N11FQ
Registered owner: AIR METHODS LLC, CO (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
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.
36 reports on file, 2000-08-01 – 2024-06-14.
Part: ATTACH ANGLE — CRACKED (CARGO BAY) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE BAGGAGE COMPARTMENT LH FWD LOWER ANGLE (P/N: 350A210053.28) IN THE FORM OF GOUGE/CRACK. THE GOUGE/CRACK DAMAGE MEASURED TO BE APPROXIMATELY 0.13â IN DIAMETER.
Part: FRAME — CORRODED (ZONE 100) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE AFT UPPER FRAME (P/N: 350A21-1242.35) IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS ON THE UPPER FLANGE OF FRAME AT LH AND RH BOTTOM SIDE NEAR THE AFT LOWER FRAME. THE LH SIDE CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 0.71: X 2.05â AND THROUGH THICKNESS DEPTH. THE RH SIDE CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 0.573â X 0.71â X 0.015â.
Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 9,295 hrs · 11,581 cycles
THE UPPER 7° BULKHEAD DOUBLER (PN: 350A21-0849.20) IS CORRODED AT THE LOCATION OF A PASS-THRU HOLE. THE DAMAGE AREA WAS REPORTED TO BE 0.80â X 0.50â AND 0.030â DEEP AT THE DEEPEST POINT
Part: FLOORBEAM — CORRODED (CABIN) · airframe 9,295 hrs · 11,581 cycles
DAMAGE IS ON THE LH CABIN FLOOR EDGE FITTING (P/N: 350A214753.20) IN THE FORM OF CORROSION AND CRACKS. THE LH FITTING PLATE IS EXCESSIVELY CORRODED AND THE CRACK DAMAGES AT TWO FASTENER HOLES TO EOP WHICH RESULTS IN REPLACEMENT OF LH FITTING.
Part: BONDING PLATE — CORRODED (FUSELAGE) · airframe 9,295 hrs · 11,581 cycles
DAMAGE IS ON THE TAIL BOOM VHF ANTENNA BASE PLATE (P/N: 350A65-1707.00) IN THE FORM OF CORROSION. THE BASE PLATE IS EXCESSIVELY CORRODED AND DEPTH OF THE DAMAGE IS ALL THE WAY THROUGH THICKNESS WHICH RESULTS IN REPLACEMENT OF ANTENNA BASE PLATE.
Part: CROSSBEAM — CORRODED (UNKNOWN) · airframe 9,295 hrs · 11,581 cycles
THE RH X2244 CROSSBEAM (PN: 350A21-0861.20) IS CORRODED IN AN AREA ON THE LOWER OUTBOARD CORNER OF THE CROSSBEAM. THE DAMAGE WAS REPORTED TO BE 0.572â X 0.179â AND 0.028â DEEP
Part: CROSSTUBE — CORRODED (MLG) · airframe 9,295 hrs · 11,581 cycles
THE AFT LANDING GEAR CROSSTUBE FITTING (PN: 350A21-0960.20) IS CORRODED IN MULTIPLE AREAS ON THE LOWER SURFACE. THE DEEPEST DAMAGE AREA WAS REPORTED TO BE 0.022â DEEP AND THE LARGEST AREA IS APPROXIMATELY 0.40â WIDE WITH VARIOUS LENGTHS
Part: CROSSBEAM — CORRODED (BS 1790) · airframe 9,295 hrs · 11,581 cycles
THE RH X1790 CROSSBEAM (PN: 350A21-0572.20) IS CORRODED IN AN AREA WHERE IT CONTACTS THE RH Y400 BEAM (PN: 350A21-0587.20)
Part: CRADLE — CORRODED (FUEL) · airframe 9,295 hrs · 11,581 cycles
THE LH FWD FUEL CRADLE REINFORCEMENTS HAD DAMAGE IN THE FORM OF CORROSION. THE LH FWD CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 1.0â X 0.80â X 0.008â.
Part: ATTACH ANGLE — CORRODED (MLG) · airframe 9,295 hrs · 11,581 cycles
REAR LANDING GEAR ATTACHMENT LOWER ANGLE HAS DAMAGE IN THE FORM OF CORROSION. THE DAMAGE NEAR THE ANGLE OVERLAPS WITH MACHINED FRAME AND AFT LOWER BELLY FAIRING. THE DAMAGE IS ON THE VERTICAL FACE OF THE ANGLE AT PREVIOUS REPAIR LOCATION AND IS MEASURED TO BE APPROXIMATELY 0.50â X 1.02â X 0.038â.
