# Service difficulty reports: N524MC, cancelled Feb 14, 2018

A list on [N524MC, cancelled Feb 14, 2018](https://openairdocs.org/deregistered/N524MC-2018-02-14.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 · 142 reports

- [SDR UIEA2011112700697](https://openairdocs.org/sdr/UIEA2011112700697.md): Thrust Reverser · damaged · Nov 22, 2011 · N524MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING MX WALKAROUND, FOUND DAMAGE TO THE NR 3 ENGINE RT THRUST REVERSER TRANSLATING COWL EXTERNAL SKIN PUNCTURED (3 PLACES). THE DAMAGE IS LOCATED NEAR THE REVERSER BLOWOUT DOOR AT 6 O'CLOCK POSITION.
- [SDR UIEA2011111200648](https://openairdocs.org/sdr/UIEA2011111200648.md): Lamp · burned out · Nov 10, 2011 · N524MC · Boeing 7472D7B · Escape Slide
  > EMERGENCY UNARMED LIGHT BURNED OUT. RELAMPED BULBS IAW AMM 33-11-07.
- [SDR UIEA2011101900601](https://openairdocs.org/sdr/UIEA2011101900601.md): Vent · open · Oct 19, 2011 · N524MC · Boeing 7472D7B · Cargo/Baggage Doors
  > DURING CLIMBOUT, AFT CARGO DOOR LIGHT CAME ON F/E PANEL. LIGHT WENT OUT DURING DURING DESCENT AT APPROX 3000FT. ON ARRIVAL, FOUND MAIN DECK CARGO VENT DOORS OPEN. INSPECTED DOOR, NO DEFECTS NOTED TO DOOR OR STRUCTURE. OPS CHECKED NORMAL. AFT CARGO DOOR INSPE
- [SDR UIEA2011101900575](https://openairdocs.org/sdr/UIEA2011101900575.md): Manifold · cracked · Oct 13, 2011 · N524MC · Boeing 7472D7B · Engine Cooling System
  > UPON OPENING OF THE NR 1 ENGINE NACELLE, MX FOUND THE LOWER LPT COOLING MANIFOLD BROKEN AT SEVERAL LOCATIONS. REFER TO FIG 1 FOR DAMAGE LOCATION AND DETAILS. DUE TO PRESENCE OF CRACKS AROUND THE LPT COOLING MANIFOLD WAS OVER LIMITS WITH AMM 75-24-00, SUBMITTE
- [SDR UIEA2011092200521](https://openairdocs.org/sdr/UIEA2011092200521.md): Support · cracked · Sep 22, 2011 · N524MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > DURING MX, DAMAGE FOUND AT MAIN DECK - LT BS 1920 - SIDEWALL/LINER SUPPORT CONSISTING OF CRACK. LOCATED AFT OF THE MDSCD, MEASURING 1.5 IN. LONG (REF FIG 1). DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS. CONS
- [SDR UIEA2011081800457](https://openairdocs.org/sdr/UIEA2011081800457.md): Wire · burned · Aug 18, 2011 · N524MC · Boeing 7472D7B · Flight Control System Wiring
  > WIRE BUNDLES BURNED INSIDE THE CONDUIT USED FOR THE AILERON LOCK OUT ACTUATOR, THE LATERAL NR 1 HYD SOV AND NR 1 REFUEL VALVE PERFORMED A TIME LIMITED REPAIR IAW PART 1.
- [SDR UIEA2011080900444](https://openairdocs.org/sdr/UIEA2011080900444.md): Stringer · cracked · Aug 9, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Longeron/Stringer
  > A 1.3" CRACK IN STRINGER AT BS 940, S-8L. CRACK WAS FOUND DURING ROUTINE INSPECTIONS. REPAIRED WAS ACCOMPLISHED IAW SRM 53-10-03, FIG 4.
- [SDR UIEA2011080900438](https://openairdocs.org/sdr/UIEA2011080900438.md): Frame · cracked · Aug 9, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DISCOVERED 2 EA 0.5" CRACKS IN THE FRAME DOUBLER AT BS 360, S-17L, REF SHEET 3 OF FIG 1. REPAIRED.
