# Service difficulty reports: N820SA, cancelled Oct 20, 2017

A list on [N820SA, cancelled Oct 20, 2017](https://openairdocs.org/deregistered/N820SA-2017-10-20.md).

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

- [SDR Q2SA820002](https://openairdocs.org/sdr/Q2SA820002.md): Fan · faulty · Jul 8, 2011 · N820SA · Boeing 747243B · Air Distribution Fan
  > NOTICED BURNING SMELL WITH FLIGHT DECK FAN ON, WITH THE FAN OFF, THE SMELL STOPPED. FOUND RECIRCULATING FAN TO BE THE CAUSE OF SMOKE/FUMES IN THE COCKPIT. THE ITEM WAS TRANSFERRED TO DI 25211 AS PER MEL 21-20, CAT C. ADDITIONALLY, PERFORMED SMOKE IN THE CAB
- [SDR Q2SA820001](https://openairdocs.org/sdr/Q2SA820001.md): Acm · inoperative · Nov 5, 2010 · N820SA · Boeing 747243B · Cabin Cooling System
  > NR 1 A/C PACK EMITTED BURNING TYPE ODOR ALONG WITH EXCESSIVE NOISE. INSPECTED ACM IAW AMM 21-00-00 AND DETERMINED ACM TO BE AT FAULT. CONDITIONAL (SMOKE) INSPECTION ACCOMPLISHED IAW AMM 05-51-50. NR 1 ACM PACK INOPERATIVE, TRANSFERRED TO DMI NR 23431, PER M
- [SDR VGQY2010062300038](https://openairdocs.org/sdr/VGQY2010062300038.md): Stiffener · worn · Jun 30, 2010 · N820SA · Boeing 747243B · Nacelle/Pylon Miscellaneous Structure
  > NR 3 PYLON - ADP LT MOUNT BUSHING MISSING. COMPLIED WITH EN 1101-10, REPAIR FOR NR 3 PYLON NAC STA 365.51 BULKHEAD STIFFENER 65B90413-42 ELONGATED HOLE.
- [SDR VGQY2010063000040](https://openairdocs.org/sdr/VGQY2010063000040.md): Skin · cracked · Jun 30, 2010 · N820SA · Boeing 747243B · Fuselage Main, Plate/Skin
  > APU COMPARTMENT CROWN AREA AT STA 2638-2658 BETWEEN RIGHT STR 1 AND 2, FUSELAGE SKIN FOUND CRACKED. TRIMMED OFF CRACKED SKIN MATERIAL PER SRM 53-30-00 REV 116 FIGURE 1A. HFEC INSPECTION CARRIED OUT PER B747 NDTM D6-7170 REV 134 PART 6, SRM 51-00-00 FIGURE 23
- [SDR VGQY2010062300039](https://openairdocs.org/sdr/VGQY2010062300039.md): Web · cracked · Jun 23, 2010 · N820SA · Boeing 747243B · Horizontal Stabilizer Miscellaneous Structure
  > LEFT HORZ STAB AT STAB BL 421.50, RIB WEB AFT END FOUND CRACK AT FASTENER HOLE (CRACK LENGTH APPROX = 0.575 INCH). NO SRM REPAIR. REMOVED CRACKED WEB PER SRM 51-30-02, REV 116. WEB TRIMMED OFF, WEB AND SPLICE FABRICATED 7075-T6 AL CLAD SHEET AND INSTALLED.
