# Service difficulty reports: Turbomeca ARRIEL-2D

A list on [Turbomeca ARRIEL-2D](https://openairdocs.org/engine/turbomeca-arriel-2d.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 3 · 138 reports

- [SDR QMLA 202608272006](https://openairdocs.org/sdr/QMLA%20202608272006.md): Main Rotor · fod · Aug 27, 2026 · N213SH · Urocop EC130T2 · Main Rotor Head
  > JUST PRIOR TO LANDING, A SMALL PLASTIC BAG FLOATED UP AND INTO THE MAIN ROTOR SYSTEM. IT BLEW OUT ALMOST IMMEDIATELY AFTER THE FACT. A NORMAL LANDING AND SHUTDOWN WERE PERFORMED.
- [SDR QMLA2026071820047](https://openairdocs.org/sdr/QMLA2026071820047.md): Bearing · faulted · Jul 15, 2026 · N106VU · Urocop EC130T2 · Hydraulic Pump (Electric/Engine), Main
  > PILOTS REPORT "AFTER ILLUMINATION OF THE HYD2 AND SERVO LIGHTS, NURSE AND MEDIC SAW WHITISH GRAY SMOKE FROM VICINITY IN FRONT OF THE CABIN TDFM RADIO CONTROL HEAD, NEAR THE O2 SHUT-OFF LEVER. I SMELLED A BURNT RUBBER SMELL BUT NEVER SAW ANY SMOKE WHEN I LOOKE
- [SDR PG9A2026070600568](https://openairdocs.org/sdr/PG9A2026070600568.md): Hydraulic System · faulted · Jul 4, 2026 · N699GC · Urocop EC130T2 · Hydraulic System, Main
  > AIRCRAFT WAS DOING LEFT 180 AT QUARTERMASTER CANYON FOR BURNT SPRINGS PILOT STARTED TO NOTICE A STRANGE ODOR IN THE AIRCRAFT. ABOUT 5 SECONDS LATER, A TON OF WHITE SMOKE STARTED TO POUR INTO THE CABIN THROUGH THE A/C VENTS. PILOT IMMEDIATELY TURNED OFF THE A/
- [SDR 9SZA202607100147](https://openairdocs.org/sdr/9SZA202607100147.md): Terminal · loose · Mar 24, 2026 · N362AC · Snias AS350B3 · Fire Protection System Wiring
  > ENGINE FIRE CAUTION LIGHT INTERMITTENT. FIRE DETECTORS PASSED BENCH TEST PROCEDURES IAW MM. WITH EXCESSIVE VIBRATION AND MOVEMENT, ENG FIRE CAUTION LIGHT INTERMITENT ILLUMINATION.
- [SDR 9SZA202609100148](https://openairdocs.org/sdr/9SZA202609100148.md): Terminal · loose · Mar 24, 2026 · N362AC · Snias AS350B3 · Fire Protection System Wiring
  > ENGINE FIRE CAUTION LIGHT INTERMITTENT. FIRE DETECTORS PASSED BENCH TEST PROCEDURES IAW MM. WITH EXCESSIVE VIBRATION AND MOVEMENT, ENG FIRE CAUTION LIGHT INTERMITENT ILLUMINATION.
- [SDR 2A6D20260305001](https://openairdocs.org/sdr/2A6D20260305001.md): Fuel Line · bent · Mar 3, 2026 · N11KQ · Urocop EC130T2 · Aircraft Fuel Distribution System
  > WHILE HOVER TAXIING THE AIRCRAFT DURING CHECK FLIGHTS, THE PILOT REPORTED A FUEL P LIGHT AND TURNED THE AIRCRAFT AROUND TO RETURN TO THE RAMP. DURING THE FLIGHT BACK, THE PILOT WAS ALERTED TO AN AMBER GOV LIGHT AND NOTICED THAT THE AIRCRAFT WAS LOSING POWER. T
- [SDR QMLA2025101420105](https://openairdocs.org/sdr/QMLA2025101420105.md): Unknown · odor · Oct 14, 2025 · N240SH · Urocop EC130T2 · Air Distribution System
  > STRONG BURNING SMELL IN COCKPIT.
