# Service difficulty reports: N540MC, cancelled Sep 30, 2011

A list on [N540MC, cancelled Sep 30, 2011](https://openairdocs.org/deregistered/N540MC-2011-09-30.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 3 · 127 reports

- [SDR UIEA2011050500255](https://openairdocs.org/sdr/UIEA2011050500255.md): Skin · damaged · May 5, 2011 · N540MC · Boeing 747243B · Leading Edge Devices
  > DURING WALK AROUND INSP BEING PERFORMED, MX FOUND THE LT WS 594.0, 16" AFT OF L/E - L/E KRUEGER FLAP - LOWER SURFACE EXTERNAL SKIN WITH DELAMINATION DAMAGE (AREA:MEASURES APPROX 12 IN DIA) (REF FIGURE 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR
- [SDR UIEA2011041500248](https://openairdocs.org/sdr/UIEA2011041500248.md): Blowout Panel · open · Apr 15, 2011 · N540MC · Boeing 747243B · Pneumatic Distribution System
  > AIR TURN BACK- CLIMBING THROUGH 4000 FT, NR 4 ENGINE FIRE INDICATION WITH BELL AND MASTER FIRE WARNING; LIGHT ON. NR 4 ENGINE NACELLE TEMP A AND B AT 9.5. ENGINE FIRE CHECKLIST PERFORMED. NR 4 ENGINE SHUTDOWN. ON ARRIVAL, FOUND NR 4 ENGINE NR 4 "C" DUCT BLOW
- [SDR UIEA2010122900248](https://openairdocs.org/sdr/UIEA2010122900248.md): Latch · broken · Dec 29, 2010 · N540MC · Boeing 747243B · Engine Thrust Reverser
  > DURING MX WALKAROUND OF ACFT, REVEALED NR 1 ENGINE THRUST REVERSER LOWER AFT ACCESS DOOR AND BLOWOUT DOOR WERE FOUND OPENED. UPON FURTHER INSP, MX FOUND THE AFT TENSION LATCH BROKEN. (DISPOSITION IS TO ACCOMPLISH A TIME LIMITED REPAIR BY INSPECTING THE 2 OTH
- [SDR UIEA201000232](https://openairdocs.org/sdr/UIEA201000232.md): Doubler · cracked · Oct 17, 2010 · N540MC · Boeing 747243B · Fuselage Main, Plate/Skin
  > DURING MX WALKAROUND, MX FOUND THE MAIN DECK - MDSCD AREA - BS1910 ROLL OUT GUIDE - DOUBLER CRACKED (REF FIG 1). THE DAMAGE EXCEEDS THE ALLOWABLE LIMITS IAW AMM 25-58-00. DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRU
- [SDR UIEA2010092700166](https://openairdocs.org/sdr/UIEA2010092700166.md): Sleeve · cracked · Sep 27, 2010 · N540MC · Boeing 747243B · Engine Collector/Tailpipe/Nozzle
  > DURING MX WALK AROUND, MX FOUND 2 EA CRACK ON THE EXHAUST NOZZLE OUTER SLEEVE, NR1 STARTING AT APPROX THE 7 O'CLOCK POSITION. THE CIRCUMFERENTIAL CRACK IS APPROX 3.0 IN LONG, THE NR2 CRACK IS LOCATED AT INBD SIDE AND AFT OF EXHAUST CONE AREA MEASURING 0.750 I
- [SDR UIEA2010091100155](https://openairdocs.org/sdr/UIEA2010091100155.md): Tire · failed · Sep 11, 2010 · N540MC · Boeing 747243B · Tire Tube
  > MLG WHEELS NR 2, 4, 6, 8 HAD THERMAL DISCHARGE AT GATE. (REPLACED NR 2, 4, 6, 8 WHEELS. SPIN AND LEAK CHECK OK. ANTI SKID TEST AND CHAPTER 5-51-26 INSP ACCOMPLISHED AND ALL NORMAL.)
