING INSPECTION THE NR1 ENGINE RT THRUST REVERSER LOWER AFT FAIRING WAS FOUND WITH A CRACK AND MISSING MATERIAL AS SHOWN IN FIGURES 2 AND 3. TRIMMED OUT THE DAMAGED FAIRING SKIN. HFEC INSPECTED THE REWORKED AREA TO ENSURE NO CRACKS OR OTHER DEFECTS. INSTASDR UIEA2011060100290Structure · corrodedEO 4753B352: DURING ACCOMPLISHMENT OF SB 747-53A2562, FOUND HEAVY CORROSION AT BS 340, RBL 37, WL 120, PN 65B07935-544 TEE THROUGH VERTICAL FLANGE AS SHOWN IN FIG 1. (PROPOSED THE REPAIR SHOWN IN FIG 1 WHICH DEEMED ACCEPTABLE WITH THE FOLLOWING PROVISIONS: MACSDR UIEA2011051700289Spar · damagedREPORTED DAMAGE TO RT HORIZ STABILIZER REAR SPAR HINGE FITTING HOLE NR28, MFG PROPOSED THE REPAIR SHOWN IN FIG 1 (FABRICATE AND INSTALL FREEZE PLUG AT SUBJECT HOLE LOCATION IAW SRM 51-10-08). DEEMED THE REPAIR ACCEPTABLE WITH THE FOLLOWING PROVISIONS: PERFORM SDR UIEA2011051700269Nozzle · crackedDURING A "C" CHECK OF AIRCRAFT, MX FOUND CRACKS ON THE NR 1 AND NR 2 ENGINE FIXED COWL EXHAUST NOZZLE FWD FLANGE CORE COWL SUPPORT ASSY (REF FIG 1 AND 2 ). (THE CRACKS CAN BE REPAIRED IAW THE ENGINE SHOP MANUAL (ESM) TASK 78-33-05, REPAIR 78-33-05, REPAIR 002SDR UIEA2011051400317Power Supply · inoperativeEMERGENCY LIGHT FOUND INOPERATIVE. EMERGENCY LIGHT POWER SUPPLY; REPLACED AND LT OPS CHECK FOUND NORMAL IAW AMM 33-51-07.SDR UIEA2011051300318Terminal · unsecureL1 DOOR, AFT DOOR SILL LIGHT FOUND INOP. (L1 AFT DOOR SILL LIGHT ASSY TERMINAL RESECURED AND TEST NORMAL. AMM 33-51-07)SDR UIEA2011050900319Battery · inoperativeM/D STATION 460, 2 EA EMERGENCY LIGHT FOUND INOPERATIVE. EMERGENCY LIGHT BATTERY REPLACED AND TEST NORMAL IAW AMM 33-51-07.SDR UIEA2011012800038Structure · damagedDURING A-CHECK BEING PERFORMED, MX FOUND DAMAGE TO THE LOWER AFT CARGO COMPARTMENT - BS1820 - BS1840, BL 0 CONSISTING IN: "Z" SECTION FROM BS 1820 TO BS 1840, RBL3.0 IS 0.050" 7075-T6. REPAIRED IAW SRM 51-40-03 FIG 1 REF FIG 1. TOP PANEL FROM BS 1820 TO BS 18SDR UIEA2011012800036Structure · damagedDURING A-CHECK BEING PERFORMED, MX FOUND DAMAGE TO THE RT INBD NR 7 SPOILER T/E. PERMANENT REPAIR PERFORMED IAW THE SRM 51-40-06 FIG 3 & AMP; FIG 4 SHEET 1 AND PREPREG 250A° F CURE IAW SRM 51-40-20.SDR UIEA2010111000177Nacelle · crackedTHE PURPOSE OF THIS EO 4771A096 & NBSP; IS TO DOCUMENT A MAJOR REPAIR. DURING WALK-AROUND INSPECTION AT RMS, MX FOUND THE NR 1 RT FAN COWL WITH DAMAGE; CRACK MEASURING 6.0 IN. LONG (REF FIG 1). THE DAMAGE IS BEYOND THE ALLOWABLE DAMAGE LIMITS IAW SRM 51-40-06,SDR UIEA201000235Conduit · damagedDURING WALKAROUND INSP, MX FOUND THE ELECTRICAL CONDUIT AND CONNECTOR MOUNT HOUSING AT THE NOSE GEAR DAMAGED (REF FIG 1). DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, INITIATE REPEAT INSPECTIONS AT EVERY 5 FLIGSDR UIEA2010080200127Actuator · damagedUPON ARRIVAL, THE NR2 RT THRUST REVERSER, MX FOUND THE T/R NOT COMPLETELY STOWED. AFTER INSP, MX