N255CA
Registered owner: HYANNIS AIR SERVICE INC, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| HYANNIS AIR SERVICE INC. (HYIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING SCHEDULED INSPECTION MAINTENANCE FOUND THE LEFT ENGINE TURBO TRANSITION PIPE CRACKED. THE TRANSITION PIPE WAS REPLACED WITH NO FURTHER DEFECTS NOTED.
PILOT REPORTED EXCESSIVE ENGINE VIBRATION DURING TAKE OFF AND CRUISE. MAINTENANCE INSPECTED AND FOUND THE #6 CYLINDER DEAD, THE CYLINDER WAS REPLACED ALONG WITH CYLINDER #5'S SPARK PLUGS WITH NO FURTHER DEFECTS NOTED.
PILOT REPORTED STALL HEAT INOPERATIVE. MAINTENANCE INSPECTED AND FOUND THE LIFT TRANSDUCER HEATING ELEMENT SWITCH AND CONNECTOR MELTED. THE CONTROL PANEL WAS REPLACED WITH NO FURTHER DEFECTS.
PILOT REPORTED SMOKE SMELL IN THE COCKPIT ASSOCIATED WITH THE HEATER. MAINTENANCE INVESTIGATED AND CONFIRMED FAULT TO BE HEATER RELATED AND PLACED SYSTEM ON MEL.
DURING SCHEDULED INSPECTION, EXCESSIVE RADIAL END PLAY WAS NOTED IN THE AFT ATTACH BEARINGS (HINGE ASSY.) FOR THE HORIZONTAL STABILIZER PN: 212-55-10-1006-000. THESE ATTACH BEARING ASSEMBLIES WILL BE REMOVED AND REPLACED USING NEW PARTS.
THE NLG ATTACH STRUCTURE WAS FOUND TO BE DAMAGED DURING AN INSPECTION INITIATED DUE TO SIMILAR FINDINGS ON OTHER COMPANY AIRCRAFT. THE DAMAGE IS LOCATED AT FWD MOST FUSELAGE BULKHEAD, LWR CENTER SECTION, IN THE AREA CORRESPONDING TO THE NLG MOUNTS. THE STRUCTURE AFT OF NLG BULKHEAD WAS INSPECTED WITH THE FOLLOWING DEFECTS NOTED: THE FWD SECTIONS OF FLOORBOARD SUPPORTS AS THEY ARE RIVETED TO FORWARD-MOST FUSELAGE BULKHEAD ARE CRACKED. THE OEM HAS BEEN NOTIFIED AND A FLEETWIDE INSPECTION HAS BEEN ISSUED FOR ALL COMPANY AIRCRAFT.
LANDING GEAR SELECTOR LOCK DID NOT RELEASE AFTER TAKEOFF. SECURED LOOSE AIR/GROUND SENSOR WIRING CONNECTION (PO316).
HYDRAULIC LEAK, RIGHT HAND WHEEL WELL. REPLACED O RING AT DOOR SEQUENCE VALVE.
DOOR WARNING DURING TAKEOFF. FOUND FUEL SERVICE DOOR OPEN, CLOSED AND LATCHED DOOR.
DOOR WARNING DURING TAKEOFF. SINGLE POINT FUEL SERVICE DOOR NOT LATCHED. SECURED DOOR.
DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP. THE BUTT-STRAP WAS REPLACED PER SRM STANDARD PRACTICES.
DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE LEFT HAND T-SECTION AT FRAME 16. THE T-SECTION WAS REPLACED PER SRM STANDARD PRACTICES.
DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER OMEGA BEAM. THE OMEGA BEAM WAS REPAIRED PER AERODESIGN REPORT NR 1957-5, REV IR, 6-23-98.
DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE RIGHT HAND T-SECTION AT FRAME 16. THE T-SECTION WAS REPLACED PER SRM STANDARD PRACTICES.
DURING AIRCRAFT MAINTENANCE, CORROSION WAS FOUND ON THE FUSELAGE FORWARD CABIN FLOOR SUPPORT STRUCTURE CENTER BUTT STRAP. THE BUTT STRAP WAS REPLACED PER AERODESIGN REPORT NR 1671-1, REV A, 1-28-97.
FLAP AND ADVANCED SWS INDICATIONS ON MAP. REPLACED THE FLAP CONTROL UNIT.
LOW OIL PRESSURE WARNING ON RIGHT HAND ENGINE INFLIGHT SHUTDOWN. REPLACED OIL COOLER HOSE ASSEMBLY THAT WAS LEAKING DUE TO CHAFING DAMAGE.
