# Service difficulty reports: Eurocopter Deutschland EC135T2

A list on [Eurocopter Deutschland EC135T2](https://openairdocs.org/model/eurocopter-deutschland-ec135t2.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 6 · 264 reports

- [SDR 2A6R2026110376102](https://openairdocs.org/sdr/2A6R2026110376102.md): Frame · modification · Nov 3, 2026 · N877CR · Urocop EC135T2 · Fuselage Main, Frame
  > DURING INSPECTION, CORROSION DAMAGE WAS FOUND ON FRAME 1 REQUIRING THE FRAME 1 TO BE REPLACED (P/N: L533M1011104). IN ORDER TO REPLACE FRAME 1, THE UPPER WEB (P/N: L533M1011212) ABOVE THE FEED-THROUGH HOLES IN THE FRAME MUST BE CUT TO ALLOW MULTIPLE WIRE BUNDL
- [SDR 2A6R2026102676101](https://openairdocs.org/sdr/2A6R2026102676101.md): Frame · chafed · Oct 26, 2026 · N877CR · Urocop EC135T2 · Fuselage Main, Frame
  > CHAFING DAMAGE WAS DISCOVERED ON THE R/H FRAME 4 INBOARD SKIN LOCATED JUST FORWARD OF THE RT HEATING DUCT OUTLET. THE CHAFING DAMAGE MEASURED 0.008” IN DEPTH AND APPROXIMATELY 1.20” X 0.80”. A 0.040” 2024-T3 ALUMINUM REPAIR DOUBLER WAS FABRICATED AND INSTALLED
- [SDR QMLA2026102020079](https://openairdocs.org/sdr/QMLA2026102020079.md): Unknown · odor · Oct 19, 2026 · N864NC · Urocop EC135T2 · Air Distribution System
  > ELECTRICAL BURNING SMELL IN COCKPIT. PERFORMED VISUAL INSP OF ACFT INSTRUMENTS AND WIRING PER AC 43.13.1B. NO CHAFING OF WIRES OR SMOKE DETECTED DURING PWR ON CHECKS OR GROUND RUN. COULD NOT DUPLICATE FAULT.
- [SDR 2A6R2026101375412](https://openairdocs.org/sdr/2A6R2026101375412.md): Frame · gouged · Oct 13, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Frame
  > DAMAGE WAS FOUND TO THE SURFACE OF THE RH SIDE WINDOW FRAME PN: L533M1207205 IN THE FORM OF MULTIPLE GOUGES AND CRACKS, REQUIRING REPLACEMENT OF THE WINDOW FRAME
- [SDR 2A6R2026100275411](https://openairdocs.org/sdr/2A6R2026100275411.md): Beam · cracked · Oct 2, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Structure
  > MULTI-CRACKS ARE FOUND ON THE UPPER SHEET OF BEAM FRAME 5, AND OEM OUTER DOUBLER, APPROXIMATELY 1- 2.25” LONG, REF RDAS-EC135-53-2026-3392
- [SDR 2A6R2026100275410](https://openairdocs.org/sdr/2A6R2026100275410.md): Frame · mechanic error · Oct 2, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Frame
  > TWO DRILL MARKS ON THE STRUCTURE UNDERNEATH OF THE TRANSMISSION DECK. THE MARK IS 0.129" IN DIAMETER WITH A DEPTH OF 0.016". THE DAMAGE TO THE FRAME IS 0.128" IN DIAMETER WITH A MAX DEPTH OF 0.018"