FOUND THE CTR BALLSCREW SHEARED AND THE UPPER BALLSCREW ACTUATOR SUPPORT BRACKET DAMAGED. (DISPOSITION IS TO REPLACE THE CTR BALLSCREW WITH A SERVICEABLE UNIT, RESDR UIEA2010060600028Floor Panel · damagedDURING CARGO LOADING AT DOV; MX FOUND DAMAGE TO THE MAIN DECK FLOORBOARD AT BS 1080, RBL 45. THE DAMAGE TO THE MD FLOORBOARD PANEL AT BS1080, RBL45 AIS S FOLLOWS: THE DAMAGE IS ABOUT 7 INCHES LONG AND ABOUT .5 INCH WIDE, AND .2500 INCH DEEP. (DISPOSITION WAS MSDR UIEA201000138Blowout Door · damagedREF EO 4778A150- NR 2 T/R ACCESS AMD BLOWOUT DOOR REPAIR. PART ONE TIME LIMITED REPAIR ACCOMPLISHED. PART TWO INSPECTION REQUIRED EVERY FLIGHT CYCLE (SCHEDULE WITHIN 10 CALENDAR DAYS AFTER ACCOMPLISHMENT PART 1).SDR UIEA2010022300139Fairing · puncturedWING TO BODY FAIRING AT BS 1680 WITH A PUNCTURE/DAMAGE (HONEYCOMB EXPOSURE) MEASURING 2.5 IN. X 0.5 IN (REF FIG 1) (PERFORMED A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 OF EO 4753B253 PART 1 OF WORK INSTRUCTIONS. SCHEDULE REPEAT INSP AT EVERY 3 FC AND PERMANSDR UIEA201000063Stringer · corrodedDURING C-CHECK, MAINTENANCE FOUND LEVEL 2 CORROSION IN THE 65B04369-175 STRINGER AT BS 1960, S-50R. EFFECTED AREA WAS REMOVED AND REPAIRED AS PER FAA FORM 8100-9 DATED 05 FEB 2010 AND EO 4753B249.SDR UIEA201000062Frame · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION IN THE 65B04331-165 AFT LOWER LOBE FRAME TEE CAP AT BS 1880, LBL 21-22. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 04 FEB 2010 AND EO 4753B246.SDR UIEA201000061Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION IN THE SKIN LAP JOINTS BETWEEN BS 1700 AND 1960 AND S-40L. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 05 FEB 2010 AND EO 4753B248.SDR UIEA201000060Frame · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION ON THE FLANGE OF THE OUTER CHORD 65B10365-10 OF FRAME 1265 IS WHEEL WELL S-30 R-S-31R. CORROSION WAS BLENDED AS PER FAA FORM 8100-9 DATED 05 FEB 2010 AND EO 4753B245.SDR UIEA201000154Skin · corrodedDURING C-CHECK, CORROSION WAS FOUND BETWEEN BS 2020 AND 2040 AT S-46L IN THE 65B04151-2 FUSELAGE SKIN. THE DENT WAS TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-30-03, FIG 19. THE 65B04151-2 SKIN PANEL IS MADE FROM 0.063 INCH THICK 2024-T3 CLAD ASDR UIEA201000064Frame · crackedDURING C-CHECK, MAINTENANCE FOUND CRACKS IN THE 65B07415-5 FRAME WEB AT BS 720 BETWEEN S-42L AND S-44L. EFFECTED AREA WAS REMOVED AND REPAIRED AS PER EO 4753B243.SDR UIEA201000059Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND LEVEL 2 CORROSION AT BS 1970 AT S46L IN THE 65B04151-2 FUSELAGE SKIN. AREA WAS TRIMMED OUT AND A REPAIR DOUBLER WAS INSTALLED AS PER EO 4753B244.SDR UIEA201000066Skin · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION ON THE INTERSPAR SKIN AFT OF REAR SPAR. CORROSION WAS BLENDED OUT AS PER EO 4757A493 AND FAA 8100-9 DATED 1 FEB 2010.SDR UIEA201000058Structure · corrodedDURING C-CHECK, MAINTENANCE FOUND CORROSION BETWEEN BS 2020 AND 2040 AT S 46L. CORROSION WAS BLENDED OUT AS PER EO 4752B242.SDR UIEA200900054Actuator · failedAIR TURN BACK DUE TO RED GEAR LIGHT ILLUMINATED AFTER GEAR RETRACTION . F/E PANEL RIGHT WING GEAR DOOR OPEN ON BOTH PRIMARY AND ALTERNATE . AFTER FHB CHECK WITH GEAR EXTENDED LIGHTS EXTINGUISHED. RIGHT WING GEAR DOOR ACTUATOR REPLACED, GEAR SWING ACCOMPLISHEDSDR UIEA200900047Skin · crackedFUSELAGE SKIN RT SIDE ABOVE STABILIZER CUT-OUT AT STA 2589.5 TO 2598, SKIN MISSING CRACKED AND MISSING MATERIAL. PERMANENT REPAIR ACCOMPLISHED IAW SRM 53-30-03 FIG 1A. ALSO, REFERENCE EO 4753B229.SDR UIEA200900046Skin · puncturedRT WING INBD FLAP HAS 0.500 INCH DIAMETER PUNCTURED HOLE AT LWR SURFACE, WBL 188.30 AND 4.0 INCHES FROM L/E. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09 FIG. 5, SHEETS 4 AND 8, 250* F CURE IAW SRM 51-40-12. REF: EO 4757A485.SDR UIEA200800343Panel · crackedRT WING UPPER L/E PANEL HAS A 19 INCH COMPOSITE CRACK AT ILES 657.22, 5.0 INCHES FROM PANEL FRONT EDGE. PERMANENT REPAIR ACCOMPLISHED AS PER SRM 51-40-09 FIG 18, SHEETS 2 AND 5 AND SRM 51-40-12. REF ATLAS AIR EO 4757A467.SDR UIEA200800342Panel · delaminatedRT WING PREVIOUS REPAIR ON UPPER WING SURFACE L/E PANEL AN AREA OF 6.0 BY 38.0 INCHES IS DELAMINATED AT ILES 522.06 AND 7.5 INCHES FROM PANEL FRONT EDGE. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 18, SHEETS 2, 5 AND SRM 51-40-12. REF. ATLSDR UIEA200800281APanel · crackedRT WING UPPER AFT TRAILING EDGE PANEL, OUTBOARD OF INBOARD AILERON HAS 2 EACH SMALL COMPOSITE CRACKS AT WBL 445.00. FORWARD CRACK IS .500 INCH LONG AND AFT CRACK IS 1.0 INCH LONG. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09 FIG 2, SHEETS 2 AND SDR UIEA200800282Panel · crackedRT WING UPPER LEADING EDGE PANEL HAS A 20.0 INCH COMPOSITE CRACK AT ILES 522.56 AND IS 26 INCHES FROM FORWARD END OF PANEL. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09 FIG 18, SHEETS 2 AND 5, PREPEG LAYUP 250 DEGREES F CURE PER SRM 51-40-12. RESDR UIEA200800269Engine · vibrationBLOCK TURNBACK NR 2 ENGINE EGT FLAG IN VIEW WITH UNUSUAL NOISE (RUMBLING) HEARD AND FELT DURING THROTTLE MOVEMENT FROM NR 2 ENGINE. REPLACED ENGINE IAW WORK CARD E2008. (A)SDR UIEA200800215Panel · crackedMAIN DECK L-2 DOOR FWD UPPER INNER REVEAL PANEL FOUND CRACKED. CRACKED AREA REPAIRED IAW EO NR 4753B148.SDR UIEA200800214Floorbeam · crackedMAIN DECK FLOORBEAM WEB FOUND CRACKED AT STA 1200 LBL 120. MAIN DECK FLOOR WEB CRACKED AREA REPAIRED PER EO 4753B154.SDR UIEA200800213Floorbeam · crackedMAIN DECK FLOORBEAM WEB FOUND CRACKED AT STA 1180 LBL 120. MAIN DECK FLOOR WEB CRACKED AREA REPAIRED PER EO 4753B153.SDR UIEA200800212Frame · crackedMAIN DECK STA 1740 STRINGER 13R - 14R FRAME FOUND CRACKED. FRAME CRACKED AREA REPAIRED PER EO NR 4753B152.
Back to N522MC, cancelled Apr 11, 2012