- [SDR UIEA2011080900437](https://openairdocs.org/sdr/UIEA2011080900437.md): Frame · cracked · Aug 9, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DISCOVERED 2 CRACKS, 1- 0.875" AND ANOTHER 0.75", IN THE FRAME DOUBLER AT BS 240, S24AL, REF SHEET 1 OF FIG 1. REPAIRED.
- [SDR UIEA2011080500447](https://openairdocs.org/sdr/UIEA2011080500447.md): Spar · corroded · Aug 5, 2011 · N524MC · Boeing 7472D7B · Trailing Edge Flaps
  > RT INBD AFT FLAP MOST OTBD MIDDLE EDGE AREA CORROSION FOUND. CORROSION AREA TRIMMED AWAY AND REPAIR CARRIED OUT IAW HRS NR R57-50-37178 RVC REV B AND EO 4757A519 PART 1.
- [SDR UIEA2011080400416](https://openairdocs.org/sdr/UIEA2011080400416.md): Nozzle · cracked · Aug 4, 2011 · N524MC · Boeing 7472D7B · Engine Collector/Tailpipe/Nozzle
  > DURING AN ENGINE CHANGE AT AN A-CHECK, MX FOUND 3 EA CRACKS ON THE NR 4 ENGINE FIXED COWL EXHAUST NOZZLE FOWARD FLANGE CORE COWL SUPPORT ASSY (REF FIGURE 1). REPAIRED IAW EO 4778A148.
- [SDR UIEA2011080300417](https://openairdocs.org/sdr/UIEA2011080300417.md): Frame · chafed · Aug 3, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > INSPECTION VISUALLY FOUND CHAFING DAMAGE ON FRAME PN 65B04600-7 AT STA 1980 AND COMMON TO STRINGERS 22R AND 23 R. THIS WAS DOCUMENTED ON NRC 51305. (THE DAMAGE WAS REPAIRED BY BLENDING OUT THE CHAFE MARKS. THE BLENDED AREAS WERE HFEC INSPECTED TO ENSURE CRACK
- [SDR UIEA2011080200427](https://openairdocs.org/sdr/UIEA2011080200427.md): Frame · cracked · Aug 2, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING C4/A6 CHECK, DETECTED 6 EA CRACKS ON THE FRAME STRAP FASTENER HOLES; 2 EA CRACKS ON THE FWD INNER CHORD FASTENER HOLES; 3 EA CRACKS ON THE AFT INNER CHORD FASTNER HOLES AND 2 EA CRACKS ON THE DOOR REVEAL PANEL FASTENER HOLES. THE DETAIL OF THE CRACK FI
- [SDR UIEA2011080200422](https://openairdocs.org/sdr/UIEA2011080200422.md): Frame · cracked · Aug 2, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING C4/A6 CHECK, INSPECTION DETECTED 2 EA CRACKS, APPROX 0.50 INCH LONG RUNNING INBD AND 1.8 INCHES LONG RUNNING OTBD AT S-23L CUTOUT AND ANOTHER CRACK APPROX 0.50 INCH LONG, RUNNING INBD AT S-24AL CUTOUT ON THE LT SIDE, BS 380 FRAME.