THE LT MLG INTRANSIT LIGHTS REMAINED ON AFTER GEAR RETRACTION. LANDING GEAR WAS CYCLED AND 2ND RETRACTION WAS NORMAL. COULD NOT DUPLICATE DISCREPANCY. CLEANED INDICATION SENSORS AND CONNECTIONS. AIRCRAFT RETURNED TO SERVICE.
DURING PREFLIGHT INSPECTION, THE RIGHT PROPELLER SPINNER BULKHEAD WAS FOUND TO BE CRACKED APPROXIMATELY 1.5 INCH ALONG THE BULKHEAD OUTER WALL BEHIND BLADE NR 2. AIRCRAFT WAS FERRIED BACK TO CVG HANGAR AND BULKHEAD REMOVED FOR REPAIR. DAMAGE APPEARS TO BE DUE TO MATERIAL DEFECT, NO EXTERNAL DAMAGE WAS FOUND.
LANDING GEAR DID NOT EXTEND WHEN SELECTED DOWN. EMERGENCY SYSTEM USED TO LOWER LANDING GEAR. REPLACED DEFECTIVE RT MLG DOWNLOCK PROXIMITY SENSOR.
DURING TEARDOWN OF BRAKE ASSY P/N 2-1585, THE ACCESSORY SHOP FOUND THE NUMBER ONE STATOR CRACKED. OVERHAULED BRAKE.
DURING 4C INSEPCTION TASK 5320-151-01I, REVEALED RIGHT T-SECTION AT FRAME 28 TO BE CORRODED. REMOVED CORRODED T-SECTION AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51.
DURING 4C INSPECTION TASK 5320-151-01I, REVEALED RIGHT FLOORBEAM AT FRAME 33 TO BE HEAVILY CORRODED. REMOVED CORRODED PART AND INSTALLED SERVICEABLE PART USING EMB SRM STANDARD PRACTICES CHAPTER 51 FOR LIKE TO LIKE PART REPLACEMENT.
DURING 4C INSPECTION TASK 5330-161-01I, REVEALED RIGHT CARGO COMPARTMENT SILL TO BE CORRODED BEYOND LIMITS. REMOVED SILL AND INSTALLED SERVICEABLE SILL USING EMB SRM STANDARD PRACTICES CHAPTER 51.
DURING 4C INSPECTION TASK 5320-151-01I, REVEALED AFT EMERGENCY EXIT GUIDE PIN FITTINGS TO HAVE CORROSION BETWEEN FITTINGS AND THE EXIT SILL LOWER ATTACHE ANGLE. FURTHER INVESTIGATION REVEALED THAT THERE IS NO PRIMER OR SEALANT BETWEEN OR ON THESE PIECES. REPLACED CORRODED ANGLE WITH SERVICEABLE PART IAW EMB SRM CHAPTER 51.
DURING 4C INSPECTION TASK 5320-151-01I, REVEALED AFT EMERGENCY EXIT GUIDE PIN FITTINGS TO HAVE CORROSION BETWEEN THE FITTINGS AND THE EXIT SILL LOWER ATTACH ANGLE. FURTHER INVESTIGATION REVEALED THAT THERE IS NO PRIMER OR SEALANT BETWEEN OR ON THESE PIECES. REPLACED CORRODED FITTINGS WITH SERVICEABLE PARTS. INSTALLED PARTS WITH PRIMER AND SEALANT USING EMB STANDARD SRM PRACTICES CHAPTER 51.
ON C-CHECK TASK 35-09, THE PASSENGER OXYGEN MASKS AT SEAT 1BC FAILED TO DEPLOY. THE OXYGEN MASK DOOR SOLENOID AT THAT LOCATION WAS REPLACED, SYSTEM TESTS NORMAL.
LANDING GEAR WOULD NOT RETRACT. REPLACED DEFECTIVE WIRING CONNECTOR AT RT MLG UPLOCK.
PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT DUE TO BEING STRUCK BY LAVORATORY CART WHILE STATIC ON AIRCRAFT RAMP. DURING PROPELLER IMPACT INSPECTION ACTUATOR FEATHER STOP TAB WAS FOUND TO BE DISPLACED APPROXIMATELY .125 FEET. ACTUATOR S/N 20383 WAS SUBSEQUENTLY REMOVED FROM THE PROPELLER ASSEMBLY AND THE PITCHLOCK SCREW S/N 49 WAS REMOVED FROM ACTUATOR AND RETURNED TO MANUFACTURER.
