N910U

Eurocopter France EC-130 B4 No injuries Part 91 — Air Methods Corp.

Operated by Air Methods (per NTSB report)

ATA 2121

Part: BLOWER MOTOR — BURNED OUT (ZONE 100) · airframe 8,558 hrs · 1,463 cycles

ODOR OF BURNT ELECTRICAL WIRING. FOUND SMELL COMING FROM AFT AC VENTS. FOUND CONDENSATION/WATER IN ELECTRICAL MOTOR. REPLACED AFT BLOWER MOTOR

ATA 2197

Part: ELEC CONNECTOR — BURNED (EVAPORATOR) · airframe 8,555 hrs · 29,966 cycles

ON APPROACH PILOT AND CREW DETECTED FAINT ELECTRICAL SMELL NO SMOKE PRESENT. AMT DISCOVERED 1 EACH MOLEX CONNECTER WITH DISCOLORATION REPLAIRED DAMAGED WIRING.

ATA 5310

Part: CHANNEL — CORRODED (ZONE 100) · airframe 8,304 hrs · 29,312 cycles

DAMAGE TO THE RH EDGE FRAME Z CHANNEL, IN THE FORM OF CORROSION, WAS FOUND AT SEVERAL LOCATIONS FWD AND AFT OF FUSELAGE STATION 1405 MM. DAMAGE AFT OF FUSELAGE STATION 1405 MM WAS REMOVED, AND A FABRICATED Z CHANNEL WAS SPLICED IN. DAMAGE FWD OF FUSELAGE STATION 1405 MM WAS REPAIRED BY FABRICATING AND INSTALLING A L SHAPED DOUBLER. A DETAILED DESCRIPTION OF THE APPROVED REPAIR PROCEDURES IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC130-53-2024-0040, ISSUE A DATED 09 JAN 2024.

ATA 5310

Part: CROSSBEAM — CHAFED (ZONE 100) · airframe 8,304 hrs · 29,312 cycles

DAMAGE TO THE AFT MAIN LANDING GEAR FITTING AREA WAS FOUND IN 2 LOCATIONS. CHAFE DAMAGE WAS FOUND ON A PREVIOUSLY INSTALLED “AFT LANDING GEAR CROSS BEAM REPAIR BLOCK” (P/N RDAS AHI 130 53 005 24.01) IN THE FORM OF CHAFING. DAMAGE WAS ALSO FOUND ON THE AFT LANDING GEAR CROSS BEAM (P/N 350A214311.20) IN THE FORM OF CHAFING. A NEW REPAIR BLOCK (P/N: RDAS-EC130-53-2025-2585.01) WAS FABRICATED, USING 17-4 PH, H1025 1.5” PLATE, AND INSTALLED. ALL DAMAGE TO THE AFT LANDING GEAR CROSS BEAM WAS BURNISHED TO A SMOOTH CONTOUR. A DETAILED DESCRIPTION OF THE DAMAGE AND THE APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC130-53-2025-2585 A, ISSUE A DATED 22 AUG 2025.

ATA 5200

Part: BEARING — CHAFED (ZONE 800) · airframe 8,304 hrs · 29,312 cycles

LH DOOR POST BEARING (P/N 350A21-4459-2251) WAS FOUND TO BE CHAFED BY CONTACT WITH LH SLIDING DOOR CENTER ARM. A NEW DOOR POST BEARING WAS FABRICATED FROM .050” 2024-T3 ALUMINUM SHEET AND LABELED WITH PN: 350A21-4459-2251-AMC. A DETAILED DESCRIPTION OF THE DAMAGE AND AN APPROVED FABRICATION PROCEDURE IS PROVIDED IN AIR METHODS ENGINEERING AUTHORIZATION 17-5300-EA-5249 REV – DATED 28 AUG 2025 AND IS SUBSTANTIATED BY FAA FORM 8110-3 BY RYAN D. LEE, DER-Y # 905240204, DATED 29 AUG 2025 WITH DER SPECIFIC SEQUENCE # 25RL017AM.

ATA 5310

Part: RAIL — CHAFED (ZONE 200) · airframe 8,304 hrs · 29,312 cycles

DAMAGE TO THE RH TRDS SUPPORT RAIL (PN 350A23-1053-59) WAS FOUND IN THE FORM OF SEVERAL CHAFES AT THE #3 BEARING SUPPORT (PN 350A23-1053-42). THE #3 BEARING SUPPORT IS ALSO CHAFED JUST ABOVE THE UPPER EDGE OF THE RAIL. ALL CHAFED AREAS WERE BURNISHED, AND A DOUBLER (PN RDAS-EC130-53-2025-2566.01) WAS FABRICATED AND INSTALLED. A DETAILED DESCRIPTION OF THE DAMAGE AND THE APPROVED REPAIR PROCEDURE IS PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC130-53-2025-2566 A, ISSUE A DATED 12 AUG 2025.