Part: WEB — CORRODED (ZONE 100) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE LOWER CENTER WEB IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS TOWARDS THE AFT SIDE OF THE WEB NEAR LIGHTENING HOLES AND MEASURED TO BE THROUGH THICKNESS IN DEPTH.
Part: BRACE — CORRODED (ZONE 100) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE LH VERTICAL ANGLE (PN: 350A62-1148.21) ON THE AFT SECTION FWD LOWER FRAME IN THE FORM OF CORROSION. THE CORRODED AREA IS LOCATED AT THE BOTTOM END OF THE ANGLE, AND WAS MEASURED TO BE APPROXIMATELY 0.875â X 0.875â IN SIZE THROUGH THE FULL THICKNESS OF THE PART.
Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 9,295 hrs · 11,581 cycles
CORROSION DAMAGE ON THE FWD UPPER SKIN MEASURED TO BE APPROXIMATELY 0.80â X 0.60â X 0.003â
Part: SKIN PANEL — CORRODED (ZONE 200) · airframe 9,295 hrs · 11,581 cycles
FIRST DAMAGE IS ON THE AFT FUSELAGE LH SIDE SKIN PANEL IN THE FORM OF CORROSION. THE LH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15â X 0.35â X 0.009â.
Part: CRADLE — CORRODED (FUEL) · airframe 9,295 hrs · 11,581 cycles
RH AFT FUEL CRADLE REINFORCEMENTS HAS DAMAGE IN THE FORM OF CORROSION. THE RH AFT CORROSION DAMAGE MEASURED TO BE APPROXIMATELY 2.1â X 0.80â X 0.009â.
Part: SKIN PANEL — CORRODED (ZONE 200) · airframe 9,295 hrs · 11,581 cycles
DAMAGE IS ON THE AFT FUSELAGE RH SIDE SKIN PANEL (P/N: 350A210046-21 IN THE FORM OF CORROSION. THE RH SIDE SKIN DAMAGE IS NEAR TOP EDGE WHERE ENGINE DECK OVERLAPS AND MEASURED TO BE APPROXIMATELY 0.15â X 0.20â X 0.011â.
Part: STIFFENER — CORRODED (TAIL BOOM) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE TAIL BOOM LH FWD STIFFENER MEASURED TO BE APPROXIMATELY 0.85â X 0.85â X 0.0125â IN THE FORM OF CORROSION.
Part: SUPPORT ANGLE — CORRODED (ZONE 100) · airframe 9,294 hrs · 11,581 cycles
EXFOLIATION CORROSION LOCATED ON FWD. L/H SIDE STIFFENER OF MASTER ELECTRICAL BOX.
Part: ANGLE — CORRODED (ZONE 100) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE LH VERTICAL ANGLE (PN: 350A62-1148.21) ON THE AFT SECTION FWD LOWER FRAME IN THE FORM OF CORROSION. THE CORRODED AREA IS LOCATED AT THE BOTTOM END OF THE ANGLE, AND WAS MEASURED TO BE APPROXIMATELY 0.875â X 0.875â IN SIZE THROUGH THE FULL THICKNESS OF THE PART
Part: WEB — CORRODED (ZONE 100) · airframe 9,295 hrs · 11,581 cycles
DAMAGE TO THE LOWER CENTER WEB (P/N: 350A21-4300.20) IN THE FORM OF CORROSION. THE CORROSION DAMAGE IS TOWARDS THE AFT SIDE OF THE WEB NEAR LIGHTENING HOLES AND MEASURED TO BE THROUGH THICKNESS IN DEPTH.