- [SDR UIEA2010071700115](https://openairdocs.org/sdr/UIEA2010071700115.md): Metering Valve · inoperative · Jul 17, 2010 · N540MC · Boeing 747243B · Landing Gear Retraction/Extension System
  > WITH TAKEOFF POWER SET, ACFT PULLED RT. TAKEOFF ABANDONED AT 40 KNOTS, ENGINE POWER EVEN. (INSPECTED CABLE RUNS AND PULLEYS, CHECKED CABLE TENSIONS, NO DEFECTS NOTED. PERFORMED RIG CHECK, ALL OK. REPLACED METERING VALVE, ALL OPS NORMAL)
- [SDR UIEA201000193](https://openairdocs.org/sdr/UIEA201000193.md): Bushing · missing · Jul 1, 2010 · N540MC · Boeing 747243B · Landing Gear Steering System
  > ON TAKEOFF ROLL, ACFT VEERED RT UNCOMMANDED. FULL LT RUDDER WAS APPLIED BUT HAD NO APPARENT EFFECT AS AIRSPEED INCREASED RATE OF TURN INCREASED. RTO INITIATED TO PREVENT RUNWAY DEPARTURE. NOTE: ALL ENGINE N1 AND N2 WERE OBSERVED TO BE EVEN. ADJ/TEST IAW MM 32
- [SDR UIEA2010060800027](https://openairdocs.org/sdr/UIEA2010060800027.md): Skin · delaminated · Jun 8, 2010 · N540MC · Boeing 747243B · Wing, Plate/Skin
  > DURING WALK AROUND INSP BEING PERFORMED, MX FOUND THE- LEADING EDGE PANEL - LOWER SURFACE EXTERNAL SKIN WITH DELAMINATION DAMAGE (AREA: MEASURES 33.0 IN. X 36 IN.) (REF FIGURE 1).(EO4757A497 DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN
- [SDR UIEA201000079](https://openairdocs.org/sdr/UIEA201000079.md): Frame · cracked · Mar 26, 2010 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > DURING C-CHECK, A CRACK WAS FOUND IN THE 65B07373-4 1540, LBL 15-17 LOWER LOBE FRAME INNER CHORD. THE DAMAGE WAS TRIMMED OUT AND NEW SECTION WAS SPLICED IAW NRC 727 AND SRM 51-40-04, FIG 2. THE 65B07373-4 CHORD IS MADE FROM BAC1505-100166 EXTRUSION IN 7075-T6
- [SDR UIEA201000078](https://openairdocs.org/sdr/UIEA201000078.md): Skin · damaged · Mar 26, 2010 · N540MC · Boeing 747243F · Fuselage Main, Plate/Skin
  > DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B04144-3 SKIN AT BS 1790, S-38R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 732 AND SRM 53-30-03, FIG 1. THE 65B04144-3 SKIN IS MADE FROM 0.100 INCH THICK 2024-T3 CLAD ALUMINUM SHEET IAW QQ-A-250/5. THE REPAIR CO
- [SDR UIEA201000077](https://openairdocs.org/sdr/UIEA201000077.md): Beam · damaged · Mar 26, 2010 · N540MC · Boeing 747243F · Fuselage Main, Structure
  > DURING C-CHECK, DAMAGE WAS FOUND IN THE 65B04721-2 AFT LOWER CARGO DOOR LOWER BEAM WEB BETWEEN BS 1840 TO 1852. DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 786 AND SRM 51-40-03, FIG 1. THE 65B04721-2 WEB IS MADE FROM 0.125 INCH THICK 7075-0 SHEET IAW QQ-A-25
- [SDR UIEA201000073](https://openairdocs.org/sdr/UIEA201000073.md): Frame · cracked · Mar 26, 2010 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > DURING C-CHECK, A CRACK WAS FOUND IN THE 65B06871-2 BS 560, RBL 35 LOWER LOBE FRAME INNER CHORD. THE DAMAGE WAS TRIMMED OUT AND NEW SECTION WAS SPLICED IAW NRC 305 AND SRM 51-40-04, FIG 2. 65B06871-2 CHORD IS MADE FROM BAC1505-100246 EXTRUSION IN 7075-0 ALUMI
- [SDR UIEA201000072](https://openairdocs.org/sdr/UIEA201000072.md): Skin · cracked · Mar 26, 2010 · N540MC · Boeing 747243F · Nacelle/Pylon, Plate/Skin
  > DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94052-1, NR3 PYLON RT SKIN ASSY AT THE NAC STA 248 PRECOOLER EXHAUST. THE CRACK WAS REPAIRED BY TRIMMING OUT THE DAMAGE AND RESTORING THE SURFACE FINISH IAW RFTA 00664-0006, REV A AND REA MF00664R0006, REV A (FIG 1
