# Service difficulty reports: N11FQ

A list on [N11FQ](https://openairdocs.org/aircraft/N11FQ.md).

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

- [SDR 2A6D20240614001](https://openairdocs.org/sdr/2A6D20240614001.md): Attach Angle · cracked · Jun 14, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Attach Fittings
  > DAMAGE TO THE BAGGAGE COMPARTMENT LH FWD LOWER ANGLE (P/N: 350A210053.28) IN THE FORM OF GOUGE/CRACK. THE GOUGE/CRACK DAMAGE MEASURED TO BE APPROXIMATELY 0.13” IN DIAMETER.
- [SDR 2A6D20240528001](https://openairdocs.org/sdr/2A6D20240528001.md): Frame · corroded · May 28, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Frame
  > DAMAGE TO THE AFT UPPER FRAME (P/N: 350A21-1242.35) IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS ON THE UPPER FLANGE OF FRAME AT LH AND RH BOTTOM SIDE NEAR THE AFT LOWER FRAME. THE LH SIDE CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 0.71: X 2.05” AND TH
- [SDR 2A6D20240509003](https://openairdocs.org/sdr/2A6D20240509003.md): Floorbeam · corroded · May 9, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Floor Beam
  > DAMAGE IS ON THE LH CABIN FLOOR EDGE FITTING (P/N: 350A214753.20) IN THE FORM OF CORROSION AND CRACKS. THE LH FITTING PLATE IS EXCESSIVELY CORRODED AND THE CRACK DAMAGES AT TWO FASTENER HOLES TO EOP WHICH RESULTS IN REPLACEMENT OF LH FITTING.
- [SDR 2A6D20240509002](https://openairdocs.org/sdr/2A6D20240509002.md): Bonding Plate · corroded · May 9, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Structure
  > DAMAGE IS ON THE TAIL BOOM VHF ANTENNA BASE PLATE (P/N: 350A65-1707.00) IN THE FORM OF CORROSION. THE BASE PLATE IS EXCESSIVELY CORRODED AND DEPTH OF THE DAMAGE IS ALL THE WAY THROUGH THICKNESS WHICH RESULTS IN REPLACEMENT OF ANTENNA BASE PLATE.
- [SDR 2A6D20240509001](https://openairdocs.org/sdr/2A6D20240509001.md): Bulkhead · corroded · May 9, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Bulkhead
  > THE UPPER 7° BULKHEAD DOUBLER (PN: 350A21-0849.20) IS CORRODED AT THE LOCATION OF A PASS-THRU HOLE. THE DAMAGE AREA WAS REPORTED TO BE 0.80” X 0.50” AND 0.030” DEEP AT THE DEEPEST POINT
- [SDR 2A6D20240508003](https://openairdocs.org/sdr/2A6D20240508003.md): Crosstube · corroded · May 8, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Structure
  > THE AFT LANDING GEAR CROSSTUBE FITTING (PN: 350A21-0960.20) IS CORRODED IN MULTIPLE AREAS ON THE LOWER SURFACE. THE DEEPEST DAMAGE AREA WAS REPORTED TO BE 0.022” DEEP AND THE LARGEST AREA IS APPROXIMATELY 0.40” WIDE WITH VARIOUS LENGTHS
- [SDR 2A6D20240508002](https://openairdocs.org/sdr/2A6D20240508002.md): Crossbeam · corroded · May 8, 2024 · N11FQ · Urocop EC130T2 · Fuselage Structure (General)
  > THE RH X2244 CROSSBEAM (PN: 350A21-0861.20) IS CORRODED IN AN AREA ON THE LOWER OUTBOARD CORNER OF THE CROSSBEAM. THE DAMAGE WAS REPORTED TO BE 0.572” X 0.179” AND 0.028” DEEP
- [SDR 2A6D20240508001](https://openairdocs.org/sdr/2A6D20240508001.md): Crossbeam · corroded · May 8, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Structure
  > THE RH X1790 CROSSBEAM (PN: 350A21-0572.20) IS CORRODED IN AN AREA WHERE IT CONTACTS THE RH Y400 BEAM (PN: 350A21-0587.20)
- [SDR 2A6D20240425009](https://openairdocs.org/sdr/2A6D20240425009.md): Skin Panel · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Plate/Skin
  > CORROSION DAMAGE ON THE FWD UPPER SKIN MEASURED TO BE APPROXIMATELY 0.80” X 0.60” X 0.003”
- [SDR 2A6D20240425008](https://openairdocs.org/sdr/2A6D20240425008.md): Stiffener · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Rotorcraft Tail Boom
  > DAMAGE TO THE TAIL BOOM LH FWD STIFFENER MEASURED TO BE APPROXIMATELY 0.85” X 0.85” X 0.0125” IN THE FORM OF CORROSION.
- [SDR 2A6D20240425007](https://openairdocs.org/sdr/2A6D20240425007.md): Attach Angle · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage, Landing Gear Attach Fittings
  > REAR LANDING GEAR ATTACHMENT LOWER ANGLE HAS DAMAGE IN THE FORM OF CORROSION. THE DAMAGE NEAR THE ANGLE OVERLAPS WITH MACHINED FRAME AND AFT LOWER BELLY FAIRING. THE DAMAGE IS ON THE VERTICAL FACE OF THE ANGLE AT PREVIOUS REPAIR LOCATION AND IS MEASURED TO BE