- [SDR 2A6R2026092975409](https://openairdocs.org/sdr/2A6R2026092975409.md): Bracket · corroded · Sep 29, 2026 · N110VU · Urocop EC135T2 · Fuselage Miscellaneous Structure
  > EC135 S/N 0605 WAS FOUND TO HAVE HEAVY CORROSION ON THE T-CAP P/N L533M1028203 ON TOP OF T-CAP UNDER MAIN CABIN FLOOR AT FS3150MM, LBL100MM – RBL450MM THE DAMAGE REQUIRED REPLACEMENT OF THE T-CAP, AND DUE TO AVAILABILITY, A NEW T-CAP WAS LOCALLY FABRICATED
- [SDR 2A6R2026092475408](https://openairdocs.org/sdr/2A6R2026092475408.md): Xmsn Deck · dented · Sep 24, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Structure
  > A SURFACE DAMAGE (DENT) IS FOUND ON THE TRANSMISSION DECK UPPER SURFACE, UNDER AFT OTBD SECTION OF THE RH XY FITTING, APPROXIMATELY 2.5” LONG, 0.05” WIDE AND 0.032” DEPTH. FOR DETAILS SEE AIRBUS RDAS-EC135-53-2026-3264A
- [SDR 2A6R2026092275407](https://openairdocs.org/sdr/2A6R2026092275407.md): Keelbeam · corroded · Sep 22, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Keel
  > DAMAGE TO THE LH KEEL BEAM CAP IN THE FORM OF SEVERAL AREAS OF CORROSION WAS DISCOVERED. THE DAMAGE IS LOCATED ON THE UPPER SURFACE OF THE PART UNDER THE COCKPIT FLOOR, WITH THE LARGEST DAMAGE AREA REPORTED TO BE APPROXIMATELY 0.5” X 0.5” IN SIZE AND 0.018”
- [SDR 2A6R2026091675406](https://openairdocs.org/sdr/2A6R2026091675406.md): Frame · cracked · Sep 16, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Frame
  > DAMAGE WAS DISCOVERED ON THE CABIN OVERHEAD LONGERON (PN: L533M1017282) IN THE FORM OF TWO CRACKS ON EITHER SIDE OF THE CUTOUT. THE CRACK MEASURES APPROXIMATELY 0.50” LONG (AFT) AND 1.00” LONG (FWD)
- [SDR 2A6R2026091675405](https://openairdocs.org/sdr/2A6R2026091675405.md): Gusset · corroded · Sep 16, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Attach Fittings
  > EC135 S/N 0605 WAS FOUND TO HAVE CORROSION DAMAGE TO THE BULKHEAD, PN L533M1028221 (APPROX. FS 3150 MM)AND GUSSETS PN: L533M1028227 AND PN: L533M1028228. REPLACEMENTS WERE NOT AVAILABLE WITHIN SCHEDULED RTS AND PARTS WERE FABRICATED
- [SDR 2A6R2026091675404](https://openairdocs.org/sdr/2A6R2026091675404.md): Angle · corroded · Sep 16, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Structure
  > ACFT WAS FOUND TO HAVE CORROSION DAMAGE TO THE FRAME 2 ANGLE PN L533M1043427 (APPROX. FS 2675 MM). REPLACEMENT WAS NOT AVAILABLE WITHIN SCHEDULED RTS AND PART WAS FABRICATED
- [SDR 2A6R2026090375403](https://openairdocs.org/sdr/2A6R2026090375403.md): Frame · corroded · Sep 3, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Frame
  > FOUND CORROSION DAMAGE ON FRAME 1, REQUIRING REPLACEMENT OF THE FRAME.