- [SDR UIEA201000071](https://openairdocs.org/sdr/UIEA201000071.md): Skin · cracked · Mar 26, 2010 · N540MC · Boeing 747243B · Nacelle/Pylon, Plate/Skin
  > DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94052-1 NR 2 PYLON RT SKIN ASSY AT THE NAC STA 248 PRECOOLER EXHAUST. CRACK WAS REPAIRED BY TRIMMING OUT THE DAMAGE AND RESTORING THE SURFACE FINISH IAW RFTA 00664-0005, REV A AND REA MF00664R0005, REV A (FIG 1 & 2
- [SDR UIEA201000076](https://openairdocs.org/sdr/UIEA201000076.md): Shear Tie · cracked · Mar 25, 2010 · N540MC · Boeing 747243B · Fuselage Internal Mounting Structure
  > DURING C-CHECK, CORROSION AND CRACKING WAS FOUND IN THE 65B04175-1 BS 780 FRAME SHEAR TIE BETWEEN S-46L AND -47R. THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 699 AND SRM 53-10-04, FIG 4. THE 65B04175-1 FRAME SHEAR TIE IS MADE FROM 0.056 INCH THICK 7075-0
- [SDR UIEA201000070](https://openairdocs.org/sdr/UIEA201000070.md): Stringer · cracked · Mar 25, 2010 · N540MC · Boeing 747243B · Fuselage Main, Longeron/Stringer
  > DURING C-CHECK, CORROSION AND CRACKING WAS FOUND IN THE 65B04161-17, STR 49L BETWEEN BS 2180 AND 2200. DAMAGE WAS TRIMMED OUT AND A NEW STR SECTION WAS INSTALLED IAW REA MF00664R0004. THE 65B04161-17 STRINGER IS MADE FROM BAC1498-144 EXTRUSION IN 7075-0 SHEE
- [SDR UIEA201000069](https://openairdocs.org/sdr/UIEA201000069.md): Bulkhead · cracked · Mar 25, 2010 · N540MC · Boeing 747243F · Nacelle/Pylon, Bulkhead/Firewall
  > DURING C-CHECK, CRACKING WAS FOUND IN THE 65B94107-19 NAC STA 270 BULKHEAD UPPER WEB ASSY ON THE NR1 PYLON. THE WEB ASSY WAS REPLACED IAW DWG 65B94107 WITH MINOR DEVIATIONS IAW REA 00664R0002. THIS EO DOCUMENTS THE REPLACEMENT OF THE WEB IAW DWG 65B94107 AND
- [SDR UIEA201000080](https://openairdocs.org/sdr/UIEA201000080.md): Cargo Track · corroded · Mar 20, 2010 · N540MC · Boeing 747243B · Fuselage, Seat/Cargo Attach Fittings
  > MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO AFT CARGO COMPARTMENT - BS1480 - BS1500, RBL45 SEAT TRACK WITH CORROSION (REF FIG 1) IAW SRM 53-11-25, FIG 7 (ITEM 2) CARGO TRACK IS MADE OF BAC1520-1682 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFORMED
- [SDR UIEA201000081](https://openairdocs.org/sdr/UIEA201000081.md): Seat Track · cracked · Mar 20, 2010 · N540MC · Boeing 747243B · Fuselage, Seat/Cargo Attach Fittings
  > THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE MAIN DECK - BS1980, LBL98 - SEAT TRACK WITH A CRACK (REF FIG 1) IAW SRM 53-10-23, FIG 4C (ITEM 1) CARGO TRACK IS MADE OF BAC1520-1566 (7178-T6511) EXTRUSION. PERMANENT REPAIR WAS PERFOR
- [SDR UIEA201000075](https://openairdocs.org/sdr/UIEA201000075.md): Cargo Track · damaged · Mar 20, 2010 · N540MC · Boeing 747243B · Fuselage, Seat/Cargo Attach Fittings
  > THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE AFT CARGO COMPARTMENT - BS1900 - BS1920, LBL24.75 CARGO TRACK WITH A CRACK (REF FIG 1) IAW SRM 53-10-23, FIG 5 (ITEM 3) THE CARGO TRACK IS MADE OF BAC1520-1682 (7178-T6511) EXTRUSION. P
- [SDR UIEA201000074](https://openairdocs.org/sdr/UIEA201000074.md): Cargo Track · damaged · Mar 20, 2010 · N540MC · Boeing 747243B · Fuselage, Seat/Cargo Attach Fittings
  > THIS EO DOCUMENTS A MAJOR REPAIR. DURING C-CHECK, DAMAGE WAS FOUND TO THE FWD CARGO COMPARTMENT - BS560 - BS580, RBL45.5 CARGO TRACK WITH A CRACK (REF FIG 1). IAW SRM 53-10-21, FIG 5 (ITEM 3) THE CARGO TRACK IS MADE OF BAC1520-1687 (7178-T6511) EXTRUSION. PER