OUTBOARD FLAPS FAILED TO RETRACT. REPLACED THE ROLLERS ON THE RT OUTBOARD FLAP.
FLAP DISAGREEMENT AFTER TAKEOFF. CLEANED LEFT OUTBOARD FLAP TRACKS.
FLAP FAIL WARNING. REPLACED LEFT OUTBOARD FLAP, OPERATIONAL CHECK GOOD.
FLAP DISAGREEMENT UPON FLAP RETRACTION AFTER TAKEOFF. REPLACED LT OUTBOARD FLAP ROLLERS 4 EACH. OPERATIONAL CHECK GOOD.
DOOR LIGHT ON MAP CAME ON DURING TAKEOFF. RESECURED FUEL DOOR FASTENERS.
INSPECTION REVEALED A CRACK IN THE RIGHT NACELLE LT STRINGER 1. THE STRINGER WAS REPAIRED PER AERODESIGN REPORT NR 2000-1, DATED 8-17-96.
INSPECTION REVEALED CORROSION ON THE FORWARD CABIN FLOOR SUPPORT OM26A BEAM BUTT STRAP ON THE LEFT SIDE GALLEY AREA. THE BUTT STRAP WAS REPLACED WITH A NEW PART PER EMB120 5RM STANDARD PRACTICES.
RT HYDRAULIC RESERVOIR LOW PRESSURE WARNING ILLUMINATED. DRAINED MOISTURE FROM RESERVOIR, SYSTEM CHECK NORMAL.
RT BLEED AIR DUCT OVERHEAT WARNING CAME ON DURING FLIGHT. REPLACED DEFECTIVE DUCT OVERHEAT SWITCH.
AUTO FEATHER SYSTEM WILL NOT TEST OR ARM. REPLACED THE RT ENGINE SIGNAL CONDITIONER UNIT.
TAKEOFF TRIM AURAL WARNING SOUNDED DURING TAKEOFF. TRIM WAS CONFIRMED IN THE GREEN BAND. REPLACED THE LT ELEVATOR TRIM PROXIMITY SENSOR.
RT ENGINE IS LEAKING FUEL. REPLACED THE MOTIVE FLOW FUEL RETURN HOSE AND FITTING AT THE ENGINE HMU, DUE TO DAMAGED THREADS.
TAKEOFF AURAL WARNING SOUNDED DURING TAKEOFF ROLL. REPLACED THE AURAL WARNING UNIT.
RT ELECTRIC HYDRAULIC PUMP IS INOP. REPLACED THE RT ELECTRIC MOTOR DRIVEN HYDRAULIC PUMP.
PILOTS VSI TUBE BLANK. REPLACED THE 1VA-81A TA/VS1.
FLAP DISAGREEMENT WARNING DURING TAKEOFF CLIMB. REPLACED THE OUTBD FLAP SECTION ROLLERS.
STRONG SMELL OF ELECTRICAL BURNING IN COCKPIT AREA. FOUND BURNED GALLEY POWER WIRE. SECURED POWER TO GALLEY BY PULLING BREAKERS AND PLACED ON DEFERRED MAINT LIST.
DURING TAKEOFF ROLL, THE STALL WARNING CAME ON. REPLACED STALL WARNING COMPUTER.
CREW REPORTED, THAT POWER LEVERS WERE NOT EVEN AT FLIGHT IDLE STOP. THE RT POWER LEVER FLIGHT IDLE STOP PIN AND ROLLER WERE FOUND TO BE WORN OVER 50 PERCENT. THE RT POWER LEVER ASSY WAS REPLACED.
ELEVATOR TRIM IS BINDING. REPLACED THE RT ELEVATOR TRIM ACTUATOR.
DURING INSPECTION TASK 5530-324-03I AND 5530-324-02I, VERTICAL STABILIZER TO FUSELAGE ANGLE WAS FOUND TO BE CRACKED. REPLACED ANGLE IAW AERODESIGN REPORT 1446-1 AND EMB SRM.
HYDRAULIC LEAK, LEFT MLG. TIGHTENED FITTINGS ON HYDRAULIC SWIVEL.
HYDRAULIC LEAK, LEFT MLG. REPLACED LEAKING BRAKE LINE SWIVEL.
LT MLG GREEN SAFE LIGHT IS INOP, AND RED INTRANSIT LIGHT IS ILLUMINATED. REPLACED THE DOWN LOCK PROXIMITY SENSOR.