- [SDR VGQY2010061700035](https://openairdocs.org/sdr/VGQY2010061700035.md): Frame · cracked · Jun 17, 2010 · N820SA · Boeing 747243B · Fuselage Main, Frame
  > APU COMPT STA 2716.60 ABOUT 2FT ABOVE LT APU DOOR HINGE, LT FRAME FOUND CRACKED. LT DOOR HINGE FRAME REMOVED PER SRM 51-40-02 REV 116. FRAME CRACKED MATERIAL TRIMMED OFF, REPAIR FRAME FILLER, DOUBLER FABRICATED AND INSTALLED PER SRM 51-40-03 REV 116 AND SRM
- [SDR VGQY2010061500034](https://openairdocs.org/sdr/VGQY2010061500034.md): Floor Support · cracked · Jun 15, 2010 · N820SA · Boeing 747243B · Fuselage Miscellaneous Structure
  > HFEC OPEN HOLE INSP FOUND CRACK ON STA 1265 RT FLOOR INTERCOSTAL WEB AS MARKED. COMPLIED WITH EN 1115-10 (REPAIR FOR CRACK ON STA 1265 FRAME WEB 65B15095-12 SB 747-53A2416 INSP TIME LIMITED REPAIR FOR 24 MONTHS OR 2,000 FLIGHT CYCLES FROM THE TIME OF REPAIR,
- [SDR VGQY2010061400033](https://openairdocs.org/sdr/VGQY2010061400033.md): Fairing · cracked · Jun 14, 2010 · N820SA · Boeing 747243B · Nacelle/Pylon Miscellaneous Structure
  > PYLON NR 2 PYLON AFT FAIRING AFT OF AFT STRUT AFT LWR SIDE WITH CRACK. 01 EACH CRACK FOUND ON OUTER SKIN OF NACELLE NR 2 FIXED FAIRING ASSY P/N 65B90813-67 AT AFT LOWER EDGE HOLE. NO SPECIFIC SRM REPAIR AVAILABLE. COMPLIED WITH EN 1098-10 (REPAIR FOR 01 CR
- [SDR VGQY2010061100031](https://openairdocs.org/sdr/VGQY2010061100031.md): Skin · damaged · Jun 11, 2010 · N820SA · Boeing 747243B · Fuselage Main, Plate/Skin
  > EXISTING EXTERNAL DOUBLER REPAIR BETWEEN STA 1760 - 1780, STR 38R - 41R FOUND WITHOUT PREVIOUS REPAIR RECORD DOCUMENT.
- [SDR VGQY2010061000029](https://openairdocs.org/sdr/VGQY2010061000029.md): Bulkhead · cracked · Jun 10, 2010 · N820SA · Boeing 747243B · Fuselage Main, Bulkhead
  > MAIN DECK CARGO STA 160 SIDEWALL JUST AFT OF FWD PRESSURE BULKHEAD WEB FOUND CRACKED. FLOOR WEB REMOVED AT STA 160 PER SRM 51-30-02 REV 116. FLOOR WEB FABRICATED PER DWG 65B01870 AND INSTALLED PER SRM 51-30-02 REV 116.
- [SDR VGQY2010060900028](https://openairdocs.org/sdr/VGQY2010060900028.md): Fitting · corroded · Jun 9, 2010 · N820SA · Boeing 747243B · Nacelle/Pylon Miscellaneous Structure
  > CORROSION / NR 4PYLON / UNDERWING DUAL SIDE BRACE FITTING / BORE. COMPLIED WITH SB 747-54A2218 FIGURE 9. REMOVED AND REPLACED 2 EACH BEARING AS PER BOEING SOPM 20-50-03 REV 90.
- [SDR VGQY2010060900027](https://openairdocs.org/sdr/VGQY2010060900027.md): Bearing · corroded · Jun 9, 2010 · N820SA · Boeing 747243B · Nacelle/Pylon Miscellaneous Structure
  > CORROSION NR 1 PYLON / UNDERWING DUAL SIDE BRACE FITTING/BORE. COMPLIED WITH SB 747-54A2218 FIGURE 9. REMOVED AND REPLACED 2 EACH BEARING AS PER SOPM 20-50-03 REV 90.
- [SDR VGQY2010060800026](https://openairdocs.org/sdr/VGQY2010060800026.md): Rib · cracked · Jun 8, 2010 · N820SA · Boeing 747243B · Wing, Rib/Bulkhead
  > LT WING SURGE TANK WS 1516.6 RIB / LOWER CHORD SUSPECT CRACK/ ACCESS FROM TANK PANEL 555AB. LOWER CHORD REMOVED AND REPLACED AS PER SRM 51-30-02 REV 116.
