# Service difficulty reports: N522MC, cancelled Apr 11, 2012

A list on [N522MC, cancelled Apr 11, 2012](https://openairdocs.org/deregistered/N522MC-2012-04-11.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 4 · 157 reports

- [SDR UIEA2011122800737](https://openairdocs.org/sdr/UIEA2011122800737.md): Jackscrew · damaged · Dec 27, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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 DESCRIB
- [SDR UIEA2011122700736](https://openairdocs.org/sdr/UIEA2011122700736.md): Jackscrew · broken · Dec 27, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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 UIEA2011121200714](https://openairdocs.org/sdr/UIEA2011121200714.md): Nozzle · cracked · Dec 8, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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 7
- [SDR UIEA2011111800665](https://openairdocs.org/sdr/UIEA2011111800665.md): Skin · damaged · Nov 16, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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 UIEA2011091900514](https://openairdocs.org/sdr/UIEA2011091900514.md): Skin · damaged · Sep 15, 2011 · N522MC · Boeing 7472D7B · Vertical Stabilizer, Plate/Skin
  > DURING 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 UIEA2011101900597](https://openairdocs.org/sdr/UIEA2011101900597.md): Lamp · inoperative · Aug 25, 2011 · N522MC · Boeing 7472D7B · Emergency Lighting
  > UPPER 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 UIEA2011061400320](https://openairdocs.org/sdr/UIEA2011061400320.md): Power Supply · inoperative · Jun 14, 2011 · N522MC · Boeing 7472D7B · Emergency Lighting
  > RIGHT SIDE U/D DR SLIDE EMERGENCY LIGHT INOP. EMERGENCY LT POWER PACK REPLACED.
- [SDR UIEA2011061100296](https://openairdocs.org/sdr/UIEA2011061100296.md): Intercostal · cracked · Jun 11, 2011 · N522MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > FOUND 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 OR
- [SDR UIEA2011061000312](https://openairdocs.org/sdr/UIEA2011061000312.md): Skin · cracked · Jun 10, 2011 · N522MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > CRACK 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 CRACK
- [SDR UIEA2011061000299](https://openairdocs.org/sdr/UIEA2011061000299.md): Structure · cracked · Jun 10, 2011 · N522MC · Boeing 7472D7B · Passenger/Crew Doors
  > L3 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 SH
- [SDR UIEA2011060700310](https://openairdocs.org/sdr/UIEA2011060700310.md): Skin · cracked · Jun 7, 2011 · N522MC · Boeing 7472D7B · Passenger/Crew Doors
  > CRACKS 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. DA
- [SDR UIEA2011060700300](https://openairdocs.org/sdr/UIEA2011060700300.md): Bulkhead Web · cracked · Jun 7, 2011 · N522MC · Boeing 7472D7B · Fuselage Main, Bulkhead
  > DURING 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 S
- [SDR UIEA2011060300315](https://openairdocs.org/sdr/UIEA2011060300315.md): Tension Tie · damaged · Jun 3, 2011 · N522MC · Boeing 7472D7B · Fuselage Main, Structure
  > DAMAGE 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 UIEA2011060200298](https://openairdocs.org/sdr/UIEA2011060200298.md): Stiffener · damaged · Jun 2, 2011 · N522MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > NOSE 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, WA
- [SDR UIEA2011060200286](https://openairdocs.org/sdr/UIEA2011060200286.md): Fairing · cracked · Jun 2, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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. INSTA
- [SDR UIEA2011060100290](https://openairdocs.org/sdr/UIEA2011060100290.md): Structure · corroded · Jun 1, 2011 · N522MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > EO 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: MAC
- [SDR UIEA2011051700289](https://openairdocs.org/sdr/UIEA2011051700289.md): Spar · damaged · May 17, 2011 · N522MC · Boeing 7472D7B · Horizontal Stabilizer, Spar/Rib
  > REPORTED 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 UIEA2011051700269](https://openairdocs.org/sdr/UIEA2011051700269.md): Nozzle · cracked · May 17, 2011 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING 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 002
- [SDR UIEA2011051400317](https://openairdocs.org/sdr/UIEA2011051400317.md): Power Supply · inoperative · May 14, 2011 · N522MC · Boeing 7472D7B · Emergency Lighting
  > EMERGENCY LIGHT FOUND INOPERATIVE. EMERGENCY LIGHT POWER SUPPLY; REPLACED AND LT OPS CHECK FOUND NORMAL IAW AMM 33-51-07.