- [SDR 2A6R 09222025743](https://openairdocs.org/sdr/2A6R%2009222025743.md): Skin · cracked · Sep 22, 2025 · N223SH · Urocop EC130T2 · Rotorcraft Tail Boom
  > DURING THE 600 HOUR / 24 MONTH AIRFRAME INSPECTION, A CRACK WAS FOUND ON THE TAILBOOM SKIN (TAILBOOM P/N: 350A2307150002 S/N: TB7538) ON THE UPPER R/H CORNER OF THE BATTERY COMPARTMENT DOOR DOUBLER MEASURING 1.35" IN LENGTH AND STOPPING AT A RIVET HOLE. THIS C
- [SDR JBZA20250710001](https://openairdocs.org/sdr/JBZA20250710001.md): Elec Connector · arced · Jul 2, 2025 · N415RX · Urocop EC130T2 · Communications System Wiring
  > DURING FINAL APPROACH TO BASE AN ELECTRICAL SMELL WAS DETECTED COMING FROM THE CENTER CONSOLE TDFM / SKY TRAC PANELS. DURING EVALUATION OF THE SYSTEMS IT WAS DISCOVERED THE CONNECTOR TO THE TDFM WAS THE SOURCE OF THE SMELL. FOUND CONNECTER WITH BROKEN MALE PIN
- [SDR 2A6D20250502001](https://openairdocs.org/sdr/2A6D20250502001.md): Xmsn Deck · chafed · Jun 2, 2025 · N11UQ · Urocop EC130T2 · Fuselage Main, Structure
  > GOUGING- TOOL DAMAGE WAS DISCOVERED ON THE LH SIDE OF THE TRANSMISSION DECK. THE DEPTH IS APPROXIMATELY 0.026". THE MAXIMUM APPROXIMATE LENGTH IS.6 AND WIDTH IS 0.85".
- [SDR EVCA20250502001](https://openairdocs.org/sdr/EVCA20250502001.md): Structure · cracked · May 1, 2025 · N863LH · Urocop EC130T2 · Rotorcraft Tail Boom
  > CRACK EXCEEDING THE MANUFACTURES LIMITS IN THE HORIZONTAL STABILIZER
- [SDR 2025FA0000130](https://openairdocs.org/sdr/2025FA0000130.md): Engine · making metal · Feb 25, 2025 · Engine (Turbine/Turboprop)
  > A CUSTOMER ENGINE WAS RECEIVED AS AN EXCHANGE TO BE INSTALLED IN A AS35B3 HELICOPTER. A PRE-INSTALLATION INSPECTION FOUND SIGNIFICANT METAL CONTAMINATION IN THE OIL SYSTEM, INCLUDING THE FILTER AND MAG PLUGS. THE ENGINE WAS RECEIVED WITH AN 8130-3 INDICATING
- [SDR QMLA2025022520026](https://openairdocs.org/sdr/QMLA2025022520026.md): Fan · damaged · Feb 25, 2025 · N741AC · Urocop EC130T2 · Air Distribution Fan
  > AFTER LIFTING GENESIS EAST MED CENTER AND HEADING TO IOWA CITY. THE AV FAN CAME ON FOLLOWED BY A STRONG BURNING SMELL. FOUND INOP AVIONICS FAN RIGHT SIDE UNDER INSTRUMENT PANEL.
- [SDR QMLA2025012920009](https://openairdocs.org/sdr/QMLA2025012920009.md): Bulkhead · cracked · Jan 29, 2025 · N855CH · Urocop EC135T2 · Fuselage Main, Bulkhead
  > DURING SCHEDULED MAINTENANCE FOR THE A 0740 150 HOUR / 12 MONTH AIRFRAME INSPECTION A CRACK WAS FOUND ON THE UPPER RIGHT HAND CORNER OF THE 22 DEGREE BULKHEAD.