- [SDR VGQY2010060800025](https://openairdocs.org/sdr/VGQY2010060800025.md): Beam · cracked · Jun 8, 2010 · N820SA · Boeing 747243B · Wing Miscellaneous Structure
  > UPON REMOVAL OF RT WING L/E UPPER SURFACE FIXED PANEL NR 611CT FOUND D BEAM UPPER CHORD CRACK. REPAIRED PER SRM 57-20-03, FIGURE 7. COMPLIED WITH EN 1100-10.
- [SDR VGQY2010060700024](https://openairdocs.org/sdr/VGQY2010060700024.md): Bulkhead · canning · Jun 7, 2010 · N820SA · Boeing 747243B · Fuselage Main, Bulkhead
  > AFT PRESSURE BULKHEAD AT STA 2360, LT STR 30-31, FOUND OIL CANNING. OIL CANNING MEASURED AT STA 2360 LT STR 21 TO STR 22: L=4" X W=5" X D=0.028"; STR 22 TO STR 23: L=4.5" X W=4" X D=0.025"; STR 23 TO STR 24: L=7.375" X W=6" X D=0.036 FOUND WITHIN LIMITS AS PE
- [SDR VGQY2010060400023](https://openairdocs.org/sdr/VGQY2010060400023.md): Skin · dented · Jun 4, 2010 · N820SA · Boeing 747243B · Fuselage Main, Plate/Skin
  > FUSELAGE EXTERIOR - SKIN FOUND DENT MARK APPROX 2 INCH IN LENGTH AT STA 1764R, 0.25 INCH BELOW S-36R. COMPLIED WITH EN 1096-10.
- [SDR VGQY2010060400022](https://openairdocs.org/sdr/VGQY2010060400022.md): Beam · cracked · Jun 4, 2010 · N820SA · Boeing 747243B · Fuselage Miscellaneous Structure
  > HFEC INSP FOUND 01EA CRACK APPROX 0.5 INCH ON NOSE WHEEL WELL VERTICAL BEAM WEB (COMMON TO OUTER CHORD AREA) AT RT STA 300 WL 186. RT STA 300 WEB ASSY P/N 65B07942-504 CRACKED AT TWO (2) LOCATIONS BETWEEN WL 170 TO WL 190 COMPLIED WITH EN1097-10. INSPECTION
- [SDR VGQY2010060400021](https://openairdocs.org/sdr/VGQY2010060400021.md): Beam · cracked · Jun 4, 2010 · N820SA · Boeing 747243B · Fuselage Miscellaneous Structure
  > HFEC INSP FOUND 01 EA CRACK APPROX. 0.1875 INCH ON NOSE WHEEL WELL VERTICAL BEAM WEB (COMMON TO INNER CHORD AREA) AT LT STA 320 BETWEEN WL 170 AND WL 175 AS MARKED. LEFT STA 320 WEB ASSY P/N 65B07942-55 CRACKED AT TWO (2) LOCATIONS BETWEEN WL 170 TO WL 180 C
- [SDR VGQY2010060400020](https://openairdocs.org/sdr/VGQY2010060400020.md): Beam · cracked · Jun 4, 2010 · N820SA · Boeing 747243B · Fuselage Miscellaneous Structure
  > HFEC INSP FOUND 01EA CRACK APPROX. 0.625 INCH ON NOSE W/W VERTICAL BEAM WEB INSULATION BLANKET STANDOFF HOLE AT RT STA 300 BETWEEN WL 170 AND WL 175. COMPLIED WITH EN1097-10.
