# Service difficulty reports: N527MC, cancelled Sep 19, 2008

A list on [N527MC, cancelled Sep 19, 2008](https://openairdocs.org/deregistered/N527MC-2008-09-19.md).

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

Page 1 of 2 · 54 reports

- [SDR UIEA200800027](https://openairdocs.org/sdr/UIEA200800027.md): Bulkhead · damaged · Feb 2, 2008 · N527MC · Boeing 7472D7B · Fuselage Main, Bulkhead
  > PRELIMINARY 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 B
- [SDR UIEA200700471](https://openairdocs.org/sdr/UIEA200700471.md): Skin · delaminated · Nov 15, 2007 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > LEFT 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 UIEA200700358](https://openairdocs.org/sdr/UIEA200700358.md): Drain Valve · corroded · Aug 25, 2007 · N527MC · Boeing 7472D7B · Waste Disposal System
  > DURING 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 SEC
- [SDR UIEA200700357](https://openairdocs.org/sdr/UIEA200700357.md): Flap Track · cracked · Aug 23, 2007 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > NR 1 MOVABLE FLAP TRACK FAIRING HAS SMALL CRACK LOWER SURFACE. REPAIRED PER SRM 51-40-09 AND 51-40-12.
- [SDR UIEA200700356](https://openairdocs.org/sdr/UIEA200700356.md): Skin · damaged · Aug 22, 2007 · N527MC · Boeing 7472D7B · Leading Edge Devices
  > LEFT 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. REINS
- [SDR UIEA200700355](https://openairdocs.org/sdr/UIEA200700355.md): Skin · cracked · Aug 22, 2007 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > LEFT WING INBOARD FOREFLAP HAS 2" CRACK ON LEADING EDGE 12" FROM OUTBOARD EDGE. REPAIRED PER SRM 51-40-12 AND 51-40-08.
- [SDR UIEA200700317](https://openairdocs.org/sdr/UIEA200700317.md): Structure · damaged · Aug 14, 2007 · N527MC · Boeing 7472D7B · Leading Edge Devices
  > ON 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 UIEA200700293](https://openairdocs.org/sdr/UIEA200700293.md): Engine · failed · Jul 21, 2007 · N527MC · Boeing 7472D7B · Engine (Turbine/Turboprop)
  > NR 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 UIEA200700204](https://openairdocs.org/sdr/UIEA200700204.md): Inu · inoperative · Apr 15, 2007 · N527MC · Boeing 7472D7B · Inertial Guidance System
  > INFLIGHT, 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 UIEA200700146](https://openairdocs.org/sdr/UIEA200700146.md): Skin · corroded · Apr 2, 2007 · N527MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > FUSELAGE 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 VE
- [SDR UIEA200700038](https://openairdocs.org/sdr/UIEA200700038.md): Start Valve · faulty · Jan 27, 2007 · N527MC · Boeing 7472D7B · Engine Starter
  > NR 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 UIEA200700012](https://openairdocs.org/sdr/UIEA200700012.md): Panel · dented · Jan 22, 2007 · N527MC · Boeing 7472D7B · Wing, Plate/Skin
  > RT 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 UIEA200700011](https://openairdocs.org/sdr/UIEA200700011.md): Skin · cracked · Jan 22, 2007 · N527MC · Boeing 7472D7B · Wing, Plate/Skin
  > LT 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 475
- [SDR UIEA200600218](https://openairdocs.org/sdr/UIEA200600218.md): Skin · cracked · Aug 15, 2006 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > PYLON 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 UIEA200600219](https://openairdocs.org/sdr/UIEA200600219.md): Skin · dented · Aug 14, 2006 · N527MC · Boeing 7472D7B · Wing, Plate/Skin
  > RIGHT 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 FILL
- [SDR UIEA200600217](https://openairdocs.org/sdr/UIEA200600217.md): Hinge Fitting · cracked · Aug 13, 2006 · N527MC · Boeing 7472D7B · Horizontal Stabilizer Structure
  > HORIZONTAL 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 FREEZ
- [SDR UIEA200600211](https://openairdocs.org/sdr/UIEA200600211.md): Skin · cracked · Aug 7, 2006 · N527MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > NOSE 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 CURRENT
- [SDR UIEA200600137](https://openairdocs.org/sdr/UIEA200600137.md): Rod · damaged · Jun 16, 2006 · N527MC · Boeing 7472D7B · Landing Gear Retraction/Extension System
  > AFTER 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 SUP
- [SDR UIEA200600080](https://openairdocs.org/sdr/UIEA200600080.md): Skin · delaminated · Apr 10, 2006 · N527MC · Boeing 7472D7B · Wing, Plate/Skin
  > LEFT 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 UIEA200600012](https://openairdocs.org/sdr/UIEA200600012.md): Fan Blade · bird strike · Feb 22, 2006 · N527MC · Boeing 7472D7B · Turbine Engine Air Inlet Section
  > ON 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 A
- [SDR UIEA200500038](https://openairdocs.org/sdr/UIEA200500038.md): Spar · corroded · Mar 24, 2005 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > DURING 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 REPAIRE
- [SDR UIEA200500039](https://openairdocs.org/sdr/UIEA200500039.md): Skin · delaminated · Mar 24, 2005 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > DURING 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 CON
- [SDR UIEA200500037](https://openairdocs.org/sdr/UIEA200500037.md): Mount · cracked · Mar 23, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Bulkhead/Firewall
  > DURING 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 REM
- [SDR UIEA200500034](https://openairdocs.org/sdr/UIEA200500034.md): Skin · dented · Mar 23, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > DURING 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 DA
- [SDR UIEA200500035](https://openairdocs.org/sdr/UIEA200500035.md): Bulkhead · cracked · Mar 23, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Bulkhead/Firewall