- [SDR UIEA2011080100434](https://openairdocs.org/sdr/UIEA2011080100434.md): Pressure Panel · cracked · Aug 1, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Bulkhead
  > DURING C4/A6 CHECK, REVEALED CRACKS ON BOTH BS1240 PRESSURE DECK CLOSEOUT PANELS AS SHOWN IN FIG 1:- RT SIDE (RBL 75.92 TO 98.58): CRACK WAS REPORTED AT 0.5" LONG, ALL DATA WAS RECORDED IN RAM 25 - NRC 512309. REPAIRED BOTH PANELS USING SB 747-53-2329R2, FIG
- [SDR UIEA2011080100433](https://openairdocs.org/sdr/UIEA2011080100433.md): Pressure Panel · cracked · Aug 1, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Bulkhead
  > DURING THE PRESENT C4/A6 CHECK, INSPECTION ON THE DATUM ACFT REVEALED CRACKS ON BOTH BS1240 PRESSURE DECK CLOSEOUT PANELS AS SHOWN IN FIGURE 1:- LT SIDE (LBL 75.92 TO 98.58): CRACK WAS REPORTED AT 3" LONG, ALL DATA WAS RECORDED IN NRC 512291. REPAIRED BOTH PA
- [SDR UIEA2011080100414](https://openairdocs.org/sdr/UIEA2011080100414.md): Stringer · cracked · Aug 1, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Longeron/Stringer
  > REPAIR DOUBLER WAS REMOVED TO FACILITATE A REPAIR TO STRINGER 27L. THE STRINGER CRACK WAS COMMON TO THE EXISTING EXTERNAL REPAIR DOUBLER BETWEEN STRINGERS 26L AND 28L. THIS WAS DOCUMENTED ON NRC FVY516326. THE INITAL REPAIR DOUBLER WAS EVALUATED AND HAD SUPPLE
- [SDR UIEA2011072800435](https://openairdocs.org/sdr/UIEA2011072800435.md): Skin · corroded · Jul 28, 2011 · N524MC · Boeing 7472D7B · Wing, Plate/Skin
  > DURING THE "C4 PLUS A6 CHECK, CORROSION DAMAGE WAS DETECTED AT THE UPPER SURFACE OF RT WING LOWER SKIN PANEL BETWEEN WS 1289 - WS 1312. THE CORROSION DAMAGE WAS SPREAD OVER A WIDTH OF 15" WITH A DEPTH OF 3" AS DOCUMENTED IAW NRC 50723. AFTER BLENDING, THE RE
- [SDR UIEA2011072800394](https://openairdocs.org/sdr/UIEA2011072800394.md): Mount · cracked · Jul 28, 2011 · N524MC · Boeing 7472D7B · Engine Mount Section
  > DURING INSP OF THE NR 4 PYLON REAR ENGINE MOUNT NAC STA 270 BULKHEAD, 1 CRACK WAS FOUND ON THE SUBJECT UPPER SIDE RT BULKHEAD CHORD (PN 65B94107-54) FROM THE MOST INBD FLANGE TOWARDS THE SECOND FASTENER HOLE. THE CRACK IS APPROX 1.72" LONG. (THE DAMAGE WAS RE
- [SDR UIEA2011072700440](https://openairdocs.org/sdr/UIEA2011072700440.md): Frame · cracked · Jul 27, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > FRAME AT BS 760 BETWEEN S-5R AND S-7R FOUND CRACKED AND WAS FOUND DURING THE SECTION 42 UPPER LOBE INSPECTION ACCOMPLISHED IAW EO 4753A165, REV C (SB 747-53-2349 REV 3, AD 2009-18-07). THE CRACK WAS LOCAL ONLY TO THE FRAME PN AND WAS LOCATED AT S-6R. THE CRACK
- [SDR UIEA2011072700439](https://openairdocs.org/sdr/UIEA2011072700439.md): Frame · cracked · Jul 27, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DECK FRAME AT BS 760 BETWEEN S-5L AND S-7L FOUND CRACKED AND WAS FOUND DURING THE SECTION 42 UPPER LOBE INSP ACCOMPLISHED IAW EO 4753A165, REV C (SB 747-53-2349 REV 3, AD 2009-18-07). THE CRACK WAS LOCAL ONLY TO THE FRAME AND WAS LOCATED AT S-6L. THE CRACK WAS
- [SDR UIEA2011072700367](https://openairdocs.org/sdr/UIEA2011072700367.md): Frame · damaged · Jul 27, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > CRACK DAMAGE WAS DETECTED IN RADIUS OF BULKHEAD CHORD AT BS 1000 BETWEEN S38L - S39L. THE CRACK DAMAGE WAS THROUGH THE FULL THICKNESS OF THE CHORD AS DOCUMENTED IAW NRC 50190 FOR REPAIR ACTIONS (SEE FIG 1). REPLACED BULKHEAD CHORD AS REQUIRED IAW TLS EO 4753
- [SDR UIEA2011072700368](https://openairdocs.org/sdr/UIEA2011072700368.md): Stringer · cracked · Jul 27, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Longeron/Stringer
  > INSPECTION FOUND VISUALLY, A CRACK AT BS 525 IN STRINGER 27L DURING ROUTINE INSPECTION. THE STRINGER CRACK IS COMMON TO AN EXTERNAL REPAIR DOUBLER BETWEEN STRINGERS 26L AND 28L THAT HAS A REPETITIVE INSPECTION REQUIREMENT ACCOMPLISHED BY EO 4753A832. SEE FIG 1
- [SDR UIEA2011072600453](https://openairdocs.org/sdr/UIEA2011072600453.md): Frame · cracked · Jul 26, 2011 · N524MC · Boeing 7472D7B · Fuselage Structure (General)
  > RT BS 380, STR 18R FRAME OTBD FLANGE FOUND CRACKED AT RT BS 38 BETWEEN STR 17R AND STR 18R, FRAME REPAIRED IAW 53-23-37165, REV A.