- [SDR VGQY2010060400019](https://openairdocs.org/sdr/VGQY2010060400019.md): Beam · cracked · Jun 4, 2010 · N820SA · Boeing 747243B · Fuselage Miscellaneous Structure
  > HFEC INSP FOUND 01EA CRACK APPROX. 0.25 INCH ON NOSE WHEEL WELL VERTICAL BEAM WEB INSULATION BLANKET STANDOFF HOLE AT LT STA 320 BETWEEN WL 170 AND WL 175. COMPLIED WITH EN1097-10 [REPAIR FOR NOSE WHEEL WELL STA 300 RT SIDE PANEL WEB ASSY 65B07942-504 & STA 3
- [SDR VGQY2010060300018](https://openairdocs.org/sdr/VGQY2010060300018.md): Bulkhead · cracked · Jun 3, 2010 · N820SA · Boeing 747243B · Fuselage Main, Bulkhead
  > RIGHT BODY GEAR WHEEL WELL - SUSPECT CRACK AT AFT BULKHEAD STA 1480, RBL 108 ADJ TO LONGERON EXTENSION FITTING. CRACKED WEB ATTACHED PARTS REMOVED PER SRM 51-30-02 REV 117. CRACKED WEB TRIMMED-OFF PER B747 SRM 10-04 REV 116 FIG 122. REPAIR WEB AND DOUBLERS
- [SDR VGQY2010060300017](https://openairdocs.org/sdr/VGQY2010060300017.md): Skin · dented · Jun 3, 2010 · N820SA · Boeing 747243B · Fuselage Main, Plate/Skin
  > DWG NR 1057, FUSELAGE EXTERIOR- SKIN FOUND DENT MARK APPROX 1.75 INCH IN LENGTH AT STA 1764R, 0.5 INCH ABOVE S-36R. CONFIRMED SURROUNDING STRUCTURE IS CORROSION AND DAMAGE FREE PER SRM 51-10-01 INSPECTION GUIDELINES. TRIMMED OUT SKIN TO COMPLETELY REMOVED DE
- [SDR VGQY201005250016](https://openairdocs.org/sdr/VGQY201005250016.md): Structure · corroded · May 25, 2010 · N820SA · Boeing 747243B · Wing, Center Box
  > RIGHT WING GEAR WHEEL WELL - CORROSION FOUND AT UPPER CHORD STA 1350 RBL 65. NEW UPPER CHORD INSTALLED P/N 65B15061-16 PER DWG 65B151210 SHEET 22 ADCN 48, DWG 65B15210 PL AND SRM 51-30-02 REV 116.
- [SDR VGQY201005250015](https://openairdocs.org/sdr/VGQY201005250015.md): Panel · cracked · May 25, 2010 · N820SA · Boeing 747243B · Leading Edge Devices
  > RIGHT WING L/E UPPER FIXED PANEL ADJ TO NR 15 KRUEGER FLAP FOUND PANEL CRACKED. REPAIR CARRIED OUT IAW SRM-51-40-15, REV 116.
