N527MC, cancelled Sep 19, 2008
Service difficulty reports · 54
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 = 'N527MC' AND deregistration_id = 'N527MC-2008-09-19' 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 = 'N527MC' AND deregistration_id = 'N527MC-2008-09-19' 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 UIEA200800027Bulkhead · damagedPRELIMINARY REPORT, ON TAKEOFF ROTATION, FREIGHT CAME LOOSE ON MAIN DECK SLID AFT AND PENETRATED THE AFT PRESSURE BULKHEAD. CREW PERFORMED AN ATB AND LANDED WITHOUT INCIDENT INTO LFW. AIRCRAFT SUSTAINED APPROX 12 INCH HOLE. AIRCRAFT DAMAGE BEING EVALUATED BSDR UIEA200700471Skin · delaminatedLEFT WING INBOARD T/E FOREFLAP HAS SIGNS OF DELAMINATION 15" FROM OUTBOARD EDGE. PERFORMED WING TRAILING EDGE REPAIR AS PER SRM 51-40-09 AND 51-40-06 AND XEO 57-110707.SDR UIEA200700358Drain Valve · corrodedDURING SCHEDULED TIME REMOVAL OF THE TOILET SERVICE DRAIN VALVE FOUND HEAVY CORROSION ON THE BRACKET ABOVE THE PAN AND SERVICE DOOR INSTALLATION. REMOVED ALL BRACKET THAT HAD CORROSION DAMAGE. REPAIRED INTERNAL STRAPS PER SRM 53-30-03. REPAIRED INTERNAL SECSDR UIEA200700357Flap Track · crackedNR 1 MOVABLE FLAP TRACK FAIRING HAS SMALL CRACK LOWER SURFACE. REPAIRED PER SRM 51-40-09 AND 51-40-12.SDR UIEA200700356Skin · damagedLEFT WING NR 7 VARIABLE CAMBER FLAP OUTER SKIN HAS LOWER EDGE RIVETS LOOSE AND UPPER EDGE FASTENER HEADS BROKEN. REMOVED LT WING NR 7 L/E FLAP TO FACILITATE ACCESS FOR SHEET METAL REPAIR. REPLACED RIVETS AND FASTENERS AS NECESSARY AS PER SRM 51-30-02. REINSSDR UIEA200700355Skin · crackedLEFT WING INBOARD FOREFLAP HAS 2" CRACK ON LEADING EDGE 12" FROM OUTBOARD EDGE. REPAIRED PER SRM 51-40-12 AND 51-40-08.SDR UIEA200700317Structure · damagedON WALK AROUND FOUND NR 12 L/E KRUGER FLAP DAMAGED. PERFORMED INTERIM REPAIR IAW XEO 57-081307. PERM REPAIR TO BE ACCOMPLISHED AT NEXT "A' CHECK 20 AUG 07.SDR UIEA200700293Engine · failedNR 3 ENGINE SHUT DOWN DUE TO A LOUD BANG, N1 STARTED TO DECREASED, VISUAL INSPECTION SHOWED NO OPEN T/R BUT ENGINE WAS SWINGING EXCESSIVELY COMPARED TO NR 4 ENGINE WAS NOT SWINGING OR MOVING SMOOTH AIR SHUT DOWN IAW FHB SEC 3.SDR UIEA200700204Inu · inoperativeINFLIGHT, 7MINS AFTER T/O, NR 1 INS WENT TO WRN WITH NO DISPLAYS. NR 1 ATT FLAG AND NR 1 HDG FLAG APPEARED AND A/T WENT INOP. SWAPPED NR-1 INS NAV UNIT WING NR-3 INS NAV UNIT. TESTED NR-1 INS NAV UNIT PER AMM 34-41-03. CHECKED GOOD NO ACTION CODES.SDR UIEA200700146Skin · corrodedFUSELAGE STATION 2360 RT SIDE, BETWEEN STRINGERS 30R AND 32R HAS AN AREA OF 3.0 INCH LONG BY 11.0 INCHES WIDE OF CORROSION ON SKIN. