# Service difficulty reports: N72821, cancelled May 17, 2005

A list on [N72821, cancelled May 17, 2005](https://openairdocs.org/deregistered/N72821-2005-05-17.md).

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

- [SDR CALA0400628](https://openairdocs.org/sdr/CALA0400628.md): Beam · corroded · Sep 4, 2004 · N72821 · Doug DC982 · Fuselage Main, Bulkhead
  > INSPECTION FOUND BULKHEAD BEAM WEB CORRODED AT STA 110, S30L. THE BEAM WEB WAS REPAIRED IAW ECRA 5310-04387.
- [SDR CALA0300697](https://openairdocs.org/sdr/CALA0300697.md): Beam · corroded · Nov 20, 2003 · N72821 · Doug DC982 · Fuselage Main, Bulkhead
  > INSPECTION FOUND STA 110 BULKHEAD BEAM WEB CORRODED AT MAIN BATTERY GROUND STUD HOLE. THE BEAM WEB WAS REPAIRED IAW ECRA 5310-04387.
- [SDR CALA0200438](https://openairdocs.org/sdr/CALA0200438.md): Seat Track · corroded · Aug 9, 2002 · N72821 · Doug DC982 · Fuselage, Seat/Cargo Attach Fittings
  > INSPECTION FOUND L/H CENTER SEAT TRACK CORRODED BETWEEN STA 1079 AND 1136. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-5.
- [SDR CALA0200437](https://openairdocs.org/sdr/CALA0200437.md): Web · corroded · Aug 9, 2002 · N72821 · Doug DC982 · Fuselage Miscellaneous Structure
  > INSPECTION FOUND E&E COMPARTMENT SUBFLOOR CORRODED AT VENTRAL STAIR MECHANISM, STA 162-168, X = 54.000. A DOUBLER WAS INSTALLED IAW SRM 51-70-4.
- [SDR CALA0200436](https://openairdocs.org/sdr/CALA0200436.md): Seat Track · corroded · Aug 7, 2002 · N72821 · Doug DC982 · Fuselage, Seat/Cargo Attach Fittings
  > INSPECTION FOUND R/H CENTER AND R/H I/B SEAT TRACKS CORRODED AT STA 228. THE CORRODED SEAT TRACK SECTIONS WERE REMOVED AND NEW SECTIONS WERE SPLICED IN IAW SRM 53-05, FIGURE 4F AND 51-30-0.
- [SDR CALA0100757](https://openairdocs.org/sdr/CALA0100757.md): Skin · dented · Aug 10, 2001 · N72821 · Doug DC982 · Fuselage Main, Plate/Skin
  > THE R/H FUSELAGE SKIN WAS DENTED BETWEEN FORWARD CARGO DOOR AND RIGHT TURN OFF LIGHT AT STA 435-510 BETWEEN LONGERONS 20R AND 21R. A FLUSH SKIN PANEL REPAIR WAS INSTALLED IAW SRM 53-04, FIGURE 12C.
- [SDR CALA0100756](https://openairdocs.org/sdr/CALA0100756.md): Longeron · cracked · Aug 10, 2001 · N72821 · Doug DC982 · Fuselage Main, Longeron/Stringer
  > INSPECTION FOUND A 10" CRACK AT END OF LONGERON 2L AT STA 1418. A HAT SECTION REPAIR SPLICE WAS INSTALLED IAW SRM 53-02, FIGURE 18.
- [SDR CALA0100755](https://openairdocs.org/sdr/CALA0100755.md): Angle · cracked · Aug 10, 2001 · N72821 · Doug DC982 · Fuselage Miscellaneous Structure
  > INSPECTION FOUND A.25 INCH CRACK IN TAIL COMPARTMENT LEFT VENTRAL BOX SUPPORT ANGLE AT CANTED FRAME STA 1474. THE SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-05.
- [SDR CALA0100753](https://openairdocs.org/sdr/CALA0100753.md): Fitting · cracked · Aug 9, 2001 · N72821 · Doug DC982 · Fuselage Miscellaneous Structure
  > INSPECTION FOUND A 2 INCH CRACK IN TAIL COMPARTMENT SUPPORT FITTING BETWEEN CANTED FRAMES 1463 AND 1485 AT LOWER AFT SIDE. THE SUPPORT FITTING WAS REMOVED AND A NEW FITTING WAS INSTALLED IAW SRM 51-10-4.
- [SDR CALA0100752](https://openairdocs.org/sdr/CALA0100752.md): Plate · corroded · Aug 9, 2001 · N72821 · Doug DC982 · Horizontal Stabilizer Structure
  > INSPECTION FOUND HORIZONTAL STABILIZER PIVOT PLATE CORRODED AT LEFT I/B LUG BORES. THE PIVOT PLATES WERE REMOVED AND REPLACED IAW EA 5530-01238.