- [SDR UIEA201000068](https://openairdocs.org/sdr/UIEA201000068.md): Skin · damaged · Feb 10, 2010 · N540MC · Boeing 747243B · Landing Gear Doors
  > DOORS - RT AFT MLG BODY DOOR SKIN DAMAGE - REPAIR. APPLIED A CHEMICAL CONVERSION COATING TO THE BARE SURFACES OF THE SKIN. REFER TO SRM 51-10-02. APPLY ONE LAYER OF BMS 10-79, TYPE II PRIMER TO THE BARE SURFACES OF THE SKIN. REF TO SOPM 20-44-04. INSTALLED T
- [SDR UIEA201000184](https://openairdocs.org/sdr/UIEA201000184.md): Skin · damaged · Oct 17, 2009 · N540MC · Boeing 747243B · Fuselage Main, Plate/Skin
  > DURING JACKING OF DATUM AIRPLANE, MX DAMAGED THE FUSELAGE SKIN SECTION 48 - BS2594.5 AT S-26R (ABOVE THE TAIL JACK PAD). MEASURING 2.5 IN. D AND 0.437 IN DEPTH. THE DAMAGE IS LOCATED APPROX 3.5 IN FWD OF BS 2598 BUTT JOINT. "INTERIM REPAIR PERFORMED AS DESCRIB
- [SDR UIEA200900060](https://openairdocs.org/sdr/UIEA200900060.md): Relay · failed · Oct 10, 2009 · N540MC · Boeing 747243B · Landing Gear Position and Warning
  > AFTER TAKEOFF FROUND SAFETY RELAY LIGHT ILLUMINATED. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. PERFORMED ACTION PLAN SENT AND CHECKED OK PER AMM 32-09-02. REPLACED DEFECTIVE R226 RELAY REPLACED PRIMARY SQUAT
- [SDR UIEA200900059](https://openairdocs.org/sdr/UIEA200900059.md): Connector · dirty · Oct 9, 2009 · N540MC · Boeing 747243B · Navigation System Wiring
  > AIR TURN BACK AFTER TAKEOFF GROUND SAFETY RELAY LIGHT ON. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. AUTO THROTTLES/FRATTS DISENGAGED AUTO PRESSURIZATION INOP. WIRING CHECKED PER WDM 32-09-00. FOUND R952 ON
- [SDR UIEA200900058](https://openairdocs.org/sdr/UIEA200900058.md): Relay · misinstalled · Oct 9, 2009 · N540MC · Boeing 747243B · ATC Transponder System
  > AIR TURN BACK. ATC TRANSPONDER INOP. GROUND SAFETY RELAY LIGHT ON IN FLIGHT COULD NOT PRESSURIZE PAST 1.8 PSID. LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. RESET C/B BOTH TRANSPONDERS RERACKED, GROUND OPS CHECKED OK. SWAPPED RELAY BETWEEN R952 AND K3. FOU
- [SDR UIEA200900037](https://openairdocs.org/sdr/UIEA200900037.md): Skin Panel · corroded · Jul 9, 2009 · N540MC · Boeing 747243B · Trailing Edge Flaps
  > RT WING INBOARD AFT FLAP UPPER EXTERNAL SURFACE PANEL HAS EVIDENCE OF CORROSION AT WBL 259.30 AND 12 INCHES FROM TRAILING EDGE. CUT OUT AREA OF CORROSION AND PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 57-50-02 FIG 5, SHEET 4 AND 10 AND SRM 51-40-06. A
- [SDR UIEA200900019](https://openairdocs.org/sdr/UIEA200900019.md): Brace · chafed · Feb 27, 2009 · N540MC · Boeing 747243B · Nacelle/Pylon Miscellaneous Structure
  > PYLON NR 1 DIAGONAL BRACE IS CHAFED ON OTBD SIDE 11 O'CLOCK POSITION, ZONE 5, 29.5 INCHES FROM FORWARD END. CHAFE IS 2.0 INCH LONG BY 0.125 INCH WIDE. INTERIM REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 54-41-01, FIG 3 SHEETS 1 THRU 4. REFERENCE ATLAS AIR EO
- [SDR UIEA200900018](https://openairdocs.org/sdr/UIEA200900018.md): Panel · delaminated · Feb 27, 2009 · N540MC · Boeing 747243B · Wing, Plate/Skin
  > LT WING UPPER SURFACE L/E FIXED PANEL AT ILES 664.97 HAS AN AREA OF 6.0 BY 18.0 INCHES OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 2 AND 5. PREPREG 250* F CURE PER SRM 51-40-12. REFERENCE ATLAS AIR EO 4757A477.
