N587MH
Registered owner: AIR METHODS LLC, CO (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Air Methods Corp. (QMLA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
8 reports on file, 2012-06-01 – 2023-06-02.
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 4,365 hrs · 16,425 cycles
CHAFFE DAMAGE FOUND TO FRAME 4 GUSSET P/N B533K3231-202 AT RH WL 2,650MM AND CHAFFE DAMAGE FOUND TO THE FRAME 5 INTERCOSTAL P/N BK533230-201 LH WL 2650 MM. REPAIRED PER AIRBUS RDAS-BK117-53-2023-1491
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 4,365 hrs · 16,425 cycles
CORROSION DAMAGE FOUND LH KEEL BEAM LOWER CAP P/N B533K5515-201 WHERE IT JOINS TO THE AFT CROSS TUBE CHANNEL DOUBLER AFT STRAP P/N B533K7011. REPAIRED PER AIRBUS RDAS-BK117-53-2023-1425
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 4,365 hrs · 16,425 cycles
CORROSION DAMAGE FRAME 1 AT STATION 1,672.5MM AND FWD CABIN FLOOR P/N B533K8032-201 ON PILOT'S SIDE. COMPLETED REPAIR PER RDAS-BK117-53-2023-1375
Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 4,625 hrs · 16,425 cycles
CHAFE DAMAGE WAS DISCOVERED ON LH FWD KEEL BEAM WEB P/N B531K1221-201 NEAR THE ADC MOUNTING BRACKET. CHAFE DAMAGE WAS ALSO DISCOVERED ON THE LH VIBRATION ABSORBER BRACKET P/N B183M1015202. REPAIRED PER AIRBUS RDAS-BK117-53-2023-0588
Part: TRIM TAB — CRACKED (ROTOR BLADE) · airframe 2,114 hrs · 7,958 cycles
PILOT PERFORMING AIRWORTHINESS INSPECTION FOUND A CRACK AT THE UPPER INBD TAB ATTACHMENT OF THE TRIM TAB ON THE YELLOW MAIN ROTOR BLADE. INSPECTED THE TRIM TAP & FOUND 10 MM CRACK AT TRIM TAB RIVET ATTACHMENT, 7 MM WAS ALLOWABLE & THE ACFT WAS TAKEN OUT OF SERVICE FOR THE TRIM TAB REPLACEMENT. MAIN ROTOR BLADE SN 1018 WAS REMOVED FOR TRIM TAB REPLACEMENT. THE TRIM TAB WAS REMOVED & THE TRIM TAB SURFACE WAS INSPECTED & THERE WAS DELAMINATION FROM 1 RIVET HOLE TO THE TE. THE TECH REP WAS CONTACTED & PICTURES SENT FOR THEIR OPINION. IT WAS DETERMINED THAT THE DELAMINATION WAS OUT OF LIMITS & THE BLADE WILL BE SENT FOR REPAIR OF THE TRIM TAB ATTACHMENT AREA & INSTALLATION OF A NEW TRIM TAB.
Part: TRANSMISSION — MAKING METAL (MAIN ROTOR) · airframe 1,437 hrs · 5,522 cycles
PILOT WAS IN CRUISE FLIGHT, TO AIRPORT FOR FUEL AND MAIN TRANSMISSION CHIP LIGHT ILLUMINATED, PERFORMED CHIP BURN AND REMAINED ILLUMINATED. LANDED AND PERFORMED SECOND BURN AND AND THE CHIP LIGHT WENT OUT. MECHANIC WAS CALLED, INSPECTED THE CHIP DETECTORS AND FOUND SMALL AMOUNT OF FUZZ THAT WAS WITHIN THE "NORMAL WEAR" CATEGORY IAW MM CHAP 63-41-00, 6-02. CLEANED, REINSTALLED AND PERFORMED 10 MIN GROUND RUN WITH NO FURTHER CHIP INDICATIONS. ACFT RETURNED TO SERVICE.
Part: GEARBOX — MAKING METAL (TAIL ROTOR) · airframe 1,435 hrs · 5,515 cycles
AFTER TAKEOFF FROM BASE PAD, TAIL ROTOR CHIP LIGHT CAME ON, PILOT RETURNED TO BASE, ATTEMPTED TO BURN CHIP AND LIGHT REMAINED ON. PILOT CALLED THE MECHANIC. MECHANIC INSPECTED TAIL ROTOR GEAR BOX AND INTERMEDIATE GEAR BOX. FUZZ WAS FOUND ON THE INTERMEDIATE GEAR BOX CHIP DETECTOR AND NO CHIPS. GEAR BOX WAS DRAINED, FLUSHED AND SERVICED. ACFT WAS GROUND RUN FOR 10 MINUTES AND NO CHIP LIGHTS ILLUMINATED. INTERMEDIATE GEAR BOX CHIP PLUG WILL BE INSPECTED IN 10 HOUR IAW MM CH 65-22-00,6-1.
Part: FCU — OUT OF TOLERANCE (NR 1 ENGINE) · airframe 1,130 hrs · 4,337 cycles
PERFORMED ENGINE ZONE 8 INSPECTION, RUN UP AND LEAK CHECKED, AND STARTED POWER CHECK PROCEDURE. N1, N2 AND TORQUE FLUCTUATING, 1-2 PERCENT ON N1, 2-3 PERCENT ON THE TORQUE. INSPECTED P2 LINE, PERFORMED LEAK CHECKS, AS DIRECTED BY THE TECH REP AND RAN UP AGAIN. ENGINE NOT STARTING SMOOTH AND FLUCTUATION CONTINUED, MORE PRONOUNCED AT HIGHER SPEED. REPLACED THE FCU.