- [SDR QMLA2024090620108](https://openairdocs.org/sdr/QMLA2024090620108.md): Engine · power loss · Sep 5, 2024 · N930U · Urocop EC130T2 · Engine (Turbine/Turboprop)
  > ON PICKUP I NOTICED THE FLI WAS HIGHER THAN NORMAL, I CAN USUALLY LIFTOFF AT 7/7.5 ON THE FLI AT MGW BUT THIS TIME I WAS 100LBS UNDER MGW AND IT DIDNT LIFT OFF UNTIL OVER 8 ON THE FLI. ON CLIMB-OUT IT FELT SLUGGISH SO I CHECKED MY NUMBERS. I WAS AROUND 98 N1/N
- [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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 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 M3XA2024012219001](https://openairdocs.org/sdr/M3XA2024012219001.md): B-Nut · loose · Jan 19, 2024 · N892GT · Urocop EC130T2 · Turbine Engine Oil System
  > PILOT REPORTED ON POST FLIGHT INSPECTION, DISCOVERED OIL ON OUTSIDE OF ENGINE COWLING, DRAINING FROM ENGINE DECK DRAIN LINES AND SMOKE COMING OFF OUTSIDE OF EXHAUST DUCT AND OIL ON OUTSIDE OF THE ENGINE. MECHANIC FOUND B-NUT VENT LINE LOOSE AND DISCONNECTED.
- [SDR QMLA202312231222](https://openairdocs.org/sdr/QMLA202312231222.md): Unknown · unknown · Dec 23, 2023 · N11YQ · Urocop EC130T2 · Rotorcraft Flight Control
  > DURING CLIMB OUT THE AIRCRAFT HAD SIGNIFICANT INCREASED RIGHT CYCLIC PRESSURE THAT SUDDENLY RELEASED CAUSING THE AIRCRAFT TO SLIGHTLY JOLT TO THE RIGHT. THE FLIGHT WAS ABORTED AND AIRCRAFT SAFELY LANDED BACK AT BASE.
- [SDR QMLA2023092620077](https://openairdocs.org/sdr/QMLA2023092620077.md): Unknown · unknown · Sep 26, 2023 · N741AC · Urocop EC130T2 · Air Distribution System
  > COLLECTIVE APPLICATION DURING TAKEOFF CREW NOTICE A SMELL OF BURNING RUBBER. I THOUGHT IT WAS AN AC BELT BURNING, RETURNED TO PAD SHUT DOWN, WENT BACK TO TRANSMISSION AND NOTICED THE AC BELT WAS STILL INTACT. CALLED MX, MAINTENANCE INVESTIGATED AND SMELLED ARE
- [SDR EVCA09252023](https://openairdocs.org/sdr/EVCA09252023.md): Support · damaged · Sep 21, 2023 · N202AH · Urocop EC130T2 · Engine/Transmission Coupling
  > PERFORMED TRANSMISSION SHAFT BEARING SUPPORT 10HR REOCCURRING AD 2022-01-05, DISCOVERED SHEARED RIVET AND CRACKS ON REAR TRANSMISSION SHAFT BEARING SUPPORT.
- [SDR 2A6D20230825001](https://openairdocs.org/sdr/2A6D20230825001.md): Bulkhead · chafed · Aug 25, 2023 · N790K · Urocop EC130T2 · Fuselage Main, Bulkhead
  > DAMAGE WAS DISCOVERED ON THE LH SIDE OF THE 15 DEGREE BULKHEAD ON THE AFT FACE. THE CHAFE CORRESPONDS TO AN ANGLE CLIP OF THE SHEET METAL LOX ENCLOSURE RUBBING ON THE AFT WALL. THE CHAFE MEASURES APPROX. 0.029” DEEP, 0.1” LONG AND 0.2” WIDE.