- [SDR UIEA2011072600450](https://openairdocs.org/sdr/UIEA2011072600450.md): Frame · cracked · Jul 26, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > M/D LT BS 360 BETWEEN STR 23L AND STR 26L FRAME CRACKED 10 LOCATIONS. FRAME REPAIRED IAW HXRS, NR 53-12-37160, REV B.
- [SDR UIEA2011072600420](https://openairdocs.org/sdr/UIEA2011072600420.md): Angle · corroded · Jul 26, 2011 · N524MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > DURING THE PRESENT C4/A6 CHECK, INSPECTION ON THE DATUM ACFT REVEALED CORROSION ON THE BS 1241 CANTED PRESSURE WEB ANGLE COMMON TO WING CENTER SECTION. THE CORROSION WAS REPORTED AT APPROX RBL 80 AND PENETRATED THE A SECTION OF THE ANGLE WHICH WAS TRIMMED IAW
- [SDR UIEA2011072500449](https://openairdocs.org/sdr/UIEA2011072500449.md): Frame · cracked · Jul 25, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > M/D LEFT BS 320 STR 14EL FRAME WEB CRACK AT STRINGER CUT OUT. FRAME WEB REPAIRED IAW HXRS NR 53-12-37169, REV A.
- [SDR UIEA2011072500448](https://openairdocs.org/sdr/UIEA2011072500448.md): Fuse Pin · cracked · Jul 25, 2011 · N524MC · Boeing 7472D7B · Nacelle/Pylon Miscellaneous Structure
  > NR 4 PYLON UPPER LINK FWD MOUNT BOLT THREAD SEIZED AND NDT FOUND CRACKED AT THREAD ROOT AREA. FUSE PIN REPLACED IAW AMM 54-10-03.
- [SDR UIEA2011072200442](https://openairdocs.org/sdr/UIEA2011072200442.md): Stringer · corroded · Jul 22, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Longeron/Stringer
  > STRINGER 42L WAS FOUND WITH A CORROSION LOCATED AT BS 890 TO BS 910. THE CORROSION WAS FOUND DURING NORMAL CHECK INSPECTIONS OF THE FWD CARGO COMPARTMENT BILGE AREA. THE CORROSION WAS APPROX 1INCH WIDE BY 3 INCH LONG AND APPROX 0.034 INCH DEEP. THE CORRODED S
- [SDR UIEA2011072200419](https://openairdocs.org/sdr/UIEA2011072200419.md): Fitting · damaged · Jul 22, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Attach Fittings
  > DURING ACCOMPLISHMENT OF EO 4753B354 (SB 747-53A2562, AD 2006-22-15) REPLACEMENT FITTING WAS FOUND TO HAVE (2) ATTACH PILOT HOLES WITH THE CENTER SHIFTED APPROX. 0.080 INCH COMPARED TO THE EXISTING STRUCTURE. (THE MISALIGNED HOLES WERE REPAIRED BY INSTALLATION
- [SDR UIEA2011072200376](https://openairdocs.org/sdr/UIEA2011072200376.md): Frame · cracked · Jul 22, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING THE PRESENT C4-CHECK, CRACKS WERE FOUND AT BS 480 SIDE BETWEEN S-27L AND S-28L. BOTH CRACKS WERE REPORTED AT 2 FASTENER HOLES RUNNING FWD WITH LENGTHS 0.25" AND 0.125" RESPECTIVELY. (CARRIED OUT A CATEGORY B REPAIR BASED ON SRM 53-30-03, FIG 1 (WITH SU