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 53-30-03 FIG 1. AREA OF CORROSION WAS CUT-OUT AND HFEC WAS ACCOMPLISHED TO VESDR UIEA200700038Start Valve · faultyNR 3 ENGINE START VALVE OPEN LIGHT CAME ON DURING CRUISE, FOLLOWED FHB PROCEDURES AND SHUT DOWN THE ENGINE. TRANSFERRED TO DEFERRED ITEM M07-010, MEL 80-1-1. AS PER MCC REQUEST REMOVED AND REPLACED START VALVE. REMOVED AND REPLACED START VALVE AS REQUIRED.SDR UIEA200700012Panel · dentedRT WING INBOARD LEADING EDGE PANEL AT WBL 158.0 HAS A 2.0 INCH LONG BY 1.5 INCH WIDE BY .073 INCH DEEP DENT. ACCOMPLISHED PERMANENT REPAIR AS PER B747-200 SRM 51-40-09 FIG 18 SHEET 1 THRU 5. ALSO, REFERENCE ATLAS AIR EO NO. 4757A314.SDR UIEA200700011Skin · crackedLT WING, UPPER SURFACE, TRAILING EDGE PANEL, AFT OF REAR SPAR, WBL 445 IS CRACKED AROUND FASTENER HOLE. ACCOMPLISHED PERMANENT REPAIR AS PER B747-200 SRM 51-40-09 FIG 2, SHEETS 1 THRU 5. REPAIR AREA IS 4.0 INCH BY 4.0 INCH ALSO, REFERENCE ATLAS AIR EO NR 475SDR UIEA200600218Skin · crackedPYLON NR 2 ACCESS PANEL 462AL CUTOUT FOUND A CRACK NAC STA 220 0.75 INCH LONG. CARRIED OUT HFEC INSPECTION AS PER NTM PT 6 51-00-00 FIG 23 & 16. NIL CRACK INDICATION. CRACK ON SKIN WAS TRIMMED OUT & HFEC INSPECTED & REPAIR AS PER FAA FORM 8100-9.SDR UIEA200600219Skin · dentedRIGHT WING L/E CAP AT WING ROOT FOUND WITH A DENT. HFEC CARRIED OUT ON THE OUTER SKIN OF THE DENTED AREA. NIL CRACK. NTM PART 6 51-00-00 FIGURE 23. L/E CAP SKIN (INNER & OUTER SKIN), AND STRUCTURE INSPECTED FOUND NO DAMAGE OR DELAMINATION AERO DYNAMIC FILLSDR UIEA200600217Hinge Fitting · crackedHORIZONTAL STABILIZER CENTER SECTION ZONE-B, OPEN HOLE HFEC INSPECTION, FOUND RIGHT INBOARD VERTICAL HINGE FITTING AFT SIDE CRACK AT 6 O'CLOCK POSITION. LENGHT 15MM AND DEPTH 5MM THROUGH THE HINGE FITTING. CRACKED FITTING REMOVED & SENT TO WORKSHOP FOR FREEZSDR UIEA200600211Skin · crackedNOSE GEAR WHEEL WELL PRESSURE PAN CUT OUT AREA FOUND SKIN CRACKED AT STA 400 RT LOWER CORNER RBL 15. CRACKED PRESSURE PAN CUTOUT SKIN REPAIRED IAW BOEING MSG 1-215478617-2 DATED 02 AUG 06. REPAIR DOUBLERS USED 2 OFF 7075-T6, 0.080". CARRIED OUT EDDY CURRENTSDR UIEA200600137Rod · damagedAFTER T/O THE LEFT WING GEAR WOULD NOT RETRACT. R&R LT WING GEAR WHEEL WELL DOOR RADIUS ROD AS PER AMM 32-12-00. R&R FWD RADIUS ROD ASSY AS PER AMM 32-12-00. R&R FWD RADIUS ROD ASSY AS PER AMM 32-12-00. R&R FWD RADIUS ROD ASSY AS PER AMM 32-12-00. R&R SUPSDR UIEA200600080Skin · delaminatedLEFT WING UPPER LEADING EDGE PANEL AT NR 2 ENGINE PYLON DELAMINATED AT PREVIOUS REPAIR JUST I/B OF L/E GAP PANEL. REMOVED DAMAGE LEADING EDGE PANEL IAW B-747-200 SRM 51-30-02.SENT TO OUTSIDE SERVICE AIRCRAFT CONNECTION INC. REPAIRED PER SRM 51-40-08 PAGE 1, SDR UIEA200600012Fan Blade · bird strikeON WALKAROUND FOUND NR 3 ENGINE SUSTAINED BIRD STRIKE, FOUND FAN BLADE BENT. PERFORMED CHAPTER FIVE BIRD STRIKE INSPECTION, NO FINDINGS. REMOVED AND