- [SDR UIEA2011051300318](https://openairdocs.org/sdr/UIEA2011051300318.md): Terminal · unsecure · May 13, 2011 · N522MC · Boeing 7472D7B · Light System Wiring
  > L1 DOOR, AFT DOOR SILL LIGHT FOUND INOP. (L1 AFT DOOR SILL LIGHT ASSY TERMINAL RESECURED AND TEST NORMAL. AMM 33-51-07)
- [SDR UIEA2011050900319](https://openairdocs.org/sdr/UIEA2011050900319.md): Battery · inoperative · May 9, 2011 · N522MC · Boeing 7472D7B · Emergency Lighting
  > M/D STATION 460, 2 EA EMERGENCY LIGHT FOUND INOPERATIVE. EMERGENCY LIGHT BATTERY REPLACED AND TEST NORMAL IAW AMM 33-51-07.
- [SDR UIEA2011012800038](https://openairdocs.org/sdr/UIEA2011012800038.md): Structure · damaged · Jan 28, 2011 · N522MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING 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 18
- [SDR UIEA2011012800036](https://openairdocs.org/sdr/UIEA2011012800036.md): Structure · damaged · Jan 28, 2011 · N522MC · Boeing 7472D7B · Spoilers
  > DURING 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 UIEA2010111000177](https://openairdocs.org/sdr/UIEA2010111000177.md): Nacelle · cracked · Nov 10, 2010 · N522MC · Boeing 7472D7B · Nacelle/Pylon, Main Frame
  > THE 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 UIEA201000235](https://openairdocs.org/sdr/UIEA201000235.md): Conduit · damaged · Oct 22, 2010 · N522MC · Boeing 7472D7B · Flight Control System Wiring
  > DURING 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 FLIG
- [SDR UIEA2010080200127](https://openairdocs.org/sdr/UIEA2010080200127.md): Actuator · damaged · Aug 2, 2010 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > UPON 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, RE
- [SDR UIEA2010060600028](https://openairdocs.org/sdr/UIEA2010060600028.md): Floor Panel · damaged · Jun 6, 2010 · N522MC · Boeing 7472D7B · Fuselage Floor Panel
  > DURING 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 M
- [SDR UIEA201000138](https://openairdocs.org/sdr/UIEA201000138.md): Blowout Door · damaged · Apr 17, 2010 · N522MC · Boeing 7472D7B · Engine Thrust Reverser
  > REF 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 UIEA2010022300139](https://openairdocs.org/sdr/UIEA2010022300139.md): Fairing · punctured · Feb 23, 2010 · N522MC · Boeing 7472D7B · Aerodynamic Fairings
  > WING 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 PERMAN
- [SDR UIEA201000063](https://openairdocs.org/sdr/UIEA201000063.md): Stringer · corroded · Feb 5, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Longeron/Stringer
  > DURING 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 UIEA201000062](https://openairdocs.org/sdr/UIEA201000062.md): Frame · corroded · Feb 5, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING 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 UIEA201000061](https://openairdocs.org/sdr/UIEA201000061.md): Skin · corroded · Feb 5, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > DURING 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 UIEA201000060](https://openairdocs.org/sdr/UIEA201000060.md): Frame · corroded · Feb 5, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING 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 UIEA201000154](https://openairdocs.org/sdr/UIEA201000154.md): Skin · corroded · Jan 31, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > DURING 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 A
- [SDR UIEA201000064](https://openairdocs.org/sdr/UIEA201000064.md): Frame · cracked · Jan 28, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING 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 UIEA201000059](https://openairdocs.org/sdr/UIEA201000059.md): Skin · corroded · Jan 28, 2010 · N522MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > DURING 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 UIEA201000066](https://openairdocs.org/sdr/UIEA201000066.md): Skin · corroded · Jan 15, 2010 · N522MC · Boeing 7472D7B · Wing, Plate/Skin
  > DURING 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 UIEA201000058](https://openairdocs.org/sdr/UIEA201000058.md): Structure · corroded · Jan 15, 2010 · N522MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > DURING C-CHECK, MAINTENANCE FOUND CORROSION BETWEEN BS 2020 AND 2040 AT S 46L. CORROSION WAS BLENDED OUT AS PER EO 4752B242.