- [SDR UIEA2011072000377](https://openairdocs.org/sdr/UIEA2011072000377.md): Shear Web · cracked · Jul 20, 2011 · N524MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > THE PURPOSE OF THIS EO, IS TO DOCUMENT A CATEGORY B REPAIR ACCOMPLISHED DURING C4 / A6 CHECK, DURING JULY 2011. INSP VISUALLY FOUND A CRACK IN THE SHEAR WEB AT S-14R BETWEEN BS 380 AND 400 DURING ROUTINE INSPECTION. THE CRACK WAS 4 IN LONG WHEN FOUND AND DOC
- [SDR UIEA2011071900428](https://openairdocs.org/sdr/UIEA2011071900428.md): Frame · cracked · Jul 19, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING C4/A6 CHECK, INSP DETECTED 2 EACH CRACKS ON THE RT SIDE, BS 320 FRAME AT S-15R CUTOUT. THE FIRST CRACK IS FOUND ON THE WEB LAYER ONLY AND IS APPROX 2 IN LONG RUNNING INBD AND DOWNWARD. THE SECOND CRACK IS ALSO ON THE WEB LAYER ONLY AND IS APPROX 0.50
- [SDR UIEA2011071900418](https://openairdocs.org/sdr/UIEA2011071900418.md): Frame · cracked · Jul 19, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING INSPECTION, DETECTED 2 EACH CRACK ON THE RT SIDE, BS 380 FRAME AS SHOWN IN FIG 1. THE FIRST CRACK IS FOUND ON THE WEB LAYER ONLY AND IS APPROX 0.5 INCH LONG RUNNING INBD AND UPDWARD. THE SECOND CRACK IS ALSO ON THE WEB LAYER ONLY AND IS APPROX 0.125 I
- [SDR UIEA2011071800443](https://openairdocs.org/sdr/UIEA2011071800443.md): Frame · cracked · Jul 18, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING THE ACCOMPLISHMENT OF EO 4753B324, REV B (SB 747-53A2450, REV 6, AD 2010-20-08). ONE FASTENER HOLE ON THE FRAME STRAP (PN 65B01849-26) WAS FOUND WITH A 0.0625 INCH CRACK EXTENDING IN THE AFT DIRECTION AS SEEN IN THE REF /2/ RS R53-62-37168 REV A. IN A
- [SDR UIEA2011071500430](https://openairdocs.org/sdr/UIEA2011071500430.md): Tension Tie · cracked · Jul 15, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING INSPECTION OF DATUM ACFT IAW EO 4753B328, A CRACK WAS FOUND ON AT BS 880, LT SIDE TENSION TIE STR 9L, AFT CHANNEL AT HOLE NR 16 FIG 1 CRACK LENGTH WAS 0.040" AND RUNNING INBD AT 9 O'CLOCK. THE DAMAGED TENSION TIE WAS REPAIRED IAW WORK STEP 23D OF PART
- [SDR UIEA2011071500426](https://openairdocs.org/sdr/UIEA2011071500426.md): Tension Tie · cracked · Jul 15, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Structure
  > THE PURPOSE OF THIS EO IS TO DOCUMENT A MAJOR REPAIR THAT WAS ACCOMPLISHED DURING C4/A6 CHECK. DURING INSPECTION OF DATUM ACFT IAW EO 4753B328, CRACK WAS FOUND ON AT BS 940 LT SIDE TENSION TIE STR - 8L AFT CHANNEL AT HOLE NR 20 (FIGURE 1) (CRACK LENGHT WAS 0.0
- [SDR UIEA2011071500425](https://openairdocs.org/sdr/UIEA2011071500425.md): Tension Tie · damaged · Jul 15, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING INSPECTION OF DATUM ACFT IAW EO 4753B328, ELONGATION FASTENER HOLE WAS FOUND ON AT BS 920 RT SIDE TENSION TIE AFT CHANNEL (FIG 1). THE DAMAGED TENSION TIE WAS REPAIRED IAW WORK STEP 29D OF PART 2 OF EO 4753B328. IAW WORK STEP 29D OF PART 2 OF THE EO,