- [SDR 2A6R2026082575402](https://openairdocs.org/sdr/2A6R2026082575402.md): Frame · cracked · Aug 25, 2026 · N110VU · Urocop EC135T2 · Fuselage Main, Frame
  > TWO CRACKS APPROXIMATELY 6MM IN LENGTH EACH WERE DISCOVERED ON THE LH UPPER FRAME 5 MEDICAL INTERIOR MOUNT LOCATION. BOTH CRACKS PROPAGATED FROM THE SAME RIVET HOLE AT APPROXIMATELY FS: 4780, WL: 2400, AND BL: -710. THE CRACKS WERE LESS THAN 1.5” IN LENGTH AN
- [SDR 2A6R2026081675401](https://openairdocs.org/sdr/2A6R2026081675401.md): Attach Angle · corroded · Aug 16, 2026 · N110VU · Urocop EC135T2 · Fuselage Miscellaneous Structure
  > CORROSION DAMAGE OF VARYING DEPTHS WAS FOUND ON THE LOWER LT AND RT BROOM CLOSET ATTACHMENT ANGLES (P/N: L533M1052317), AS WELL AS THE AFT ATTACHMENT ANGLE (P/N: L533M1052318)
- [SDR 2A6R2026061575601](https://openairdocs.org/sdr/2A6R2026061575601.md): Floor Skin · dented · Jun 15, 2026 · N831ME · Urocop EC135T2 · Fuselage Main, Structure
  > DENTS AND LOCALIZED DELAMINATION WERE FOUND ON THE UNDERSIDE SKIN OF THE CABIN FLOOR, MEASURING UP TO 89 MM × 914 MM (3.5 IN × 36 IN) AND 50 MM × 610 MM (2 IN × 24 IN). REPAIRED IN ACCORDANCE WITH AIRBUS HELICOPTERS RDAS RDAS EC135 53 2026 2040A, ISSUE DATE 11
- [SDR 2A6R2026060875601](https://openairdocs.org/sdr/2A6R2026060875601.md): Attach Angle · corroded · Jun 8, 2026 · N381ME · Urocop EC135T2 · Fuselage Main, Attach Fittings
  > CORROSION DAMAGE WAS FOUND ON THE LOWER LT AND RT ANGLE AND AFT ATTACHMENT ANGLE PN: L533M1052318. REPLACEMENT ANGLE BRACKETS WERE NOT AVAILABLE WITHIN SCHEDULED RTS. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES IS PROVIDED IN AIR METHO
- [SDR 2A6R2026060475601](https://openairdocs.org/sdr/2A6R2026060475601.md): Liner · cracked · Jun 3, 2026 · N831ME · Urocop EC135T2 · Main Rotor Blades
  > POST REMOVING DAMAGED TEFLON LINER ON BLADE. DISCOVERED CRACK ON WEDGE ON WEDGE OF UPPER TRAILING BUSH HOLE TO OUTER ROVING LOOP.
- [SDR 2A6R2026060375601](https://openairdocs.org/sdr/2A6R2026060375601.md): Keelbeam · corroded · Jun 3, 2026 · N831ME · Urocop EC135T2 · Fuselage Main, Keel
  > DAMAGE WAS NOTED TO THE RH KEEL BEAM CAP (P/N: L533M1010203) HORIZONTAL FLANGE IN THE FORM OF SEVERAL AREAS OF CORROSION. THERE ARE REPORTED TO BE 3EA AREAS OF CORROSION IN THE RH KEEL BEAM CAP. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDUR
- [SDR HDNA2026FA0000445](https://openairdocs.org/sdr/HDNA2026FA0000445.md): Frame · cracked · May 27, 2026 · N139MH · Urocop EC135T2 · Fuselage Main, Structure
  > FRAME 5 CRACK FOUND WHILE CONDUCTING A 1000H SCHEDULED INSPECTION. REPAIRED WITH APPROVED DATA FROM THE AIRCRAFT MANUFACTURER.
