N899CA
Registered owner: ALPINE AVIATION INC, UT (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| ALPINE AVIATION, INC. (TIMA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
WE WERE SCHEDULED FOR AN AIRCRAFT SWAP IN KBTM. I TOOK OFF OUT OF KRXE AT 10AM ON OUR IFR FLIGHT PLAN. ON THE WAY INTO KBTM WE ENCOUNTED SOME WEATHER, WE DID THE ILS 15 INTO KBTM. INBOUND ON THE ILS WE PUT THE GEAR DOWN AND NOTICED WE DIDN'T HAVE THE RIGHT GEAR INDICTION SO WE WENT MISSED AND FLEW THE HOLD AND NOTIFIED SALT LAKE CENTER. WE TROUBLE SHOOTED IN THE HOLD AND COULDN'T GET THE LIGHT TO INDICATE WE HAD ENOUGH FUEL TO FLY BACK TO SALT LAKE CITY, SO WE DIVERTED THERE. ONCE ON WITH SALT LAKE APPROACH WE PUMPED THE GEAR DOWN AND DID A VISUAL LOW APPROACH TO VERIFY THE GEAR WAS DOWN. AFTER WE GOT TOLD THE GEAR APPEARED TO BE DOWN WE LANDED 35 SAFELY.
WITH LANDING GEAR HANDLE SELECTED DOWN, NO GREEN DOWN AND LOCKED INDICATION ALONG WITH RED HANDLE WARNING. PILOT NOTED LANDING GEAR CIRCUIT BREAKER TRIPPED. RESET THE CIRCUIT BREAKER WHICH RESULTED IN NORMAL OPERATION. INVESTIGATION FOUND LANDING GEAR SELECTOR HANDLE HAD A METAL ID PLATE SEPARATED FROM THE HANDLE CAUSING SHORT TO HANDLE CONTACTS. REMOVED THE ID PLATE, NO FURTHER DEFECTS NOTED IN REGARDING OPERATION.
AFTER TAKEOFF THE LANDING GEAR FAILED TO RETRACT. LANDING GEAR CB WAS POPPED. PILOT ELECTED TO RETURN TO THE AIRFIELD AND LANDED UNEVENTFULLY. SUBSEQUENT INVESTIGATION FOUND THE LANDING GEAR REMOTE CIRCUIT BREAKER HAD VERY HIGH RESISTANCE IN THE CLOSED POSITION.
GEAR IN TRANSIT WARNING STAYED ON AFTER GEAR SELECTED UP, FOLLOWING TAKEOFF. PILOT RETURNED TO TAKEOFF AIRFIELD FOR UNEVENTFUL LANDING. SUBSEQUENT INSPECTION DETERMINED ALL GEAR FUNCTIONS WERE NORMAL. ERRONEOUS IN TRANSIT WARNING DETERMINED TO BE CAUSED BY FAULTY LG WARNING HORN FLASHER.
A CRACK WAS DISCOVERED IN THE UPPER WING SKIN OUTBOARD OF THE NACELLE AND AFT OF THE MAIN WING SPAR ON THE RIGHT WING. REMOVED THE DAMAGED SECTION OF SKIN. FABRICATED A NEW SECTION OF SKIN USING THE SAME TYPE MATERIAL AND THICKNESS AND INSTALLED USING A SPLICE DOUBLER OF ONE SIZE GREATER THICKNESS AND TWO ROWS OF SOLID RIVETS IAW BEECH 99 SIRM CHAP 20.
WHEN THE PILOT SELECTED GEAR UP AFTER DEPARTURE FROM BIL, THE GREEN LIGHTS EXTINGUISHED BUT THE RED IN-TRANSIT LIGHT DID NOT EXTINGUISHED. EXTENDED THE GEAR AND GOT 3 GREEN, RETRACTED THEM AGAIN AND STILL HAD THE IN TRANSIT LIGHT STAY ON. AT THIS POINT RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE LEFT GEAR DOOR CAM WAS DAMAGED WHICH PREVENTED THE LEFT GEAR FROM FULLY RETRACTING AND CONTACTING THE GEAR UP SWITCH. THE CAM WAS CHANGED AND THE GEAR OPERATED NORMALLY.
GEAR-IN-TRANSIT LIGHT DID NOT EXTINGUISH AFTER TAKE-OFF AND GEAR UP. PILOT CYCLED GEAR AGAIN WITH SAME RESULT. PILOT RETURNED TO DEPARTURE AND LANDED. MECHANIC FOUND THAT THE LT POWER LEVER SWITCH HAD FAILED. REPLACING THE SWITCH RESOLVED THE PROBLEM.
AIRCRAFT IN FLIGHT AT 13000 FT OIL PRESSURE AND TORQUE STARTS TO FLUCTUATED SLIGHTLY, MOMENTS LATER THE ENGINE FAILED. NO CAUSE FOR FAILURE HAS BEEN FOUND AT THIS TIME. THE ENGINE HAS BEEN TAGGED. THE ENGINE HAS 87.5 HOURS SINCE REPAIRS TO THE ENGINE AT AN ENGINE SHOP. (K)
DURING AN INSPECTION OF THE ELEVATOR, IT WAS FOUND THAT THE OUTBOARD ELEVATOR COLLAR WAS CRACKED AT THE TAPER PIN. THE DEFECTIVE TORQUE TUBE WAS REPLACED AND THE NEW TUBE (SERVICEABLE) WAS RIGGED IAW MM. INSPECTION OF THE CRACKED COLLAR WAS INCONCLUSIVE AS TO WHETHER THE CRACK WAS CAUSED BY NORMAL WEAR OR POSSIBLE OVER TORQUING DUE TO THE AMOUNT OF PAINT IN THE AREA.
IT WAS DISCOVERED DURING AN ENGINE CHANGE, THAT THE TUBE MOUNT HAD CHAFE MARKS BEYOND LIMITS. THE TUBE MOUNT WAS REPLACED WITH A SERVICABLE TUBE MOUNT. THE CAUSE OF THE CHAFING WAS DUE TO INDEQUATE CLEARANCE BETWEEN MOUNT AND BAFFLING AND FUEL LINES.
DURING PROPELLER CHANGE ON LEFT ENGINE, A SERIES OF CRACKS WERE FOUND ON THE INBOARD EXHAUST FLANGE. THE FLANGE IS A PART OF THE POWER SECTION, SO FIELD REPAIR WAS NOT POSSIBLE. THE AFFECTED POWER SECTION WAS REPLACED WITH A SERVICEABLE POWER SECTION. A POSSIBLE CAUSE FOR THE CRACKED FLANGE MAY HAVE BEEN THE RESULT OF OVERTORQUING THE HARDWARE ATTACHING THE EXHAUST STACKS TO THE FLANGE. (X)
SHIMMY DAMPENER ROD WAS FOUND TO HAVE CORROSION INSIDE AND OUT CAUSING FLUID TO LEAK BY THE O-RINGS. CORROSION SEEMS TO BE FROM NORMAL OPERATION. ROD WAS REPLACED.