ATA 7261

Part: VENT LINE — LEAKING (ENG OIL) · airframe 8,225 hrs · 13,909 cycles

MAJOR OIL LEAK. DISCOVERED BY NURSE STOWING EQUIPMENT IN REAR COMPARTMENT. HE ADVISED ME OF OIL ALL OVER THE SIDE OF AIRCRAFT. I SHUT DOWN THE AIRCRAFT AND EXITED TO INSPECT. REMOVED AND RE-INSTALLED OIL VENT LINE FROM TANK, GROUND RUN, LEAK CHECK WAS GOOD, REINSTALLED MAIN ROTOR BLADES, RII CHECKLIST AND OPERATIONAL CHECK FLIGHT COMPLETED.

ATA 5310

Part: CROSSBEAM — CHAFED (FUSELAGE) · airframe 7,980 hrs · 28,113 cycles

THE AFT LANDING GEAR CROSS BEAM (P/N: 350A214311.20). THE AFT CROSS BEAM IS DAMAGED DUE TO AFT LANDING GEAR FITTING LOWER HALF REPOSITIONED AND WORN WHICH CREATED LATERAL MOVEMENT OF LANDING GEAR CROSS TUBE AND CAUSED CHAFE DAMAGE TO THE AFT CROSS BEAM. NO CRACKS OR CORROSION NOTED, BUT PER GOM 5.8, ITEM 14 ANTICIPATE A REPAIR CLASSIFICATION AS MAJOR. AWAITING OFFICIAL RDAS FROM AIRBUS.

ATA 2810

Part: FUEL TANK — LEAKING (ZONE 100) · airframe 6,656 hrs · 23,804 cycles

AFTER INSTALLING A VECTOR AEROSPACE CRASH RESISTANT FUEL TANK FAA STC SR02492AK IN THE HELICOPTER. WE PROCEEDED TO COMMENCE OUR REQUIRED FUEL CHECKS. FUELED THE HELICOPTER AND VERIFIED CORRECT OPERATION OF THE FUEL LOW LEVEL INDICATION SYSTEM. ALL CHECKS WERE SATISFACTORY. COMMENCED TO FILL THE ENTIRE FUEL TANK AND CHECK FOR LEAKS. NONE WERE NOTED. BROUGHT AIRCRAFT BACK INSIDE AND LAID A LARGE SHEET OF PAPER UNDER THE FUEL TANK AREA. RETURNED THE NEXT MORNING AND FOUND FUEL LEAKING. AFTER FURTHER INVESTIGATION DETERMINED THE FUEL WAS LEAKING THRU THE FUEL QUANTITY INDICATOR WIRING HARNESS. REPLACE THE FUEL QUANTITY SENDING UNIT AND REFUELED THE AIRCRAFT. NO FURTHER LEAKS WERE NOTED.

ATA 5311

Part: FRAME — CRACKED (ZONE 100) · airframe 6,656 hrs · 23,804 cycles

DURING INSPECTION FOUND A CRACK IN THE RIGHT SIDE CABIN FLOOR STRUCTURE NEAR THE DOOR POST WITHIN THE DOOR STRUT FITTING. REPAIRED THE FRAME AS PER AIRBUS HELICOPTERS RDAS AHI 130 53 028 19A

ATA 5610

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 4,340 hrs · 15,207 cycles

WHILE COMING UP TO A 2 FT HOVER, A CRACK APPEARED ON THE LT PILOTS WINDSHIELD BEGINNING AT THE RT CTR OF WINDOW, CRACK GREW TO APPROX 8 INCHES IN LENGTH, MOVING TOWARD THE LT SIDE OF WINDOW, ALMOST EYE LEVEL, ABORTED TAKEOFF, LANDED BACK ON HELIPAD.

ATA 2110

Part: COMPRESSOR — SEIZED (A/C PACK) · airframe 3,707 hrs · 12,934 cycles

DURING TAKEOFF STRONG ELECTRICAL FUMES IN COCKPIT. SOURCE OF ELECTRICAL FUMES ISOLATED TO AIR CONDITIONER. AIR CONDITIONER TURNED OFF, FUMES DISSIPATED RAPIDLY. PERFORMED PRECAUTIONARY LANDING TO POINT OF ORIGINAL DEPARTURE.