  > DURING 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 EDG
- [SDR UIEA200500036](https://openairdocs.org/sdr/UIEA200500036.md): Bulkhead · cracked · Mar 23, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Bulkhead/Firewall
  > DURING 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 STO
- [SDR UIEA200500029](https://openairdocs.org/sdr/UIEA200500029.md): Bulkhead · cracked · Mar 21, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Bulkhead/Firewall
  > DURING 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 FORWARD
- [SDR UIEA200500030](https://openairdocs.org/sdr/UIEA200500030.md): Link · migrated · Mar 21, 2005 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > DURING 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 TH
- [SDR UIEA200500025](https://openairdocs.org/sdr/UIEA200500025.md): Skin · cracked · Mar 18, 2005 · N527MC · Boeing 7472D7B · Leading Edge Devices
  > DURING 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. REFINI
- [SDR UIEA200500027](https://openairdocs.org/sdr/UIEA200500027.md): Spar · cracked · Mar 18, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Frame/Spar/Rib
  > DURING 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 UIEA200500026](https://openairdocs.org/sdr/UIEA200500026.md): Bulkhead · cracked · Mar 18, 2005 · N527MC · Boeing 7472D7B · Fuselage Main, Bulkhead
  > DURING 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 DOUBLE
- [SDR UIEA200500023](https://openairdocs.org/sdr/UIEA200500023.md): Frame · chafed · Mar 17, 2005 · N527MC · Boeing 7472D7B · Fuselage Main, Frame
  > D-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 UIEA200500024](https://openairdocs.org/sdr/UIEA200500024.md): Fitting · elongated · Mar 15, 2005 · N527MC · Boeing 7472D7B · Cargo/Baggage Doors
  > DURING 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 UIEA200500019](https://openairdocs.org/sdr/UIEA200500019.md): Link · gouged · Mar 14, 2005 · N527MC · Boeing 7472D7B · Trailing Edge Flaps
  > DURING 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 LI
- [SDR UIEA200500016](https://openairdocs.org/sdr/UIEA200500016.md): Skin · cracked · Mar 8, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > DURING 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 AT
- [SDR UIEA200500015](https://openairdocs.org/sdr/UIEA200500015.md): Skin · cracked · Mar 8, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > DURING 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 NACELLE
- [SDR UIEA200500017](https://openairdocs.org/sdr/UIEA200500017.md): Cap · chafed · Mar 8, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon Miscellaneous Structure
  > DURING 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 REMOVE
- [SDR UIEA200500014](https://openairdocs.org/sdr/UIEA200500014.md): Skin · cracked · Mar 8, 2005 · N527MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > DURING 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 UIEA200400106](https://openairdocs.org/sdr/UIEA200400106.md): Door · cracked · Jun 1, 2004 · N527MC · Boeing 7472D7B · Passenger/Crew Doors
  > R-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 UIEA200300043](https://openairdocs.org/sdr/UIEA200300043.md): Transmitter · loose · Aug 2, 2003 · N527MC · Boeing 7472D7B · Trailing Flap Position Indicating System
  > TLV - 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 TRANSMITT
- [SDR UIEA200200049](https://openairdocs.org/sdr/UIEA200200049.md): Sensor · malfunctioned · Sep 29, 2002 · N527MC · Boeing 7472D7B · Landing Gear Position and Warning
  > NOSE 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 GE
- [SDR UIEA200200035](https://openairdocs.org/sdr/UIEA200200035.md): Control Unit · failed · Aug 29, 2002 · N527MC · Boeing 7472D7B · DC Generating System
  > ON 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 UIE2002F00007](https://openairdocs.org/sdr/UIE2002F00007.md): Panel · separated · May 14, 2002 · N527MC · Boeing 7472D7B · Wing, Plate/Skin
  > TURN 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. ACC
- [SDR UIEA02009](https://openairdocs.org/sdr/UIEA02009.md): Structure · cracked · Feb 11, 2002 · N527MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING 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 O
- [SDR UIEA02008](https://openairdocs.org/sdr/UIEA02008.md): Structure · cracked · Feb 11, 2002 · N527MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING 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 AREAS
- [SDR UIEA02007](https://openairdocs.org/sdr/UIEA02007.md): Spar · corroded · Feb 11, 2002 · N527MC · Boeing 7472D7B · Wing Spar
  > DURING 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 HO
- [SDR UIEA01061](https://openairdocs.org/sdr/UIEA01061.md): Door Actuator · failed · Jun 11, 2001 · N527MC · Boeing 7472D7B · Air Conditioning System
  > NR 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 UIEA01039](https://openairdocs.org/sdr/UIEA01039.md): Display · failed · Apr 13, 2001 · N527MC · Boeing 7472D7B · Engine Indicating System
  > DURING 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 SC
- [SDR UIEA00024](https://openairdocs.org/sdr/UIEA00024.md): Frame · cracked · May 2, 2000 · N527MC · Boeing 7472D7B · Fuselage Main, Frame
  > FOUND 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 UIEA00023](https://openairdocs.org/sdr/UIEA00023.md): Frame · cracked · May 2, 2000 · N527MC · Boeing 7472D7B · Fuselage Main, Frame
  > FOUND 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)

Next page: https://openairdocs.org/deregistered/N527MC-2008-09-19/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/deregistered/N527MC-2008-09-19/reports

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