- [SDR VGQY2010052400014](https://openairdocs.org/sdr/VGQY2010052400014.md): Skin · bulged · May 24, 2010 · N820SA · Boeing 747243B · Wing, Plate/Skin
  > RT WING LEADING EDGE BEAM WEB P/N 65B10652-68 AT OLES 1300 AFT FACE FOUND SKIN BULGING. BULGED SKIN 1.00 INCH DIAMETER TRIMMED AND CHECKED FOR CORROSION AT THE ADJACENT AREA AROUND THE WEB TRIM OUT. NO CORROSION FOUND. COMPLIED WITH EN 1089-10. INSPECTION
- [SDR VGQY2010052400013](https://openairdocs.org/sdr/VGQY2010052400013.md): Skin · corroded · May 24, 2010 · N820SA · Boeing 747243B · Wing, Plate/Skin
  > LEFT WING UPPER SKIN SURFACE MID SPAR AT APPROX WS 130 FOUND SURFACE CORROSION. CORROSION REMOVED AS PER SRM 51-10-01 REV 116. ORIG THICKHNESS: 0.354 INCH, MATERIAL REMAINING: 0.350 INCH, MATERIAL REMOVED: 0.004 INCH, WITHIN LIMITS PER SRM 57-30-01 FIGURE 1,
- [SDR VGQY2010052400012](https://openairdocs.org/sdr/VGQY2010052400012.md): Skin · bulged · May 24, 2010 · N820SA · Boeing 747243B · Fuselage Main, Plate/Skin
  > FUSELAGE SKIN FOUND BULGING AT STA 2360 STR 34L - 42L. REMOVED BOLTS AND NUTS (TOTAL 8 EACH) AT STA 2360 BULKHEAD STR 34L TO STR 42L PER AMM 20-51-01 REV 90. HFEC INSPECTION CARRIED OUT IAW NDTPM D6-7170 REV 134 PART 6 51-00-00 FIG 23 ON BULGING SKIN. NO CR
- [SDR VGQY2010052000010](https://openairdocs.org/sdr/VGQY2010052000010.md): Skin · cracked · May 20, 2010 · N820SA · Boeing 747243B · Wing, Plate/Skin
  > DRWS NR:0381, LT WING UPPER SKIN SURFACE FRONT SPAR AT APPROX WS420 FOUND SKIN CRACKED. REPAIR CARRIED OUT PER SRM 51-40-14 REV. 116
- [SDR VGQY2010052000011](https://openairdocs.org/sdr/VGQY2010052000011.md): Skin · cracked · May 20, 2010 · N820SA · Boeing 747243B · Wing, Plate/Skin
  > LEFT WING UPPER SKIN SURFACE FRONT SPAR AT APPROX WS 700 FOUND SKIN CRACKED. REPAIRED CARRIED OUT PER SRM 51-40-15 REV 116. REPAIR AREA PAINTED PER MM 51-24-11 REV 90.
- [SDR VGQY2010052000009](https://openairdocs.org/sdr/VGQY2010052000009.md): Bulkhead · cracked · May 20, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > LT BODY GEAR WHEEL WELL - CRACKS FOUND AT AFT BULKHEAD STA 1480, LBL 110. CRACKED WEB TRIMMED, REPAIR WEB FABRICATED AND INSTALLED AS PER SRM 53-10-04 FIGURE 122 REV 116.
- [SDR VGQY2010051900008](https://openairdocs.org/sdr/VGQY2010051900008.md): Mount · corroded · May 19, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION PRODUCTS (RUST) NR 3 ENGINE - PYLON / AFT UPPER MOUNT / MATING SURFACE. COMPLIED WITH EN 1090-10, NR 3 & NR 4 STRUT NAC WL 131 LWR AFT SPAR NAC STA 286 FILLER DOUBLER 65B94115-7 FOUND WITH SURFACE RUST.
- [SDR VGQY2010051900007](https://openairdocs.org/sdr/VGQY2010051900007.md): Mount · corroded · May 19, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION PRODUCTS RUST NR 4 ENGINE - PYLON / AFT UPPER MOUNT / MATING SURFACE. COMPLIED WITH EN 1090-10, NR 3 & NR 4 STRUT NAC WL 131 LWR AFT SPAR NAC STA 286 FILLER DOUBLER 65B94115-7 FOUND WITH SURFACE RUST.
- [SDR VGQY2010051900006](https://openairdocs.org/sdr/VGQY2010051900006.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > "SUPPLEMENTAL INFORMATION" - CORRECTIVE ACTION TO UNIQUE CONTROL VGQY2010051900006 - NR 1 ENGINE AFT UPPER MOUNT REMOVED AND REPLACED PER AMM 71-21-04 REV 90.
- [SDR VGQY2010051800005](https://openairdocs.org/sdr/VGQY2010051800005.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747281F · Engine Mount Section
  > DRWS NR 0020, NR 3 ENGINE AFT. UPPER MOUNT FOUND RUST. REMOVED AND REPROTECTED PER OHM CMM 71-20-02. MATERIAL REMOVED = 0.008", FOUND WITHIN LIMITS PER OHM CMM 71-20-02.