- [SDR CALA0100751](https://openairdocs.org/sdr/CALA0100751.md): Plate · corroded · Aug 9, 2001 · N72821 · Doug DC982 · Horizontal Stabilizer Structure
  > INSPECTION FOUND HORIZONTAL STABILIZER PIVOT PLATES CORRODED AT RIGHT O/B AND RIGHT I/B LUG BORES. THE PIVOT PLATES WERE REMOVED AND REPLACED IAW EA 5530-01238.
- [SDR CALA0100750](https://openairdocs.org/sdr/CALA0100750.md): Frame · cracked · Aug 9, 2001 · N72821 · Doug DC982 · Fuselage Main, Frame
  > INSPECTION FOUND A 2" CRACK IN TAIL COMPARTMENT CANTED FRAME AT STA 1474, LEFT LOWER SIDE, BY VENT BOX DRAIN HOSE. REPAIRED IAW ECRA 5310-04173.
- [SDR CALA0100747](https://openairdocs.org/sdr/CALA0100747.md): Attach Angle · cracked · Aug 8, 2001 · N72821 · Doug DC982 · Fuselage, Stabilizer Attach Fittings
  > INSPECTION FOUND A 3/4" CRACK COMING FROM RIVET HOLE IN R/H SIDE VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE AT STA 1463. THE CRACKED AREA WAS CUT OUT AND A REPAIR ANGLE WAS INSTALLED IAW SRM 53-05, FIGURE 23.
- [SDR CALA0100743](https://openairdocs.org/sdr/CALA0100743.md): Pan · cracked · Aug 7, 2001 · N72821 · Doug DC982 · Landing Gear Doors
  > INSPECTION FOUND A 1" CRACK IN L/H MLG I/B DOOR PAN AT LEADING EDGE. THE DOOR PAN WAS REMOVED AND REPLACED IAW SRM 51-30-2, 51-30-3, 51-30-8, AND 51-10-2.
- [SDR CALA9901487](https://openairdocs.org/sdr/CALA9901487.md): Skin · cracked · Nov 12, 1999 · N72821 · Doug DC982 · Wing, Plate/Skin
  > INSPECTION FOUND A 3 CRACK IN RT WING LEADING EDGE UPPER SKIN AT STA XOS 286. A DOUBLER WAS INSTALLED IAW ECRA 5720-01773 AND A DIP WAS INITIATED TO REINSPECT THE REPAIR AT INTERVALS NOT TO EXCEED 14 DAYS AND TO INSTALL A PERMANENT REPAIR WITHIN 12 MONTHS.
- [SDR CALA9900245](https://openairdocs.org/sdr/CALA9900245.md): Skin · cracked · Mar 11, 1999 · N72821 · Doug DC982 · Service Doors
  > INSPECTION FOUND A 1 INCH CRACK IN AFT SERVICE DOOR SKIN AT TOP AFT EDGE OF HOLD OPEN HOOK CUTOUT. REPAIRED IAW ECRA 5205-01008.
- [SDR CALA9900243](https://openairdocs.org/sdr/CALA9900243.md): Bayonet · worn · Mar 10, 1999 · N72821 · Doug DC982 · Aerodynamic Fairings
  > THE FORCE REQUIRED TO RELEASE TAIL CONE USING EXTERNAL HANDLE WAS LOW. THE LEFT LOWER TAIL CONE BAYONET WAS REMOVED AND REPLACED DUE TO WEAR. AN ADJUSTMENT/TEST OF THE TAIL CONE RELEASE MECHANISM WAS PERFORMED IAW MM 53-53-00.
- [SDR CALA9900236](https://openairdocs.org/sdr/CALA9900236.md): Pan · cracked · Mar 9, 1999 · N72821 · Doug DC982 · Cargo/Baggage Doors
  > INSPECTION FOUND A 2.25 INCH CRACK IN AFT CARGO DOOR PAN AT FORWARD HOLD OPEN LATCH AND A.75 INCH CRACK IN AFT CARGO DOOR PAN AT AFT HOLD OPEN LATCH. INSTALLED REPAIRS IAW ECRA 5321-01010.
- [SDR CALA9900228](https://openairdocs.org/sdr/CALA9900228.md): Beam · cracked · Mar 6, 1999 · N72821 · Doug DC982 · Passenger/Crew Doors
  > INSPECTION FOUND TWO CRACKS IN THE NR 1 BEAM OF MAIN CABIN DOOR. THE BEAM HAD A.75 INCH CRACK ON AFT END AND A.375 INCH CRACK ON FORWARD END.
- [SDR CALA9900227](https://openairdocs.org/sdr/CALA9900227.md): Seat Track · corroded · Mar 5, 1999 · N72821 · Doug DC982 · Fuselage, Seat/Cargo Attach Fittings
  > INSPECTION FOUND SEAT TRACK CORRODED AROUND SCREW HOLES AT LT I/B POSITION, STA 1117-1174 AFT GALLEY AREA. NEW SEAT TRACK SECTIONS WERE INSTALLED IAW SRM 53-05.