- [SDR 2A6R2026052675602](https://openairdocs.org/sdr/2A6R2026052675602.md): Frame · chafed · May 26, 2026 · N381ME · Urocop EC135T2 · Fuselage Main, Frame
  > CHAFING DAMAGE WAS DISCOVERED ON ACSN 0493 AT THE RH FRAME 4 INBOARD SKIN. THE DAMAGE MEASURES APPROXIMATELY 0.062” TALL BY 0.175” WIDE WITH A MAXIMUM DEPTH OF.032” (THRU THICKNESS). A DETAILED DESCRIPTION OF THE DAMAGE REPAIR AND APPROVED REPAIR PROCEDURES A
- [SDR 2A6R2026031675004](https://openairdocs.org/sdr/2A6R2026031675004.md): Ehsi · wrong part · Mar 16, 2026 · N135LC · Urocop EC135T2 · Attitude and Direction Data System
  > DURING REINSTALLATION OF THE EHSI (ELECTRONIC HORIZONTAL SITUATION INDICATOR), THE INSTALLING TECHNICIAN NOTED THAT THE LOCKING TEETH RETAINER ON THE UNIT'S J3 CONNECTOR WOULD NOT LOCK AS EXPECTED WHEN CONNECTING THE AIRFRAME P3 D-SUB CONNECTOR. IT WAS ALSO NO
- [SDR 2A6R2026021975003](https://openairdocs.org/sdr/2A6R2026021975003.md): Floor Panel · dented · Feb 19, 2026 · N135LC · Urocop EC135T2 · Fuselage Floor Panel
  > DAMAGE WAS DISCOVERED TO THE CABIN FLOOR UPPER SKIN PANEL IN THE FORM OF MULTIPLE DENTS. THE DENTS WERE FILLED WITH AN EA9309.3NA RESIN/MICRO BALLOON MIXTURE AND.025” 2024-T3 REPAIR DOUBLERS WERE FABRICATED AND INSTALLED OVER TOP OF THE REPAIR AREA. A DETAILE
- [SDR 2A6R2026021975002](https://openairdocs.org/sdr/2A6R2026021975002.md): Floor Panel · dented · Feb 19, 2026 · N135LC · Urocop EC135T2 · Fuselage Floor Panel
  > DENT DAMAGE MEASURING 13.5” LONG AND 2.5” WIDE WITH A MAXIMUM DEPTH OF 0.065” WAS DISCOVERED ON THE L/H SIDE OF THE COCKPIT FLOOR SKIN NEAR F.S 2,675MM APPROXIMATELY 0.5” FROM THE EDGE OF THE CENTER CONSOLE. THE DAMAGED AREA WAS POTTED WITH EA9309.3NA ADHESIVE
- [SDR QMLA2026020620010](https://openairdocs.org/sdr/QMLA2026020620010.md): Crosstube · corroded · Feb 6, 2026 · N135CJ · Urocop EC135T2 · Main Landing Gear
  > DURING A 2060 1000 HOUR INSPECTION THE WAS SOME CORROSION FOUND BETWEEN THE RIGHT HAND FORWARD STEP MOUNT AND THE FORWARD CROSSTUBE. THE BOLTS WERE REMOVED SO THE CORROSION COULD BE WORKED. DURING THAT TIME IT WAS FOUND THAT THERE SEEMS TO BE A CRACK IN THE CR
- [SDR 2A6R2026020275001](https://openairdocs.org/sdr/2A6R2026020275001.md): Attach Angle · corroded · Feb 2, 2026 · N135LC · Urocop EC135T2 · Fuselage Main, Attach Fittings
  > CORROSION DAMAGE OF 0.016”- 0.020” IN DEPTH WAS DISCOVERED ON THE LOWER R/H BROOM CLOSET ATTACHMENT ANGLE (L533M1052317). REPLACEMENT ANGLE BRACKETS WERE NOT AVAILABLE WITHIN THE SCHEDULED RETURN TO SERVICE DATE. THEREFORE, A REPLACEMENT ANGLE WAS FABRICATED U
- [SDR 2A6R2026052675601](https://openairdocs.org/sdr/2A6R2026052675601.md): Deck Plate · dented · Jan 22, 2026 · N831ME · Urocop EC135T2 · Fuselage Main, Structure
  > DURING 500-HOUR INSPECTION, A DENT WAS DISCOVERED ON THE R/H SIDE OF THE TRANSMISSION DECK (P/N: L533M1017295). THE MAXIMUM DEPTH IS APPROXIMATELY 0.022" WITH A MAXIMUM DIAMETER OF 0.8. AN APPROXIMATE LOCATION OF THE DAMAGE IS AT STA. 4600MM, W.L. 2465MM, AND
- [SDR QMLA2025120620123](https://openairdocs.org/sdr/QMLA2025120620123.md): Extension · cracked · Dec 6, 2025 · N864NC · Urocop EC135T2 · Main Landing Gear
  > DURING INSPECTIONS, THE LT FORWARD LANDING GEAR EXTENSION WAS FOUND TO BE CRACKED AT THE BOLT HOLE.