- [SDR VGQY2010051800006](https://openairdocs.org/sdr/VGQY2010051800006.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION PRODUCTS (RUST) NR 1 ENGINE - PYLON / AFT UPPER MOUNT / MATING SURFACE.
- [SDR VGQY2010051800004](https://openairdocs.org/sdr/VGQY2010051800004.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > NR 3 ENGINE AFT UPPER MOUNT FOUND CORRODED. MOUNT REMOVED PER AMM 71-21-03 REV 90. CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER OHM 71-20-02. MATERIAL REMOVED: 0.008 INCH. RE-INSTALLED PER AMM 71-21-03 REV 90.
- [SDR VGQY2010051800003](https://openairdocs.org/sdr/VGQY2010051800003.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION ON NR 2 ENGINE PYLON AFT UPPER MOUNT MATING SURFACE. MOUNT REMOVED PER AMM 71-21-03 REV 90. CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER OHM 71-20-02. MATERIAL REMOVED: 0.008 INCH. RE-INSTALLED PER AMM 71-21-03 REV 90.
- [SDR VGQY2010051800002](https://openairdocs.org/sdr/VGQY2010051800002.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION PRODUCTS (RUST) NR 4 ENGINE-PYLON / AFT UPPER MOUNT / MATING SURFACE. NR 4 ENGINE AFT UPPER MOUNT REWORKED AND REMOVED CORROSION PER OHM 71-20-02 REV 23, FIG 402, REPAIR 2G. MPI INSPECTION CARRIED OUT PER SOPM 20-20-01 REV 28. NO CRACK EVIDENT. R
- [SDR VGQY2010051800001](https://openairdocs.org/sdr/VGQY2010051800001.md): Mount · corroded · May 18, 2010 · N820SA · Boeing 747243B · Engine Mount Section
  > CORROSION PRODUCTS (RUST) NR 4 ENGINE / AFT LOWER MOUNT / MATING SURFACE. REMOVED AND REPLACED PER AMM 71-21-04 REV 90.
- [SDR VGQY2010070200043](https://openairdocs.org/sdr/VGQY2010070200043.md): Doubler · cracked · Jan 7, 2010 · N820SA · Boeing 747243B · Horizontal Stabilizer Miscellaneous Structure
  > RT HORZ STAB TIP AREA, MOST O/B RIB WEB LWR CHORD FOUND CRACK. REMOVED AND REPLACED EXISTING REPAIR DOUBLER PER SRM 52-30-06 REV 166, FIGURE 1. REPAIR DIMENSION: 12.50 INCH BY 6.00 INCH; INSPECTION THRESHOLD: 20,000 FLIGHT CYCLES FROM DELIVERY OF AIRPLANE;
- [SDR VGQY2010070100042](https://openairdocs.org/sdr/VGQY2010070100042.md): Support Fitting · corroded · Jan 7, 2010 · N820SA · Boeing 747243B · Main Landing Gear Attach Section
  > RIGHT WING LANDING GEAR INBOARD TRUNNION UPPER SUPPORT FITTING FORWARD OUTBOARD FASTENER HOLE AREA FOUND CORROSION AT BOLT HEAD SIDE. REMOVED CORROSION AND PFI PER SOPM 20-20-02. COMPLIED WITH EN 1122-10.
- [SDR VGQY2010070100041](https://openairdocs.org/sdr/VGQY2010070100041.md): Door · corroded · Jan 7, 2010 · N820SA · Boeing 747243B · Landing Gear Doors
  > RIGHT WING LANDING GEAR SHOCK STRUT DOOR - UPPER 'U' CAP FOUND CORRODED AT UPPER SIDE. REMOVED AND REPLACED RT WLG SHOCK STRUT UPPER DOOR PER AMM 32-12-07 REV 90.

## 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 = 'N820SA' AND deregistration_id = 'N820SA-2017-10-20'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N820SA-2017-10-20/reports

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