# Service difficulty reports: Lockheed P-3A

A list on [Lockheed P-3A](https://openairdocs.org/model/lockheed-p-3a.md).

Newest first. General aviation reporting is voluntary.

- [SDR 2021FA0000011](https://openairdocs.org/sdr/2021FA0000011.md): Control Panel · inflt separation · Sep 25, 2020 · N923AU · Lkheed P3A · Cabin Pressure Control System
  > DURING OPERATION AN AIR CONTROL PANEL FAILED AND SEPARATED FROM THE AIRCRAFT. THE AIR CONTROL PANEL FAILED BEHIND THE NUMBER 4 NACELLE. DUE TO THE FAILURE OF THE AIR CONTROL PANEL, THE TAILING EDGE SKIN IMMEDIATELY ABOVE THE AIR CONTROL PANEL ENCOUNTERED AN
- [SDR AUCR20110215004](https://openairdocs.org/sdr/AUCR20110215004.md): Fitting · cracked · Feb 15, 2011 · N921AU · Lkheed P3A · Fuselage, Wing Attach Fittings
  > DURING ANNUAL INSPECTION, A DETAILED ULTRA-SONIC INSPECTION OF THE FUSELAGE WING ATTACH RING FITTINGS WERE INITIATED BY OUR BY OUR INTERNAL SB. A FATIGUE CRACK WAS APPRECIATED IN THE RT FWD FITTING JUST BELOW THE UPPER MOST AFT HOLE ON THE VERTICAL OTBD FLANG
- [SDR AUCR20110215](https://openairdocs.org/sdr/AUCR20110215.md): Attach Fitting · cracked · Feb 15, 2011 · N921AU · Lkheed P3A · Fuselage, Wing Attach Fittings
  > DURING ANNUAL INSPECTION, A DETAILED ULTRA-SONIC INSPECTION OF THE FUSELAGE WING ATTACH RING FITTINGS WERE INITIATED BY AN INTERNAL SB. A FATIGUE CRACK WAS APPRECIATED IN THE LT FWD FITTING, VERTICAL OTBD FLANGE APPROX 6" ABOVE UPPER TENSION BOLT.
- [SDR AUCR20110215003](https://openairdocs.org/sdr/AUCR20110215003.md): Attach Fitting · cracked · Feb 15, 2011 · N917AU · Lkheed P3A · Fuselage, Wing Attach Fittings
  > DURING ANNUAL INSPECTION, A DETAILED ULTRA-SONIC INSPECTION OF THE FUSELAGE WING ATTACH RING FITTINGS WERE INITIATED BY AN INTERNAL SB. FATIGUE CRACKS WERE APPRECIATED IN THE RT FWD FITTING'S CHORDWISE FLANGE AT THE UPPER TENSION BOLT.
- [SDR AUCR20110215002](https://openairdocs.org/sdr/AUCR20110215002.md): Fitting · cracked · Feb 15, 2011 · N900AU · Lkheed P3A · Fuselage, Wing Attach Fittings
  > DURING ANNUAL INSP, A DETAILED ULTRA-SONIC INSP OF THE FUSELAGE WING ATTACH RING FITTINGS WERE INITIATED BY AN INTERNAL SB. A FATIGUE CRACK WAS APPRECIATED IN THE RT AFT FITTING'S VERTICAL OTBD FLANGE.
- [SDR AUCR20110215001](https://openairdocs.org/sdr/AUCR20110215001.md): Flange · cracked · Feb 15, 2011 · N900AU · Lkheed P3A · Fuselage Miscellaneous Structure
  > DURING ANNUAL INSPECTION A DETAILED ULTRA-SONIC INSPECTION OF THE FUSELAGE WING ATTACH RING FITTINGS WERE INITIATED BY AN INTERNAL SB. A FATIGUE CRACK WAS APPRECIATED IN THE RT FWD FITTING'S VERTICAL OTBD FLANGE.