- [SDR UIEA200800349](https://openairdocs.org/sdr/UIEA200800349.md): Amplifier · failed · Dec 15, 2008 · N540MC · Boeing 747243B · Fire Detection
  > HIGH SPEED REJECTED TAKEOFF FOR CARGO FIRE INDICATION, NR 1 MAIN DECK WARNING ON TAKEOFF ROLL. REJECTED SPEED 146KTS. PERFORMED HIGH ENERGY STOP INSPECTION PER 5-31-10, ALL CHECKED OKAY. REMOVED AND REPLACED NR 1 SMOKE DETECTOR AMPLIFIER, ALL OPS CHECKED OK
- [SDR UIEA200800334](https://openairdocs.org/sdr/UIEA200800334.md): Bolt · loose · Oct 14, 2008 · N540MC · Boeing 747243B · Emergency Exits
  > AIR TURNBACK AFTER TAKEOFF LOUD NOISE FROM OVERHEAD HATCH. CARRIED OUT HATCH SEAL CHECK AND DOOR CUTOUT CHECK FOR ABNORMALITIES ALL OKAY. FOUND HINGE BOLTS LOOSE. TIGHTENED SAME PER STANDARD PRACTICES. PRESSURIZED AIRCRAFT AND LEAK CHECKED, NO LEAKS NOTED.
- [SDR UIEA200800333](https://openairdocs.org/sdr/UIEA200800333.md): Element · false activation · Oct 11, 2008 · N540MC · Boeing 747243B · Fire Detection
  > DURING CLIMBOUT AT 17000 FEET NR 2 ENGINE FIRE WARNING BELL AND LIGHT CAME ON. ACCOMPLISHED CHECKLIST, BOTH FIRE BOTTLES WERE DISCHARGED, HYD PUMP SUPPLY OFF FOR 1 HOUR AND 30 MINUTES NR 2 FIRE WARNING LIGHT AND NACELLE TEMP STAYED AT 7.9 AND 8.9 AFTER BLOCK
- [SDR UIEA200800268](https://openairdocs.org/sdr/UIEA200800268.md): Bleed Valve · leaking · Jul 18, 2008 · N540MC · Boeing 747243B · Compressor Bleed Valve
  > LT WING LEADING EDGE OVERHEAT LIGHT ILLUMINATED. LIGHT DID NOT GO OUT UNTIL THROTTLE WAS RETARDED. FOUND PYLON VALVE LEAKING. REPLACED VALVE, OPS CHECKED OK. (A)
- [SDR AIEA200800259](https://openairdocs.org/sdr/AIEA200800259.md): Frame · cracked · Jul 7, 2008 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > DURING C-CHECK FOUND FRAME CRACKED AT STATION 320 STRINGER 25R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)
- [SDR AIEA200800258](https://openairdocs.org/sdr/AIEA200800258.md): Frame · cracked · Jul 7, 2008 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > DURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26L. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)
- [SDR AIEA200800257](https://openairdocs.org/sdr/AIEA200800257.md): Frame · cracked · Jul 7, 2008 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > DURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)
- [SDR UIE2008F00023](https://openairdocs.org/sdr/UIE2008F00023.md): Skin · cracked · Jul 7, 2008 · N540MC · Boeing 747243B · Engine Collector/Tailpipe/Nozzle
  > CARRY OUT NR 4 PYLON EXHAUST SKIN CRACK CONDITIONAL CHECK REF EO NR 4754A250. REPAIRED CRACK IAW MFG MESSAGE 1-299984882-19. (K)
- [SDR UIE2008F00022](https://openairdocs.org/sdr/UIE2008F00022.md): Stringer · cracked · Jul 7, 2008 · N540MC · Boeing 747243B · Fuselage Main, Longeron/Stringer
  > STA 396, STRINGER 25 L, FATIGUE CRACKED. REPLACED STRINGER IAW DWG 65B11089. (K)
- [SDR UIE2008F00024](https://openairdocs.org/sdr/UIE2008F00024.md): Stringer · cracked · Jul 6, 2008 · N540MC · Boeing 747243B · Fuselage Main, Longeron/Stringer
  > STA 320, STRINGER 25L HAS FATIGUE CRACK. FRAME REPAIRED AT STA 320 LT SIDE IAW SRM 53-10-04, FIG 10. (K)