- [SDR CALA9900224](https://openairdocs.org/sdr/CALA9900224.md): Skin · dented · Mar 5, 1999 · N72821 · Doug DC982 · Fuselage Main, Plate/Skin
  > INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 237 ABOVE CUSP. A NEW SKIN SECTION WAS INSTALLED BETWEEN LONGERON 15L AND 18L IAW ECRA 5330-02445.
- [SDR CALA9900221](https://openairdocs.org/sdr/CALA9900221.md): Pan · cracked · Mar 4, 1999 · N72821 · Doug DC982 · Cargo/Baggage Doors
  > INSPECTION FOUND A 1.5 INCH CRACK IN MID CARGO BIN DOOR PAN. THE CRACK WAS STOP DRILLED AND A DOUBLER REPAIR WAS INSTALLED IAW SRM 52-05, FIGURE 26A.
- [SDR CALA9900220](https://openairdocs.org/sdr/CALA9900220.md): Seat Track · corroded · Mar 4, 1999 · N72821 · Doug DC982 · Fuselage, Seat/Cargo Attach Fittings
  > INSPECTION FOUND LEFT CENTER SEAT TRACK CORRODED AROUND SCREW HOLES FROM GALLEY NR 3 TO GALLEY NR 4 AREA, STA 1117 TO 1174. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 4F.
- [SDR CALA9900212](https://openairdocs.org/sdr/CALA9900212.md): Angle · corroded · Mar 3, 1999 · N72821 · Doug DC982 · Fuselage Miscellaneous Structure
  > INSPECTION FOUND AFT CARGO COMPARTMENT Z-ANGLE CORRODED. THE Z-ANGLE WAS REMOVED AND REPLACED IAW SRM 53-05, FIGURE 63 AND 51-30-5.
- [SDR CALA9800659](https://openairdocs.org/sdr/CALA9800659.md): Sensor · inoperative · Apr 15, 1998 · N72821 · Doug DC982 · Landing Gear Position and Warning
  > THE AIRCRAFT HAD A BRIEF HISTORY OF THE NOSE GEAR UNSAFE LIGHT REMAINING ILLUMINATED AFTER TAKEOFF. CYCLING THE GEAR WOULD EXTINGUISH THE LIGHT. THE NOSE GEAR LOCK SENSOR WAS REMOVED AND REPLACED IAW MM 32-60-05, PAGES 216-220. THE NOSE GEAR WAS SWUNG WITH O
- [SDR CALA9700365](https://openairdocs.org/sdr/CALA9700365.md): Skin · damaged · Mar 12, 1997 · N72821 · Doug DC982 · Fuselage Main, Plate/Skin
  > FINGER DOUBLERS WERE INSTALLED TO FUSELAGE SKIN AT STA 427 TO 507, LONGERON 20L IAW SRM 53-04, FIGURE 12B. THE SKIN DAMAGE HAD BEEN REPAIRED PREVIOUSLY AND DEFERRED PER DIP NR D16874.
- [SDR CALA9700363](https://openairdocs.org/sdr/CALA9700363.md): Channel · cracked · Mar 12, 1997 · N72821 · Doug DC982 · Fuselage Miscellaneous Structure
  > INSPECTION FOUND A 1 INCH CRACK IN RT MLG INBOARD DOOR FORWARD JAMB CHANNEL. A REPAIR WAS INSTALLED IAW SRM 53-01, FIGURE 2.
- [SDR CAL950872](https://openairdocs.org/sdr/CAL950872.md): Skin · torn · Sep 25, 1995 · N72821 · Doug DC982 · Fuselage Main, Plate/Skin
  > TUS - FLT 0425 - INSPECTION FOUND A 1.5 INCH TEAR IN FUSELAGE SKIN AND DAMAGE TO TWO SKIN CLIPS DUE TO GROUND DAMAGE. THE DAMAGE WAS LOCATED AT STA 427-STA 507 AND LONGERONS 19L AND 20L. THE SKIN TEAR WAS REPAIRED IAW ECRA 5330-02317 AND SRM 53-04, FIGURE 12
- [SDR CAL950464](https://openairdocs.org/sdr/CAL950464.md): Eel Pwr Supply · inoperative · Jun 7, 1995 · N72821 · Doug DC982 · Emergency Lighting
  > FLT NR 0305 - EWR - BOTH OVERWING EMERGENCY EXIT LIGHTS WERE FOUND INOPERATIVE. THE POWER SUPPLY WAS REPLACED AND OPERATION OF THE OVERWING EMERGENCY EXIT LIGHTS WAS RESTORED. (M)

## 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 = 'N72821' AND deregistration_id = 'N72821-2005-05-17'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N72821-2005-05-17/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, except the copies of manufacturers’ service documents, which belong to their rights holders.