- [SDR UIEA2011071300436](https://openairdocs.org/sdr/UIEA2011071300436.md): Frame · cracked · Jul 13, 2011 · N524MC · Boeing 7472D7B · Fuselage Main, Frame
  > DURING ACCOMPLISHMENT OF SB 747- 53A2414 (AD 99-07-03) IAW CEO 72530A, A CRACK WAS FOUND IN THE WEB OF THE LT 488 FRAME. THE CRACK WAS FOUND BELOW THE NR1 STOP FITTING. REPAIRED BY ACCOMPLISHING A DOUBLER REPAIR IAW SRM 53-10-04, FIG 92 AS INSTRUCTED BY SB 74
- [SDR UIEA2011071300424](https://openairdocs.org/sdr/UIEA2011071300424.md): Tension Tie · cracked · Jul 13, 2011 · N524MC · Boeing 7472D7B · Fuselage Miscellaneous Structure
  > DURING INSPECTION OF DATUM ACFT IAW EO 4753B328, A CRACK WAS FOUND ON AT BS 920, RT SIDE TENSION TIE FWD CHANNEL AT HOLE NR 5 (FIGURE 1) CRACK LENGTH WAS 0.060" AND RUNNING INBD AT 3 O'CLOCK. THE DAMAGED TENSION TIE WAS REPAIRED IAW WORK STEP 29D OF PART 2 OF
- [SDR UIEA2011071300359](https://openairdocs.org/sdr/UIEA2011071300359.md): Nozzle · cracked · Jul 13, 2011 · N524MC · Boeing 7472D7B · Engine Collector/Tailpipe/Nozzle
  > DURING A 'C4/A4' CHECK OF ACFT, MX FOUND 2 CRACKS ON THE NR 1 ENGINE EXHAUST NOZZLE OUTER SKIN AT 12 O'CLOCK POSITION (REFER TO FIG 1 AND 2). (THE CRACKS CAN BE REPAIRED IAW THE ENGINE MANUAL (ESM) TASK 78-11-01-300-011. REPAIR 78-11-01 REPAIR 011. THIS RE
- [SDR UIEA2011061900322](https://openairdocs.org/sdr/UIEA2011061900322.md): Inu · failed · Jun 19, 2011 · N524MC · Boeing 7472D7B · Navigation System
  > AFTER TAKEOFF, CAPTAINS FLIGHT INSTRUMENTS HAD ATT FLAG IN ADI, HSI. FLAG IN HSI FOLLOWING RED WARNING LIGHT ON INU NR1, CODE 591 IN INS, PLATFORM FAILURE. INS WAS SHUTDOWN, UNABLE TO RESTORE CAPTAINS HSI AND ADI. USING FHB PROCEDURE CIWS LIGHTS ON CAPTAINS S
- [SDR UIEA2011052300265](https://openairdocs.org/sdr/UIEA2011052300265.md): Access Door · cracked · May 23, 2011 · N524MC · Boeing 7472D7B · Engine Thrust Reverser
  > DURING MX WALKAROUND, MX FOUND 1 EA CRACK ON THE NR 1 ENGINE THRUST REVERSER LWR ACCESS DOOR (PN: 9071M77G12). DAMAGE LOCATED AT 6 O'CLOCK POSITION. THE CRACK IS APPROX 2.0625 IN LONG. (IAW AMM 78-11-01 THE LENGTH OF THE CRACK IS OUT OF LIMITS. DISPOSITION IS
- [SDR UIEA2011051900262](https://openairdocs.org/sdr/UIEA2011051900262.md): Skin · dented · May 19, 2011 · N524MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > MX FOUND THE NR1 ENGINE INLET NOSE COWL - OUTER BARREL SKIN DENT, MEASURING: 12.0" X 9.0" AND THE DEPTH 0.250 (REF FIG 1), LOCATED APPROX AT 3 O'CLOCK POSITION. THE DAMAGE IS BEYOND THE ALLOWABLE DAMAGE LIMITS IAW SRM 54-31-01, FIG 1, IAW SRM 51-40-06, FIG 2.
