Eurocopter Deutschland EC135T2
Service difficulty reports · 264
Newest first. General aviation reporting is voluntary.
Query with SQL
duckdb -csv -c "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"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
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
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR 2A6R2026110376102Frame · modificationDURING 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 BUNDLSDR 2A6R2026102676101Frame · chafedCHAFING 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 INSTALLEDSDR QMLA2026102020079Unknown · odorELECTRICAL 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 2A6R2026101375412Frame · gougedDAMAGE 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 FRAMESDR 2A6R2026100275411Beam · crackedMULTI-CRACKS ARE FOUND ON THE UPPER SHEET OF BEAM FRAME 5, AND OEM OUTER DOUBLER, APPROXIMATELY 1- 2.25” LONG, REF RDAS-EC135-53-2026-3392SDR 2A6R2026100275410Frame · mechanic errorTWO 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 2A6R2026092975409Bracket · corrodedEC135 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 FABRICATEDSDR 2A6R2026092475408Xmsn Deck · dentedA 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-EC135-53-2026-3264ASDR 2A6R2026092275407Keelbeam · corrodedDAMAGE 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 2A6R2026091675406Frame · crackedDAMAGE 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 2A6R2026091675405Gusset · corrodedEC135 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 FABRICATEDSDR 2A6R2026091675404Angle · corrodedACFT 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 FABRICATEDSDR 2A6R2026090375403Frame · corrodedFOUND CORROSION DAMAGE ON FRAME 1, REQUIRING REPLACEMENT OF THE FRAME.SDR 2A6R2026082575402Frame · crackedTWO 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 ANSDR 2A6R2026081675401Attach Angle · corrodedCORROSION 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 2A6R2026061575601Floor Skin · dentedDENTS 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 11SDR 2A6R2026060875601Attach Angle · corrodedCORROSION 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 METHOSDR 2A6R2026060475601Liner · crackedPOST REMOVING DAMAGED TEFLON LINER ON BLADE. DISCOVERED CRACK ON WEDGE ON WEDGE OF UPPER TRAILING BUSH HOLE TO OUTER ROVING LOOP.SDR 2A6R2026060375601Keelbeam · corrodedDAMAGE 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 PROCEDURSDR HDNA2026FA0000445Frame · crackedFRAME 5 CRACK FOUND WHILE CONDUCTING A 1000H SCHEDULED INSPECTION. REPAIRED WITH APPROVED DATA FROM THE AIRCRAFT MANUFACTURER.SDR 2A6R2026052675602Frame · chafedCHAFING 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 ASDR 2A6R2026031675004Ehsi · wrong partDURING 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 NOSDR 2A6R2026021975003Floor Panel · dentedDAMAGE 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 DETAILESDR 2A6R2026021975002Floor Panel · dentedDENT 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 ADHESIVESDR QMLA2026020620010Crosstube · corrodedDURING 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 CRSDR 2A6R2026020275001Attach Angle · corrodedCORROSION 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 USDR 2A6R2026052675601Deck Plate · dentedDURING 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 QMLA2025120620123Extension · crackedDURING INSPECTIONS, THE LT FORWARD LANDING GEAR EXTENSION WAS FOUND TO BE CRACKED AT THE BOLT HOLE.SDR QMLA2025120520121Transfer Pump · failedFAILED AFT FUEL TRANSFER PUMP.SDR QMLA2025112520117Circuit Breaker · trippedELECTRICAL BURNING SMELL DURING APPROACH BACK TO BASE. SMELL FADED, INSTRUMENT LIGHTING WAS NO LONGER FUNCTIONING. INSTRUMENT LIGHTS C/B HAD TRIPPED.SDR QMLA2025112220115Starter Gen · faultedWHILE CONDUCTING STARTUP CHECKS AND UPON ENGINES REACHING IDLE, THE NR 1 GEN DISCON CAUTION LIGHT ILLUMINATED. REPLACED STARTER GEN.SDR 2025FA0000765Fadec · failedSEVENTEEN 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 2A6R2025103074503Floorbeam · corrodedDURING 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 2A6R2025103074502Floor Skin · dentedDURING 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 DSDR 2A6R2025103074501Attach Angle · corrodedDURING 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 AUSDR QMLA2025081820088Control Unit · failedNR 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. ALSDR QMLA2025080720085Gps · failedDURING A HIGH RECON ABOVE AN LZ AT A SENDING FACILITY, BOTH GPS UNITS LOST SIGNAL.SDR QMLA2025072620077Vhf Comm · faulted#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 ASDR QMLA2025072520076Profile · crackedDURING 500HR AIRFRAME INSPECTION FOUND THE LH AND RH A-PROFILES CRACKED AND A CRACK IN THE TRANSMISSION DECK FLOOR .SDR 2A6R2025052272602Frame · crackedCRACK 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 RESDR 2A6R2025052272601Floor Skin · dentedDENT 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 SSDR QMLA2025031920037Probe · malfunctionedAIRCRAFT 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 QMLA2025030320031Indicator · malfunctionedDURING 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 QMLA2025022020022Engine · making metalABOUT 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 PROCEDSDR QMLA2025021720018Blade · damagedOBJECT 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 2A6R2025021272504Frame · crackedDURING 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 EC135-53-031SDR 2A6R2025021272503Frame · chafedDURING 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-5011SDR 2A6R2025021272502Frame · corrodedDURING A 1000 HOUR AIRFRAME INSPECTION FOUND SEVERE CORROSION ON FRAME ONE ALONG THE LOWER FLANGE. REPAIRING IAW AIRBUS RDAS-EC135-53-2025-0282ASDR 2A6R2025021272501Floor Panel · corrodedDURING 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 HELICSDR QMLA2025012920009Bulkhead · crackedDURING 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.
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