- [SDR 2010FA0000923](https://openairdocs.org/sdr/2010FA0000923.md): Wheel Half · cracked · Aug 31, 2010 · N925A · Lkheed P3A · Wheel/Ski/Float
  > WHILE TOWING ACFT CREW NOTED EXCESSIVE NOISE FROM NR2 MAIN WHEEL ASSY. FURTHER INVESTIGATION REVEALED THE INBD HALF OF THE NR 2 WHEEL WAS FRACTURED, OUT FROM THE BRG CUP RACE SEAT OTBD TO ONE OF THE WHEEL HALF SPOKE HOLES.
- [SDR 2009FA0000757](https://openairdocs.org/sdr/2009FA0000757.md): Skin · cracked · Sep 3, 2009 · N925AU · Lkheed P3A · Wing, Plate/Skin
  > DISCREPANCY IDENTIFIED BY SLIGHT FUEL WEEP ON PREFLIGHT, LEFT WING STATION 90.5. FURTHER EVALUATION WITH ULTRASONIC NDT DISCLOSED A CRACK ON THE LOWER WING PANEL NO.3. THE CRACK EMANATED FROM ATTACH HOLE, THROUGH RISER AND APPROXIMATELY 1/2" INTO PLANK.
- [SDR 2009FA0000238](https://openairdocs.org/sdr/2009FA0000238.md): Fitting · cracked · Mar 20, 2009 · N920AU · Lkheed P3A · Wing, Attach Fittings
  > DURING PHASE DEPOT INSP THE LWR FWD LT RING FITTING, PN 903220-1 WAS FOUND FRACTURED THRU THE HORIZONTAL BOTTOM FLANGE AT THE FILLET NUT PLATE HOLE AND HAD PROPAGATED ACROSS THE BOTTOM WEB AND UP THE VERTICAL THROUGH TWO FASTENERS; THE FIRST.1875 INCHAND THE
- [SDR 2008FA0000724](https://openairdocs.org/sdr/2008FA0000724.md): Spar Cap · cracked · Oct 29, 2008 · N921A · Lkheed P3A · Wing Spar
  > DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A TERTIARY FRACTURE WAS FOUND ON THE FORWARD SPAR CAP, HORIZONTAL FLANGE, WING STA 143.5. THE FRACTURE WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY CURRENT. AN INTERNAL VISUAL EXAMINATION IDEN
- [SDR 2008FA0000723](https://openairdocs.org/sdr/2008FA0000723.md): Spar Cap · cracked · Oct 29, 2008 · N921A · Lkheed P3A · Wing Spar
  > DURING FURTHER EVALUATION FOLLOWING PREVIOUSLY REPORTED DAMAGE A SECOND CRACK WAS FOUND ON THE FORWARD LOWER CAP AT BUTTLINE 56R. THE CRACK WAS VISUALLY IDENTIFIED AND CONFIRMED WITH EDDY-CURRENT SURFACE SCAN.
- [SDR 2008FA0000704](https://openairdocs.org/sdr/2008FA0000704.md): Spar Cap · fractured · Oct 24, 2008 · N921AU · Lkheed P3A · Wing Spar
  > DURING INSPECTION TO DETERMINE THE SOURCE OF A FUEL LEAK A FRACTURE WAS FOUND IN THE LOWER FORWARD RIGHT SPAR CAP AT WING STA 75 EMANATING FROM NUT PLATE FASTENER HOLE ON FORWARD FLANGE TO THE EDGE OF FLANGE MEMBER WITH SLIGHT ENCROACHMENT AFT FROM SAME HOLE,
- [SDR AUCR200600006](https://openairdocs.org/sdr/AUCR200600006.md): Spar Cap · cracked · May 31, 2006 · N900AU · Lkheed P3A · Wing Spar
  > DURING SCHEDULED INSPECTION FOUND CORROSION INDUCED CRACK IN UPPER AFT SPAR CAP EXTENDING OUTBOARD FROM PREVIOUS REPAIR IN THE AREA OF FLAP TRACK 5, WS 346. DURING DISASSEMBLY TO EFFECT REPAIR FOUND ADDITIONAL STRESS CORROSION FRACTURE ON UPPER AFT SPAR CAP A
- [SDR 200600005](https://openairdocs.org/sdr/200600005.md): Panel · cracked · Apr 27, 2006 · N925AU · Lkheed P3A · Wing, Plate/Skin
  > NR 2 FUEL CELL LOWER WING SKIN, PLANK NR 2 CRACKED RISER. NO SRM STANDARD REPAIR FOR THIS DAMAGE. REPAIR WILL BE ACCOMPLISHED IAW EO 462557001.
