N24BH
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
WHILE IN CRUISE FLIGHT THE CIRCUIT BREAKER PANEL STARTED SMOKING. PILOT REQUESTED APPROACH FOR PRIORITY IN HELENA, MT. PILOT SAID THE SMOKE SHORTLY STOPPED AFTER 5 SECONDS. PILOT HAD A NORMAL LANDING IN KHLN AND CONTACTED MAINTENANCE. MAINTENANCE SAID THAT DE-ICE FLUID HAD LEAKED INTO THE PANEL.
DURING CRUISE CLIMB AT APPROX 9000 FT, THE LT ENG SUDDENLY LOST ALL POWER. ACFT RETURNED TO DEPARTURE LOCATION & LANDED WITHOUT INCIDENT. INSPECTION REVEALED THE LT ENG HIGH PRESS FUEL PUMP GEAR SET SPLINE WAS STRIPPED RESULTING IN FUEL PUMP FAILURE.
INSPECTION REVEALED A CRACK IN THE RT ELEVATOR LE RIB. THE RIB WAS REPLACED WITH A NEW RIB.
COWL OPENED AFTER TAKEOFF. PILOT STATED THAT HE LATCHED THE COWL, BUT THERE IS NO WAY TO VISUALLY CONFIRM THAT THE LATCHES WERE CONNECTED. COWL WAS SUBSTANTIALLY DAMAGED BY BUFFETING.
THE SKIN ON THE UPPER LEADING EDGE OF THE RT AILERON WAS FOUND TO BE TEARING AFT. INVESTIGATION DETERMINED THAT THERE WAS SIGNIFICANT CORROSION ON THE INSIDE OF THE AILERON. (K)
LANDING GEAR FAILED TO EXTEND. INSPECTION FOUND A CORRODED GROUND WIRE. THE FAILURE WAS INTERMITTENT THIS CAUSED CONSIDERABLE TROUBLE IN THE TROUBLESHOOTING AND SEVERAL HOURS OF TIME TO REPAIR THE PROBLEM. (K)
LEFT ENGINE COWLING SIDE DOOR DEPARTED FROM AIRCRAFT DURING FLIGHT. INSPECTION REVEALED THAT THE CAUSE WAS MOST LIKELY, FAILURE TO SECURE DOOR PANEL PRIOR TO FLIGHT NM-SLC-FSDO. (M)
THE AIRCRAFT WAS BROUGHT INTO MAINTENANCE FOR A SCHEDULED INSPECTION. UPON INSPECTION OF THE LEFT ENGINE, A HOLE WAS FOUND IN THE POWER SECTION CASE. THE HOLE CAUSED DAMAGE TO EXTERNAL WIRING AND TRANSFER TUBES. SUBMITTER STATED CAUSED BY A LIGHTING STRIKE. (X)
A TREND HAS DEVELOPED INDICATING PROCEDURES, TECHNIQUES, OR WORKMANSHIP OF OVERHAULED VANE RINGS IS RESULTING IN PREMATURE FAILURE OF PN 3032651 WHICH RESULTS IN UNSATISFACTORY ENGINE PERFORMANCE AND POSSIBLE ENGINE FAILURE. (X)
NOSE STEERING REPORTED LOOSE AND INSPECTION REVEALED NOSE STEERING TORQUE ARM HOLE TO ACTUATOR ELONGATED. REPLACED NOSE STEERING TORQUE ARM WITH SERVICEABLE ARM. THE ELONGATION COULD HAVE BEEN PREVENTED WITH THE ADDITION OF SHIMS BETWEEN THE CLEVIS ARM AND THE ROD END OF THE ACTUATING ROD. (X)
NOSE STEERING WAS REPORTED TO BE LOOSE. INSPECTION REVEALED RUDDER PEDAL ARM PIVOT HOLES ELONGATED. REPLACED RUDDER ARM ASSY WITH NEW COMPONENT AND NEW HARDWARE AS NECESSARY. LACK OF LUBRICATION IN THIS AREA POSSIBLY ACCELERATED THE WEAR OF THE PIVOT HOLES. THE BE99 MM DOES NOT SPECIFICALLY REFERENCE THIS PARTICULAR AREA FOR LUBRICATION. (CHAP 12). MAINT DEPT HAS BEEN USING EITHER LPS 2 OR 3. (X)
DISCOVERED FUEL LEAKING FROM LOWER COWL ON THE LEFT ENGINE ON A POST-FLIGHT INSP. INSP REVEALED THE FUEL LEAK SOURCE TO BE A HIGH PRESSURE FUEL LINE FROM THE FCU TO THE START FLOW CONTROL UNIT. THE SS LINE HAD A SMALL CRACK WHERE THE FERRULE WAS SECURED TO THE TUBING. THIS CONDITION COULD HAVE BEEN THE RESULT OF IMPROPER BENDING OF THE LINE TO FACILITATE INSTALLATION. SUBMITTER STATED THIS PARTICULAR LINE SHOWED SIGNS OF POSSIBLE MFG DEFECTS DURING ASSEMBLY OF FERRULE TO TUBE. (X)
FUEL BOOST PUMP INOPERABLE.
