N911UG
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.
4 reports on file, 2022-10-11 – 2025-02-20.
Part: ENGINE — MAKING METAL (NR 1) · airframe 8,453 hrs · 30,453 cycles
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 PROCEDURE WAS COMPLETED WITH NO JOY. OEI POWER WAS ESTABLISHED AND #1 ENG WAS BROUGHT TO GROUND IDLE AND SUBSEQUENTLY THE ENG CHIP LIGHT EXTINGUISHED. KCAE WAS APPROXIMATELY 6 NM AWAY, CONTACT WAS MADE AND THEY WERE NOTIFIED OF OUR SITUATION. UPON SHORT FINAL THE #1 ENG WAS BROUGHT TO FLIGHT AND WHEN THE POWER WAS BROUGHT ABOVE 50% TQ THE #1 ENG CHIP LIGHT ILLUMINATED. LANDING AT THE FBO RAMP WENT WITHOUT INCIDENT. THE PROPER CHANNELS WERE CALLED AS PER THE PMIC. THERE WAS NO SURGING OR ABNORMAL INDICATIONS OTHER THAN THE ENG CHIP LIGHT.
Part: FRAME — CRACKED (ZONE 200) · airframe 7,269 hrs · 26,714 cycles
DURING A SCHEDULED INSPECTION ASB21-01, DAMAGE WAS DISCOVERED AT FRAME 5 AT APPROXIMATELY FS 4,709MM RELATING TO THE STC SR00566DE, DRAWING 739-1600, WALL. THE DAMAGE IS ADJACENT TO THE MEDICAL WALL ATTACH FITTING LOCATIONS. PERFORMED THE ALERT SERVICE BULLETIN ASB21-01, REVISION A. ADDITIONAL DAMAGE WAS ALSO NOTED ON THE LT AND RT CABIN FRAME 5 ASSEMBLY AND REINFORCEMENT ANGLE AT APPROXIMATELY FUSELAGE STATION 4,709MM, WATER LINE 2,600MM. THIS DAMAGE IS RELATED TO STC SR09164 â DRAWING 135M-420, EMS SEAT & STRUCTURE INST-EC-135. THIS INSTALLATION WAS REMOVED AND REPLACED WITH THE AMC EMS INTERIOR PREVIOUSLY MENTIONED ABOVE. THERE IS ONE CRACK ON THE LT STRUCTURE WHERE THE BEAM ASSY ATTACHED TO THE FRAME 5 MEASURING APPROXIMATELY 0.50 IN LENGTH AND ONE CRACK IN THE RT STRUCTURE WHERE THE BEAM ASSY ATTACHED TO THE FRAME 5 MEASURING APPROXIMATELY 0.70 IN LENGTH. THESE CRACKS WERE STOP DRILLED, THEN REINFORCED VIA REPAIR DOUBLERS IAW RDAS AHI 135 53 048 19, REVISION B.
Part: DECK PLATE — DELAMINATED (CABIN) · airframe 7,269 hrs · 26,714 cycles
DURING 1000 HOUR INSPECTION, DELAMINATION DAMAGE WAS DISCOVERED ON THE AFT CABIN FLOOR (PN: L533M1015104) ON THE LOWER SKIN PANEL (PN: L533M1416234) MEASURING APPROXIMATELY 8.5â X 7.75â AT THE FORWARD SIDE OF THE FLOOR. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2022-2329, ISSUE A DATED 16 SEP 2022.
Part: DECK PLATE — CORRODED (COCKPIT) · airframe 7,269 hrs · 26,714 cycles
DURING 1000 HOUR INSPECTION, CORROSION DAMAGE WAS DISCOVERED ON THE COCKPIT FLOOR (PN: L533M1013108) AT THE RH FORWARD GROUNDING POINT. A DETAILED DESCRIPTION OF THE DAMAGE AND APPROVED REPAIR PROCEDURES ARE PROVIDED IN AIRBUS REPAIR DESIGN APPROVAL SHEET RDAS-EC135-53-2022-2375, ISSUE A DATED 16 SEP 2022.