- [SDR UIEA2011031100149](https://openairdocs.org/sdr/UIEA2011031100149.md): Check Valve · failed · Mar 11, 2011 · N524MC · Boeing 7472D7B · Engine (Turbine/Turboprop)
  > BLOCK TURN BACK DUE NR 4 ENGINE FAILED TO ACCELERATE PAST 40 PERCENT N1, WITH HIGH EGT AND 4 COMPRESSOR STALLS WERE EXPERIENCED. (REPLACED 8TH STAGE CHECK VALVE AND PERFORMED ENGINE RUNUP. ALL OPERATES NORMAL. DUE TO COMPRESSOR STALL, BOROSCOPE INSPECTION ACC
- [SDR UIEA2010122900247](https://openairdocs.org/sdr/UIEA2010122900247.md): Panel · cracked · Dec 29, 2010 · N524MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING A-CHECK INSP, CRACKS WERE FOUND ON LT AND RT SIDE PANELS IN THE NLG WW AREA OF LT PANEL: THE CRACK WAS LOCATED BETWEEN BS260 AND 280, WL 150, AND THE CRACK LENGTH WAS APPROX 2.0 INCHES (FIG 1). RT PANEL: THE CRACK WAS LOCATED BETWEEN BS300 AND 320, WL
- [SDR UIEA2010122900246](https://openairdocs.org/sdr/UIEA2010122900246.md): Panel · cracked · Dec 29, 2010 · N524MC · Boeing 7472D7B · Fuselage Main, Structure
  > DURING A-CHECK INSP, CRACK WAS FOUND AT BS 318 LBL 20 AREA. THE CRACK WAS LOCATED ON THE TOP PANEL ALONG THE EDGE OF THE STIFFENER (PN: 65B13797-50), THE CRACK RUN FROM FWD TO AFT AND THE LENGTH OF IT WAS APPROX 1.5 INCH (FIG 1). (REPAIR WAS ACCOMPLISHED IAW
- [SDR UIEA2010081700140](https://openairdocs.org/sdr/UIEA2010081700140.md): Lens · broken · Aug 17, 2010 · N524MC · Boeing 7474D7 · Exterior Lighting
  > ON WALK AROUND, FOUND LT INBD LANDING LIGHT LENS SHATTERED. LT INBD LANDING LIGHT CONSIDERED INOP. (ACCOMPLISHED EO 4733A032, PART 1 AS REQUIRED. OPENED NON MEL 18697)
- [SDR UIEA2010062400033](https://openairdocs.org/sdr/UIEA2010062400033.md): Skin · dented · Jun 24, 2010 · N524MC · Boeing 7472D7B · Nacelle/Pylon, Plate/Skin
  > DURING WALKAROUND INSPECTION IN HKG, MAINTENANCE FOUND DAMAGE TO THE NR 2 ENGINE RT FAN COWL DENT DAMAGE, BELOW THE SERVICE OIL DOOR (REF FIGURE 1). DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS; SCHEDULE REPEA
- [SDR UIEA201000194](https://openairdocs.org/sdr/UIEA201000194.md): Trim System · malfunctioned · May 11, 2010 · N524MC · Boeing 7472D7B · Stabilizer Position Indicating
  > MANUAL STAB TRIM LEVERS MORE THAN 1 KNOB SPLIT (AT CRUISE. (DIVERSION) ACCOMPLISHED STAB TRIM / ADJ TEST IAW 27-41-00. IN PITOT STATIC TEST SET IAW 34-11-00. BROUGHT L/E TO ORIGINAL AND 20000 FT. COULD NOT DUPLICATE. TESTED RIGGING TENSION IAW 27-41-00, FIG 50

Next page: https://openairdocs.org/deregistered/N524MC-2018-02-14/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 = 'N524MC' AND deregistration_id = 'N524MC-2018-02-14'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N524MC-2018-02-14/reports

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