A NEW TIRE WITH 151 CYCLES INSTALLED ON 9-13-99. DURING INSPECTION, FOUND TIRE TREAD SPLIT AND SEPARATED THE SAME DIRECTION AS TIRE GROOVES.
CREW DOOR LEAKS AIR IN-FLIGHT DUE TO SLIGHT MIS-ALIGNMENT ON FORWARD EDGE. PROBLEM FOUND TO BE BENT HINGE ON UPPER FORWARD SIDE. REPLACED HINGE AND INSPECTED AREA FOR HIDDEN DAMAGE. NO OTHER DISCREPANCIES TO REPORT. THE DESIGN OF THE HINGE IS SUCH THAT THIS PROBLEM COULD RECUR IF DOOR IS HANDLED ROUGHLY OR DOOR SEAL IS NOT PROPERLY SHIMMED. FORTUNATELY, INSPECTIONS ARE FREQUENTLY CONDUCTED TO INCLUDE THIS AREA. THE HINGE SHOWED NO SIGN OF CRACKS THROUGH VISUAL INSPECTION.
PILOT REPORTED FUEL LEAKING FROM AREA OTHER THAN THE FUEL SUMPS IN THE VICINITY OF THE NACELLE. INSPECTION REVEALED VARIOUS SMALL LEAKS IN THE BLADDER OF THE CELL. THE CELL WAS REPLACED WITH A SERVICEABLE CELL AND AIRCRAFT TANK LINER RE-TAPED WITH CHAFE RESISTANT FUEL BAY TAPE. IT WAS DETERMINED THE CAUSE OF THE LEAKS WAS NORMAL WEAR. THE AGE OF THE FUEL CELL WAS UNKNOWN. TANK HANGERS WERE STILL IN PLACE AT TIME OF REMOVAL OF THE DEFECTIVE FUEL CELL.
FLAPS WERE INOPERATIVE. MOTOR WINDINGS COOKED (BRUSHES WORN). REPLACED FLAP MOTOR AND GEARBOX AS AN ASSEMBLY. VERIFIED RIGGING OK. MOTOR INOPERATIVE DUE TO NORMAL WEAR.
PILOT REPORTS RM FUEL LEAK, FUEL DRIPPING FROM GEAR DOOR. FUEL CELL REMOVED AND TESTED. REPLACED CELL.
PILOT REPORTED TO MAINTENANCE ICE REMAINING ON TAIL AFTER LANDING. (SPECIFICALLY, BOTH HORIZONTAL SURFACE DEICERS.) OPERATIONAL CHECK OF BOOTS BROKE ICE FORM SURFACE, HOWEVER, A CLOSER INSPECTION OF SURFACE DEICERS REVEALED MINOR HOLES IN LEADING EDGES. FURTHERMORE, WHEN SUPPLY PRESSURE LINES WERE REMOVED, WATER WAS FOUND IN LINES TO THE BOOTS. BOOTS WERE REPLACED AND AIRCRAFT LINES CLEARED OF WATER USING DRY SHOP AIR AND ISOPROPHYL ALCOHOL.