Earlier reports · 2000–2014 · 16 reports
2014
Part: BOLT — LOOSE (M/R MAST) · airframe 1,628 hrs · 2,199 cycles
THE DIGITAL NR READING WAS FLUCTUATING IN FLIGHT. AFTER TROUBLESHOOTING OF THE NR PICKUP ON THE NR GAUGE, IT WAS DECIDED TO INSPECT THE PHONIC WHEEL FOR SECURITY. UPON REMOVAL OF THE EPICYCLIC, IT WAS FOUND THAT SIX ATTACHMENT BOLTS, 2 WERE TORQUED TO 100 IN LBS & 4 WERE AT 20 IN LBS, 195 IN LBS IS BOOK TORQUE. UPON INSPECTION OF THE PHONIC WHEEL IT WAS DETERMINED THAT IT WAS SPINNING DUE TO LOSS OF TORQUE ON THE BOLTS, WHICH WAS DUE TO THE GRAPH OIL COATING DETERIORATING FROM THE MATING SURFACES OF THE PHONIC WHEEL, EPICYCLIC & MAST CONTACT SURFACES. REPLACEMENT OF THE PHONIC WHEEL HAS FIXED THE NR FLUCTUATING READING.
Part: ENGINE — MAKING METAL
DURING FLIGHT, ENGINE CHIP LIGHT ILLUMINATED AND PILOT MADE A PRECAUTIONARY LANDING. MECHANIC INSPECTED ENGINE CHIP PLUGS. A SIGNIFICANT AMOUNT OF METAL WAS FOUND ON THE ELECTRIC PLUG, MODULE 01 CHIP PLUG AND THE ENGINE OIL TANK CHIP PLUG. IT WAS DETERMINED TO CHANGE THE ENGINE IN THE FIELD.
2003
Part: MODULE — SHORTED (ROW 17)
DURING (A) CHECK PIE MAINTENANCE FOUND FLOOR EMERGENCY LIGHT AT ROW 17 WHITE LIGHT NOT WORKING. REMOVED AND REPLACED LAMP MODULE IAW MD80 MM 33-53-01. OPERATIONAL CHECK GOOD.
Part: COVER — LOOSE (CABIN)
FLOOR PATH LIGHTING LOOSE. REMOVED AND REPLACED SECTIONS OF FLOOR PATH LIGHTING COVERS THAT WOULD NOT STAY IN PLACE IAW MD-80 MM 33-53-01. OPERATIONAL CHECK GOOD. (M)
2002
Part: BATTERY — DISCHARGED (CABIN)
FORWARD FLIGHT ATTENDANTS EMERGENCY FLASHLIGHT INOPERATIVE. PROBLEM WAS DETERMINED TO BE BATTERIES. REMOVED AND REPLACED BATTERIES IAW 25-60-00 MM. OPERATIONAL CHECK GOOD. (M)
Part: WINDSHIELD — CRACKED (COCKPIT)
AFTER TAKEOFF AT 8000 FEET, THE CAPTAINS WINDSHIELD OUTER PANE CRACKED. AIR RETURN CLE FOR REPLACEMENT OF WINDSHIELD. REMOVED AND REPLACED THE CAPTAINS WINDSHIELD IAW MM 56-10-02, ALSO REMOVED AND REPLACED CAPTAINS WINDSHIELD TEMPERATURE CONTROLLER DUE OT WINDSHIELD CHANGE IAW MM 30-41-01, OPERATIONAL CHECK GOOD. (M)
Part: SWITCH — DIRTY (R1 DOOR)
AT 6000 FEET, R-1 DOOR OPEN ANNUNCIATOR LIGHT ILLUMINATED. NO PRESSURIZATION LEAKS. NO AIR LEAKS. RETURNED TO PUJ FOR EVALUATION. MEL'D INDICATION PER MEL 52-7. PERFORMED OVERWEIGHT INSPECTION. CLEANED SWITCH, OPERATIONAL CHECK GOOD IAW MM 52-07-00. (M)
Part: SWITCH — INTERMITTENT (R1 DOOR)
AT 6000 FT REAR 1 DOOR OPEN ANNUNCIATOR LIGHT ILLUMINATED. NO PRESSURIZATION LEAKS. NO AIR LEAKS. RETURNED TO AIRPORT FOR EVALUATION. AIRCRAFT CONTINUED FLIGHT WHERE MAINTENANCE CLEANED SWITCH, OPERATIONAL CHECK GOOD IAW MM, MEL CLEARED.