- [SDR QMLA2025120520121](https://openairdocs.org/sdr/QMLA2025120520121.md): Transfer Pump · failed · Dec 5, 2025 · N135TG · Urocop EC135T2 · Fuel Transfer Valve
  > FAILED AFT FUEL TRANSFER PUMP.
- [SDR QMLA2025112520117](https://openairdocs.org/sdr/QMLA2025112520117.md): Circuit Breaker · tripped · Nov 21, 2025 · N110VU · Urocop EC135T2 · Light System Wiring
  > ELECTRICAL BURNING SMELL DURING APPROACH BACK TO BASE. SMELL FADED, INSTRUMENT LIGHTING WAS NO LONGER FUNCTIONING. INSTRUMENT LIGHTS C/B HAD TRIPPED.
- [SDR QMLA2025112220115](https://openairdocs.org/sdr/QMLA2025112220115.md): Starter Gen · faulted · Nov 18, 2025 · N954AL · Urocop EC135T2 · Starter-Generator
  > WHILE CONDUCTING STARTUP CHECKS AND UPON ENGINES REACHING IDLE, THE NR 1 GEN DISCON CAUTION LIGHT ILLUMINATED. REPLACED STARTER GEN.
- [SDR 2025FA0000765](https://openairdocs.org/sdr/2025FA0000765.md): Fadec · failed · Nov 13, 2025 · N911XK · Urocop EC135T2 · Engine Controls
  > SEVENTEEN MINUTES INTO THE FLIGHT, A FADEC FAIL 2 CAUTION ILLUMINATED. AT THAT TIME, THE #2 ENGINE TORQUE DECREASED FROM 58.8 TO 6.9, THEN INCREASED TO 19.9 WITHIN THREE SECONDS. THE #2 ENGINE TORQUE REMAINED AT 19.9 FOR THE REMAINDER OF THE FLIGHT. THE PILOT
- [SDR 2A6R2025103074503](https://openairdocs.org/sdr/2A6R2025103074503.md): Floorbeam · corroded · Oct 30, 2025 · N104VU · Urocop EC135T2 · Fuselage Main, Floor Beam
  > DURING INSPECTION, HEAVY CORROSION WAS DISCOVERED ON T-CAP P/N L533M1028203 ON TOP OF T-CAP UNDER MAIN CABIN FLOOR AT FS3150MM, LBL500MM - RBL500MM. THE T-CAP IS NOT AVAILABLE FOR PURCHASE.; THEREFORE, A REPLACEMENT T-CAP WAS FABRICATED AS PER THE INSTRUCTION
- [SDR 2A6R2025103074502](https://openairdocs.org/sdr/2A6R2025103074502.md): Floor Skin · dented · Oct 30, 2025 · N104VU · Urocop EC135T2 · Fuselage Floor Panel
  > DURING INSPECTION, DAMAGE WAS DISCOVERED TO THE COCKPIT FLOOR UPPER SKIN PANEL (P/N: L533M1014217) IN THE FORM OF MULTIPLE DENTS AND DEBONDED SKIN. THE DENTED AND DEBONDED AREAS ARE REPORTED TO BE FROM 0.50” X 0.50” IN SIZE TO 4.0” X 4.0” IN SIZE. A DETAILED D
- [SDR 2A6R2025103074501](https://openairdocs.org/sdr/2A6R2025103074501.md): Attach Angle · corroded · Oct 30, 2025 · N104VU · Urocop EC135T2 · Fuselage Main, Attach Fittings
  > DURING INSPECTION, CORROSION DAMAGE WAS DISCOVERED ON THE LOWER LH, RH & AFT BROOM CLOSET ATTACHMENT ANGLES (L533M1052317 (X2) & L533M1052318). A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED FABRICATED PROCEDURE IS PROVIDED IN AIR METHODS ENGINEERING AU
- [SDR QMLA2025081820088](https://openairdocs.org/sdr/QMLA2025081820088.md): Control Unit · failed · Aug 18, 2025 · N105VU · Urocop EC135T2 · Fuel Controlling System
  > NR 2 ENG FADEC FAIL IN FLIGHT. SLIDE ON LANDING NO DAMAGE. TROUBLESHOT DOWN TO NR 2 ENGINE FADEC ( EECU) INOPERATIVE. READ POWER TO CONNECTORS, SWAPPED EECU WITH NR 1 SIDE AND PROBLEM FOLLOWED. INSPECTED AIRCRAFT FOR OTHER DAMAGE OF SKIDS AND SKID PLATES. AL
- [SDR QMLA2025080720085](https://openairdocs.org/sdr/QMLA2025080720085.md): Gps · failed · Aug 7, 2025 · N28WS · Urocop EC135T2 · Global Positioning System
  > DURING A HIGH RECON ABOVE AN LZ AT A SENDING FACILITY, BOTH GPS UNITS LOST SIGNAL.