- [SDR UIEA200900054](https://openairdocs.org/sdr/UIEA200900054.md): Actuator · failed · Sep 3, 2009 · N522MC · Boeing 7472D7B · Landing Gear Door Actuator
  > AIR 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 ACCOMPLISHED
- [SDR UIEA200900047](https://openairdocs.org/sdr/UIEA200900047.md): Skin · cracked · Jul 31, 2009 · N522MC · Boeing 7472D7B · Fuselage Main, Plate/Skin
  > FUSELAGE 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 UIEA200900046](https://openairdocs.org/sdr/UIEA200900046.md): Skin · punctured · Jul 31, 2009 · N522MC · Boeing 7472D7B · Trailing Edge Flaps
  > RT 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 UIEA200800343](https://openairdocs.org/sdr/UIEA200800343.md): Panel · cracked · Nov 21, 2008 · N522MC · Boeing 7472D7B · Wing, Plate/Skin
  > RT 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 UIEA200800342](https://openairdocs.org/sdr/UIEA200800342.md): Panel · delaminated · Nov 21, 2008 · N522MC · Boeing 7472D7B · Wing, Plate/Skin
  > RT 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. ATL
- [SDR UIEA200800281A](https://openairdocs.org/sdr/UIEA200800281A.md): Panel · cracked · Aug 14, 2008 · N522MC · Boeing 7472D7B · Wing, Plate/Skin
  > RT 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 UIEA200800282](https://openairdocs.org/sdr/UIEA200800282.md): Panel · cracked · Aug 14, 2008 · N522MC · Boeing 7472D7B · Leading Edge Devices
  > RT 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. RE
- [SDR UIEA200800269](https://openairdocs.org/sdr/UIEA200800269.md): Engine · vibration · Jul 20, 2008 · N522MC · Boeing 7472D7B · Engine (Turbine/Turboprop)
  > BLOCK 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 UIEA200800215](https://openairdocs.org/sdr/UIEA200800215.md): Panel · cracked · May 18, 2008 · N522MC · Boeing 7472D7B · Passenger/Crew Doors
  > MAIN DECK L-2 DOOR FWD UPPER INNER REVEAL PANEL FOUND CRACKED. CRACKED AREA REPAIRED IAW EO NR 4753B148.
- [SDR UIEA200800214](https://openairdocs.org/sdr/UIEA200800214.md): Floorbeam · cracked · May 18, 2008 · N522MC · Boeing 7472D7B · Fuselage Main, Floor Beam
  > MAIN DECK FLOORBEAM WEB FOUND CRACKED AT STA 1200 LBL 120. MAIN DECK FLOOR WEB CRACKED AREA REPAIRED PER EO 4753B154.
- [SDR UIEA200800213](https://openairdocs.org/sdr/UIEA200800213.md): Floorbeam · cracked · May 18, 2008 · N522MC · Boeing 7472D7B · Fuselage Main, Floor Beam
  > MAIN DECK FLOORBEAM WEB FOUND CRACKED AT STA 1180 LBL 120. MAIN DECK FLOOR WEB CRACKED AREA REPAIRED PER EO 4753B153.
- [SDR UIEA200800212](https://openairdocs.org/sdr/UIEA200800212.md): Frame · cracked · May 18, 2008 · N522MC · Boeing 7472D7B · Fuselage Main, Frame
  > MAIN DECK STA 1740 STRINGER 13R - 14R FRAME FOUND CRACKED. FRAME CRACKED AREA REPAIRED PER EO NR 4753B152.

Next page: https://openairdocs.org/deregistered/N522MC-2012-04-11/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 = 'N522MC' AND deregistration_id = 'N522MC-2012-04-11'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N522MC-2012-04-11/reports

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.