N259AM

EUROCOPTER EC130 No injuries Part 135 — Air Methods Corp.

Operated by Air Methods Corporation (per NTSB report)

ATA 5300

Part: FRAME — CHAFED (ZONE 100) · airframe 4,577 hrs · 15,247 cycles

DAMAGE WAS NOTED TO THE X1790.15 FRAME (PN: 350A21-4099) IN THE FORM OF A CHAFE DAMAGE AREA. THE CHAFE DAMAGE IS LOCATED NEAR THE INBOARD RH CAMLOC AND WAS MEASURED TO BE APPROXIMATELY 0.70” X 0.175

ATA 5300

Part: MOUNT — UNKNOWN (ZONE 100) · airframe 4,577 hrs · 15,247 cycles

DAMAGE TO THE AFT LANDING GEAR FITTING (P/N: 350A21-4674.20) IN THE FORM OF A GOUGE / CHAFE. THE DAMAGE IS AT THE TWO HOLES OF THE TWIN CLEVIS, AND WAS MEASURED TO BE APPROXIMATELY 10.381MM (0.409”). THE BOLT HOLE IS ORIGINALLY 10JS13 MM (10.0MM (+/- 0.11)) DIAMETER (0.394” (+/-0.004”)).

ATA 5300

Part: BULKHEAD — CHAFED (ZONE 200) · airframe 4,577 hrs · 15,247 cycles

DAMAGE TO THE FWD BULKHEAD LH PANEL (PN: 350A21-4444.21) IN THE FORM OF 3EA CHAFED AREAS IN THE PART; 2EA OF WHICH ARE LOCATED NEAR STIFFENING FEATURES, AND 1EA IS LOCATED NEAR THE INBOARD EOP. THE 2EA CHAFE DAMAGE AREAS NEAR THE STIFFENING FEATURES WERE MEASURED TO BE APPROXIMATELY 0.15” X 0.05” AND 0.015” DEEP, AS WELL AS 0.10” X 0.03” AND 0.007” DEEP. THE CHAFE DAMAGE AREA NEAR THE INBOARD EOP WAS MEASURED TO BE APPROXIMATELY 0.225” X 0.125” AND 0.007” DEEP.

ATA 5302

Part: TAIL BOOM — CHAFED (ZONE 200) · airframe 4,577 hrs · 15,247 cycles

DAMAGE TO THE TAIL BOOM LH SKIN (P/N: 350A23-4288.20) IN THE FORM OF A CHAFE DUE TO DRILL START LOCATED AT LOWER FORWARD SIDE OF THE AFT BATTERY BOX AREA. THE DAMAGE MEASURED TO BE APPROXIMATELY 0.1285” X 0.1285” AND 0.0175” DEEP.

ATA 5300

Part: WEB — CRACKED (FLOOR) · airframe 3,550 hrs · 11,963 cycles

DURING AAIP A1660 600HR SCHEDULED INSPECTION IT WAS DISCOVERED THAT THE WEB @ STA. 845 RBL 673.5 HAS A CRACK APPROX 2.50 INCHES ON TOP R/H SIDE IN WHICH IS ALMOST IDENTICAL TO EA 17-5310-EA-2632 DATED 01/23/2019 FOR ACFT. 7248. THIS CRACK IS BEYOND LIMITS TO STOP DRILL AND REQUIRES STRUCTUAL SHEET METAL REPAIR. AIRCRAFT IS CURRENTLY OUT OF SERVICE.

ATA 2820

Part: VENT LINE — OUT OF POSITION (FUEL SYSTEM)

THE AIRCRAFT FUEL QUANTITY READING DECREASED RAPIDLY IN FLIGHT ON THE VEMD CAUSING THE PILOT TO PERFORM A PRECAUTIONARY LANDING. THE CAUSE WAS THE AFT HOSE FROM THE FUEL SYSTEM NORMALLY PROTRUDING FROM THE BELLY OF THE AIRCRAFT DIRECTLY BELOW THE FUEL CELL WAS CAUGHT AT AN ANGLE IN THE BELLY PANEL. THIS ALLOWED NO VENTING TO TAKE PLACE AND CAUSED AN INTERNAL SUCTION WHICH ADVERSELY AFFECTED THE INDICATION OF FUEL QUANTITY. WHEN FREED TO ITS NORMAL OPERATING POSITION, THE HOSE SUCKED AIR FOR APPROXIMATELY 30 SECONDS. THE VEMD THEN DISPLAYED PROPER FUEL QUANTITY.

ATA 5302

Part: FRAME — CRACKED (TAILBOOM) · airframe 2,937 hrs · 9,998 cycles

DURING A 300 HOUR INSPECTION OF THE HORIZONTAL STABILIZER, FOUND THE UPPER RT ATTACH FITTING BROKEN, AND THE FRAME IN THE TAILBOOM CRACKED.

ATA 7397

Part: CONNECTOR — DIRTY (FADEC) · airframe 2,124 hrs · 7,373 cycles

THE PILOT REPORTED THAT UPON TAKEOFF WITH CREW & PATIENT ONBOARD HE HEARD A WARNING TONE AS HE WAS CLIMBING & TRANSITIONING TO FWD FLIGHT. HE IMMEDIATELY REDUCED POWER & GLANCED AT THE CAUTION & WARNING PANEL & VEMD. THERE WAS AN EXCEEDANCE DETECTED INDICATION THAT WAS OBSERVED. THE PILOT IMMEDIATELY RETURNED TO THE HELIPAD & CALLED THE MECHANIC. THE MECHANIC ARRIVED & FOUND THE VEMD HAD RECORDED AN OVER TORQUE OF 106% FOR 1 SECOND. PERFORMED THE NECESSARY INSPECTIONS IAW THE AMM, CLEANED THE FADEC CONNECTIONS WITH STABILIZER 22 & RETURNED THE ACFT TO SERVICE.

ATA 5310

Part: DOOR FRAME — CRACKED (BATTERY BAY) · airframe 812 hrs · 2,722 cycles

DURING AIR WORTHINESS CHECK, MECHANIC FOUND A CRACK ABOUT 1.5 INCH LONG IN THE UPPER RT CORNER OF THE BATTERY COMPARTMENT ACCESS DOOR OPENING. THE CRACK WAS ORIGINALLY NOTICED IN THE DOUBLER AND UPON FURTHER INSPECTION FOUND A CRACK IN THE SKIN BENEATH THE DOUBLER. OPEN

ATA 7200

Part: ENGINE — MAKING METAL (NR 1) · airframe 179 hrs · 541 cycles

ENG 1 CHIP LIGHT ILLUMINATED IN CRUISE FLIGHT. 3 ATTEMPTS WERE MADE WITH THE CHIP BURNING SYS TO EXTINGUISH LIGHT. LIGHT REMAINED ILLUMINATED. PILOT SET UP ACFT FOR OEI OPERATIONS AND PLACED 1 ENG SWITCH TO IDLE. 1 ENG OIL PRESSURE AND TEMPS WERE MONITORED AND REMAINED WITHIN NORMAL RANGES. CHECKLIST WAS USED TO BACKUP PROCEDURE. OEI FLIGHT WAS CONTINUED TO DESTINATION WHICH AT THAT TIME WAS 8 MILES AWAY. SINGLE ENGINE LANDING WAS MADE TO A HOVER WITH REMAINING ENGINE TORQUE WITHIN 2 MINUTE RANGE. ACFT WAS SHUTDOWN AND MX CALLED.