- [SDR 2A6D20240425006](https://openairdocs.org/sdr/2A6D20240425006.md): Cradle · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuel Storage
  > RH AFT FUEL CRADLE REINFORCEMENTS HAS DAMAGE IN THE FORM OF CORROSION. THE RH AFT CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 2.1” X 0.80” X 0.009”.
- [SDR 2A6D20240425005](https://openairdocs.org/sdr/2A6D20240425005.md): Cradle · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuel Storage
  > THE LH FWD FUEL CRADLE REINFORCEMENTS HAD DAMAGE IN THE FORM OF CORROSION. THE LH FWD CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 1.0” X 0.80” X 0.008”.
- [SDR 2A6D20240425004](https://openairdocs.org/sdr/2A6D20240425004.md): Skin Panel · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Plate/Skin
  > DAMAGE IS ON THE AFT FUSELAGE RH SIDE SKIN PANEL (P/N: 350A210046-21 IN THE FORM OF CORROSION. THE RH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15” X 0.20” X 0.011”.
- [SDR 2A6D20240425003](https://openairdocs.org/sdr/2A6D20240425003.md): Skin Panel · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage Main, Plate/Skin
  > FIRST DAMAGE IS ON THE AFT FUSELAGE LH SIDE SKIN PANEL IN THE FORM OF CORROSION. THE LH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15” X 0.35” X 0.009”.
- [SDR 2A6D20240425002](https://openairdocs.org/sdr/2A6D20240425002.md): Brace · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage Miscellaneous Structure
  > DAMAGE TO THE LH VERTICAL ANGLE (PN: 350A62-1148.21) ON THE AFT SECTION FWD LOWER FRAME IN THE FORM OF CORROSION. THE CORRODED AREA IS LOCATED AT THE BOTTOM END OF THE ANGLE, AND WAS MEASURED TO BE APPROXIMATELY 0.875” X 0.875” IN SIZE THROUGH THE FULL THICKNE
- [SDR 2A6D20240425001](https://openairdocs.org/sdr/2A6D20240425001.md): Web · corroded · Apr 25, 2024 · N11FQ · Urocop EC130T2 · Fuselage Miscellaneous Structure
  > DAMAGE TO THE LOWER CENTER WEB IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS TOWARDS THE AFT SIDE OF THE WEB NEAR LIGHTENING HOLES AND MEASURED TO BE THROUGH THICKNESS IN DEPTH.
- [SDR 2A6D20240320001](https://openairdocs.org/sdr/2A6D20240320001.md): Support Angle · corroded · Mar 20, 2024 · N11FQ · Urocop EC130T2 · Fuselage Miscellaneous Structure
  > EXFOLIATION CORROSION LOCATED ON FWD. L/H SIDE STIFFENER OF MASTER ELECTRICAL BOX.
- [SDR 2A6D20240201002](https://openairdocs.org/sdr/2A6D20240201002.md): Web · corroded · Feb 1, 2024 · N11FQ · Urocop EC130B4 · Fuselage Miscellaneous Structure
  > DAMAGE TO THE LOWER CENTER WEB (P/N: 350A21-4300.20) IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS TOWARDS THE AFT SIDE OF THE WEB NEAR LIGHTENING HOLES AND MEASURED TO BE THROUGH THICKNESS IN DEPTH.
- [SDR 2A6D20240201001](https://openairdocs.org/sdr/2A6D20240201001.md): Angle · corroded · Feb 1, 2024 · N11FQ · Urocop EC130B4 · Fuselage Miscellaneous Structure
  > DAMAGE TO THE LH VERTICAL ANGLE (PN: 350A62-1148.21) ON THE AFT SECTION FWD LOWER FRAME IN THE FORM OF CORROSION. THE CORRODED AREA IS LOCATED AT THE BOTTOM END OF THE ANGLE, AND WAS MEASURED TO BE APPROXIMATELY 0.875” X 0.875” IN SIZE THROUGH THE FULL THICKNE
- [SDR HCMA201407170001](https://openairdocs.org/sdr/HCMA201407170001.md): Bolt · loose · Jul 15, 2014 · N11FQ · Urocop EC130T2 · Main Rotor Mast/Swashplate
  > THE DIGITAL NR READING WAS FLUCTUATING IN FLIGHT. AFTER TROUBLESHOOTING OF THE NR PICKUP ON THE NR GAUGE, IT WAS DECIDED TO INSPECT THE PHONIC WHEEL FOR SECURITY. UPON REMOVAL OF THE EPICYCLIC, IT WAS FOUND THAT SIX ATTACHMENT BOLTS, 2 WERE TORQUED TO 100 IN
- [SDR HCM2014F00000](https://openairdocs.org/sdr/HCM2014F00000.md): Engine · making metal · May 2, 2014 · N11FQ · Urocop EC130T2 · Engine (Turbine/Turboprop)
  > DURING FLIGHT, ENGINE CHIP LIGHT ILLUMINATED AND PILOT MADE A PRECAUTIONARY LANDING. MECHANIC INSPECTED ENGINE CHIP PLUGS. A SIGNIFICANT AMOUNT OF METAL WAS FOUND ON THE ELECTRIC PLUG, MODULE 01 CHIP PLUG AND THE ENGINE OIL TANK CHIP PLUG. IT WAS DETERMINE

## 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 = 'N11FQ' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N11FQ/reports

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