- [SDR UIE2008F00026](https://openairdocs.org/sdr/UIE2008F00026.md): Fastener · loose · Jul 5, 2008 · N540MC · Boeing 747243B · Nacelle/Pylon, Bulkhead/Firewall
  > NR 1 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS, LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)
- [SDR UIE2008F00025](https://openairdocs.org/sdr/UIE2008F00025.md): Fastener · loose · Jul 5, 2008 · N540MC · Boeing 747243B · Nacelle/Pylon, Bulkhead/Firewall
  > NR 4 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)
- [SDR UIE2008F00003](https://openairdocs.org/sdr/UIE2008F00003.md): Frame · cracked · Jul 1, 2008 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > FRAME CRACKED AT STATION 400 STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)
- [SDR UIE2008F00001](https://openairdocs.org/sdr/UIE2008F00001.md): Frame · cracked · Jul 1, 2008 · N540MC · Boeing 747243B · Fuselage Main, Frame
  > FRAME CRACKED AT STATION 400, STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)
- [SDR UIE2008F00018](https://openairdocs.org/sdr/UIE2008F00018.md): Structure · dented · Jun 30, 2008 · N540MC · Boeing 747243B · Engine Thrust Reverser
  > NR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)
- [SDR UIE2008F00017](https://openairdocs.org/sdr/UIE2008F00017.md): Skin · dented · Jun 30, 2008 · N540MC · Boeing 747243B · Engine Thrust Reverser
  > NR 3 ENGINE, RT SIDE ABOUT 4 O`CLOCK POSITION HAS 2 DENTS. NR 3 ENGINE REVERSER REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)
- [SDR UIE2008F00016](https://openairdocs.org/sdr/UIE2008F00016.md): Skin · dented · Jun 30, 2008 · N540MC · Boeing 747243B · Engine Thrust Reverser
  > NR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW CF650 ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)
- [SDR UIE2008F00020](https://openairdocs.org/sdr/UIE2008F00020.md): Reveal · cracked · Jun 29, 2008 · N540MC · Boeing 747243B · Fuselage Miscellaneous Structure
  > MAINE DECK R5 MAIN ENTRY DOOR CUTOUT FWD MIDDLE POSITION, DOOR OPENING LOCK RELEASE HANDLE CUTOUT REVEAL PANEL FOUND CRACKED. CRACKED AREA TRIMMED OUT AND REPAIRED IAW SRM 51-10-01. (K)
- [SDR UIE2008F00019](https://openairdocs.org/sdr/UIE2008F00019.md): Structure · dented · Jun 29, 2008 · N540MC · Boeing 747243B · Engine Thrust Reverser
  > NR 1 ENG IB THRUST REVERSER OUTER SURFACE FOUND LARGE DENT AT THE UPPER POSITION. NR 1 ENGINE IB THRUST REVERSER DENT REPAIRED IAW ENGINE MANUAL 78-32-01 REPAIR NR 4. (K)
- [SDR UIE2008F00002](https://openairdocs.org/sdr/UIE2008F00002.md): Skin · scratched · Jun 24, 2008 · N540MC · Boeing 747243B · Fuselage Main, Plate/Skin
  > FORWARD CARGO STA 770 LT SIDE STRINGER 28L TO 29L, FUSELAGE SKIN FOUND SCRATCHED COMMON AT LOWER PAX RELIEF VALVE. (K)

Next page: https://openairdocs.org/deregistered/N540MC-2011-09-30/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 = 'N540MC' AND deregistration_id = 'N540MC-2011-09-30'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N540MC-2011-09-30/reports

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