REPLACED FAN BLADE. BORESCOPED CORE ENGINE, NO FINDINGS. PERFORMED OPS RUNUPS WITH NO FINDINGS. RELEASED ASDR UIEA200500038Spar · corrodedDURING SCHEDULE INSPECTION, CORROSION WAS FOUND ON THE REAR SPAR ATTACHMENT HOLES OF NR 5 TRAILING EDGE FLAP TRACK. OVERSIZED THE AFFECTED ATTACHMENT HOLES. MAGNETIC PARTICLE INSPECTED THE REWORKED AREA TO ENSURE CRACK AND DEFECT FREE CONDITION. THE REPAIRESDR UIEA200500039Skin · delaminatedDURING SCHEDULE INSPECTION, DELAMINATION WAS FOUND ON THE OUTBOARD TRAILING EDGE FLAP AFT FLAP LOWER SKIN PANEL. PANELS EXCEEDED 25 PERCENT DAMAGE OF THE TOTAL AREA. TRIMMED OUT THE DELAMINATED SKIN REGIONS. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONSDR UIEA200500037Mount · crackedDURING SCHEDULED INSPECTION, NR 4 PYLON, BULKHEAD UPPER CHORD CRACKED AT STATION 270. STOP DRILLED THE CRACK PER 747 SRM 51-10-01. NDT INSPECTED THE REPAIR AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGES AND STOP DRILLED HOLES TO ENSURE CRACK REMSDR UIEA200500034Skin · dentedDURING INSPECTION, FOUND DENT (SKIN WRINKLE) NR 2 NACELLE STRUT INBOARD SKIN BETWEEN NACELLE STATION 286 TO 300.1. CONFIRMED THAT THE AFFECTED WAS FREE FROM DISCOLORATION. NDT CONDUCTIVITY MEASURED READING ACCOMPLISHED. HFEC INSPECTED AND WAS FOUND TO BE DASDR UIEA200500035Bulkhead · crackedDURING SCHEDULED INSPECTION, NR 1 PYLON, THE BULKHEAD UPPER LEFT SIDE FORWARD AND AFT CHORD ANGLES WERE FOUND CRACKED. TRIMMED AND STOP DRILLED THE CRACK PER 747 SRM 51-10-01 NDT INSPECTED THE REPAIRED AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGSDR UIEA200500036Bulkhead · crackedDURING SCHEDULED INSPECTION, NR 3 PYLON, THE BULKHEAD UPPER LEFT AND RIGHT SIDE FORWARD CHORD ANGLES WERE FOUND CRACKED. STOP DRILLED THE CRACK PER 747 SRM 51-10-01. NDT INSPECTED THE REPAIR AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGES AND STOSDR UIEA200500029Bulkhead · crackedDURING SCHEDULE MAINTENANCE, THE BULKHEAD UPPER LEFT AND RIGHT SIDE FORWARD CHORD ANGLES WERE FOUND CRACKED, NR 2 PYLON. STOPPED DRILLED THE CRACK END AND NDT INSPECTED TO ENSURE CRACK CONTAINMENT. INSTALLED ALUMINUM REPAIR ANGLES COMMON TO THE UPPER FORWARDSDR UIEA200500030Link · migratedDURING SCHEDULE MAINTENANCE, NR 4 T/E FLAP TRACK FAIL/SAFE LINK TOP END BEARING ON THE 'T' CHORD FOUND MIGRATED. THE LEFT FIXED TRAILING EDGE UPPER CHORD HOLE HAS ELONGATED DAMAGED. OVERSIZED HOUSING BORE TO A MAXIMUM OF .8930 INCH DIAMTER. NDT INSPECTED THSDR UIEA200500025Skin · crackedDURING INSPECTION, NR 16 KRUEGER FLAP, FOUND CRACK AT PANEL ATTACH FASTENER HOLE. TRIMMED OUT AFFECTED SPAR SEGMENT. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONDIION. INSTALLED REPAIR FILLER AND ALUMINUM REPAIR ANGLE WITH ADDITIONAL FASTENERS. REFINISDR UIEA200500027Spar · crackedDURING SCHEDULED MAINTENANCE, NR 3 PYLON INBOARD MIDSPAR CHORD WAS FOUND CRACKED ON THE VERTICAL FLANGE. THE AFFECTED SECTION OF CHORD WAS TRIMMED OUT. NDT INSPECTION WAS PERFORMED AT TRIMMED EDGES AND AT AL AFFECTED FASTENERS LOCATION TO ENDURE A CRACK AND SDR UIEA200500026Bulkhead · crackedDURING INSPECTION, .5 INCH CRACK FOUND ON RT WHEEL WELL SLOPING PRESSURE DECK AT STATION 1240, RBL 35. THE CRACK ORIGINATED FROM THE WATER LINE CONNECTOR HOLE AND EXTENDS UPWARDS. THE CRACKED SLOPING PRESSURE DECK WEB WAS TRIMMED OUT AND REPAIRED WITH DOUBLESDR UIEA200500023Frame · chafedD-CHECK AT SINGAPORE, DURING INSPECTION GOUGES WERE FOUND ON THE STATION 2460 BULKHEAD INNER T-CHORD TOP SURFACE AT LBL 30, AND WL 235. BLENDED OUT THE DAMAGED AREA AND INSTALLED A REPAIR STRAP OF .0710 INCH THICK CLAD 2040-T3 MATERIAL. (M)SDR UIEA200500024Fitting · elongatedDURING INSPECTION, REPORTED ELONGATED HOLES IN THE TEN LATCH FITTING OF THE MAIN DECK SIDE CARGO DOOR. THE TEN LATCH FITTING WERE REWORKED WITHIN ALLOWABLE REWORK LIMITS. (M)SDR UIEA200500019Link · gougedDURING D-CHECK, DEEP GOUGE FOUND ON THE EDGE OF THE INBOARD LINK ON THE NR 18 VARIABLE CAMBER FLAP. BLENDED OUT DAMAGE FROM SURFACE OF LINK. NDT INSPECTED TO ENSURE CRACK AND DEFECT CONDITION. SHOP PREENED PER SOPM 20-10-03, INTENSITY .006A2. REFINISHED LISDR UIEA200500016Skin · crackedDURING INSPECTION, NR 4 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NACELLE STATION 235 TO STATION 254. THE RIB INSTALLATION ATSDR UIEA200500015Skin · crackedDURING INSPECTION, NR 3 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NACELLE STATION 235 TO 254. THE RIB INSTALLATION AT NACELLESDR UIEA200500017Cap · chafedDURING SCHEDULED MAINTENANCE, CHAFING MARK WAS FOUND ON THE LEFT SIDE OF THE SKIN ASSEMBLY AT NACELLE STATION 270. AFFECTED FASTENERS WERE REMOVED AND FASTENER HOLES WERE HFEC INSPECTED TO ENSURE CRACK AND DAMAGE FREE CONDITION. THE CHAFING DAMAGE WAS REMOVESDR UIEA200500014Skin · crackedDURING INSPECTION, NR 2 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NS 235 TO STA 254. THE RIB INSTALLATION AT NACELLE STATION SDR UIEA200400106Door · crackedR-4 DOOR LOWER AFT CORNER HAS 2 CRACKS, ONE CRACK IS 4 INCHES AND THE OTHER CRACK IS 3 INCHES, STA 1715, W/L 199.8. CAUSE OF DAMAGE UNKNOWN. CRACKS FOUND DURING VISUAL INSPECTION. INSTALLED DOUBLER REPAIR IAW SRM.SDR UIEA200300043Transmitter · looseTLV - ACCEPTANCE FLIGHT FROM C-CHECK AIR TURNBACK, AFTER TAKEOFF DURING FLAP RETRACTION INBOARD FLAPS STOPPED AT 19 DEGREES INDICATES FLAP ASYMMETRY. AIRCRAFT RETURNED TO TLV. NO FUEL DUMPED. FOUND RIGHT OUTBOARD FLAP TRANSMITTER LOOSE. TIGHTENED TRANSMITTSDR UIEA200200049Sensor · malfunctionedNOSE GEAR DOOR LIGHT (RED) AND GEAR LIGHT REMAINED