Part: SWITCH — DIRTY (R1 DOOR)
AT 6000 FEET, R-1 DOOR OPEN ANNUNCIATOR LIGHT ILLUMINATED. NO PRESSURIZATION LEAKS. NO AIR LEAKS. RETURNED TO PUJ FOR EVALUATION. MEL'D INDICATION PER MEL 52-7. AIRCRAFT CONTINUED FLIGHT TO CLE WHERE MAINTENANCE CLEANED SWITCH, OPERATIONAL CHECK GOOD IAW MM 52-07-00 MEL 52-7 CLEARED. (M)
Part: COMPUTER — CONTAMINATED (E/E BAY)
IFE DIVERTED INTO BWI, LOST ALL INSTRUMENT, BOTH FMS, BOTH DFG C'S. IRU'S MAINLY WENT OUT. PROBLEM ON GROUND, MAINTENANCE FOUND WATER FROM HEAVY RAINS IN E/E. DRIED MOISTURE ON DFGC'S IAW 34-33-00 AND 22-01-5. ALL SYSTEMS OPS CHECK OK. (M)
Part: IRU — CONTAMINATED (INSTRUMENTS)
FLIGHT DIVERTED, LOST ALL INSTRUMENTS, BOTH FMS, BOTH DFG C, IRU MAINLY WENT OUT. PROBLEM ON GROUND, MAINTENANCE FOUND WATER FROM HEAVY RAINS. DRIED MOISTURE ON DFGC, IAW. ALL SYSTEMS OPS CHECKED OK.
Part: CHIP DETECTOR — WORN (LT ENGINE)
DEPARTED UNDER NORMAL CONDITIONS. LEVELING OFF AT 28,000 FEET, CRUISE ALTITUDE, LOSS OF LT ENGINE OIL QUANTITY AND LOW OIL PRESSURE WAS OBSERVED BY THE FLIGHT CREW. THE NR 1 ENG WAS SHUT DOWN. FLIGHT WAS DIVERTED AND LANDED WITH NO FURTHER INCIDENTS. DURING POST FLIGHT INSP AND IN PROCESS OF TROUBLESHOOTING CAUSE OF THE NR 1 ENGINES LOSS OF OIL QUANTITY AND LOW OIL PRESSURE MAINTENANCE FOUND THE ACCESSORY GEAR BOX CHIP DETECTOR LYING IN THE BOTTOM OF THE NR 1 ENGINE LOWER COWLING. A CLOSE INSPECTION OF THE CHIP DETECTOR HOUSING REVEALED EXCESSIVE WEAR WITH PART OF THE HOUSING RETAINER BROKEN AWAY. THE CHIP DETECTOR ASSEMBLY WAS REPLACED WITH A NEW ASSEMBLY IAW MM. AIRCRAFT WAS RETURNED TO SERVICE.
2000
Part: PANEL — CORRODED (TAIL)
CORROSION ON LEFT AND RIGHT HORIZONTAL STABILIZER LEADING EDGE PANELS. REPAIRED PER ECRA N11FQ-55-004-EAC. SUBMITTER STATED CAUSE MAY BE DUE TO OPERATING OVER SALT WATER. (X)
Part: ELEVATOR — DENTED (LT LOWER SKIN)
DENT ON LT ELEVATOR LOWER SURFACE STA XE=148. REPAIRED PER ECRA N11FQ-55-002-EAC. SUBMITTER STATED CAUSE MAYBE DUE TO SOMETHING COMING OFF THE RUNWAY. (X)
Part: PANEL — CORRODED (LT AND RT WING)
CORROSION ON LT AND RT WING LEADING EDGE DOOR ASSEMBLIES. REPAIRED PER ECRA N11FQ-57-0003-EAC. SUBMITTER STATED CAUSE MAY BE DUE TO OPERATING OVER SALT WATER. PROTECT EXTERIOR AIRCRAFT SKINS AFTER WASH. WASH AIRCRAFT MORE WHEN FLYING OVER SALT WATER. (X)
Part: WEB — CRACKED (FUSELAGE)
CORROSION AND CRACK ON CUSP WEB STA 1174 - STA 1307, LBL 45.0 - LBL 60.0. REPAIRED PER ECRA N11FQ-53-001-EAC. POSSIBLE CAUSE: WATER LEAKS FROM LAVATORIES. (X)