- [SDR QMLA2023082620067](https://openairdocs.org/sdr/QMLA2023082620067.md): Unknown · unknown · Aug 24, 2023 · N239SH · Urocop EC130T2 · Fuselage Structure (General)
  > DEPARTED HELIPAD EN-ROUTE TO AIRPORT FOR FUEL FOR AN INTERFACILITY REQUEST. AFTER HOVER CHECKS AND REPOSITIONING TO THE CENTER OF THE HELIPAD, FLIGHT CREW NOTED VISIBLE LIQUID RANGING IN SIZE FROM A SMALL PUDDLE TO SEVERAL DROPS. FLIGHT CREW CONDUCTED A QUICK
- [SDR FXTA20230926001](https://openairdocs.org/sdr/FXTA20230926001.md): Motor · failed · Aug 9, 2023 · N520A · Snias AS350B3 · Turbine Engine Oil System
  > BLOWER MOTOR MAKING LOUD NOISES DURING OPERATION. WHEN FAN SPUN BY HAND THERE WAS INDICATION OF DRAG OR ROUGHNESS IN MOTOR. MOTOR HAS ONLY BEEN INSTALLED FOR 205.1HRS.
- [SDR 2A6D20230807001](https://openairdocs.org/sdr/2A6D20230807001.md): Flange · cracked · Aug 7, 2023 · N223SH · Urocop EC130T2 · Fuselage Miscellaneous Structure
  > DAMAGE TO THE LH SIDE OF THE 7 DEG BULKHEAD FLANGE (P/N: 350A21-0980.22) IN THE FORM OF A CRACK AND A DENT AT THE FASTENER LOCATION. THE CRACK THROUGH THE FLANGE MEASURED TO BE APPROXIMATELY 0.65” IN LENGTH AND THE DENT DAMAGE MEASURED TO BE APPROXIMATELY 0.5”
- [SDR 2A6D20230807002](https://openairdocs.org/sdr/2A6D20230807002.md): Bulkhead · chafed · Aug 7, 2023 · N223SH · Urocop EC130T2 · Fuselage Main, Bulkhead
  > DAMAGE TO THE AFT BULKHEAD PANEL (P/N: 350A21-1570.20) IN THE FORM OF MULTIPLE CHAFED AREAS IN THE PART, MOST OF WHICH ARE FOUND ON THE TOPS OF THE STIFFENING FEATURES. THE LARGEST CHAFE WAS MEASURED TO BE APPROXIMATELY 1.40” X 0.70” AND 0.0075” DEEP.
- [SDR QMLA2023072520054](https://openairdocs.org/sdr/QMLA2023072520054.md): Stabilizer · cracked · Jul 24, 2023 · N11UQ · Urocop EC130T2 · Horizontal Stabilizer Structure
  > UPON DAILY INSPECTION, THE HORIZONTAL STABILIZER WAS FOUND CRACKED ON THE RIGHT HAND SIDE OF THE UPPER SKIN JUST PAST THE UPPER REINFORCEMENT SPAR.
- [SDR QMLA2023060420046](https://openairdocs.org/sdr/QMLA2023060420046.md): Cover · handler error · Jun 4, 2023 · N130HN · Urocop EC130B4 · Navigation System
  > AIRSPEED INDICATOR FAILURE DUE TO PITOT TUBE COVER REMAINING ON PITOT TUBE. COVER REMAINS ON THE TUBE DURING THE DAY WHEN HELICOPTER NOT IN SERVICE TO PREVENT BUGS FROM ENTERING THE PITOT TUBE WHILE ON GROUND, WHICH HAS OCCURRED IN IMMEDIATE HISTORY.