ON AFTER GEAR LEVER WAS RAISED. ATTEMPTED TO CORRECT PER FHB PROCEDURES TO NO AVAIL. AIR TURN BACK REQUIRED. JETTISONED APPROXIMATELY 70,000 KGS OF FUEL. LIFTED THE AIRCRAFT AND TROUBLESHOT PER MM. ALL GESDR UIEA200200035Control Unit · failedON CLIMBOUT, NR 3 AND NR 4 BUS TIES OPENED. SPLIT BUS SYSTEM OPEN. NR 3 GENERATOR WAS DISCONNECTED. NR 4 GENERATOR CHECKED GOOD VOLTS/ FREQ. NR 3 BUS LOST POWER AND COULD NOT REPOWER. DUMPED 17.0 KGS OF FUEL PRIOR TO LANDING. REMOVED AND REPLACED RIGHT SDR UIE2002F00007Panel · separatedTURN BACK DUE TO ENGINE NR 1 AND ENGINE NR 4 GAP PANELS SEPARATED FROM AIRCRAFT ON TAKE OFF ROLL. INSTALLED NR 1 ENGINE GAP PANEL ISW SRM. REPAIRED NR 4 GAP PANEL PER SRM. REINSTALLED GAP PANEL ON NR 4 ENGINE IAW MM. CHAPTER 5 INSPECTION NOT REQUIRED. ACCSDR UIEA02009Structure · crackedDURING CURRENT C-CHECK AT KLM/AMS WHILE PERFORMING SB 747-53A2450, IAW AD 2001-16-02 AND HFEC OPEN HOLE INSPECTION REVEALED CRACKS EMINATING FROM THE AFT STRAP ROW AT BS 2231, STRINGER 25L. CUT OUT BLENDED CRACK IN STRAP. HFEC INSPECTED ROUTED AREA AND ALL OSDR UIEA02008Structure · crackedDURING CURRENT C-CHECK AT KLM/AMS WHILE PERFORMING SB 747-53A2450, IAW AD 2001-16-02 AND HFEC OPEN HOLE INSPECTION REVEALED CRACKS EMINATING FROM THE AFT STRAP ROW AT BS 2231, STRINGER 24R AND 25R. CUT OUT BLENDED CRACKS IN STRAP. HFEC INSPECTED ROUTED AREASSDR UIEA02007Spar · corrodedDURING CURRENT C-CHECK AT KLM/AMS, FOUND LEVEL 1 CORROSION ON THE L/W VERTICAL FLANGE OF THE LOWER FRONT SPAR CHORD BETWEEN ILES 630.72 AND 638 (INBOARD OF NR 2 PYLON). TAPER LOCK FASTENERS IN THE AFFECTED AREA WERE REMOVED. CORROSION BLENDED AND FASTENER HOSDR UIEA01061Door Actuator · failedNR 2 AIR CONDITIONING PACK OVERHEATED WITH A DOOR OUT OF SEQUENCE INDICATION. CAUSED FUMES IN AIR CONDITIONING SYSTEM. MANUALLY POSITIONED NR 2 PACK INLET DOOR CLOSED. REPLACED INLET DOOR ACTUATOR. (M)SDR UIEA01039Display · failedDURING CRUISE FLIGHT, RIGHT ENGINE INSTRUMENT DISPLAY FAILED, NR 2 EGT SPIKED UP AND FLIGHT CREW REPORTED SMOKE IN COCKPIT AND ELECTRICAL BURNING ODOR. SMOKE CLEARED AND FLIGHT CONTINUED TO DESTINATION. REMOVED AND REPLACED RIGHT ENGINE INSTRUMENT DISPLAY SCSDR UIEA00024Frame · crackedFOUND CRACK FROM FRAME WEB AT STATION 1265 RIGHT WL 199 CRITICAL HOLE FASTENER. STOP DRILLED CRACK, INSTALLED A STEEL FRAME WEB DOUBLER, INTERCOSTAL DOUBLER AND ATTACH ANGLE PER AMOC TO PARAGRAPH A AND C OF AD2000-02-01. (M)SDR UIEA00023Frame · crackedFOUND AFTER HFEC INSPECTION, CRACK FROM FRAME WEB AT STATION 1265 LEFT WL 199 HOLE A. REMOVED INTERIM REPAIR. STOP DRILLED CRACK, INSTALLED A FRAME WEB DOUBLER, INTERCOSTAL DOUBLER AND ATTACH ANGLE PER AMOC TO PARAGRAPH A AND C OF AD2000-02-01. (M)
Back to N527MC, cancelled Sep 19, 2008