- [SDR QMLA2025072620077](https://openairdocs.org/sdr/QMLA2025072620077.md): Vhf Comm · faulted · Jul 24, 2025 · N831ME · Urocop EC135T2 · VHF Communications System
  > #1 VHF RADIO STOPPED TRANSMITTING. SHORTLY AFTER, DURING LEVEL FLIGHT, IFR, 6000MSL, 120KN, ON ATC VECTOR IN HEADING MODE AND THE NAV SOURCE IN ILS2, THE AUTOPILOT MADE AN UNCOMMANDED, ABRUPT LEFT TURN AND PITCH UP. THE MASTER CAUTION ILLUMINATED ALONG WITH A
- [SDR QMLA2025072520076](https://openairdocs.org/sdr/QMLA2025072520076.md): Profile · cracked · Jul 23, 2025 · N953AL · Urocop EC135T2 · Fuselage Main, Structure
  > DURING 500HR AIRFRAME INSPECTION FOUND THE LH AND RH A-PROFILES CRACKED AND A CRACK IN THE TRANSMISSION DECK FLOOR.
- [SDR 2A6R2025052272602](https://openairdocs.org/sdr/2A6R2025052272602.md): Frame · cracked · May 22, 2025 · N579AM · Urocop EC135T2 · Fuselage Main, Frame
  > CRACK DAMAGE WAS DISCOVERED ON THE LH AND RH FRAME 5 AND INBOARD ANGLE AT THE UPPER AND LOWER ATTACH POINTS OF THE MEDICAL INTERIOR BEAM. THE CRACK DAMAGES DISCOVERED WERE LESS THAN 2.5” IN LENGTH. AN APPROVED REPAIR PROCEDURE WAS COMPLIED WITH PER AIRBUS RE
- [SDR 2A6R2025052272601](https://openairdocs.org/sdr/2A6R2025052272601.md): Floor Skin · dented · May 22, 2025 · N579AM · Urocop EC135T2 · Fuselage Main, Structure
  > DENT DAMAGE WAS DISCOVERED ON THE COCKPIT FLOOR (PN: L533M1014106) AT THE INBOARD SIDE OF THE INBOARD COPILOT SEAT TRACK MEASURING APPROXIMATELY 24.5” IN LENGTH AND 2.63” WIDE. AN APPROVED REPAIR PROCEDURE WAS COMPLIED WITH PER AIRBUS REPAIR DESIGN APPROVAL S
- [SDR QMLA2025031920037](https://openairdocs.org/sdr/QMLA2025031920037.md): Probe · malfunctioned · Mar 18, 2025 · N110VU · Urocop EC135T2 · Fuel Indicating System
  > AIRCRAFT FUEL INDICATIONS ERRONEOUS. INDICATED 12-20 GALLONS LESS UPON TAKEOFF THAN ASSUMED TO BE IN AIRCRAFT. AFTER 15 MINUTES IN FLIGHT, FUEL INDICATIONS STILL SHOWED MORE FUEL THAN WHEN DEPARTED. REMOVED INSPECTED CLEANED AND REINSTALLED #1 AND #2 SUPPLY
- [SDR QMLA2025030320031](https://openairdocs.org/sdr/QMLA2025030320031.md): Indicator · malfunctioned · Mar 2, 2025 · N28WS · Urocop EC135T2 · Navigation System
  > DURING STARTUP OF ENGINE 1, THE TOT GAUGE DISAPPEARED AND CAUSED THE ENGINE START SEQUENCE TO ABORT AND DISPLAY A FLI_DEGR CAUTION MESSAGE. CLEANED CONNECTIONS, FUNCTIONAL CHECKS GOOD.