- [SDR QMLA2023031520014](https://openairdocs.org/sdr/QMLA2023031520014.md): V-Belt · unknown · Mar 15, 2023 · N240SH · Urocop EC130T2 · Main Rotor Drive System
  > PL DUE TO ILLUMINATION OF SERVO AND HYD2 CAUTION LIGHT. CAUTION LIGHTS ILLUMINATED WHILE AT CRUISE FLIGHT. PL CONDUCTED TO THE NEAREST AIRPORT. POST FLIGHT INSPECTION REVEALED THE BELT FOR THE BELT-DRIVEN HYDRAULIC PUMP HAD SEPARATED.
- [SDR EVCA202212280001](https://openairdocs.org/sdr/EVCA202212280001.md): Floor Support · cracked · Dec 28, 2022 · N897SE · Urocop EC130T2 · Fuselage Miscellaneous Structure
  > THERE IS AN APPROX 1/2 INCH CRACK ON LH RIB AT INBOARD OUTER EDGE OF THE FLOOR SUPPORT.
- [SDR 2025FA0000124](https://openairdocs.org/sdr/2025FA0000124.md): Elec Connector · fod · Oct 20, 2022 · N302TP · Snias AS350B3 · Turbine Engine System Wiring
  > VISUAL FOD DAMAGE TO THE AXIAL COMPRESSOR/MODULE M02 ON ARRIEL 2D ENGINE. UNKNOWN DAMAGE TO REST OF ENGINE MODULES PENDING INSPECTION. DONALDSON INLET BARRIER FILTER, MANUFACTURER PART # 121003-101, SERIAL # 0395. A SCREW FROM THE BYPASS SECTION OF THE INLE
- [SDR 2022FA0000493](https://openairdocs.org/sdr/2022FA0000493.md): Belt · failed · Sep 2, 2022 · N853MB · Snias AS350B3 · Cabin Cooling System
  > DURING FINAL APPROACH TO THE HOSPITAL IN LOVELAND CO, THE CREW REPORTED THE SMELL OF BURNT RUBBER. AFTER LANDING, THE PILOT INVESTIGATED AND FOUND THE A/C COMPRESSOR BELT SHREEDED. HE ALSO NOTED THAT THE DAMAGED A/C BELT CAUSED SIGNIFICATE DAMAGE TO THE HYRDAU
- [SDR QMLA2022083020060](https://openairdocs.org/sdr/QMLA2022083020060.md): None · none · Aug 30, 2022 · N327C · Urocop EC130T2 · Fuselage Structure (General)
  > CRACK FOUND AT L/H FRWARD CANOPY FRAME ATTACHMENT STRUCTURE. CRACK IS IN THE AREA "A" IDENTIFIED IN EC130T2 AMM TASK 53-21-00, 6-1. CRACK IS ROUGHLY 15MM (.59IN). FIELD LOCATION. NOT CURRENTLY EQUIPPED TO PERFOM REQUIRED REPAIR PER SAME AMM TASK 53-10-00,8-19.
- [SDR 2022FA0000420](https://openairdocs.org/sdr/2022FA0000420.md): Strainer · broken · Aug 1, 2022 · N203Z · Snias AS350B3 · Aircraft Fuel Filter/Strainer
  > AIRCRAFT FUEL FILLER STRAINER BROKE OFF AT SPOT-WELDS AROUND STRAINER RETAINING COLLAR CAUSING STRAINER BODY TO FALL INTO AIRCRAFT FUEL TANK.
- [SDR EVCA202207070001](https://openairdocs.org/sdr/EVCA202207070001.md): Fan · fod · Jun 30, 2022 · N894GT · Urocop EC130T2 · Air Distribution Fan
  > BURNING RUBBER SMELL IN CABIN COMPARTMENT. FOUND SMALL BIRD INGESTED INTO CABIN COMPARTMENT BLOWER ASSEMBLY.

Next page: https://openairdocs.org/engine/turbomeca-arriel-2d/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 engine_model_key = 'ARRIEL2D'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/turbomeca-arriel-2d/reports

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