N145HN
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| AIR METHODS LLC (QMLA) | Certificate holder | — | Matched by certificate designator |
| AIR METHODS LLC (QMLA) | Operator | 2016-04-26 – 2016-04-26 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
DURING INSPECTION A 4360.3 ITEM 3.4.4 FOUND CORROSION ON THE COPILOT SIDE COLLECTIVE SHAFT AT THE WELD FOR COLLECTIVE LEVER. AIRCRAFT REMAINS OUT OF SERVICE AT HIS TIME, PENDING REPLACEMENT OF COLLECTIVE CONTROL SHAFT.
PILOT REPORTED SMOKE AND OIL SEEPING FROM # 1 ENGINE LUBRICATION PIPE OF THE REAR BEARING. INSPECTED LUBRICATION PIPE OF THE REAR BEARING IAW MM 70-40-02-801. FOUND UNION LOOSE AT LUBRICATION PIPE. TORQUED UNION IAW MM 79-29-00-900-802-A01. PERFORMED GROUND RUN, NO DEFECTS WERE NOTED. RETURNED AIRCRAFT TO SERVICE.
WHILE CONDUCTING INSPECTION AAIP A 2210 â 1200 HOUR UNDER SECTION 2.3 AMM CH53-53-00, 6-1 AND FOLLOWING AMM CH 53-53-00, 4-2 TO COMPLETE INSPECTION, I REMOVED THE HORIZONTAL STABILIZER LEFT HAND END PLATE TO GAIN ACCESS TO INTERIOR OF HORIZONTAL STABILIZER FOR DETAILED INSPECTION TO COMPLETE AAIP END PLATE INSPECTION. AFTER GAINING ACCESS AND INSPECTING HORIZONTAL STABILIZER MORE DETAILED, A CRACK WAS FOUND AT THE AFT, OUTBOARD STRINGER ON THE TRAILING EDGE OF STABILIZER. THE CRACK WAS 41MM LONG THROUGH THE END POINT OF STRINGER STRETCHING OUT TO END ON HORIZONTAL STABILIZER. AFTER FINDING THE CRACK THE AMM WAS REFERRED TO FIND A REPAIR BUT THE AMM STATED âFOR INSTRUCTIONS CONTACT ECD SERVICE ENGINEERING OR A LOCAL ECD REPRESENTATIVE. MAINTENANCE HANGAR LEAD WAS NOTIFIED AND SDR WAS STARTED. THIS AIRCRAFT REMAINS OOS AT THE TIME OF THIS SUBMISSION PENDING THE COMPLETION OF THE SCHEDULED MAINTENANCE ITEMS AND REPAIR OF THIS DISCREPANCY.
CRACK FOUND IN MAIN ROTOR BLADE BY PILOT DURING PRE-FLIGHT. CRACK IS ON THE RED MAIN ROTOR BLADE, APPROX 3/4 INCHES LONG, CHORDWISE. BEGINNING APPROX 4 INCHES OTBD OF THE ROOT END OF THE BLADE. ACFT PLACED IN AOG STATUS IMMEDIATELY. CONTACTED SUPPORT FOR GUIDANCE.
UPON REMOVAL OF TAIL ROTOR SHAFT FROM GEAR BOX, FOUND METAL PARTICLES INSIDE CASING & EXCESSIVE WEAR ON END SHAFT SPLINES. EROSION IS APPROX .090 FORM END INWARD & .030 DEEP.
PILOT REPORTED OIL RESIDUE ON TAIL ROTOR GEARBOX & SCRATCH ON LEADING SIDE NEAR LT BOLT AFTER FLIGHT. AFTER FURTHER INSPECTION WITH TAIL ROTOR GEARBOX REMOVED, FOUND 1/2 INCH CRACK IN TAIL STRUCTURE AIRFRAME TOP CAP.
PILOT REPORTED OIL RESIDUE ON TAIL ROTOR GEARBOX & SCRATCH ON LEADING SIDE NEAR LT BOLT AFTER FLIGHT. MECHANIC INSPECTED & FOUND CRACK AFT OF LT AFT BOLT & TAIL ROTOR GEARBOX 1/4 QT LOW ON OIL.
AN ODOR OF FUEL IN THE NR 2 ENGINE COMPARTMENT, AND NOTICED THE ENGINE DECK HAD FUEL ON IT. DRIP FROM THE STARTING DRAIN VALVE DRAIN LINE. FOUND LEAK COMING FROM THE UNION BETWEEN THE STARTING DRAIN VALVE, AND IGNITION SOLENOID VALVE. FOUND O-RING HAD NOT PROPERLY SEATED. REMOVED O-RING, AND INSTALLED IT IAW MANUAL. OPS AND LEAK CHECKED GOOD.