- [SDR QMLA2025022020022](https://openairdocs.org/sdr/QMLA2025022020022.md): Engine · making metal · Feb 20, 2025 · N911UG · Urocop EC135T2 · Engine (Turbine/Turboprop)
  > ABOUT 1-2 MILES OUT FROM PATIENT PICKUP THE #1 ENG CHIP LIGHT ILLUMINATED. POWER WAS DECREASED AND THE LIGHT EXTINGUISHED. POWER WAS SLIGHTLY BROUGHT BACK IN TO SEE IF IT RETRIGGERED THE ANOMALY, WHICH IT DID. THE CHIP BURN SWITCH WAS IDENTIFIED AND THE PROCED
- [SDR QMLA2025021720018](https://openairdocs.org/sdr/QMLA2025021720018.md): Blade · damaged · Feb 17, 2025 · N405TJ · Urocop EC135T2 · Main Rotor Blades
  > OBJECT STRUCK ON FINAL APPROACH TO JEFFERSON UNIVERSITY HOSPITAL. UPON SHUTDOWN, DAMAGE WAS NOTED TO THE TOP OF THE FUSELAGE AND WITNESS MARKS AND DAMAGE TO 3 OF THE ROTOR BLADES.
- [SDR 2A6R2025021272504](https://openairdocs.org/sdr/2A6R2025021272504.md): Frame · cracked · Feb 12, 2025 · N136MF · Urocop EC135T2 · Fuselage Main, Frame
  > DURING A 1000 HOUR AIRFRAME INSPECTION, FOUND LEFT & RIGHT SIDES OF THE 5 ALPHA FRAME CRACKED. REPLACING THE FRAME WITH P/N L533M1022966 PER AIRBUS SERVICE BULLETIN EC135-53-031
- [SDR 2A6R2025021272503](https://openairdocs.org/sdr/2A6R2025021272503.md): Frame · chafed · Feb 12, 2025 · N136MF · Urocop EC135T2 · Fuselage Main, Frame
  > DURING A 1000 HOUR AIRFRAME INSPECTION FOUND CHAFING ON THE LEFT AND RIGHT WEBS OF FRAME FOUR. REPAIRED IAW AIR METHODS ENGINEERING AUTHORIZATION 23-5300-EA-5011
- [SDR 2A6R2025021272502](https://openairdocs.org/sdr/2A6R2025021272502.md): Frame · corroded · Feb 12, 2025 · N136MF · Urocop EC135T2 · Fuselage Main, Frame
  > DURING A 1000 HOUR AIRFRAME INSPECTION FOUND SEVERE CORROSION ON FRAME ONE ALONG THE LOWER FLANGE. REPAIRING IAW AIRBUS RDAS-EC135-53-2025-0282A
- [SDR 2A6R2025021272501](https://openairdocs.org/sdr/2A6R2025021272501.md): Floor Panel · corroded · Feb 12, 2025 · N136MF · Urocop EC135T2 · Fuselage Floor Panel
  > DURING A 1000 HOUR AIRFRAME INSPECTION FOUND MULTIPLE DAMAGES TO THE COCKPIT FLOOR IN THE FORM OF DENTS, DELAMINATION AND CORROSION TO THE UPPER SKIN PANEL AS WELL AS THE LH & RH FWD GROUNDING SHEETS. THE FLOOR WILL BE REPAIRED IN ACCORDANCE WITH AIRBUS HELIC
- [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.

Next page: https://openairdocs.org/model/eurocopter-deutschland-ec135t2/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 aircraft_model_key = 'EC135T2'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/eurocopter-deutschland-ec135t2/reports

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