- [SDR AUCR200600004](https://openairdocs.org/sdr/AUCR200600004.md): Skin Panel · damaged · Apr 27, 2006 · N925AU · Lkheed P3A · Wing, Plate/Skin
  > BOTTOM LT WING WS68.5, 4 FUEL BOOST PUMP SCREEN ATTACHING HOLES ELONGATED IN NR 17 AND NR 18 RISER.
- [SDR AUCR200600003](https://openairdocs.org/sdr/AUCR200600003.md): Panel · cracked · Apr 27, 2006 · N925AU · Lkheed P3A · Wing, Plate/Skin
  > CRACKED RISER, NR 4 FUEL TANK LOWER PLANK NR 4 AT NR 27 RISER WS397R.
- [SDR AUCR200600002](https://openairdocs.org/sdr/AUCR200600002.md): Spar Cap · corroded · Mar 21, 2006 · N922A · Lkheed P3A · Wing Spar
  > UPPER REAR SPAR CAP STRESS CORROSION CRACKED IN AFT RADIUS FORWARD OF NR 4 FLAP HANGER. DAMAGE CENTERED AT WS275. DAMAGE WAS INITIALLY DETECTED VISUALLY DURING SCHEDULED SPECIAL INSPECTION. DAMAGE WAS FURTHER EVALUATED WITH EDDY CURRENT INSPECTION AND WAS F
- [SDR AUCR200600001](https://openairdocs.org/sdr/AUCR200600001.md): Panel · cracked · Feb 1, 2006 · N927AU · Lkheed P3A · Wing, Plate/Skin
  > LT WING, STA. 82, 2.9 IN. FRACTURE IN NR 7 PLANK FORWARD TANG. FRACTURE WAS LOCATED BY ULTRASONIC INSPECTION DURING EVALUATION OF FUEL STAIN AT ANNUAL INSPECTION. THERE EXISTS AN APPROVED REPAIR FOR THIS DAMAGE IN THE SRM.
- [SDR AUCR200500005](https://openairdocs.org/sdr/AUCR200500005.md): Skin Panel · corroded · Dec 2, 2005 · N426NA · Lkheed P3A · Wing, Plate/Skin
  > RT WING LOWER SKIN PANEL NR 7 AT BUTT LINE 65 INTERNAL INTERGRANULAR CORROSION. THE DEFECTIVE PANEL WAS FIRST DETECTED BY A FUEL LEAK AT BUTT LINE 65. FURTHER INVESTIGATION REVEALED EXFOLIATION FROM INTERGRANULAR CORROSION. THE CORROSION WAS CONCEALED BY LAYER
- [SDR AUCR200500004](https://openairdocs.org/sdr/AUCR200500004.md): Spar Cap · corroded · Dec 1, 2005 · N917AU · Lkheed P3A · Wing Spar
  > RT WING UPPER FORWARD SPAR CAP W.S.73 (PREVIOUS PROCESSING BY PARTY UNKNOWN) OF THE FORWARD FLANGE HAS EXCEEDED MAXIMUM NEGLIGIBLE LIMITS FOR DAMAGE LOCATION. DUE TO THE RELATIVE LOCATION OF THE WING ATTACH CORNER FITTING THIS DAMAGE CANNOT BE REPAIRED AND WIL
- [SDR AUCR200500003](https://openairdocs.org/sdr/AUCR200500003.md): Spar Cap · corroded · Dec 1, 2005 · N917AU · Lkheed P3A · Wing Spar
  > RT WING REAR SPAR UPPER CAP WS178 AT NACELLE AFT ATTACH PLATE. DISSIMILAR METAL CORROSION ATTACKING UPPER CROWN AND AND VETICAL LEG OF THE SPAR CAP. CORROSION WAS VISUALLY DETECTED AT SCHEDULED DEPOT LEVEL INSPECTION. CORROSION EXCEEDED MAXIMUM NEGLIGIBLE LIMI
- [SDR AUCR200500002](https://openairdocs.org/sdr/AUCR200500002.md): Spar Cap · corroded · Dec 1, 2005 · N917AU · Lkheed P3A · Wing Spar
  > LT WING UPPER REAR SPAR CAP WS178, AT NACELLE AFT ATTACH PLATE. DISSIMILAR METAL CORROSION ATTACK UPPER CROWN AND VERTICAL LEG. CORROSION WAS VISUALLY DETECTED AT DEPOT LEVEL SCHEDULED INSPECTION. CORROSION WAS FOUND TO EXCEED NEGLIGIBLE DAMAGE LIMITS.
- [SDR AUCR200500001](https://openairdocs.org/sdr/AUCR200500001.md): Panel · cracked · Dec 1, 2005 · N917AU · Lkheed P3A · Wing, Plate/Skin
  > LOCATED LOWER WING PLANK RISER FRACTURE 7 INCHES IN LENGTH LT WING STA. 167. FRACTURE EMANATED ALONG BASE OF RISER EXTENDING IB AND OB SPANWISE. FRACTURE WAS VISUALLY DETECTED DURING SCHEDULED INSPECTION. FRACTURE WAS PROPAGATED BY THE MAIN LANDING GEAR TRUSS
- [SDR AUC2003F00001](https://openairdocs.org/sdr/AUC2003F00001.md): Tire · failed · Jul 30, 2003 · N900AU · Lkheed P3A · Tire
  > WHEEL ASSEMBLY WITH RECAPPED TIRES INSTALLED ON AIRCRAFT. THESE TIRES INSTALLED FOR A TOTAL OF 10 DAY AND OPERATED FOR A TOTAL OF 28 FLIGHT HOURS. UPON TAKE OFF ONE OF THE NOSE WHEELS LOST THE CENTER PORTION OF THE TIRE TREAD. THE FLIGHT CREW EXPERIENCED AN
- [SDR AUC2003F00000](https://openairdocs.org/sdr/AUC2003F00000.md): Tire · failed · Jul 30, 2003 · N927AU · Lkheed P3A · Tire
  > WHEEL ASSEMBLY WITH RECAPPED TIRES INSTALLED ON AIRCRAFT. THESE TIRES INSTALLED FOR A TOTAL OF 7 DAYS AND OPERATED FOR A TOTAL OF 14 FLIGHT HOURS. UPON TAKEOFF, ONE OF THE NOSE WHEELS LOST THE CENTER PORTION OF THE TIRE TREAD. THE FLIGHT CREW EXPERIENCED A
- [SDR 2003FA0000529](https://openairdocs.org/sdr/2003FA0000529.md): Skin · cracked · Apr 14, 2003 · N925AU · Lkheed P3A · Wing, Center Box
  > DURING ANNUAL (SPECIAL) INSPECTION CRACKS IN THE WING CENTER BOX PLANK NR 1 AND NR 3 WERE FOUND EMITTING FROM THE INTERNAL WEEP HOLES LOCATED NTHE INTERNAL PLANK RISERS. CRACK IN NR 1 PLANK, RT SIDE WAS ABOUT 3 INCHES LONG AND A 1 INCH CRACK IN SAME PLANK ON
- [SDR 20010312CW001](https://openairdocs.org/sdr/20010312CW001.md): Elt · unstable · Feb 12, 2001 · N927AU · Lkheed P3A · Emergency Locator Beacon
  > ELT SELF ACTIVATED. THIS UNIT WAS SENT TO THE FACTORY FOR WARRANTY REPAIR FOR THE SAME DEFECT 2 MOS EARLIER. AIRCRAFT WAS SITTING ON RAMP WITH NO POWER. ELT WENT OFF AT 2AM. UNITS HAVE A POOR SELF ACTIVATION RATE.
- [SDR 20001207SH018](https://openairdocs.org/sdr/20001207SH018.md): G Switch · will not test · Nov 16, 2000 · N927AU · Lkheed P3A · Emergency Locator Beacon
  > DURING ANNUAL TEST OF ELT PER FAR 91.207(S), FOUND G-SWITCH WOULD NOT ACTIVATE. (X)

## 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 aircraft_model_key = 'P3A'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/lockheed-p-3a/reports

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